A stator for a brushless DC motor, the stator comprising: a plurality of coil windings; and a layered stack of laminations positioned around a centre axis, wherein the layered stack of laminations defines an annular shape, and wherein each lamination from the layered stack of laminations has: a first plurality of teeth, wherein the first plurality of teeth extend radially towards the centre axis and define a first plurality of channels between the first plurality of teeth, wherein each channel of the first plurality of channels is configured to receive at least a portion of a coil winding; a second plurality of teeth, wherein the second plurality of teeth extend radially away from the centre axis and define a second plurality of channels between the second plurality of teeth, wherein each channel of the second plurality of channels is configured to receive at least a portion of a coil winding; and wherein each of the first plurality of channels and the second plurality of channels is provided with a layer of electrically insulating ceramic material such that each coil winding of the 15 plurality of coil windings is electrically isolated from the layered stack of laminations.
H02K 3/02 - Windings characterised by the conductor material
H02K 3/28 - Layout of windings or of connections between windings
H02K 3/30 - Windings characterised by the insulating material
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
b) configured to drive the screw nut. In use, the at least one motor applies a torque to the sleeve via the screw nut. When the applied torque is below a threshold value, the sleeve is restricted from rotating about the stroke axis, such that rotation of the screw nut causes linear displacement of the sleeve and actuator rod together along the stroke axis. When the applied torque equals or exceeds the threshold value, the sleeve is able to rotate about the stroke axis, such that rotation of the screw nut causes rotation of the sleeve, and such that rotation of the sleeve causes linear displacement of the actuator rod.
A signal transmitter apparatus configured for use in an aircraft moveable element monitoring system. The signal transmitter apparatus comprising a signal transmitter circuit. The signal transmitter circuit comprises: a first electrical path between a voltage input and a first node, the first electrical path comprising an inductor; a second electrical path between the first node and a second node, the second electrical path comprising a signal transmitter coil and a first capacitor, wherein the signal transmitter coil is electrically connected in series with the first capacitor; a third electrical path between the first node and the second node, the third electrical path comprising a second capacitor, such that the second capacitor is electrically connected in parallel to the signal transmitter coil and the first capacitor; and a fourth electrical path between the second node and the voltage input.
G01D 5/20 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying inductance, e.g. by a movable armature
B64F 5/60 - Testing or inspecting aircraft components or systems
G01R 25/00 - Arrangements for measuring phase angle between a voltage and a current or between voltages or currents
4.
PRECISION MANUFACTURE OF HYDRAULIC AND PNEUMATIC COMPONENTS
A method of manufacturing a hydraulic or pneumatic component is provided, the method comprising: providing a blank having a first surface and a second surface; applying laser radiation to the blank, thereby removing material from the blank by photoablation so as to form: a first aperture in the first surface; a second aperture in the second surface; a passage between the first aperture and the second aperture, wherein the passage is configured to provide a fluid flow path in use; and optionally a plurality of indents on an internal surface of the passage.
B23K 26/0622 - Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
B23K 26/142 - Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beamNozzles therefor for the removal of by-products
B23K 26/352 - Working by laser beam, e.g. welding, cutting or boring for surface treatment
B23K 26/361 - Removing material for deburring or mechanical trimming
B23K 26/382 - Removing material by boring or cutting by boring
A stator for a brushless DC motor, the stator comprising: a plurality of coil windings; and a layered stack of laminations positioned around a centre axis, wherein the layered stack of laminations defines an annular shape, and wherein each lamination from the layered stack of laminations has: a first plurality of teeth, wherein the first plurality of teeth extend radially towards the centre axis and define a first plurality of channels between the first plurality of teeth, wherein each channel of the first plurality of channels is configured to receive at least a portion of a coil winding; a second plurality of teeth, wherein the second plurality of teeth extend radially away from the centre axis and define a second plurality of channels between the second plurality of teeth, wherein each channel of the second plurality of channels is configured to receive at least a portion of a coil winding; and wherein each of the first plurality of channels and the second plurality of channels is provided with a layer of electrically insulating ceramic material such that each coil winding of the 15 plurality of coil windings is electrically isolated from the layered stack of laminations.
