Provided is a method that makes it possible to manufacture a fan blade made of a fiber-reinforced composite material having a complicated three-dimensional shape while ensuring the necessary tensile strength is provided without producing defects. In this manufacturing method: a fan blade is regarded as a laminated article, and a laminated article is formed by performing repetitions of a step in which the layers constituting the laminated article are approximated as an article in which a plurality of strips that assume the form of a developable surface and that have a constant width over their entire longitudinal-direction length are arranged in a direction transverse to the longitudinal direction, a strip-form UD prepreg composed of a fiber-reinforced composite material is molded into a planar shape obtained by developing each of the developable surfaces, and the individual layers are formed by laminating the strip-form UD prepreg on a die. Having been so formed, the laminated article is molded.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
Provided is a method whereby unidirectional (UD) prepreg tape can be bent into curves, with no occurrence of defects, so as to have uniform thickness and width running lengthwise along the tape. In this method of manufacturing curved UD prepreg tape, a deformation site that is between two boundary sections that are in positions symmetrical with respect to a lengthwise midsection of a linear UD prepreg tape is shear-deformed along the UD prepreg tape lengthwise, such that an operation, in which non-deformed sites that are more to the end-section sides of the UD prepreg tape than the two boundary sections are displaced in mutually opposite directions traversing the UD prepreg tape lengthwise, is reiterated while the positions of the two boundary sections are shifted from the end-section sides toward the midsection of the UD prepreg tape.
A welding device 1 comprises: a heating body 14 that is composed of a fiber-reinforced resin in which fibers are arranged in one direction and is disposed between a first adherend 10 and a second adherend 12; a plurality of systems of electrodes 20 that are attached to the heating body 14 and divide an energization region in the heating body 14 in a direction intersecting an extension direction of the fibers; a power supply device 22 that applies a voltage to the electrodes 20 to cause a current to flow in the extension direction in the heating body 14; and a pressurizing device 24 for welding the first adherend 10 and the second adherend 12 via the heating body 14 by applying pressure to at least one of the first adherend 10 and the second adherend 12 in a direction in which the first adherend 10 and the second adherend 12 approach each other in a state in which the heating body 14 is heated by the current flowing through the heating body 14.
B29C 65/20 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool with direct contact, e.g. using "mirror"
4.
FRP MOLDING MOLD, AND FRP MOLDING SYSTEM AND METHOD USING SAME
An inner-surface mold 10A or an outer-surface mold 10B of a FRP molding mold 10 comprises a mold body 12, a partial-drive mold 14, and a partial-drive device 16. The partial-drive mold 14 is attached to the mold body 12 and is configured to be movable in a pressing direction in which pressure is applied to the molding surface of the FRP material 2. The partial-drive mold 14 is a solidified-part mold 14a or a thick-part mold 14b. The partial-drive device 16 drives the partial-drive mold 14 independently relative to the mold body 12 and applies pressure to the FRP material 2, and heats the FRP material 2 under pressure to convert the FRP material into FRP.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
Provided is a method for producing a cryogenic tank for storing a cryogenic fluid, the cryogenic tank having a structure comprising an outer shell made of a fiber-reinforced composite material, a release material made of a resin, and a liner made of a resin, which have been disposed in this order from outside. The method for producing a cryogenic tank can solve various problems in conventional production methods. In the method for producing a cryogenic tank, the liner is produced by steps including: A) a step in which a liner resin film made of a liner-forming resin is prepared, B) a step in which the liner resin film is slit to produce liner resin tape, and C) a step in which, while a mandrel having an outer surface shape corresponding to the inner surface shape of the liner is being rotated on the axis thereof, the liner resin tape is wound, under tension, on the outer surface of the mandrel.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 41/02 - Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped articleApparatus therefor for making articles of definite length, i.e. discrete articles
Provided is a cryogenic tank with increased reliability compared to the state of the art. This cryogenic tank comprises: an outer shell made of a fiber-reinforced composite material; and a plurality of inner layers disposed inside the outer shell. Each of the plurality of inner layers comprises a resin liner and a resin release material disposed on an outer surface of the liner.
To provide a method with which it is possible to avoid the occurrence of deformation in one member due to flow of thermoplastic resin that has formed a liquid phase when two members made of a material containing a thermoplastic resin are joined by fusion. The method includes, in this order: a step in which a first member is placed on the upper surface of a first heat source; a step in which a second member is placed on the upper surface of the first member via or without a bonding film made of a thermoplastic resin; a step in which a second heat source is positioned above the second member; a step in which the first heat source is heated to a predetermined first temperature and the second heat source is heated to a predetermined second temperature, respectively, and the second heat source is lowered so that the lower surface presses the upper surface of the second member with a predetermined downward load applied; and a step in which, after a predetermined length of hold time has elapsed after the temperature of the first heat source has reached the first temperature and the temperature of the second heat source has reached the second temperature, the first member and the second member are cooled. The second temperature is higher than the melting point of the thermoplastic resin and lower than the thermal decomposition temperature, and the first temperature is lower than the melting point of the thermoplastic resin.
Provided is a method for charging, with ceramic, open pores formed in a matrix of a ceramic matrix composite that includes the matrix and reinforcing fibers provided in the matrix. The ceramic comes to constitute the matrix. The method includes repeating the following steps (A) and (B) in a state where the ceramic matrix composite is arranged in a liquid material serving as a matrix material. At the step (A), the ceramic matrix composite is heated such that the liquid material is brought into a film-boiling state, and the ceramic derived from the liquid material is thereby generated in the open pores. At the step (B), the ceramic matrix composite is cooled until a temperature of the ceramic matrix composite becomes lower than a boiling point of the liquid material.
A power controller of a linear actuator 10 in a docking device 1 including a six-axis parallel link mechanism 5, wherein a motor driver 11 configured to control rotation speed of a motor M of the linear actuator 10 on the basis of a load produced on the link 4 includes a speed controlling unit 31 that outputs a current command, a current controlling unit 32 that converts the current command to a voltage command, and a current command limiter 33 that limits the current command of the speed controlling unit 31 so that power consumption per one linear actuator 10 is one sixth or less of the power supply capacity for the motor power, thus allowing for mounting the docking device 1 even for a spacecraft with a small power supply capacity, without requiring modification of the power supply capacity.
Provided is a method for manufacturing a ceramic matrix composite including a matrix and reinforcing fibers provided in the matrix. The method includes infiltrating a fiber body with powder of a ceramic material that becomes a part of the matrix. The fiber body is constituted by the reinforcing fibers. The method includes arranging, in a liquid material for the matrix, the fiber body infiltrated with the powder. The method includes heating the fiber body in this state, thereby bringing the liquid material into a film-boiling state such that ceramic derived from the liquid material is generated as a part of the matrix in the fiber body.
Provided is a novel technique for obtaining, in a ceramic-based composite material, a matrix having heat resistance and inhibited from cracking. This method, which is for producing a ceramic-based composite material comprising a matrix and reinforcing fibers disposed in the matrix, comprises disposing the reinforcing fibers in a liquid raw material for the matrix (step S2), heating the reinforcing fibers in the liquid raw material to a matrix formation temperature (step S31), and heating the reinforcing fibers in the liquid raw material to a heat-resistance impartation temperature (step S32). The heat-resistance impartation temperature is higher than the matrix formation temperature, and step S31 and step S32 are repeatedly conducted.
An FRP material has a circular arc part, and a member fixed to the circular arc part. The FRP forming system has a portion-pressing device, a member positioning mechanism, and a transport device configured to form the FRP material as a single body of a circular arc-shaped FRP part. The FRP material may comprise a single layer prepreg or a plurality of prepregs that have been layered. The portion-pressing device has upper and lower molds sandwiching a portion of the FRP material in a radial direction orthogonal to the circular arc part, and compresses intermittently a portion of the FRP part. The member positioning mechanism locates the position of the member relatively to the upper or lower mold. The transport device moves the portion of the FRP material that is compressed by the portion-pressing device. The portion-pressing and the transport are repeated to form the FRP part.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 43/14 - Compression moulding, i.e. applying external pressure to flow the moulding materialApparatus therefor of articles of definite length, i.e. discrete articles in several steps
B29C 43/34 - Feeding the material to the mould or the compression means
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
13.
POWER CONTROL DEVICE FOR LINEAR ACTUATOR IN DOCKING DEVICE
This power control device is for a linear actuator 10 in a docking device 1 having a six-axis parallel link mechanism 5. A motor driver 11 for controlling the rotational speed of a motor M of the linear actuator 10 on the basis of a load generated in a link 4 comprises: a speed control unit 31 that outputs a current command; a current control unit 32 that converts the current command into a voltage command; and a current command limiter 33 that limits the current command of the speed control unit 31 so that power consumption per one linear actuator 10 becomes not more than 1/6 of a power supply capacity for powering the motor. The docking device 1 can be mounted even on a spacecraft having a small power supply capacity without improving the power supply capacity.
