A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.

A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.

Disclosed herein is an auxiliary-pod mounting system for mounting an auxiliary pod to a landing skid assembly of a helicopter. The landing skid assembly comprises a forward crossbar, a rearward crossbar, and skids coupled to the forward crossbar and the rearward crossbar. The auxiliary-pod mounting system comprises a first rail. The auxiliary-pod mounting system also comprises a second rail, spaced apart from the first rail. The auxiliary-pod mounting system further comprises a mounting plate, interposed between and coupled to the first rail and the second rail. The mounting plate comprises pod engagement features configured to engage the auxiliary pod and to secure the auxiliary pod to the mounting plate. The auxiliary-pod mounting system additionally comprises a plurality of brackets configured to couple the first rail and the second rail to the forward crossbar and the rearward crossbar of the landing skid assembly of the helicopter.

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).

A payload mechanism for a vehicle is provided. The payload mechanism comprises: a door (2) operable to be in a closed configuration or an open configuration within a recess of the vehicle, the recess having an aperture (10); a first bearing unit comprising a first bearing (3a) and a second bearing (4a), the first bearing unit being coupled to one end of the door such that the door can rotate about the axis of rotation (y) of the first bearing and wherein the first bearing unit can rotate about the axis of rotation (x) of the second bearing, wherein the axis of rotation of the first bearing is offset from the axis of rotation of the second bearing; and a drive unit arranged to selectively drive either: the first bearing and the second bearing simultaneously at opposite and equal angular rates of motion to rotate the door in a first direction about the axis of rotation of the first bearing and to rotate the first bearing unit in a second direction about the axis of rotation of the second bearing to move the door closer to or away from the aperture, or the first bearing but not the second bearing to rotate the door about the axis of rotation of the first bearing. Methods of operating said payload mechanism are also provided, along with a vehicle having the payload mechanism.

A rail launch mechanism and method for launching a payload is configured to release payload lugs of a payload from a platform. A rack for launching a payload includes multiple rails that separately engage lugs in the respective payload of the rails, and a force actuator for launching the payload by accelerating the payload along the rails, causing the lugs to separate from the respective rails. A launching system for launching the payload from the platform may include a rail, at least one payload release shoe that carries a payload lug along the rail, and a force actuator for accelerating the payload release shoe such that inertia of the payload causes the payload lug to be released from the payload release shoe.

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.

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).

A modular missile launch system for launching missiles from a mobile platform includes a rectangular first support frame having a first longitudinal beam having a platform coupling structure formed for releasably fastening the first support frame to the mobile platform. A second longitudinal beam arranged at a distance from the first longitudinal beam includes a first connecting structure on an underside and a launch tube securing structure for mounting a missile launch tube to the first support frame. The first connecting structure defines a first plug connection portion extending in a longitudinal direction, onto which a second support frame with a second plug connection portion can be plugged in the vertical direction, having at least two first through bores that are spaced apart in the longitudinal direction, through each of which one connecting device can be passed in order to secure the first and the second support frame.

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.