H02K 3/30 - Windings characterised by the insulating material
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 1/276 - Magnets embedded in the magnetic core, e.g. interior permanent magnets [IPM]
09 - Scientific and electric apparatus and instruments
Goods & Services
Road surface measurement apparatus; computer hardware and
software systems for tracking, monitoring, diagnosing and
analyzing of road surface and pavement conditions; hardware
interface which links the computer to the in-vehicle
equipment; roughness instruments to measure road roughness;
video camera with character overplay device to measure the
right of way and pavement; transverse profile loggers to
measure across the road and rutting; gyroscope for bearing,
pitch and roll; accelerometers for gradient measurements;
dust meters for dust measurements on unsealed roads; manual
longitudinal profile logger for roughness measurements
and/or calibration; hand held data loggers for manual
surveys and traffic counts.
A prosthesis or orthosis housing, including a cylinder configured to receive a piston of a piston and cylinder assembly, a pump section configured to receive part of a pump, and a plurality of passages connecting the cylinder to the pump section, the plurality of passages being smoothly curved along their lengths and devoid of any right-angle bends, wherein the cylinder, the pump section, the plurality of passages, and the prosthesis or orthosis housing form a unitary piece.
A61F 5/01 - Orthopaedic devices, e.g. long-term immobilising or pressure directing devices for treating broken or deformed bones such as splints, casts or braces
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Real-time event detection, monitoring, and reporting system
comprised of computer hardware, cameras, sensors, recorded
computer software, and downloadable mobile application
software; recorded computer software and downloadable mobile
application software for detection, monitoring, and
reporting foreign object debris, birds, drones, and pavement
damage; recorded computer software and downloadable mobile
application software for location mapping; recorded computer
software and downloadable mobile application software for
storing and reviewing event detection logs and statistics;
recorded computer software and downloadable mobile
application software for storing and reviewing images and
videos. Providing online, non-downloadable software for detection,
monitoring, and reporting foreign object debris, birds,
drones, and pavement damage; providing online,
non-downloadable software for location mapping; providing
online, non-downloadable software for storing and reviewing
event detection logs and statistics; providing online,
non-downloadable software for storing and reviewing images
and videos; providing online, non-downloadable software for
generation of predictive and preventative maintenance
reports based on analysis of data collected by a real-time
event detection, monitoring, and reporting system.
09 - Scientific and electric apparatus and instruments
Goods & Services
Road surface measurement apparatus; computer hardware and
software systems for tracking, monitoring, diagnosing and
analyzing of road surface and pavement conditions; hardware
interface which links the computer to the in-vehicle
equipment; roughness instruments to measure road roughness;
video cameras with character overplay device to measure the
right of way and pavement; transverse profile loggers to
measure across the road and rutting; gyroscope for
bearing/pitch/roll; accelerometers for gradient
measurements; dust meters for dust measurements on unsealed
roads; manual longitudinal profile loggers for roughness
measurements/calibration; hand held data loggers for manual
surveys and traffic counts.