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
H02K 7/06 - Means for converting reciprocating motion into rotary motion or vice versa
H02P 5/46 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another
14.
CERAMIC-BASED COMPOSITE MATERIAL AND METHOD FOR MANUFACTURING SAME
A method for manufacturing a ceramic-based composite material comprising a matrix and reinforcing fiber provided in the matrix, wherein: a powder of a matrix material forming a part of the matrix is impregnated into a fiber body constituted from the reinforcing fiber, the fiber body impregnated with the powder is positioned in a liquid raw material for the matrix, the fiber body is heated in this state to put the liquid raw material in a membrane boiling state, and a ceramic derived from the liquid raw material is generated in the fiber body as a part of the matrix.
Provided is a method for filling open pores, which are formed in a matrix in a ceramic-based composite material having reinforcing fibers provided in the matrix, with a ceramic material that serves as the matrix. The method comprises performing the below-mentioned steps (A) and (B) repeatedly while arranging the ceramic-based composite material in a liquid material that serves as a raw material for the matrix. (A) Heating the ceramic-based composite material to convert the liquid material in a film-boiled state, thereby forming a ceramic material derived from the liquid material in the open pores. (B) Cooling the ceramic-based composite material to a temperature lower than the boiling point of the liquid material.
A joint structure includes a connection member provided between a reinforced member and a reinforcing member and connecting both of them to each other. The connection member includes a first coupling portion and a second coupling portion that are coupled to one and another of the reinforced member and the reinforcing member, respectively. The first coupling portion is coupled to a joint portion of one of the reinforced member and the reinforcing member by an adhesive or welding. The first coupling portion and the joint portion are shaped so as to be caught by each other in a joining direction in which the reinforced member and the reinforcing member are joined to each other.
Produce prepreg with a matrix resin adhering to the cloth. Arranging a release sheet on each surface of the cloth; passing the cloth and a pair of the release sheets through a gap portion positioned in a clearance of a pair of heating rollers to be overlaid on each other and supplying the matrix resin to be accumulated above the gap portion of the heating rollers and between the pair of release sheets; and adjusting an interval of the pair of heating rollers to thereby control an adhesion amount of the matrix resin.
B29C 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29K 105/00 - Condition, form or state of moulded material
In this invention, an FRP material 2 comprises a circular arc part 5B having a circular arc shape, and a member 6 fixed to the circular arc part. The FRP forming system 100 comprises a portion-pressing device 20, a member positioning mechanism 26, and a transport device 30, and forms the FRP material 2 as a single body to produce a circular arc-shaped FRP part 3. The FRP material 2 comprises a single layer of prepreg 1, or a plurality of prepregs 1 that have been layered. The portion-pressing device 20 has an upper mold 16 and a lower mold 18 sandwiching a portion of the FRP material 2 in a radial direction orthogonal to the circular arc part 5B, and compresses intermittently a portion of the FRP part 3 to form partially the FRP part 3. The member positioning mechanism 26 locates the position of the member 6 relatively to the upper mold 16 or the lower mold 18. The transport device 30 moves intermittently the portion (press portion 15) of the FRP material 2 that is compressed by the portion-pressing device 20. The portion-pressing and the transport are repeated to compress the entirety of a single-body tool plate 14 and form the entirety of the FRP part 3.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
In this invention, an FRP material 2 comprises a circular arc part 5B having a circular arc shape, and a member 6 fixed to the circular arc part. The FRP forming system 100 comprises a portion-pressing device 20, a member positioning mechanism 26, and a transport device 30, and forms the FRP material 2 as a single body to produce a circular arc-shaped FRP part 3. The FRP material 2 comprises a single layer of prepreg 1, or a plurality of prepregs 1 that have been layered. The portion-pressing device 20 has an upper mold 16 and a lower mold 18 sandwiching a portion of the FRP material 2 in a radial direction orthogonal to the circular arc part 5B, and compresses intermittently a portion of the FRP part 3 to form partially the FRP part 3. The member positioning mechanism 26 locates the position of the member 6 relatively to the upper mold 16 or the lower mold 18. The transport device 30 moves intermittently the portion (press portion 15) of the FRP material 2 that is compressed by the portion-pressing device 20. The portion-pressing and the transport are repeated to compress the entirety of a single-body tool plate 14 and form the entirety of the FRP part 3.
B29C 43/34 - Feeding the material to the mould or the compression means
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
A fiber reinforced plastic (FRP) molding system in which FRP material, having stacked prepregs, is molded to manufacture an arc-shaped FRP component. The FRP molding system comprises inner and outer jig plates, a partial pressing device, and transfer devices. The jig plates are arc-shaped members having outer and inner surfaces that respectively fit with inner and outer surface shapes of the FRP component. The FRP material is sandwiched between the jig plates to form an integrated jig plate. The partial pressing device intermittently compresses a portion of the integrated jig plate in a radial direction orthogonal to an arc of the FRP component so that the FRP component is partially molded. The transfer devices intermittently move the compressed portion of the integrated jig plate by the partial pressing device. By repeating the partial pressing and the transport, the entire integrated jig plate is compressed to form the FRP component.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
An FRP continuous molding apparatus continuously molds an FRP from a layered sheet that includes prepreg sheets layered over each other. The prepreg sheets each include thermoplastic resin and reinforcement fibers, and differ from each other in fiber orientation. The FRP continuous molding apparatus includes: sheet feeding devices continuously feeding the layered sheets in a feeding direction; a layering device layering, over each other, the layered sheets fed from the sheet feeding devices, and thereby forming a sheet layered body; and a shaping mechanism molding the sheet layered body into an FRP while the sheet layered body is being transferred in the feeding direction. The FRP has a cross section that is a target shape. The sheet layered body includes the reinforcement fibers whose fiber orientation is the feeding direction.
An emergency deorbit device provided in a satellite flying on an orbit around the earth includes a propulsion module generating thrust for separating the satellite from the orbit, a reception unit receiving a repeat signal repeatedly sent at an interval from an sending unit of a satellite bus in the satellite, a detection unit outputting a detection signal when the reception unit does not receive the repeat signal in a set time period or when the reception unit receives a deorbit command from the sending unit or from an outside of the satellite, an activation device performing, in response to the detection signal, processing for activating the propulsion module, and a power supply device provided separately from a power supply device of the satellite bus and supplying electric power to the reception unit, the detection unit, and the activation device.
An FRP continuous molding apparatus (10) continuously molds an FRP (2) from layered sheets (1a, lb, 1c) each including prepreg sheets (4a, 4b, 4c) layered over each other. The prepreg sheets each include thermoplastic resin (12) and reinforcement fibers (13). The FRP continuous molding apparatus includes: sheet feeding devices (3a, 3b, 3c) continuously feeding the layered sheets in a feeding direction; a layering device (5) layering, over each other, the layered sheets fed from the sheet feeding devices, and thereby foiniing a sheet layered body (14); and a shaping mechanism (7) molding the sheet layered body into an FRP. The shaping mechanism includes a mold apparatus (37) including a plurality of molds (37a1 to 37a4) that compress the sheet layered body. The mold apparatus restricts both end surfaces of the sheet layered body in a direction perpendicular to the thickness direction of the sheet layered body, when viewed in the feeding direction.
GOVERNMENT OF THE UNITED STATES, AS REPRESENTED BY THE SECRETARY OF THE AIR FORCE (USA)
GOVERNMENT OF JAPAN, AS REPRESENTED BY THE COMMISSIONER OF THE ACQUISITION, TECHNOLOGY AND LOGISTICS AGENCY (Japan)
IHI AEROSPACE CO., LTD. (Japan)
Inventor
Yandek Gregory R
Edanaga Takayuki
Hashino Seiki
Sato Hiroshi
Satake Masaaki
Sakaino Masanori
Abstract
The present invention relates to resin compositions, fiber reinforced polymeric structures and electromagnetic induction processes for making same. Such magnetic induction processes are pulsed processes that can be optionally coupled with cooling steps between pulses. The aforementioned fiber reinforced polymeric structures can take forms that include, but are not limited to, pipes; pressure vessels, including rocket motor cases and fire extinguishers; golf club shafts; tennis and badminton racquets; skis; snowboards; hockey sticks; fishing rods; bicycle frames; boat masts; oars; paddles; baseball bats; and softball bats. In addition, such fiber reinforced polymeric structures can be supplemented with other materials, such as a rocket propellant, to form articles, for example, a rocket motor.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
25.
