According to various embodiments, there is provided a grinding module including a base; a cylinder mounted to the base with a longitudinal axis of the cylinder arranged at least substantially perpendicular to a surface of the base, wherein the cylinder is rotatable about the longitudinal axis of the cylinder, and wherein a cylindrical surface of the cylinder is adapted to receive a grinding belt; a linear actuator mounted to the base with a centreline of linear motion of the linear actuator arranged to intersect the longitudinal axis of the cylinder; and a holder connected to the linear actuator, the holder adapted to hold a workpiece with a surface of the workpiece facing the cylindrical surface of the cylinder, wherein the linear actuator is adapted to move the holder relative to the cylinder along the centreline of linear motion of the linear actuator, and wherein the cylindrical surface of the cylinder is adapted to define a curved profile so that the grinding belt is adapted to grind and shape the surface of the workpiece to conform to the curved profile.
B24B 41/06 - Work supports, e.g. adjustable steadies
B24B 47/06 - Drives or gearings for grinding machines or devices; Equipment therefor for performing a reciprocating movement of carriages or work-tables by liquid or gas pressure only
B24B 19/26 - Single purpose machines or devices for particular grinding operations not covered by any other main group for grinding workpieces with arcuate surfaces, e.g. parts of car bodies, bumpers or magnetic recording heads
Various embodiments provide a portable electronic device holder (400, 500, 600, 700, 900, 1100, 1400) for a passenger seat (202), including a longitudinal clamping structure (420, 520) having a generally L-shaped cross-section. The clamping structure includes a supporting flap (422, 522) forming an L-base of the generally L- shaped clamping structure and configured to support a portable electronic device, and a clamping flap (424, 524) forming an L-leg of the generally L-shaped clamping structure and configured to clamp the portable electronic device against a surface (650) abutting the portable electronic device. The portable electronic device holder further includes a mounting element (410, 510) for slidably or titlably mounting the clamping structure to the passenger seat.
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
B60N 3/00 - Arrangements or adaptations of other passenger fittings, not otherwise provided for
B60R 11/02 - Arrangements for holding or mounting articles, not otherwise provided for for radio sets, television sets, telephones, or the like; Arrangement of controls thereof
Various embodiments provide a method for installing a seat suspension on a seat frame having a first side frame member and a second side frame member opposed to and spaced apart from each other. The method may include moving a retainer on a first side of the seat suspension in a direction substantially perpendicular to a plane defined by the first and second side frame members for fastening onto a support member on the first side frame member; and moving a retainer on a second side of the seat suspension in the direction substantially perpendicular to the plane defined by the first and second side frame members for fastening onto a support member on the second side frame member. The second side of the seat suspension is opposed to and spaced apart from the first side of the seat suspension.
An apparatus for launch and recovery of an Unmanned Aerial Vehicle (UAV), a method for launching a UAV, a method for recovering a UAV and a kit of parts for launch and recovery of a UAV are disclosed. The apparatus comprises a boom having a center member for receiving the UAV, and first and second arm members extending outwardly and upwardly from the center member, wherein the boom is configured to be lifted to a predetermined height into the air from a reference point; and wherein the boom is movable in the air to an operating position forward of the reference point.
An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.
B64C 27/10 - Helicopters with two or more rotors arranged coaxially
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
A seatback for a passenger seat, a passenger seat, and a method of manufacturing a seatback for a passenger seat. The seatback comprises an upwardly extending base having a front and a rear, the front capable of supporting a passenger; a pocket attached to the rear; a tray table attached to the rear and operable between a stowage position and a use position; and wherein the rear has a longitudinal length and a transverse width, with the tray table, when in the stowage position, being at least partly transversely aligned with pocket.
Various embodiments provide a method for landing an unmanned aerial vehicle (UAV) (2) in the presence of a wind. The method comprises: performing a first flare- maneuver whilst the UAV is flying. The flare-maneuver causes a front portion of the UAV to rise with respect to a rear portion of the UAV (202). The method also comprises steering the UAV along a path heading into a direction of the wind (204). The method further comprises performing a second flare- maneuver before the UAV impacts a landing surface to land (206). Various embodiments provide a corresponding UAV.
A headrest structure for a passenger seat, a headrest cushion and passenger seat. The headrest structure comprises an adjustable headrest frame for connection to a passenger seat; and a headrest cushion mounted to the adjustable headrest frame such that the headrest cushion is moveable relative to a seat back of the passenger seat by way of the adjustable headrest frame; wherein the headrest cushion comprises a support surface facing away from the headrest frame, the support surface comprising a concave upper part and a convex bottom part relative to the passenger seat.