A linear actuator (100) comprising a stroke axis (102), an actuator rod (104)extending along the stroke axis. The actuator rod comprises: an actuator rod outer surface (110), and a first screw thread (108) on a portion of the actuator rod outer surface; a sleeve (118) positioned around, and coaxial with, the actuator rod. The sleeve comprises: a sleeve inner surface (122), a sleeve outer surface (130), a second screw thread (120) on a portion of the sleeve inner surface, the second screw thread configured to engage with the first screw thread, and a third screw thread (128) on a portion of the sleeve outer surface. A screw nut (136) is provided configured to engage with the third screw thread. At least one motor (142a, 142b) configured to drive the screw nut. In use, the at least one motor applies a torque to the sleeve via the screw nut. When the applied torque is below a threshold value, the sleeve is restricted from rotating about the stroke axis, such that rotation of the screw nut causes linear displacement of the sleeve and actuator rod together along the stroke axis. When the applied torque equals or exceeds the threshold value, the sleeve is able to rotate about the stroke axis, such that rotation of the screw nut causes rotation of the sleeve, and such that rotation of the sleeve causes linear displacement of the actuator rod.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Consultancy in the field of monitoring and analysis of road
surface and pavement conditions; research and development in
the field of hardware and software systems for tracking,
monitoring, diagnosing and analyzing of road surface and
pavement conditions.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Consultancy in the field of monitoring and analysis of road
surface and pavement conditions; research and development in
the field of hardware and software systems for tracking,
monitoring, diagnosing and analyzing of road surface and
pavement conditions.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Real-time event detection, monitoring, and reporting system comprised of computer hardware, cameras, optical sensors and radar sensors, recorded computer software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage, location mapping, storing and reviewing logs and statistics pertaining to the detection of foreign object debris, birds, drones, and pavement damage, and storing and reviewing images and videos , and downloadable mobile application software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage, location mapping, storing and reviewing logs and statistics pertaining to the detection of foreign object debris, birds, drones, and pavement damage, and storing and reviewing images and videos; recorded computer software and downloadable mobile application software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage; recorded computer software and downloadable mobile application software for location mapping; recorded computer software and downloadable mobile application software for storing and reviewing logs and statistics pertaining to the detection of foreign object debris, birds, drones, and pavement damage; recorded computer software and downloadable mobile application software for storing and reviewing images and videos. (1) Providing online, non-downloadable software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage; providing online, non-downloadable software for location mapping; providing online, non-downloadable software for storing and reviewing logs and statistics pertaining to the detection of foreign object debris, birds, drones, and pavement damage; providing online, non-downloadable software for storing and reviewing images and videos; providing software as a service (SAAS) services, namely providing online, non-downloadable software for tracking and managing airfields by generation of predictive and preventative maintenance reports based on analysis of data collected by a system for the real-time detection, monitoring, and reporting of events in the nature of foreign object debris, birds, drones, and pavement damage
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Real-time event detection, monitoring, and reporting system comprised of computer hardware, cameras, electric and radar sensors, recorded computer software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage, location mapping, storing and reviewing event detection logs and statistics, and storing and reviewing images and videos, and downloadable mobile application software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage, location mapping, storing and reviewing event detection logs and statistics, and storing and reviewing images and videos; recorded computer software and downloadable mobile application software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage; recorded computer software and downloadable mobile application software for location mapping; recorded computer software and downloadable mobile application software for storing and reviewing event detection logs and statistics; recorded computer software and downloadable mobile application software for storing and reviewing images and videos Providing online, non-downloadable software for detection, monitoring, and reporting foreign object debris, birds, drones, and pavement damage; providing online, non-downloadable software for location mapping; providing online, non-downloadable software for storing and reviewing event detection logs and statistics; providing online, non-downloadable software for storing and reviewing images and videos; providing online, non-downloadable software for generation of predictive and preventative maintenance reports based on analysis of data collected by a real-time event detection, monitoring, and reporting system
09 - Scientific and electric apparatus and instruments
Goods & Services
(1) Instruments for measuring road surface condition parameters; computer hardware and integrated software for tracking, monitoring, diagnosing and analyzing of road surface and pavement conditions; hardware interface which links the computer to the in-vehicle equipment; roughness instruments to measure road roughness; video cameras with character overplay device to measure the right of way and pavement; transverse profile loggers to measure across the road and rutting; gyroscope for bearing/pitch/roll; accelerometers for gradient measurements; dust meters for dust measurements on unsealed roads; manual longitudinal profile loggers for roughness measurements/calibration; hand held data loggers for manual surveys and traffic counts.