PREPREG CONTINUOUS PRODUCTION DEVICE AND METHOD THEREFOR
The objective of the invention is to produce a prepreg (10) comprising a cloth (4) having a matrix resin (5) adhered thereto. The invention comprises: disposing a mold release sheet (3) on each surface of the cloth (4); overlaying the pair of mold release sheets (3) onto the cloth (4) by passage thereof through a gap portion (2b) located in a space between a pair of heat rollers (2); supplying the matrix resin (5) in such a manner as to accumulate above the gap portion of the heat rollers (2) and between the pair of mold release sheets (3); and adjusting the interval (6) between the pair of heat rollers (2) thereby controlling the amount of the matrix resin (5) adhered.
A joint structure (10) includes a connection member (5) provided between a reinforced member (1) and a reinforcing member (3) and connecting both of them to each other. The connection member (5) includes a first coupling portion (5a) and a second coupling portion (5b) that are coupled to one and another of the reinforced member (1) and the reinforcing member (3), respectively. The first coupling portion (5a) is coupled to a joint portion (3a) of one of the reinforced member (1) and the reinforcing member (3) by an adhesive (9) or welding. The first coupling portion (5a) and the joint portion (3a) are shaped so as to be caught by each other in a joining direction (D3) in which the reinforced member (1) and the reinforcing member (3) are joined to each other.
This joint structure 10 is provided with a connecting member 5 that is provided between and connects a member 1 to be reinforced and a reinforcing member 3. The connecting member 5 has a first coupling part 5a and a second coupling part 5b which are respectively coupled to the member 1 to be reinforced and the reinforcing member 3. The first coupling part 5a is coupled to a joint part 3a of either of the member 1 to be reinforced or the reinforcing member 3 by an adhesive 9 or fusion. The first coupling part 5a and the joint part 3a have a shape of hooking on each other in a joint direction D3 of the member 1 to be reinforced and the reinforcing member 3.
INTER-UNIVERSITY RESEARCH INSTITUTE CORPORATION NATIONAL INSTITUTES OF NATURAL SCIENCES (Japan)
Inventor
Nagao Takahisa
Itou Mitsunori
Izawa Jun
Matsuura Yoshiki
Sasaki Masahiro
Taira Takunori
Abstract
A laser ignition device (1) is provided with an excitation light source (2) for generating excitation light, and a pulsed laser oscillator (4) connected to the excitation light source, wherein the pulsed laser oscillator generates a plurality of pulsed beams at the time of an ignition thereby producing an initial flame.
F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
F02P 23/04 - Other physical ignition means, e.g. using laser rays
Provided is an FRP molding system 100 with which an FRP material 2, in which a plurality of prepregs 1 are laminated, is molded to manufacture an arc-shaped FRP component 3. The FRP molding system 100 comprises an inner jig plate 10 and an outer jig plate 12, a partial pressing device 20, and a transport device 30. The inner jig plate 10 and the outer jig plate 12 are arcuate, and have an outer surface 10b and an inner surface 12a that respectively fit with an inner surface shape 3a and an outer surface shape 3b of the FRP component 3. The FRP material 2 is sandwiched between the inner jig plate 10 and the outer jig plate 12 to form an integrated jig plate 14. The partial pressing device 20 intermittently compresses a portion of the integrated jig plate 14 in a radial direction orthogonal to an arc of the FRP component 3 so that the FRP component 3 is partially molded. The transport device 30 intermittently moves the compressed portion (pressed portion 15) of the integrated jig plate 14 by the partial pressing device 20. By repeating the partial pressing and the transport, the entire integrated jig plate 14 is compressed to form the entire FRP component 3.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
Provided is an FRP molding system 100 with which an FRP material 2, in which a plurality of prepregs 1 are laminated, is molded to manufacture an arc-shaped FRP component 3. The FRP molding system 100 comprises an inner jig plate 10 and an outer jig plate 12, a partial pressing device 20, and a transport device 30. The inner jig plate 10 and the outer jig plate 12 are arcuate, and have an outer surface 10b and an inner surface 12a that respectively fit with an inner surface shape 3a and an outer surface shape 3b of the FRP component 3. The FRP material 2 is sandwiched between the inner jig plate 10 and the outer jig plate 12 to form an integrated jig plate 14. The partial pressing device 20 intermittently compresses a portion of the integrated jig plate 14 in a radial direction orthogonal to an arc of the FRP component 3 so that the FRP component 3 is partially molded. The transport device 30 intermittently moves the compressed portion (pressed portion 15) of the integrated jig plate 14 by the partial pressing device 20. By repeating the partial pressing and the transport, the entire integrated jig plate 14 is compressed to form the entire FRP component 3.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
Thrusters for satellites; propulsion mechanisms for
satellites; rocket engines for satellites; rocket engines or
thrusters for propulsion of satellites; rocket engines or
thrusters for attitude control of satellites; rocket engines
or thrusters for orbit correction of satellites.
32.
FRP CONTINUOUS MOLDING APPARATUS AND FRP CONTINUOUS MOLDING METHOD
This FRP continuous molding apparatus 10 continuously molds an FRP from a multilayer sheet which is obtained by laminating a plurality of prepreg sheets that contain a thermoplastic resin and reinforcing fibers, while having fiber orientations different from each other. This FRP continuous molding apparatus 10 is provided with: a plurality of sheet supply devices 3a, 3b, 3c which continuously supply a plurality of multilayer sheets 1a, 1b, 1c respectively in the feed direction; a lamination device which superposes the plurality of multilayer sheets supplied from the plurality of sheet supply devices upon each other, thereby forming a sheet laminate 14; and a shaping mechanism 7 which molds the sheet laminate into an FRP 2 having a desired cross-sectional shape, while conveying the sheet laminate in the feed direction. The sheet laminate contains reinforcing fibers, the fiber orientation of which is consistent with the feed direction.
Thrusters for satellites; rocket engines for satellites; rocket engines or thrusters for propulsion of satellites; rocket engines or thrusters for attitude control of satellites; rocket engines or thrusters for orbit correction of satellites
F02K 9/64 - Combustion or thrust chambers having cooling arrangements
F28D 7/10 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
F28F 21/08 - Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
The present invention is provided with a pressure-receiving member 12 (pressure-receiving roller 44), a pressure roller 14, a magnetic force generator 15a, and a heating device 15b. the pressure-receiving roller 44 is positioned in close contact with the back surface 1a of a material 1 to be joined made of a non-magnetic body, in a joining range 4 in which the material 1 to be joined and a joining material 2 are each superposed on each other via an adhesive 3. The pressure roller 14 has an outer circumferential surface 14a for coming in close contact with the surface of the joining material 2, and is configured so as to be able to roll along a joining material surface 2a. The magnetic force generator 15a generates a pressing force on a sandwiched part 5 sandwiched by the outer circumferential surface 14a and the pressure-receiving member 12. The heating device 15b heats the sandwiched part 5.
A method for producing a silicon-carbide-based composite. In the production of a silicon-carbide-based composite comprising a carbon-fiber-reinforced/silicon carbide composite (a C/SiC composite) or a silicon-carbide-fiber-reinforced/silicon carbide composite (a SiC/SiC composite), a film boiling method is carried out, using an organosilicon polymer having a chlorine-free polysilane skeleton and/or a chlorine-free polycarbosilane skeleton. The organosilicon polymer is in a liquid form at room temperature. The molar ratio of Si and C in the matrix of the C/SiC composite or the SiC/SiC composite is Si:C=1:1.08 to 1:1.43.
An emergency deorbit device 10 provided to an artificial satellite 100 orbiting the globe comprises: a propulsion device 27 that generates thrust for causing the artificial satellite 100 to deorbit; a receiving unit 31 that receives repeating signals repeatedly emitted at intervals from a signal-emitting unit 21 of a satellite bus 3 in the artificial satellite 100; a detection unit 33 that, when the receiving unit 31 does not receive repeating signals or when the receiving unit 31 receives a deorbit command from the signal-emitting unit 21 or outside the artificial satellite during a set time, outputs a detection signal indicating the same; an activation device 35 that performs a process for activating the propulsion device 27 in response to the detection signal; and a power source device 37 that is provided separately from a power source device 15 of the satellite bus 3, and that supplies electric power to the receiving unit 31, the detection unit 33, and the activation device 35.
A docking device including: a base ring disposed in a first space vehicle; a first-side capturing ring for coming into contact with the second space vehicle; six links that constitute a parallel link mechanism for coupling the base ring to the first-side capturing ring; and linear actuators, each of which extends and contracts the link by using a motor as a driving source, wherein resistance generation mechanisms, each of which generates a regenerative current in the motor of the linear actuator to produce resistance force when the second space vehicle comes into contact with the first-side capturing ring and the link receives a compressive load, are provided. Correction of misalignment with the second space vehicle, and attenuation of inertia force that the second space vehicle has can be performed without requiring complicated electrical control, and simplification and cost reduction of an electrical system can be implemented.
