In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

In one embodiment, an apparatus includes a door plug assembly with a sonotube-launch system to be used in a temporarily-mounted control system for an aircraft. The door plug assembly is built from one or more panels designed to fit an opening in the fuselage of the aircraft, the opening being created by the removal of a door on the side of the fuselage. The door plug assembly includes a segmented bubble window with transparent glazing, with a kick panel on the lower portion of the bubble. The door plug assembly further includes a door strut indent which allows a strut to extend from the interior of the aircraft through the indent to the exterior of the aircraft. When a strut is not being used, a close-out panel is secured to the door plug assembly to allow the interior of the aircraft to be pressurized.

In one embodiment, an apparatus includes a door plug assembly with a sonotube-launch system to be used in a temporarily-mounted control system for an aircraft. The door plug assembly is built from one or more panels designed to fit an opening in the fuselage of the aircraft, the opening being created by the removal of a door on the side of the fuselage. The door plug assembly includes a segmented bubble window with transparent glazing, with a kick panel on the lower portion of the bubble. The door plug assembly further includes a door strut indent which allows a strut to extend from the interior of the aircraft through the indent to the exterior of the aircraft. When a strut is not being used, a close-out panel is secured to the door plug assembly to allow the interior of the aircraft to be pressurized.

In one embodiment, a temporarily-mounted control system is installed in an aircraft. The temporarily-mounted control system includes a temporary door plug assembly that is adapted to in an opening in a fuselage of the aircraft, such as an opening created by removing a door in the fuselage. The temporary door plug is connected to a retraction rail assembly that connects the temporary door plug and the fuselage. One or more workstation assemblies is mounted to the floor of the aircraft using mounting plates that are attached to adaptive floor plates connected to the floor of the aircraft. An observer chair assembly is connected to the floor of the aircraft and to the workstation assemblies.

In one embodiment, a temporarily-mounted control system is installed in an aircraft. The temporarily-mounted control system includes a temporary door plug assembly that is adapted to in an opening in a fuselage of the aircraft, such as an opening created by removing a door in the fuselage. The temporary door plug is connected to a retraction rail assembly that connects the temporary door plug and the fuselage. One or more workstation assemblies is mounted to the floor of the aircraft using mounting plates that are attached to adaptive floor plates connected to the floor of the aircraft. An observer chair assembly is connected to the floor of the aircraft and to the workstation assemblies.

The system and apparatus of the present invention is generally comprised of a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly which are affixed to the Air Deployment System (ADS) rails, cargo tie down D rings, seat belt restraint ring bolt sockets, and litter bar of a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door refraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

In one embodiment, a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly are affixed to a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.