09 - Scientific and electric apparatus and instruments
Goods & Services
Road surface condition measurement apparatus; computer hardware and downloadable computer software systems for tracking, monitoring, diagnosing, and analyzing of road surface and pavement conditions; computer hardware interface which links the computer to the in-vehicle equipment; surface roughness testing instruments to measure road roughness; video cameras with character overplay device to measure the right of way and pavement; transverse profile loggers, namely, electronic data loggers to measure across the road and rutting; gyroscope for bearing, pitch, and roll; accelerometers for gradient measurements; electric dust meters for dust measurements on unsealed roads; manual longitudinal profile loggers, namely, electronic data loggers for roughness measurements and calibration; hand held electronic data loggers for manual surveys and traffic counts
09 - Scientific and electric apparatus and instruments
Goods & Services
(1) Instruments for measuring road surface condition parameters; computer hardware and integrated software for tracking, monitoring, diagnosing and analyzing of road surface and pavement conditions; hardware interface which links the computer to the in-vehicle equipment; roughness instruments to measure road roughness; video camera with character overplay device to measure the right of way and pavement; transverse profile loggers to measure across the road and rutting; gyroscope for bearing, pitch and roll; accelerometers for gradient measurements; dust meters for dust measurements on unsealed roads; manual longitudinal profile logger for roughness measurements and/or calibration; hand held data loggers for manual surveys and traffic counts.
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Consultancy in the field of monitoring and analysis of road surface and pavement conditions; research and development in the field of hardware and software systems for tracking, monitoring, diagnosing and analyzing of road surface and pavement conditions.
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Consultancy in the field of monitoring and analysis of road surface and pavement conditions; research and development in the field of hardware and software systems for tracking, monitoring, diagnosing and analyzing of road surface and pavement conditions.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific research and engineering consultancy in the field of monitoring and analysis of road surface and pavement conditions; research and development in the field of computer hardware and software systems for tracking, monitoring, diagnosing, and analyzing of road surface and pavement conditions
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific research and engineering consultancy in the field of monitoring and analysis of road surface and pavement conditions; research and development in the field of computer hardware and software systems for tracking, monitoring, diagnosing, and analyzing of road surface and pavement conditions
09 - Scientific and electric apparatus and instruments
Goods & Services
Road surface condition measurement apparatus; computer hardware and downloadable computer software systems for tracking, monitoring, diagnosing, and analyzing of road surface and pavement conditions; computer hardware interface which links the computer to the in-vehicle equipment; surface roughness testing instruments to measure road roughness; video cameras with character overplay device to measure the right of way and pavement; transverse profile loggers, namely, electronic data loggers to measure across the road and rutting; gyroscope for bearing, pitch, and roll; accelerometers for gradient measurements; electric dust meters for dust measurements on unsealed roads; manual longitudinal profile loggers, namely, electronic data loggers for roughness measurements and calibration; hand held electronic data loggers for manual surveys and traffic counts
23.
AIRCRAFT CONTROL SURFACE ELEMENT MONITORING SYSTEM
A signal transmitter apparatus configured for use in an aircraft moveable element monitoring system. The signal transmitter apparatus comprising a signal transmitter circuit. The signal transmitter circuit comprises: a first electrical path between a voltage input and a first node, the first electrical path comprising an inductor; a second electrical path between the first node and a second node, the second electrical path comprising a signal transmitter coil and a first capacitor, wherein the signal transmitter coil is electrically connected in series with the first capacitor; a third electrical path between the first node and the second node, the third electrical path comprising a second capacitor, such that the second capacitor is electrically connected in parallel to the signal transmitter coil and the first capacitor; and a fourth electrical path between the second node and the voltage input.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
H02J 50/12 - Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling of the resonant type
H02J 50/80 - Circuit arrangements or systems for wireless supply or distribution of electric power involving the exchange of data, concerning supply or distribution of electric power, between transmitting devices and receiving devices
A skew detection system for an aircraft flight control surface, the flight control surface being moveable relative to fixed structure of the aircraft by operation of a first gear rack driven by a first gear pinion and by operation of a second gear rack driven by a second gear pinion, the skew detection system including a first sensor arrangement and a second sensor arrangement, the first gear rack having a first set of teeth defining a plurality of first targets, the second gear rack having a second set of teeth defining a plurality of second targets, the plurality of first targets being configured to move relative to the first sensor arrangement and the plurality of second targets being configured to move relative to the second sensor arrangement, the skew detection system including a monitoring device to monitor the output from the first and second sensors and determine whether a skew condition has arisen in the flight control surface.