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
H03K 17/687 - Electronic switching or gating, i.e. not by contact-making and -breaking characterised by the use of specified components by the use, as active elements, of semiconductor devices the devices being field-effect transistors
1. A satellite constellation forming method comprises a satellite deployment step S2, a spacecraft acceleration step S4, a spacecraft orbiting step S5 and spacecraft deceleration step, and the aforementioned steps are repeated in order. In the satellite deployment step S2, deploying one of the satellites into the circular orbit 2 from the spacecraft 10 on the circular orbit 2. In the spacecraft acceleration step S4, accelerating the spacecraft 10 and switching the orbit from the circular orbit 2 to a spacecraft transfer orbit 3 in the same orbit plane. In the spacecraft orbiting step S5, making the spacecraft 10 orbit along the spacecraft transfer orbit 3 a plurality of times. In the spacecraft deceleration step, decelerating the spacecraft 10 and switching the orbit from the spacecraft transfer orbit 3 to the circular orbit 2 in the same orbit plane.
According to the present invention, a heat transfer body 3 having an inner space 7 in which a high temperature-side fluid is generated or flows is prepared. The heat transfer body 3 is a component of a heat exchanger, and is a wall formed of a copper material and surrounding an inner space 7 in which one among a high-temperature side fluid and a low-temperature side fluid is present. Inside the wall, a flow passage 9 is formed in which the other one among the high-temperature side fluid and the low-temperature side fluid flows. An LMD layer is directly formed, through an LMD process, on the outer peripheral surface 3a of the heat transfer body 3. In the LMD process, a metal material is supplied to a supply position on the peripheral surface 3a of the heat transfer body 3, the supply position is irradiated with a laser beam to melt both the outer peripheral surface 3a and the metal material, whereby an LMD layer 5 composed of a metal material and bonded to the peripheral surface 3a is formed. The energy density of the laser beam is set to a level high enough to melt both the metal material and the outer peripheral surface 3a.
F28D 7/10 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
B23K 26/00 - Working by laser beam, e.g. welding, cutting or boring
09 - Scientific and electric apparatus and instruments
Goods & Services
Projectiles, in the nature of weapons; rockets, in the nature of projectiles Radar reflectors, namely, radar jamming apparatus incorporating radar reflectors that function as decoys by reflecting radio waves from tracking apparatuses
The present invention is provided with a resistance generation mechanism which is provided with: a base ring 2 disposed on one space vehicle A; a one-side capturing ring 3 that comes into contact with the other-side space vehicle B; six links 4 that constitute a parallel link mechanism 5 for coupling the base ring 2 and the one-side capturing ring 3; and a linear actuator 10 that extends and contracts the links 4 by using a motor 13 as a drive source, the resistance generation mechanism generating a regenerative current in the motor 13 of the linear actuator 10 to produce a resistance force when the other-side space vehicle B comes into contact with the one-side capturing ring 3 and the links 4 receive a compressive load. Simplification and cost reduction of an electrical system can be achieved in which misalignment with the other-side space vehicle can be corrected and the inertial force of the other-side space vehicle can be attenuated without the need for complicated electrical control.
A method for producing a silicon-carbide-based complex. In the production of a silicon-carbide-based complex composed of a carbon-fiber-reinforced/silicon carbide complex (a C/SiC complex) or a silicon-carbide-fiber-reinforced/silicon carbide complex (a SiC/SiC complex), a film boiling method is carried out using an organosilicon polymer having a chlorine-free polysilane backbone and/or a chlorine-free polycarbosilane backbone. The organosilicon polymer has a liquid form at room temperature. The molar ratio of Si to C in a matrix of the C/SiC complex or the SiC/SiC complex, i.e., Si:C, is 1:1.08 to 1:1.43.
D06M 15/643 - Macromolecular compounds obtained otherwise than by reactions only involving carbon-to-carbon unsaturated bonds containing silicon in the main chain
This regenerative fuel cell system (100) comprises: a fuel cell (1) whereby hydrogen from a hydrogen storage unit (11a) and oxygen from an oxygen storage unit (11b) are reacted to generate power; a water electrolysis device (7) whereby the water discharged from the fuel cell (1) is electrolyzed to generate hydrogen and oxygen; a first gas reaction device (9a) (first reaction unit) whereby the hydrogen generated at the water electrolysis device (7) is reacted with oxygen accompanying the hydrogen generated at the water electrolysis device (7), and the hydrogen remaining after the reaction is returned to the hydrogen storage unit (11a); a second gas reaction device (9b) (second reaction unit) whereby the oxygen generated at the water electrolysis device (7) is reacted with hydrogen accompanying the oxygen generated at the water electrolysis device (7), and the oxygen remaining after the reaction is returned to the oxygen storage unit (11b); a first valve (13a) installed in-line with the piping connecting the water electrolysis device (7) to the hydrogen storage unit (11a); and a second valve (14a) installed in-line with the piping connecting the water electrolysis device (7) to the oxygen storage unit (11b).
H01M 8/0606 - Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants
C25B 1/10 - Electrolytic production of inorganic compounds or non-metals of hydrogen or oxygen by electrolysis of water in diaphragm cells
C25B 9/00 - Cells or assemblies of cellsConstructional parts of cellsAssemblies of constructional parts, e.g. electrode-diaphragm assembliesProcess-related cell features
C25B 15/08 - Supplying or removing reactants or electrolytesRegeneration of electrolytes
H01M 8/04 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
In order to make it possible to use a low toxicity HAN-based propellant in a thruster, the purpose of the present invention is to provide: a HAN-based propellant decomposition catalyst that is sufficiently heat resistant and stable with little change over time in the decomposition activity of the HAN-based propellant; a production method therefor; and a monopropellant thruster equipped with the HAN-based propellant decomposition catalyst. The present invention provides: a HAN-based propellant decomposition catalyst comprising a hexaaluminate oxide containing a platinum group element; a production method therefor; and a monopropellant thruster equipped with the HAN-based propellant decomposition catalyst.
A corner reflector includes annular balloons, which, when gas is supplied to the inside, annularly expand, and radio wave reflective films each developed to a plane by the expansion of the annular balloons. The three annular balloons are provided so as to be orthogonal to each other in the expansion. A constraint fabric wound around each annular balloon is provided. The constraint fabric includes an inner peripheral side fabric portion located on the side of a virtual central axis of the annular balloon and extending in the annular direction around the virtual central axis, and an outer peripheral side fabric portion located on the side opposite to the virtual central axis and extending in the annular direction. The elongation degree of the outer peripheral side fabric portion in the annular direction is higher than the elongation degree of the inner peripheral side fabric portion in the annular direction.
The present invention comprises a satellite deployment step S2, a spacecraft acceleration step S4, a spacecraft orbiting step S5, and a spacecraft deceleration step, and the foregoing are repeated in the order given. In the satellite deployment step S2, in a circular orbit 2, one satellite is deployed from a spacecraft 10 into the circular orbit 2. In the spacecraft acceleration step S4, the speed of the spacecraft 10 is accelerated, and within the same orbit plane, the orbit of the spacecraft is switched from the circular orbit 2 to a spacecraft transfer orbit 3. In the spacecraft orbiting step S5, the spacecraft 10 is caused to orbit multiple times in the spacecraft transfer orbit 3. In the spacecraft deceleration step, after the multiple orbits, the spacecraft 10 is slowed down, and within the same orbit plane, the orbit of the spacecraft is switched from the spacecraft transfer orbit 3 to the circular orbit 2.
A cylindrical case main body, and a connecting ring body fitted and fixed to a first end of the case main body and having an annular groove open in the centrifugal direction, are provided. The connecting ring body has a notch open to a side opposite to a second end of the case main body. Into the notch of the connecting ring body, a reinforcement body is fitted, and the reinforcement body has an arc-shaped groove continuing to the annular groove of the connecting ring body in a state where the reinforcement body is fitted into the notch of the connecting ring body. In addition to attaining high rigidity, reduction in weight and reduction in manufacturing cost can also be achieved.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A spacecraft 10 includes wings 11 or an airframe 12 which generates lift in an atmosphere 2, a thruster 14 which accelerates or decelerates rotating speed in an orbit, an attitude controller 16 which controls an attitude of the airframe 12, and an orbital plane controller 18 which controls the orbital plane change. The orbital plane controller causes the spacecraft 10 to enter the earth's atmosphere 2 within a pre-change orbital plane Fb (A→B→C), changes the orbital plane by using the lift of the wings 11 or airframe 12 in the earth's atmosphere 2 (C→D→E), and then lifts the spacecraft 10 up to the post-change orbital altitude (E→F).
A cylindrical case body made of a composite material; a linking ring made of aluminum, fitted and fixed to a rear end portion of the case body and having an annular groove which receives a reverse thrust load from a reverse thrust transmission body; and ring constituent bodies made of titanium alloy, each of which is placed in the rear end portion of the case body and has an arcuate groove which undertakes a reverse thrust load larger than that received by the linking ring, are provided in a fan case. The ring constituent bodies are fitted in notches of the linking ring and are brought into contact with outward receiving walls of the linking ring. The ring constituent bodies are positioned relative to the case body in the axis direction and in the radial direction, and the annular groove and the arcuate grooves continue to each other.