A support structure for attachment to a tray table for a passenger seat, a tray table for a passenger seat, and a passenger seat. The support structure comprises a support arm shaped to substantially match at least a first portion of a peripheral contour of the tray table; and a connecting structure for connecting the support arm to the tray table in a manner such that the support arm is configurable into a stowed position in which the support arm extends substantially along said at least first portion of the peripheral contour of the tray table and at least one support position for supporting an item on the tray table in an angled orientation between a surface of the item and the surface of the tray table.
A seat leg assembly for a passenger seat, a frame for a passenger seat, and a passenger seat. The seat leg assembly comprising a brace member configured to extend from a front end of a base frame of the passenger seat to a rear floor fitting; a front leg configured to extend from a front floor fitting to the brace member and connected to the brace member; a rear leg portion extending from a rear end of the base frame to the brace member; and a first joint structure connecting the rear leg portion to the brace member.
A seat structure for a passenger seat, and a passenger seat. In one embodiment, the seat structure comprises a seat pan for mounting on a frame structure of the passenger seat in a manner such that the seat pan is moveable in forward and backward directions relative to the frame independently from movement of a seat back of the passenger seat; and biasing means for biasing the seat pan in a default position.
A seat pan for a passenger seat and a passenger seat. The seat pan is corrugated for partially absorbing a downward loading applied to the seat pan through deformation of a corrugation pattern of the seat pan as a result of a counter force applied by a support structure of the passenger seat.
Various embodiments provide a method for improving crosswind stability of a propeller duct. The method comprises defining an initial duct section based on a predetermined airfoil section having an initial value of a geometric parameter such that the geometric parameter of a portion of the initial duct section has the initial value. The method also comprises determining fluid flow paths around the initial duct section when subject to a crosswind having a predetermined crosswind speed. The method further comprises varying the initial value of the geometric parameter of the initial duct section to a threshold value which causes separation of fluid flow paths at a windward side of the initial duct section at and above the predetermined crosswind speed to form an improved duct section. Various embodiments provide a corresponding apparatus, system and/or computer readable medium.
An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
Disclosed herein is a single arm adjustment mechanism for supporting an object, the single arm adjustment mechanism comprising: a support arm; an upper adjustment assembly coupled to an upper end of said support arm, said upper adjustment assembly capable of being coupled to said object such that said object pivots about a first axis; and a lower adjustment assembly capable of being fixed to a support and pivotally coupled to a lower end of said support arm such that said support arm pivots about a second axis parallel to said first axis in order to maintain said object in a desired angular orientation with respect to said support.
Embodiments of the present invention provide a tow hook for use in launching an unmanned aerial vehicle (UAV), the tow hook comprising: a first end capable of releasably engaging a wing of the UAV, a second end capable of being connected to a tow line; and a rigid member connecting the first end to the second end to extend a connection point said tow line below said wing towards a center of gravity of said UAV. Additional embodiments provide for a system and method for launching a UAV using the tow hook.
A system and method for collision avoidance between an aircraft and surrounding objects on the ground is provided. The system may include a controller interface; a plurality of laser sensors mounted on the aircraft and electrically connected to the controller interface, each of the plurality of laser sensors having a detection area, such that said detection areas cumulatively cover at least a periphery of both a left and a right wing of the aircraft; audio and visual warning means located in a cockpit of the aircraft, each of the audio and visual warning means being electrically connected to the controller interface; and at least one video camera mounted on the aircraft and electrically connected to the controller interface, such that when said at least one video camera is activated, said video camera provides an image of said periphery to said visual warning means; wherein the controller interface receives a signal from at least one of the laser sensors indicating the presence of an object within the detection area and activates at least one of the audio warning means and said at least one video camera to alert an operator of the aircraft that a collision is possible.
A method and system for conducting radar cross section measurements are provided. The method comprises the steps of positioning an active screen between a transceiver unit and a target area; periodically switching the active screen between an OPEN position in which the active screen is electromagnetically transparent and a CLOSE position in which the active screen is electromagnetically opaque; transmitting electromagnetic signals towards the target area utilising the transceiver unit; measuring a first received signal when the active screen is in the OPEN position; measuring a second received signal when the active screen is in the CLOSE position; and deriving a target signature based on the measured first and second received signals; wherein a frequency of the switching of the active screen is chosen such that respective background components in the first and second received signals are substantially constant.
G01S 7/41 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group using analysis of echo signal for target characterisation; Target signature; Target cross-section
patents