c). An exemplary moveable element signal transmission unit (115) includes a first signal transmission unit coil and a second signal transmission unit coil, the first signal transmission unit coil being electrically connected to the second signal transmission unit coil. Each moveable element signal transmission unit is configured to be installed on a respective moveable element of an aircraft. The signal transmitter coil, the one or more moveable element signal transmission units and the signal receiver coil form an inductively coupled transmission line. The signal generator is configured to provide an electrical signal to the signal transmitter coil and the signal detector is configured to detect the electrical signal via the signal receiver coil. The signal detector is further configured to determine a condition of the one or more moveable elements by comparing the detected electrical signal to a predetermined signal characteristic.
A device having an input element, an output element, and a drive element, the device having a first position configured such that the drive element is engaged with the input element and the output element to prevent movement of the input element in a first direction relative to the output element, the device having a second position configured such that the drive element is engaged with the input element and a further element to prevent movement of the input element in the first direction relative to the further element.
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
F16D 43/204 - Internally controlled automatic clutches actuated entirely mechanically controlled by torque, e.g. overload-release clutches, slip-clutches with means by which torque varies the clutching pressure of the ratchet type with intermediate balls or rollers
F16D 3/10 - Couplings with means for varying the angular relationship of two coaxial shafts during motion
F16D 7/06 - Slip couplings, e.g. slipping on overload, for absorbing shock of the ratchet type with intermediate balls or rollers
F16H 35/10 - Arrangements or devices for absorbing overload or preventing damage by overload
27.
Control surface element skew and/or loss detection system
An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part. The sensor is configured to detect a first relative position of the first and second parts indicative of the wing structure supporting a load, and a second relative position of the first and second parts indicative of the wing structure being supported.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01L 5/10 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring tension in flexible members, e.g. ropes, cables, wires, threads, belts or bands using electrical means
A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).
A skew detection system for an aircraft flight control surface, the flight control surface being moveable relative to fixed structure of the aircraft by operation of a first gear rack driven by a first gear pinion and by operation of a second gear rack driven by a second gear pinion, the skew detection system including a first sensor arrangement and a second sensor arrangement, the first gear rack having a first set of teeth defining a plurality of first targets, the second gear rack having a second set of teeth defining a plurality of second targets, the plurality of first targets being configured to move relative to the first sensor arrangement and the plurality of second targets being configured to move relative to the second sensor arrangement, the skew detection system including a monitoring device to monitor the output from the first and second sensors and determine whether a skew condition has arisen in the flight control surface.
An aircraft moveable element monitoring system is provided. An exemplary aircraft moveable element monitoring system includes a signal generator (108), a signal transmitter coil (110) electrically connected to the signal generator (108); a signal detector (112); a signal receiver coil (114) electrically connected to the signal detector (112); and one or more moveable element signal transmission units (115a-c). An exemplary moveable element signal transmission unit (115) includes a first signal transmission unit coil and a second signal transmission unit coil, the first signal transmission unit coil being electrically connected to the second signal transmission unit coil. Each moveable element signal transmission unit is configured to be installed on a respective moveable element of an aircraft. The signal transmitter coil, the one or more moveable element signal transmission units and the signal receiver coil form an inductively coupled transmission line. The signal generator is configured to provide an electrical signal to the signal transmitter coil and the signal detector is configured to detect the electrical signal via the signal receiver coil. The signal detector is further configured to determine a condition of the one or more moveable elements by comparing the detected electrical signal to a predetermined signal characteristic.
An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part. The sensor is configured to detect a first relative position of the first and second parts indicative of the wing structure supporting a load, and a second relative position of the first and second parts indicative of the wing structure being supported.