This corner reflector (10) is equipped with ring-shaped balloons (3a, 3b, 3c) that expand to a ring shape when a gas is supplied to the interior, and a radio wave reflecting film (5) that deploys to a flat surface due to the expansion of the ring-shaped balloons. The three ring-shaped balloons (3a, 3b, 3c) are placed so as to be mutually orthogonal when expanded. Constraint fabric (7) is wrapped onto each ring-shaped balloon. The constraint fabric (7) includes an inner peripheral-side fabric section (7a) positioned towards a hypothetical center axis (C) of the ring-shaped balloon and extending in a ring-shaped direction about the hypothetical center axis (C), and an outer peripheral-side fabric section (7b) positioned towards the opposite side from the hypothetical center axis (C) and extending in a ring-shaped direction. The degree of extension of the outer peripheral-side fabric section (7b) in the ring-shaped direction is greater than the degree of extension of the inner peripheral-side fabric section (7a) in the ring-shaped direction.
The present invention comprises: a cylindrical case main body 10, and a connecting ring body 20 that is fitted and fixed to one end of the case main body 10 and that has an annular groove 21 which opens in the centrifugal direction. Notches 22 that open toward the opposite side of the other end of the case main body 10 are formed in the connecting ring body 20, and a reinforcing body 30 is fitted into the notches 22 of the connecting ring body 20. An arc-shaped groove 31, which communicates with the annular groove 21 of the connecting ring body 20 in a state in which the reinforcing body 30 is fitted into the notches 22 of the connecting ring body 20, is formed in the reinforcing body 30. In addition to achieving high rigidity, the present invention also enables reductions in weight and manufacturing costs.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
F04D 29/52 - CasingsConnections for working fluid for axial pumps
54.
Method of manufacturing fan blade and apparatus for manufacturing the same fan blade
A blank sheet including a plurality of main fibers arranged in parallel with each other, auxiliary fibers and a resin that consolidates the fibers is heated to a temperature at which the resin softens, and then pressed against a fan blade mold with the direction of the main fibers aligned with the longitudinal direction of the fan blade mold. The fan blade mold is shaped so that the length thereof in the longitudinal direction along the surface of a center part thereof in the width direction is shorter than the length thereof in the longitudinal direction along the surface of end parts thereof in the width direction. When the blank sheet is pressed against the fan blade mold, a center part in the width direction of the blank sheet at an end part in the longitudinal direction is pulled with a greater force than end parts in the width direction of the blank sheet at the end part in the longitudinal direction, thereby preventing occurrence of wrinkling.
B29C 51/00 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
Provided is a wheel drive system for aircraft RS including a motor 2 that is connected to a wheel 12, and provided with two voltage supply lines L1 and L2 for supplying the voltages Vta and Vpr with varying the length of a winding 21 to be energized; a voltage supply unit for supplying the voltage Vta and Vpr to the two voltage supply lines L1 and L2; and a control unit 8 for controlling the voltage supply unit, wherein the control unit 8 is configured to select one of the two voltage supply lines L1 and L2, and supply the voltage Vta or Vpr, by controlling the voltage supply unit.
A cylindrical case includes a case main body made of a composite material of reinforcing fibers impregnated with a thermosetting resin, and an outward flange on the case main body. The outward flange includes: a bonding layer; a foundation layer disposed on the bonding layer; one flange constituting layer having a leg layer which is laminated from one slope surface of the foundation layer to the bonding layer and a wall layer which rises from the one slope surface; and the other flange constituting layer having a leg layer which is laminated from the other slope surface of the foundation layer to the bonding layer and a wall layer which rises from the other slope surface. The foundation layer is formed by laminating roving layers, while the flange constituting layers are formed by laminating a plurality of biaxial fabric layers including a biaxial fabric of a non-crimp structure.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 37/18 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
B32B 38/00 - Ancillary operations in connection with laminating processes
A cylindrical case includes a case main body, and a groove disposed annularly at one end of the case main body. A peripheral wall of the case main body is formed by alternately laminating a biaxial fabric layer, which includes a biaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45°, and a roving layer. A groove wall of the groove is formed by alternately laminating the biaxial fabric layer, which continues to the case main body side, and a triaxial fabric layer, which includes a triaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45° and a reinforcing fiber band having an orientation angle of 0°.
B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
A fan case is provided with: a cylindrical case main body (10) comprising a composite material; a linking ring (20) made of Al, the linking ring (20) being fittably secured to the rear end of the case main body (10) and being provided with an annular groove (21) for receiving a reverse thrust load from a reverse-thrust-force-transmitting body (8); and a ring construct (30) made of a Ti alloy, the ring construct (30) being arranged on the rear end of the case main body (10) and being provided with an arcuate groove (31) for receiving and holding a greater reverse thrust load than the reverse thrust load received by the linking ring (20). The ring construct (30) is fitted into an incision (22) in the linking ring (20), and is brought in contact with an outward receiving wall (23) of the linking ring (20), whereby the ring construct (30) is positioned along an axial center (CL) direction and a radial direction relative to the case main body (10), and the annular groove (21) and the arcuate groove (31) are continuous with each other. The ring construct made of a Ti alloy for receiving a great reverse thrust load can be arranged with high positioning accuracy, and can be made to receive and hold the reverse thrust load without imbalance.
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
A fan case is provided with: a cylindrical case main body (10) comprising a composite material; a linking ring (20) made of Al, the linking ring (20) being fittably secured to the rear end of the case main body (10) and being provided with an annular groove (21) for receiving a reverse thrust load from a reverse-thrust-force-transmitting body (8); and a ring construct (30) made of a Ti alloy, the ring construct (30) being arranged on the rear end of the case main body (10) and being provided with an arcuate groove (31) for receiving and holding a greater reverse thrust load than the reverse thrust load received by the linking ring (20). The ring construct (30) is fitted into an incision (22) in the linking ring (20), and is brought in contact with an outward receiving wall (23) of the linking ring (20), whereby the ring construct (30) is positioned along an axial center (CL) direction and a radial direction relative to the case main body (10), and the annular groove (21) and the arcuate groove (31) are continuous with each other. The ring construct made of a Ti alloy for receiving a great reverse thrust load can be arranged with high positioning accuracy, and can be made to receive and hold the reverse thrust load without imbalance.
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
A 0-axis current calculator 7 configured to calculate a target value of the 0-axis current by setting the current of the open phase to be zero when one of the phases becomes open, or determines that the target value of the 0-axis current is zero when there is no open phase is provided. Based on the target values of the d-axis current and the q-axis current, the target value of the 0-axis current calculated by the 0-axis current calculator 7, and the d-axis current, the q-axis current, and the 0-axis current transformed by the d-q-0 transformer 8, the current supplied to each phase of the motor are controlled.
H02P 6/00 - Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor positionElectronic commutators therefor
H02P 29/02 - Providing protection against overload without automatic interruption of supply
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 5/00 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors
G05B 11/38 - Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential for obtaining a proportional characteristic
G05B 11/36 - Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential
62.
Coupling part structure for vane and jet engine including the same
A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A groove is formed in one end portion joint surface of the coupling support member, a linear protrusion is formed on the other end portion joint surface, the vane proximal end portion is formed into a concavo-convex shape, a linear protrusion that is engaged with the groove which is formed in the end portion joint surface is formed on a joint surface to the one end portion joint surface, a groove that is engaged with the linear protrusion formed on the end portion joint surface is formed in the joint surface to the other end portion joint surface. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.
Each sheet material is formed by arraying carbon fiber lines, each having a predetermined width, in parallel with one another. Meanwhile, an array direction of the carbon fiber lines of each sheet material is set to form an angle in a range from ±30° to ±60° to a weaving advancing direction of a stitching yarn. Moreover, a stretch ratio of the stitched base material in its lengthwise direction in a case where a load per inch width of the stitched base material is applied in the weaving advancing direction of the stitching yarn is equal to or below 4% when the load is 5 N, and is equal to or above 10% when the load is 25 N.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 7/08 - Interconnection of layers by mechanical means
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
An aircraft electric power system provided in an aircraft includes a predetermined DC power supply bus for supplying electric power to a load. The DC power supply bus is configured to always be connected to two or more types of power supply devices having different forms.
An aircraft electric actuator drive apparatus has an electric actuator and a secondary power supply device. The electric actuator is driven using electric power from a main power unit provided in an aircraft. The secondary power supply device can temporarily supply electric power to the electric actuator while electric power from the main power unit is applied to the electric actuator.
