Abstract: A door assembly for a payload bay (10) having an opening (12), the door assembly comprising at least one door (20, 220). The at least one door comprises: a panel section (22, 222) having a first end (24, 224) and a second end (26, 226); and a first mounting member (30, 230) arranged orthogonally to the panel section at the first end and having a first engagement feature (31, 231) having a rotational axis (18, 218) about which the panel section is arranged to rotate. The engagement feature is arranged to engage with a first fixing member (16, 216) on one side of the payload bay to rotatably couple the panel section to the payload bay. The at least one door is arranged to translate between a closed configuration, in which the panel section is arranged in the same plane as the opening, and an open configuration, in which the panel section is arranged at at least 90 degrees to the plane of the opening, by rotating about the rotational axis.

Abstract: A payload mechanism for a vehicle is provided.

Abstract: A payload mechanism for a vehicle is provided.

Abstract: The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one planar control surface moves from a first position to a second position, and wherein in the first position the planar control surface is controllable to affect substantially only the pitch of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the yaw, or in the first position the planar control surface is controllable to affect substantially only the yaw of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the pitch of the vehicle. The present invention also provides a method of controlling a vehicle.

Abstract: The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one planar control surface moves from a first position to a second position, and wherein in the first position the planar control surface is controllable to affect substantially only the pitch of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the yaw, or in the first position the planar control surface is controllable to affect substantially only the yaw of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the pitch of the vehicle. The present invention also provides a method of controlling a vehicle.

Abstract: The present invention provides an actuating system, comprising: a rotatable member rotatable relative to a fixed member; at least one actuator coupled to the rotatable member and to the fixed member; and a planar control surface coupled to the rotatable member such that the control surface extends perpendicularly from the periphery of the rotatable member wherein, in use, when a first actuator is in a first configuration the rotatable member is rotated such that the planar control surface is arranged in a first position, and when the first actuator is in a second configuration the rotatable member is rotated such that the planar control surface rotates about the central axis of the rotatable member to be arranged in a second position. The present invention also provides a vehicle and a part for a vehicle having the actuating system, as well as a method of actuating a control surface for a vehicle.

Abstract: An aircraft (2) comprising a launch tube (14) extending along at least part of a length of a wing of the aircraft (2), and through which an item (24) may be launched from the aircraft (2). The launch tube (14) comprises an opening (22) at a distal end of the wing (6).

Abstract: An aircraft (2) comprising a launch tube (14) extending along at least part of a length of a wing of the aircraft (2),and through which an item (24) may be launched from the aircraft (2). The launch tube (14) comprises an opening (22) at a distal end of the wing (6).

Abstract: A system comprising: a low observable aircraft (2) having its external surfaces oriented at a limited number of directions; a device (12) mounted to the aircraft (2) outside the external surfaces of the aircraft (2); and a fairing (10) located outside the external surfaces of the aircraft (2), the fairing (10) being releasably coupled to the one or more external surfaces of the aircraft (2), at least part of the fairing (10) being spaced apart from one or more of the external surfaces of the aircraft (2) so as to define a chamber between the fairing (10) and that one or more external surfaces of the aircraft (2). The device (12) is wholly located within the chamber. One or more external surfaces of the fairing (10) are oriented in the same direction as at least one external surface of the aircraft (2).

Abstract: A system comprising: a low observable aircraft (2) having its external surfaces oriented at a limited number of directions; a device (12) mounted to the aircraft (2) outside the external surfaces of the aircraft (2); and a fairing (10) located outside the external surfaces of the aircraft (2), the fairing (10) being releasably coupled to the one or more external surfaces of the aircraft (2), at least part of the fairing(10) being spaced apart from one or more of the external surfaces of the aircraft (2) so as to define a chamber between the fairing (10) and that one or more external surfaces of the aircraft (2). The device (12) is wholly located within the chamber. One or more external surfaces of the fairing (10) are oriented in the same direction as at least one external surface of the aircraft (2).

Abstract: A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.

Abstract: A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.