A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device(103), a second actuator (104A)for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator(104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
A prosthesis comprises a housing(100); a piston (221) and piston rod (222) housed within a cylinder of the housing(100); and a pump (244) mounted on and partially within the housing(100). The housing (100) is a unitary piece and comprises a plurality of passages (151, 152, 153, 154) connecting the cylinder to the part of the housing (100) where the pump (244) is mounted.
An actuator including a housing, a piezo electric disc having a first side and a second side and defining an outer rim, an elastomeric seal, wherein the outer rim is received in the housing and the elastomeric seal engages the first side proximate the outer rim to seal the first side to the housing, the elastomeric seal engages the second side proximate the outer rim to seal the second side to the housing.
F16K 11/07 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
A method for releasing a fluid from a pressure vessel assembly, the method including the steps of providing:- a pressure vessel; a piezo electric device; and an electric field generator; arranging the piezo electric device in a sealed relationship with a part of the pressure vessel, thereby providing the pressure vessel assembly, providing a fluid contained within the pressure vessel assembly under pressure, and using the electric field generator to apply an electric field to the piezo electric device, such that the piezo electric device fails, thereby releasing the fluid from the pressure vessel assembly.
A firing mechanism (25) for activation of a pneumatic stored energy system having a motor (50) connected to a vessel (20) by a tether, the vessel (20) containing a pressurised fluid. Activation of the motor (50) causes the tether to wind, applying a linear force to an attachment region of the vessel, fracturing the vessel (20) to release the pressurised fluid thereby activating the pneumatic stored energy system.
B60R 21/274 - Inflatable occupant restraints or confinements designed to inflate upon impact or impending impact, e.g. air bags characterised by the inflation fluid source or means to control inflation fluid flow using instantaneous release of stored pressurised gas characterised by means to rupture or open the fluid source
A servovalve has a pilot stage (100) having a piezoelectric element (150) actuating a pilot stage spool valve (196), which pilot stage spool valve comprises an output control fluid line to a main stage.
F15B 13/043 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure with electrically-controlled pilot valves
A servovalve pilot stage assembly is provided having a first fluid conduit (152) having a first orifice (156), a second fluid conduit (154) having a second orifice (158), a flapper (44) having a deformable first region (176) disposed between the first orifice and the second orifice, an actuator (24) arranged to drive the flapper (44) from a first condition in which the first region of the flapper has a first width between the first and second orifice to a second condition in which the first region of the flapper has a second width between the first and second orifice, the second width being less than the first width.
F15B 13/043 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure with electrically-controlled pilot valves
An aircraft control surface actuation assembly comprises a first electromechanical actuator assembly (44) driven by two independent motors (48, 50) for redundancy, with a damping assembly (46) provided to mitigate flutter.
A servovalve pilot stage (100) comprises a piezoelectric actuator (130) joined to a flow guide (132) and feedback wire (136) for connection to a main stage spool valve. The flow guide (132) and the piezoelectric actuator (130) may be integral.
F15B 13/043 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure with electrically-controlled pilot valves
F16K 31/363 - Operating meansReleasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor the fluid acting on a piston
A servovalve pilot stage (100) comprises a piezoelectric actuator (130) joined to a flow guide (132) and feedback wire (136) for connection to a main stage spool valve. The flow guide (132) and the piezoelectric actuator (130) may be integral.
F16K 31/363 - Operating meansReleasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor the fluid acting on a piston
F15B 13/043 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure with electrically-controlled pilot valves
The present invention relates generally to flow regulation in aircraft systems. More particularly, the present invention relates to a flow regulator 100 and a high-lift system 200 for an aircraft incorporating such a flow regulator 100. The flow regulator 100 comprises a fluid input port 102 for receiving a pressurized fluid, a fluid output port 104 for providing fluid having a regulated flow rate, and a regulator valve 106 connected in fluid communication between the fluid input port 102 and the fluid output port 104. The regulator valve 106 is operable to provide regulated fluid at a substantially constant output flow rate to the fluid output port 104. The flow regulator 100 also includes a flow switching mechanism 108 for switching the substantially constant output flow of the flow regulated fluid provided by the regulator valve 106 between a first flow rate and a second flow rate, the first flow rate being less than the second flow rate.