A boss for attachment of an auxiliary device to a fan case of an engine includes a pedestal including a plurality of accumulated layers of reinforcement fibers and a matrix combining the reinforcement fibers together, the pedestal including a bottom face in a shape capable of being in close contact with an outer periphery of the fan case; and an embedded body embedded in the pedestal and including a combining structure combinable with the auxiliary device.
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F16B 5/02 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening members using screw-thread
67.
METHOD OF MANUFACTURING FAN BLADE AND APPARATUS FOR MANUFACTURING THE SAME FAN BLADE
A blank sheet (7), which has multiple main fibers (71) arranged in parallel, auxiliary fibers (72), and a resin for consolidating these fibers, is heated to a temperature at which the resin softens, and the blank sheet is pressed into a fan blade mold (6b) with the direction of the main fibers (71) aligned with the longitudinal direction of the fan blade mold (6b). The fan blade mold (6b) has a shape such that the length in the longitudinal direction of the fan blade mold along the surface at a center part (64x) in the width direction is shorter than the length in the longitudinal direction along the surface at both end parts (64y) in the width direction. When the blank sheet (7) is pressed into the fan blade mold (6b), the center portion (7x) in the width direction at the longitudinal ends (7a) of the blank sheet (7) is pulled along the main fibers (71) with greater pulling force than the side portions (7y) in the width direction at the longitudinal ends (7a) of the blank sheet (7), thereby suppressing the occurrence of wrinkling.
A blank sheet (7), which has multiple main fibers (71) arranged in parallel, auxiliary fibers (72), and a resin for consolidating these fibers, is heated to a temperature at which the resin softens, and the blank sheet is pressed into a fan blade mold (6b) with the direction of the main fibers (71) aligned with the longitudinal direction of the fan blade mold (6b). The fan blade mold (6b) has a shape such that the length in the longitudinal direction of the fan blade mold along the surface at a center part (64x) in the width direction is shorter than the length in the longitudinal direction along the surface at both end parts (64y) in the width direction. When the blank sheet (7) is pressed into the fan blade mold (6b), the center portion (7x) in the width direction at the longitudinal ends (7a) of the blank sheet (7) is pulled along the main fibers (71) with greater pulling force than the side portions (7y) in the width direction at the longitudinal ends (7a) of the blank sheet (7), thereby suppressing the occurrence of wrinkling.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A corner reflector includes: annular hollow balloons having flexibility and airtightness, and when gas is supplied therein, the annular hollow balloons expand with pressure of the gas to be an annular shape; and a radio wave reflection film having an outer edge part that is attached to the annular hollow balloons so that expansion of the annular hollow balloons makes the radio wave reflection film unfold over a plane of the annular shape. The three of the annular hollow balloons are provided so as to be mutually orthogonal after expansion. Binding members are attached to outer faces of the annular hollow balloons, the binding members being for preventing expansion of the annular hollow balloons beyond their limit volume.
G01S 7/38 - Jamming means, e.g. producing false echoes
F41J 9/08 - Airborne targets, e.g. drones, kites, balloons
F42B 12/70 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materialsProjectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for producing chemical or physical reactionProjectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for signalling for dispensing discrete solid bodies for dispensing radar chaff or infrared material
H01Q 15/00 - Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
A corner reflector includes: a radio wave reflection film having three reflection faces that are mutually orthogonal, and an unfolding device which unfolds the radio wave reflection film three-dimensionally. The corner reflector further includes: a canopy that unfolds concurrently with unfolding of the radio wave reflection film, and the canopy is connected to the unfolding device so as to partially overlie the radio wave reflection film.
F41J 9/08 - Airborne targets, e.g. drones, kites, balloons
F42B 12/70 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materialsProjectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for producing chemical or physical reactionProjectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for signalling for dispensing discrete solid bodies for dispensing radar chaff or infrared material
G01S 7/38 - Jamming means, e.g. producing false echoes
H01Q 15/00 - Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
71.
CYLINDRICAL CASE AND MANUFACTURING METHOD OF CYLINDRICAL CASE
The present invention is provided with a case body (9C) comprising a composite material in which reinforcing fibers are impregnated with a thermosetting resin, and an outward-facing flange (10) on the case body (9C), the outward-facing flange (10) is provided with a bonded bonding layer (11c), a foundation layer (12) disposed on the bonding layer (11c), a one-side flange constituent layer (13) having a base layer (13a) layered on the bonding layer (11c) from a one-side inclined face (12a) of the foundation layer (12) and a wall layer (13b) standing upright from the one-side inclined face (12a), and an other-side flange constituent layer (11) having the base layer (13a) layered on the bonding layer (11c) from an other-side inclined face (12b) of the foundation layer (12) and a wall layer (11b) standing upright from the other-side inclined face (12b), the foundation layer (12) is formed by layering a roving layer, and the flange constituent layers (11, 13) are formed by layering a plurality of biaxial fabric layers including a biaxial fabric (15) having a non-crimped structure. High structural strength can thereby be maintained in an outward-facing flange of a fan case made from a composite material of reinforcing fibers and a thermosetting resin.
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
72.
CYLINDRICAL CASE AND MANUFACTURING METHOD OF CYCLINDRICAL CASE
A cylindrical case equipped with: a case main body (10) formed from a composite material obtained by impregnating reinforcing fibers with a thermosetting resin; and a groove (12) disposed annularly at an end of the case main body (10). The circumferential wall (10a) of the case main body (10) has been formed by alternately superposing: biaxial woven fabric layers (13) each comprising biaxial woven fabric (13A) of a non-crimp structure which comprises reinforcing fiber bands (13a, 13b) oriented at the angles of ±45º; and roving layers (14) each containing rovings (14A) which are bundles of reinforcing fibers and which extend along the circumferential direction. The groove wall (12a) of the groove (12) has been formed by alternately superposing: biaxial woven fabric layers (13) each continuing toward the case main body (10); and triaxial woven fabric layers (15) each containing triaxial woven fabric (15A) of a non-crimp structure which comprises reinforcing fiber bands (15a, 15b) oriented at the angles of ±45º and a reinforcing fiber band (15c) oriented at the angle of 0º. Since the fan case is formed from, as a material, the composite material comprising reinforcing fibers and a thermosetting resin and has an annular groove, this fan case as a whole can retain high torsional strength and torsional rigidity.
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
73.
CYLINDRICAL CASE AND METHOD FOR MANUFACTURING CYLINDRICAL CASE
The present invention is provided with a case body (9C) comprising a composite material in which reinforcing fibers are impregnated with a thermosetting resin, and an outward-facing flange (10) on the case body (9C), the outward-facing flange (10) is provided with a bonded bonding layer (11c), a foundation layer (12) disposed on the bonding layer (11c), a one-side flange constituent layer (13) having a base layer (13a) layered on the bonding layer (11c) from a one-side inclined face (12a) of the foundation layer (12) and a wall layer (13b) standing upright from the one-side inclined face (12a), and an other-side flange constituent layer (11) having the base layer (13a) layered on the bonding layer (11c) from an other-side inclined face (12b) of the foundation layer (12) and a wall layer (11b) standing upright from the other-side inclined face (12b), the foundation layer (12) is formed by layering a roving layer, and the flange constituent layers (11, 13) are formed by layering a plurality of biaxial fabric layers including a biaxial fabric (15) having a non-crimped structure. High structural strength can thereby be maintained in an outward-facing flange of a fan case made from a composite material of reinforcing fibers and a thermosetting resin.
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
74.
CYLINDRICAL CASE AND PROCESS FOR PRODUCING CYLINDRICAL CASE
A cylindrical case equipped with: a case main body (10) formed from a composite material obtained by impregnating reinforcing fibers with a thermosetting resin; and a groove (12) disposed annularly at an end of the case main body (10). The circumferential wall (10a) of the case main body (10) has been formed by alternately superposing: biaxial woven fabric layers (13) each comprising biaxial woven fabric (13A) of a non-crimp structure which comprises reinforcing fiber bands (13a, 13b) oriented at the angles of ±45º; and roving layers (14) each containing rovings (14A) which are bundles of reinforcing fibers and which extend along the circumferential direction. The groove wall (12a) of the groove (12) has been formed by alternately superposing: biaxial woven fabric layers (13) each continuing toward the case main body (10); and triaxial woven fabric layers (15) each containing triaxial woven fabric (15A) of a non-crimp structure which comprises reinforcing fiber bands (15a, 15b) oriented at the angles of ±45º and a reinforcing fiber band (15c) oriented at the angle of 0º. Since the fan case is formed from, as a material, the composite material comprising reinforcing fibers and a thermosetting resin and has an annular groove, this fan case as a whole can retain high torsional strength and torsional rigidity.
