A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

A vertical takeoff and landing (VTOL) aircraft, including: a vehicle controller circuit programmed to operate the VTOL aircraft without an onboard human operator; a rotor system; an airframe; and an external cargo coupling to receive an external payload of at least approximately 300 pounds beneath the airframe.

A system and method for ejecting a store from an aircraft include a stowage tube configured to retain the store. The stowage tube includes an open rear end. A door panel is coupled to the stowage tube. An actuator driven linkage is coupled to the door panel. The actuator driven linkage is configured to rotate the door panel about a pivot axis at a forward edge opposite from an aft end between a closed position associated with a stowed position of the system and an open position associated with a deployed position of the system. The stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed 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.

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

A projectile delivery module to be mounted on an aerial vehicle includes a projectile delivery system including a kinetic projectile and a base system. The kinetic projectile includes a projectile body, an RF receiver, and an onboard steering system including: a steering mechanism operable to change an attitude, orientation, and/or direction of flight of the kinetic projectile; and a steering actuator. The base system includes: an RF transmitter to communicate with the RF receiver; a projectile holder; a target tracking system; and a projectile guidance system including a projectile tracking system and a projectile control system. The base system is configured to: release the kinetic projectile from the projectile holder such that the kinetic projectile is driven toward a target by gravity; track the target using the target tracking system; track the released kinetic projectile using the projectile tracking system; and automatically control the onboard steering system using the projectile control system to adjust a trajectory of the falling kinetic projectile to steer the kinetic projectile to the target.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.