A control surface element skew and/or loss detection system (100) is provided which combines a cable (168, 178) system linked to movement transducers (120) via mechanical links (114, 116) connecting the fixed wing structure (102) to the control surface elements (106, 112).
The present invention relates generally to flow regulation in aircraft systems. More particularly, the present invention relates to a flow regulator (100) and a high-lift system (200) for an aircraft incorporating such a flow regulator (100). The flow regulator (100) comprises a fluid input port 102 for receiving a pressurised fluid, a fluid output port (104) for providing fluid having a regulated flow rate, and a regulator valve (106) connected in fluid communication between the fluid input port (102) and the fluid output port (104). The regulator valve 106 is operable to provide regulated fluid at a substantially constant output flow rate to the fluid output port (104). The flow regulator (100) also includes a flow switching mechanism (108) for switching the substantially constant output flow of the flow regulated fluid provided by the regulator valve (106) between a first flow rate and a second flow rate, the first flow rate being less than the second flow rate.
The present invention provides a panel device for modifying airflow about a wing (110) of an aircraft (120). The panel device may be used to provide a flap (100) or a leading edge slat. The panel device comprises a plurality of independently operable panel sub-sections (102, 104, 106). Each panel sub-section (102, 104, 106) has a panel authority lower than a predetermined critical threshold value so as to allow simple economic control of synchronisation. The panel device provides for both improved fuel efficiency as well as enhanced operational safety of the aircraft (120).
The present invention relates to a hydraulic actuator, in particular an electrically driven hydraulic actuator. An example of the electrically driven hydraulic actuator comprises a variable speed motor, a variable capacity displacement pump arranged to be driven by the variable speed motor; and a hydraulic actuator driven by the variable displacement pump. Being able to vary the speed of the motor and the displacement of the pump enables the actuator to be able to be operated very flexibly and the motor does not have to be driven at an excessively high or low speed reducing wear and over-heating of the motor.
F15B 11/042 - Systems essentially incorporating special features for controlling the speed or the actuating force or speed of an output member for controlling the speed by means in the feed line
F15B 15/18 - Combined units comprising both motor and pump
A diaphragm coupling having first and second diaphragm plates that are joined together around their outer edges. Each diaphragm plate has a central, axially-extending hub. The hub of the first plate supports within it a pin member having an outwardly projecting shoulder at each end adapted to engage an internal shoulder on the hub of the first plate at one end and an internal shoulder on the hub of the second plate at the other end so as to limit axial separation of the two hubs—from one another.
F16D 3/79 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members shaped as an elastic disc or flat ring, arranged perpendicular to the axis of the coupling parts, different sets of spots of the disc or ring being attached to each coupling part, e.g. Hardy couplings the disc or ring being metallic
48.
MAGNETIC TORQUE COUPLING HAVING AN INNER ROTOR MOUNTED FOR AXIAL MOVEMENT RELATIVE TO AN OUTER ROTOR
The invention broadly provides a torque coupling (20) arranged to act between a variable-speed rotating shaft (21) and an energy-storage device (22), comprising: an inner rotor (23) mounted for rotation with the shaft and mounted for movement along the axis of the shaft; an outer rotor (25) surrounding the shaft, adapted to surround the inner rotor, and operatively connected to the energy-storage device, the inner rotor being rotationally coupled to the outer rotor when the inner rotor is arranged within the outer rotor and being rotationally uncoupled from the outer rotor when the inner rotor is arranged axially beyond the outer rotor; and an actuator (A) operatively arranged to selectively move the inner rotor axially along the shaft axis relative to the outer rotor; whereby the inner rotor may be selectively moved to a position relative to the outer rotor to permit the transfer of energy between the shaft and the energy-storage device.
