Abstract: The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

Abstract: A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibers, a matrix incorporating the fibers, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.

Abstract: The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

Abstract: A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibres, a matrix incorporating the fibres, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.

Abstract: The invention covers a missile canister (10) for accommodating a missile (20) along a longitudinal axis (L) of the canister. The canister comprises a plurality of generally planar longitudinal wall portions (14) connected together to form a tubular vessel having a polygonal cross-section. The interconnecting portions (16) between wall sections (14) are generally flexible so that when a missile (20) is launched the bending moment at the interconnecting portions (16) generated by the increase of pressure in the vessel is substantially less than the bending moment (10) generated at the wall portions (14). The interconnecting portions (16) allow relative angular deflection between adjacent wall portions (14) at respective interconnecting portions (16) when said missile (20) is launched.

Abstract: The invention covers a missile canister (10) for accommodating a missile (20) along a longitudinal axis (L) of the canister. The canister comprises a plurality of generally planar longitudinal wall portions (14) connected together to form a tubular vessel having a polygonal cross-section. The interconnecting portions (16) between wall sections (14) are generally flexible so that when a missile (20) is launched the bending moment at the interconnecting portions (16) generated by the increase of pressure in the vessel is substantially less than the bending moment (10) generated at the wall portions (14). The interconnecting portions (16) allow relative angular deflection between adjacent wall portions (14) at respective interconnecting portions (16) when said missile (20) is launched.

Abstract: A missile launcher comprising a canister for housing a missile and piston based launcher, the piston being arrested in the tube after launch of the missile.

Abstract: A missile launcher comprising a canister for housing a missile and piston based launcher, the piston being arrested in the tube after launch of the missile.

Abstract: A dual servo system for a seeker actuator comprises a seeker head gimballed on a platform and driven in the pitch and yaw senses by respective fast, i.e. high bandwidth low ambit, servo sub-systems, the platform being pivotally mounted with respect to a base and driven in the pitch and yaw senses by respective slow, i.e. low bandwidth high ambit, servo systems. The pivotal mounting between the platform and the base is configured to provide a spherical bearing of relatively large area (typically about 85° solid angle) to provide good resistance to high acceleration loads.

Abstract: A projectile reaction control system includes a nozzle assembly in which the efflux exhausted thereby may be controlled in a continuously variable fashion. In one example control is by means of a slidable piston so that the thrust developed by the nozzle assembly is substantially linearly dependent on the displacement of the piston, whereby the reaction control system may be controlled by an autopilot with little or no modification.