Abstract: In one embodiment, a method includes removing a cargo handling rail from a cargo floor of an aircraft and installing a brace system directly into the cargo floor. The brace system includes a support plate and a spreader bar. The support plate is parallel to the cargo floor and has a surface that interfaces with the cargo floor and multiple slots for rollers. The spreader bar is parallel to the cargo floor and perpendicular to a cargo handling rail face and parallel to the support plate.

Abstract: Particular embodiments include a mission payload mounting apparatus. The mission payload apparatus includes a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut.

Abstract: 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.

Abstract: Particular embodiments include a mission payload mounting apparatus. The mission payload apparatus includes a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut.

Abstract: In particular embodiments, a mission payload mounting apparatus comprises a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The strut is capable of being rotationally actuated about an axis exterior to the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut between the axis and the second end.

Abstract: 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.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system comprising a pressurized door plug assembly installed in an opening on the side of an aircraft fuselage. A rotationally-actuated strut extends from a first end connected to an interior of the aircraft fuselage, through the pressurized door plug assembly, to a second end of the strut connected to one or more payloads. The rotational axis of the strut is exterior to the aircraft fuselage.

Abstract: 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.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system comprising a pressurized door plug assembly installed in an opening on the side of an aircraft fuselage. A rotationally-actuated strut extends from a first end connected to an interior of the aircraft fuselage, through the pressurized door plug assembly, to a second end of the strut connected to one or more payloads. The rotational axis of the strut is exterior to the aircraft fuselage.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting System (AMS) plate is placed over an ADS rail section and restrained in position. Once the AMS plate is secured, an articulated or fixed position strut can be attached to the AMS plate through the opened side doorway without removing the original door. A removable load transfer brace (LTB) can be coupled from the AMS plate inboard to the floor of the aircraft. The LTB is hinged to the AMS plate, and can be disconnected from the floor of the aircraft and rotated to a vertical position from the AMS plate.

Abstract: 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.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting System (AMS) plate is placed over an ADS rail section and restrained in position. Once the AMS plate is secured, an articulated or fixed position strut can be attached to the AMS plate through the opened side doorway without removing the original door. A removable load transfer brace (LTB) can be coupled from the AMS plate inboard to the floor of the aircraft. The LTB is hinged to the AMS plate, and can be disconnected from the floor of the aircraft and rotated to a vertical position from the AMS plate.

Abstract: 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.

Abstract: 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.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to the AMP through the opened side doorway without removing the original door. Once the strut is secured to the AMP, a one-piece or segmented two-piece pressurized door plug is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft. The mission payload mounting system can be housed in a strut transport and alignment case which is temporarily attached to the floor of the aircraft during installation of the system, then removed.

Abstract: 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.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to the AMP through the opened side doorway without removing the original door. Once the strut is secured to the AMP, a one-piece or segmented two-piece pressurized door plug is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft. The mission payload mounting system can be housed in a strut transport and alignment case which is temporarily attached to the floor of the aircraft during installation of the system, then removed.

Abstract: Particular embodiments comprise a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to it through the opened side doorway without removing the original door. Once the fixed position or articulated strut is bolted to the AMP, a one piece or segmented two piece pressurized door plug indented along its lower periphery to accommodate the protruding form factor of the fixed position or articulated strut is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft.

Abstract: Particular embodiments comprise a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to it through the opened side doorway without removing the original door. Once the fixed position or articulated strut is bolted to the AMP, a one piece or segmented two piece pressurized door plug indented along its lower periphery to accommodate the protruding form factor of the fixed position or articulated strut is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft.

Abstract: 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 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.