A missile launching system for launching missiles from a mobile platform includes a rectangular primary carrier frame having a platform coupling structure for releasably fastening the first carrier frame to the mobile platform, and a launch tube. A locking device on the primary carrier frame includes a lock hook which projects from the primary carrier frame and has a receiving piece. A stop piece extends transverse to the receiving piece. A locking plate is inserted between the receiving piece and the stop piece. The launch tube has a fastening bracket with a fastening recess fitted onto the receiving piece and locked with the lock hook by inserting the locking plate between the stop piece and the receiving piece. Alternatively, two launch tube receiving devices are laterally attached to the primary carrier frame, each of which is designed as a closed frame defining a receiving opening.

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.

An autonomous aircraft system an airframe configured with a ventrally located payload bay open to the empennage of said airframe and payload bay terminating with a forward bulkhead which is configured to receive a payload module. The payload bay and the payload module are configured with corresponding fittings for connecting the payload module to the aircraft control systems and for securing the payload module within the payload bay.

An autonomous aircraft system an airframe configured with a ventrally located payload bay open to the empennage of said airframe and payload bay terminating with a forward bulkhead which is configured to receive a payload module. The payload bay and the payload module are configured with corresponding fittings for connecting the payload module to the aircraft control systems and for securing the payload module within the payload bay.

A computer implemented method for integrating a platform, different stores, and/or carriage racks is implemented in an electronics control system that is communicatively couplable to each of the platform, the different stores, and/or the carriage racks. The computer implemented method includes defining parameters for a plurality of predetermined electrical interfaces for predetermined platforms, stores, and carriage racks, and message sets corresponding thereto, identifying electrical interfaces of the platform, at least one store and/or at least one carriage rack based on the defined parameters, communicating different messages between the platform, the store and/or the carriage rack without affecting an Operational Flight Program (OFP) of the platform, with each communication between the platform, and the store and/or the carriage rack being independent, translating messages between the platform and the store and/or the carriage rack, and controlling operation of the carriage rack and/or the store based on the messages.

A computer implemented method for integrating a platform, different stores, and/or carriage racks is implemented in an electronics control system that is communicatively couplable to each of the platform, the different stores, and/or the carriage racks. The computer implemented method includes defining parameters for a plurality of predetermined electrical interfaces for predetermined platforms, stores, and carriage racks, and message sets corresponding thereto, identifying electrical interfaces of the platform, at least one store and/or at least one carriage rack based on the defined parameters, communicating different messages between the platform, the store and/or the carriage rack without affecting an Operational Flight Program (OFP) of the platform, with each communication between the platform, and the store and/or the carriage rack being independent, translating messages between the platform and the store and/or the carriage rack, and controlling operation of the carriage rack and/or the store based on the messages.

A device for accommodating and deploying at least one payload on a flying machine includes at least one housing. The housing includes at least two opposite first side surfaces which extend over at least a portion of a length of a payload to be accommodated. The payload to be accommodated is releasably held between the two first side surfaces of the housing. The housing is at least partially arranged in a cavity on an outer surface of a flying machine. The cavity includes at least one outwardly open first opening, and the housing can be at least partially moved out of the cavity for deploying and/or receiving the payload to be accommodated.

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.

A system and method for cooling a missile includes an assembly of Peltier tiles configured to be reversibly attached to the skin of the missile with the cold sides of the Peltier tiles against the skin. The Peltier tiles are electrically powered to cool a portion of the missile skin. A thermally conductive paste or sheets of a heat conductive material may be placed between the Peltier tiles and missile skin. When the missile is launched, the assembly of Peltier tiles detach from the missile.