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A steam spray device equipped with: a box-shaped chassis (2); a propellant holding unit (3) arranged in the chassis (2) and forming a space for holding a propellant; a gas storage unit (4) which is arranged in the chassis (2), and which forms a space partitioned from the propellant holding unit (3) by means of a partition wall (21) having a connecting hole (2a), and which stores a gas; a device storage unit (5), which is arranged in the chassis (2), and which forms a space portioned from the propellant holding unit (3) and the gas storage unit (4) by means of partition walls (21, 21'), and which stores devices; nozzles (6) which are connected to the chassis (2) and which discharge gas to the outside; gas flow paths (7), which are formed within the chassis (2) and supply the gas stored in the gas storage unit (4) to the nozzles (6); and a heater (8) which is arranged in the chassis (2) and heats at least the gas storage unit (4).
F02K 7/00 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof
A steam spray device equipped with: a box-shaped chassis (2); a propellant holding unit (3) arranged in the chassis (2) and forming a space for holding a propellant; a gas storage unit (4) which is arranged in the chassis (2), and which forms a space partitioned from the propellant holding unit (3) by means of a partition wall (21) having a connecting hole (2a), and which stores a gas; a device storage unit (5), which is arranged in the chassis (2), and which forms a space portioned from the propellant holding unit (3) and the gas storage unit (4) by means of partition walls (21, 21'), and which stores devices; nozzles (6) which are connected to the chassis (2) and which discharge gas to the outside; gas flow paths (7), which are formed within the chassis (2) and supply the gas stored in the gas storage unit (4) to the nozzles (6); and a heater (8) which is arranged in the chassis (2) and heats at least the gas storage unit (4).
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
B29C 65/00 - Joining of preformed partsApparatus therefor
A stitched carbon fiber base material and a wet prepreg having the same are provided. The stitched carbon fiber base material includes sheet materials. The sheet material is formed by arraying carbon fiber lines, each having a predetermined width, in parallel with one another. An array direction of the carbon fiber lines of each sheet material is set to form an angle in a range from ~30.degree. to ~60.degree. to a weaving advancing direction of a stitching yarn. A stretch ratio of the stitched base material in its lengthwise direction in a case where a load per inch width of the stitched base material is applied in the weaving advancing direction of the stitching yarn is equal to or below 4% when the load is N, and is equal to or above 10% when the load is 25 N.
B29B 15/08 - Pretreatment of the material to be shaped, not covered by groups of reinforcements or fillers
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
79.
STITCHED CARBON FIBER BASE MATERIAL AND WET PREPREG USING SAME
The present invention addresses the problem of providing: a stitched carbon fiber base material which exhibits excellent form stability and shapability and which ensures excellent handleability in processing a wet prepreg in a CFRP manufacturing step and facilitates the production of a three-dimensional product; and a wet prepreg using the same. Sheet materials (1) are each made by arranging carbon fiber yarns (11) having a prescribed width in such a state that the carbon fiber yarns (11) are present in parallel with each other, while the arrangement direction of carbon fiber yarns (11) in each sheet material (1) is adjusted to an angle of ±30° to ±60°to the direction in which the knitting of a stitching yarn (2) proceeds. The lengthwise elongation of the stitched carbon fiber base material in a case wherein a load of 5N is applied to the base material is adjusted to 4% or less, and that in a case wherein a load of 25N is applied thereto is adjusted to 10% or more, each load being applied per inch of the width of the base material in the direction in which the knitting of the stitching yarn (2) proceeds.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B29B 15/08 - Pretreatment of the material to be shaped, not covered by groups of reinforcements or fillers
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
80.
VANE LINKING PORTION STRUCTURE, AND JET ENGINE USING SAME
At a linking portion between a vane proximal end portion (21) of a guide vane (20) and a mounting flange (31f), a linking support member (33) including a pair of segment pieces (34, 34) joined to the vane proximal end portion (21) from both sides in a vane thickness direction is disposed. In one end joining surface (35a) of the linking support member (33), a groove (35b) is formed, while a ridge (35c) is formed on the other end joining surface (35a). The vane proximal end portion (21) is formed in a concave-convex shape and includes a joint surface (21a) for the one end joining surface (35a) with a ridge (21b) for engaging with the groove (35b) formed in the end joining surface (35a), and a joint surface (21a) for the other end joining surface (35a) with a groove (21c) for engaging with the ridge (35c) formed in the end joining surface (35a). The vane proximal end portion (21) is held between the segment pieces (34, 34) of the linking support member with a fastening force applied to the linking support member (33) from both sides in the vane thickness direction. The invention provides high structural strength while contributing to weight reduction of a jet engine.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
Multipliers (21a, 21b) multiply the total driving instruction value Es by first and second gains G1 and G1 and output the products as first and second driving instruction values E1 and E2, respectively. Controllers (23a, 23b) control first and second actuators (motors) (5, 7) on the basis of the first and second driving instruction values, respectively. A gain calculator (27) calculates the gains G1 and G2 on the basis of Ef1, Ef and Ef2, where Ef1 and Ef2 are detected values of the amounts of driving for the actuators are called and Ef is the detected value of the amount of driving for the member to be driven. If Ef1, Ef2, or Ef approaches zero, the first gain G1 is made close to (Ef1 - Lmax/2)/(Ef - Lmax), where Lmax is the the upper limit of Ef which indicates the amount of driving for the member to be driven.
A thruster designed to produce thrust by introducing a propellant to a catalyst layer from a propellant valve via a propellant introduction member and spurting out a gas resulting from decomposition of the propellant occurring on the catalyst layer, wherein the thruster comprises a chamber of an Ni alloy for holding the catalyst layer inside, the propellant introduction member is made of an Ni alloy and connects the propellant valve and the chamber, and a propellant valve flange of a Ti alloy with a plurality of columns of a Ti alloy is arranged between the chamber and the propellant valve to support the chamber by the columns.
The boss for installing an accessory onto an engine fan case comprises multiple stacked layers of reinforcing fibers and a matrix that binds the reinforcing fibers to each other, and is equipped with a seat provided with a bottom surface shape that can adhere closely to the outer surface of the fan case, and an embedded body, which is embedded in the seat and comprises a fastening structure that can be fastened to the accessory.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
84.
SPACE DEBRIS REMOVING DEVICE AND SPACE DEBRIS REMOVING METHOD
Provided is a device for removing space debris and a method for removing the space debris which enable the installation of a deceleration device with ease with respect to the space debris which is undergoing a tumbling motion. The present invention comprises a propulsion device (3) for performing access control and attitude control on target debris (1); a capturing device (4) which comprises a harpoon (41) which may be ejected toward the target debris (1); an observation device (5) which calculates a capture position (E) and a capture attitude at which the harpoon (41) can be driven into a tank (11) (hollow portion) of the target debris (1) by observing a motion of the target debris (1); a deceleration device (6) which decelerates the target debris (1) in direct or indirect connection to the harpoon (41); and a main body portion (21) on which the propulsion device (3), the capturing device (4), the observation device (5), and the deceleration device (6) are mounted.
Provided is a device for removing space debris and a method for removing the space debris which enable the installation of a deceleration device with ease with respect to the space debris which is undergoing a tumbling motion. The present invention comprises a propulsion device (3) for performing access control and attitude control on target debris (1); a capturing device (4) which comprises a harpoon (41) which may be ejected toward the target debris (1); an observation device (5) which calculates a capture position (E) and a capture attitude at which the harpoon (41) can be driven into a tank (11) (hollow portion) of the target debris (1) by observing a motion of the target debris (1); a deceleration device (6) which decelerates the target debris (1) in direct or indirect connection to the harpoon (41); and a main body portion (21) on which the propulsion device (3), the capturing device (4), the observation device (5), and the deceleration device (6) are mounted.
A pulse rocket motor has a hollow cylinder-like first grain situated in a rear section of a pressure vessel; a first igniter for igniting the first grain; a hollow cylinder-like second grain situated in a front section of the pressure vessel; a second igniter for igniting the second grain; and a dividing sheet member that covers the second grain within the pressure vessel. The dividing sheet member includes a dividing sheet expanding at least along the inner circumferential surface of the second grain and holders formed integrally with the dividing sheet at both ends of the dividing sheet by cure adhesion and attached to the pressure vessel. The dividing sheet includes a brittle portion that expands along the inner circumferential surface of the second grain through a rear end face of the second grain and is more brittle than other portions.
F02K 9/08 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants
F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
F02K 9/32 - Constructional partsDetails not otherwise provided for
A corner reflector (11) is provided with a radio wave reflecting film (11a) having three reflective surfaces that are orthogonal to each other, and a deployment device (11b) that causes the radio wave reflecting film (11a) to deploy in a three-dimensional manner; and is further provided with a canopy (12) that deploys simultaneously with the deployment of the radio wave reflecting film (11a). The canopy (12) is connected to the deployment device (11b) in such a manner as to cover part of the radio wave reflecting film (11a).
