A mitigation control system is arranged in an environment containing an energetic material and includes an abnormal temperature sensor for detecting an abnormal temperature of the environment, a power source that is mechanically actuated by the abnormal temperature sensor when the abnormal temperature exceeds a predetermined abnormal temperature threshold, a mitigation controller that is actuated by the power source, and a plurality of local temperature sensors that are communicatively coupled to the mitigation controller and are arranged for detecting critical temperatures in specific regions of the environment. The mitigation controller executes a mitigation action when one of the critical temperatures exceeds a predetermined critical temperature threshold for the corresponding specific region.

The present disclosure relates to an ejecting system (1) for dispensing countermeasure. The system (1) comprising at least one magazine (2) comprising at least one expendable cartridge (3) and a transporting rack (4) extending in a first direction (D1). Further, the system (1) comprises a magazine feeding mechanism (5) arranged to cooperate with said transporting rack (4) to move each of the at least one magazines (2) from a stored position to a loaded position. Further, the system (1) comprises a dispensing means (6) arranged to hold said at least one magazine (2) when said at least one magazine (2) is in a loaded position, wherein the dispensing means (6) comprises an electrical connector arrangement (7). Moreover, the system (1) comprises a first positioning mechanism (8) arranged to move said dispensing means (6) and the at least one magazine (2) from the loaded position to a protruding position.

The present invention relates to a casing intended to be externally applied, connected or fixed to the fuselage or to a wing of an aircraft or to a central or wing station/hardpoint of an aircraft, the casing entirely or partly delimiting a housing zone (HZ) of a super-orbital, orbital or sub-orbital launch vehicle.

A multi-mission munition adapter for an aircraft may be configured to attach to a hardpoint and hold a plurality of munitions, such as missiles and bombs. A top of the multi-mission munition adapter may have suspension lugs configured to attach to a hardpoint on an aircraft. Sides of the multi-mission munition adapter may have one or more launcher attachment fittings configured to attach missile launchers. A bottom of the multi-mission munition adapter may have one or more munitions ejector hangers configured to attach air-to-ground munitions ejectors. The adapter may comprise an electrical system that permits an aircraft to communicate with and/or power all functions of the bomb rack, missile launchers, and the weapons employed.

Arming apparatus is installable between twin arming units of an ejector release unit in a military aircraft, and a single fuzing unit of a store. The arming apparatus comprises sequentially breakable links which ensure reliable ejection of the store in an armed state, or jettisoning of the store in an unarmed state, as desired.

The present disclosure relates to an ejecting system (1) for dispensing countermeasure. The system (1) comprising at least one magazine (2) comprising at least one expendable cartridge (3) and a transporting rack (4) extending in a first direction (D1). Further, the system (1) comprises a magazine feeding mechanism (5) arranged to cooperate with said transporting rack (4) to move each of the at least one magazines (2) from a stored position to a loaded position. Further, the system (1) comprises a dispensing means (6) arranged to hold said at least one magazine (2) when said at least one magazine (2) is in a loaded position, wherein the dispensing means (6) comprises an electrical connector arrangement (7). Moreover, the system (1) comprises a first positioning mechanism (8) arranged to move said dispensing means (6) and the at least one magazine (2) from the loaded position to a protruding position.

A deployment system for deploying a store from an aircraft includes a lock member that selectively engages the store to the deployment system, an ejector that selectively ejects the store from the deployment system, and a deployment system controller communicatively coupled to the lock member and to the ejector, the system controller communicatively coupled to the aircraft to receive commands from the aircraft, wherein upon receipt of a master arm command from the aircraft the system controller maintains the lock member in an engaged state relative to the store, and wherein upon receipt of a fire command from the aircraft the system controller disengages the lock member from the store and activates the ejector to eject the store from the deployment system.

A deployment system for deploying a store from an aircraft includes a lock member that selectively engages the store to the deployment system, an ejector that selectively ejects the store from the deployment system, and a deployment system controller communicatively coupled to the lock member and to the ejector, the system controller communicatively coupled to the aircraft to receive commands from the aircraft, wherein upon receipt of a master arm command from the aircraft the system controller maintains the lock member in an engaged state relative to the store, and wherein upon receipt of a fire command from the aircraft the system controller disengages the lock member from the store and activates the ejector to eject the store from the deployment system.

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.