This corner reflector is provided with: flexible and airtight hollow annular balloons (3a, 3b, 3c) which, when a gas is supplied internally, expand due to the gas pressure and become ring-shaped; and a radio wave reflecting film (5), the outer peripheral edge of which is attached to the annular hollow balloons (3a, 3b, 3c) in such a manner as to deploy along an annular flat plane due to the expansion of the annular hollow balloons. The three annular hollow balloons (3a, 3b, 3c) are disposed in such a manner as to be orthogonal to each other when expanded. A restraint member (7), which prevents the annular hollow balloons (3a, 3b, 3c) from expanding beyond a limited volume, is attached to the outer surface of the annular hollow balloons (3a, 3b, 3c).
The present invention enables an actuator drive motor at which an anomaly such as failure has occurred to be halted/arrested in a shorter period of time without adopting a mechanical brake mechanism. The present invention is an electric actuator drive device having: a power source; actuator drive motors (11A, 11B) fed by the power source and for driving an actuator (B1); and a motor control circuit (C) for performing a regenerative braking operation on the actuator drive motors (11A, 11B). The electric actuator drive device has: an anomaly occurrence determination means (D1) that determines wither or not an anomaly has occurred at a needed location; and a regenerative braking means (D3) that, by means of the motor control circuit (C), performs a regenerative braking operation on the actuator drive motors (11A, 11B).
H02P 3/22 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an AC motor by short-circuit or resistive braking
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
90.
Electricity generation device and permanent-magnet electric generator
An electricity generation device includes a permanent-magnet electric generator with three or more phase windings each having an output terminal and connected to a neutral point, and bidirectional semiconductor switching circuits capable of interrupting connections between the respective phase windings and the neutral point. Each switching circuit allows current to flow in both directions. A gate signal generation circuit outputs to one of the switching circuits during a period including the time at which the AC voltage excited in the corresponding phase winding turns from positive to negative and during a period including the time at which the AC voltage excited in the corresponding phase winding turns from negative to positive. A startup gate signal output circuit outputs a startup gate signal to all of the bidirectional semiconductor switching circuits when the permanent-magnet electric generator is to be started.
H02P 9/14 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field
H02P 29/02 - Providing protection against overload without automatic interruption of supply
H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
H02P 9/00 - Arrangements for controlling electric generators for the purpose of obtaining a desired output
The present invention enables greater compactness and lightweightness in addition to being able to be applied to transient, large, instantaneous current arising during electric actuator acceleration. The present invention is an electric actuator drive device having an electric actuator (10) and a generator motor (50) for driving the electric actuator (10), wherein the electric actuator drive device has a generator motor drive means (C8) that rotationally drives the generator motor (50) in a manner so as to be at a rotational frequency at which large, instantaneous current arising during electric actuator (10) acceleration/deceleration is delivered.
H02K 7/20 - Structural association with auxiliary dynamo-electric machines, e.g. with electric starter motors or exciters
H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
An additional pad 27 is additionally and integrally arranged from an outer surface of a flange 17 opposite to a contacting side of the flange 17 to a small-diameter curved surface of a bend 19 and from there to an end of an outer surface of a part body 13. On an outer surface side of the additional pad 27, a fastening seat 27f is formed by machining. An area end PAe of a processed area PA formed by machining is positioned on the part body 13 beyond the bend 19.
B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
Provided is a moulded article in which an additional pad (27) is added and provided as a single piece from an outer surface on the opposite side to a butting side of a flange (17), running over a curved surface on the small diameter side of a curved part (19), up to one end on the outer surface of an article body (13). A clamping seat surface (27f) is formed by mechanical processing on the outer surface of the additional pad (27), and an area end (PAe) of the processed area (PA) which has been mechanically processed is located on the article body (13) side beyond the curved part (19).
B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
When it is determined that the number of times that motor rotation-indicative quantity has been detected has exceeded a measurement interval, a feedback speed value is calculated from a motor rotation-indicative quantity detected immediately before, a motor rotation-indicative quantity detected immediately before the last time a measurement interval determination means determined that the number of times had exceeded the measurement interval, and time that has elapsed since the last time the measurement interval determination means determined that the number of times had exceeded the measurement interval, and the measurement interval having a length calculated from a greater one between the calculated feedback speed value and a speed command value is set for the measurement interval determination means to refer to.
H02P 3/00 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters
G05B 19/29 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by positioning or contouring control systems, e.g. to control position from one programmed point to another or to control movement along a programmed continuous path using an absolute digital measuring device for point-to-point control
B64C 17/06 - Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus by gyroscopic apparatus
G01P 3/481 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
H02P 23/03 - Arrangements or methods for the control of AC motors characterised by a control method other than vector control specially adapted for very low speeds
A space probing apparatus is provided that can further enhance its thermal protective function for electronic apparatuses and batteries that are apparatuses each having a narrow range of permissible temperature.
The space probing apparatus includes, as a vehicle body 1 that is an apparatus body, an inner housing 13 that accommodates an electronic apparatus 11 and a battery 12, and an outer housing 15 that accommodates the inner housing 13 supporting the inner housing 13 afloat therein. A thermal insulating layer 16 is formed between the inner housing 13 and the outer housing 15 using a space therebetween. A heat dissipating body 17 is included in an upper portion of the inner housing 13. A lid 18 is included in an upper portion of the outer housing 15. The whole outer faces of the inner and the outer housings 13 and 15 are each covered with a thermal insulating material 20. Thereby, in the nighttime, the temperature of the battery 12 is maintained using the least necessary amount of heat generated and, thereby, the electronic apparatus 11 and the battery 12 are protected from an ultralow temperature. In the daytime, the lid 18 is opened and heat is discharged using the heat dissipating body 17 and, thereby, the electronic apparatus 11 and the battery 12 are protected from a high temperature.
A method for manufacturing a cylindrical structure having an axial direction includes: winding a first layer around a mandrel, the first layer including a plurality of fabrics each made of fibers, the fabrics forming a first join line extending in a circumferential direction with edges of the fabrics in contact with each other; winding a second layer around the first layer, the second layer including a plurality of fabrics each made of the fibers, the fabrics forming a second join line extending in the circumferential direction with edges of the fabrics in contact with each other, in such a manner as to displace the second join line from the first join line in the axial direction; winding a third layer around the second layer, the third layer including a plurality of fabrics each made of the fibers, the fabrics forming a third join line extending in the circumferential direction with edges of the fabrics in contact with each other, in such a manner as to displace the third join line from both of the first join line and the second join line in the axial direction; and joining the layers together by using a resin.
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
97.
CYLINDRICAL STRUCTURE AND METHOD FOR MANUFACTURING SAME
A method for manufacturing a cylindrical structure having an axial direction comprises: winding fabric around a mandrel, the fabric containing first reinforcing fibers oriented in a first direction intersecting the circumferential direction which is perpendicular to the axial direction; helically winding roving around the mandrel, the roving containing second reinforcing fibers oriented in the longitudinal direction thereof; and joining the fabric and the roving by means of a resin.
B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
C08J 5/06 - Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F04D 29/52 - CasingsConnections for working fluid for axial pumps
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A method for manufacturing a cylindrical structure having an axial direction includes: winding a fabric around a mandrel in a circumferential direction that is perpendicular to the axial direction, the fabric containing first fibers oriented in a first direction intersecting the circumferential direction; winding a roving into a helical shape around the mandrel, the roving containing second fibers oriented in a longitudinal direction of the roving; and joining the fabric and the roving together by using a resin.
B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
C08J 5/06 - Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F04D 29/52 - CasingsConnections for working fluid for axial pumps
99.
CYLINDRICAL STRUCTURE AND METHOD OF PRODUCTION THEREOF
The disclosed method for production of a cylindrical structure having an axis direction comprises winding a first layer containing plural textile layers composed respectively of reinforced fibers around a mandrel to form a first join line by contact of the edges thereof extending in the circumferential direction; winding a second layer containing plural textile layers composed respectively of the reinforced fibers around the first layer to form a second join line by contact of the edges thereof extending in the circumferential direction with the second join line shifted from the first join line in the axis direction; winding a third layer containing plural textile layers composed respectively of the reinforced fibers around the second layer to form a third join line by contact of the edges thereof extending in the circumferential direction with the third join line shifted from both of the first join line and the second join line in the axis direction; and bonding the layers together with a resin.
B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29C 70/10 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
Disclosed is a fiber-reinforced plastic structure, comprising: fibers comprising one or more substances selected from a group consisting of glass, carbon, aramid, alumina, and boron; and a matrix resin composition with which the fibers are impregnated and bonded to one another. The matrix resin composition comprises: a matrix containing a bisphenol-based epoxy-containing resin and a curing agent; and particles containing one or more elastomers selected from a group consisting of polybutadiene rubber, styrene butadiene rubber, and butyl rubber, having an average particle diameter of from 0.01 to 0.5 μm, and primarily dispersed in the matrix by mixing with the matrix in an amount of from 1 to 50 parts by weight based on 100 parts by weight of the resin.
