Aircraft based non-dedicated special mission pod mounting apparatus

• US 10,106,239 B2
• Filed: 08/31/2017
• Issued: 10/23/2018
• Est. Priority Date: 10/17/2007
• Status: Active Grant

• Current Assignee: 1281329 Alberta Ltd.
• Original Assignee: 1281329 Alberta Ltd.
• Inventors: Woodland, Richard L. K., Neyedly, Ross James
• Primary Examiner(s): Lee, Benjamin P
• Application Number:
  US15/692,903
• Publication Number:
  US 20180022437A1
• Time in Patent Office: 418 Days
• CPC Class Codes: B64C 1/1461 Structures of doors or surrounding frames
• CPC Class Codes: B64C 1/36 adapted to receive antennas or radomes
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B64D 7/00 Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft dropping bombs or the like B64D1/00; armaments or mountings therefor per se F41

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.

Claims

1. A mission payload mounting apparatus comprising:

an adaptive mounting system (AMS) plate adapted to attach to one or more Air Deployment System (ADS) rails of an aircraft via one or more restraint and bolt devices;

a strut that is coupled to the AMS plate, wherein the strut extends from an interior of the aircraft to an exterior of the aircraft; and

one or more removable load transfer braces (LTB s) which interface to the AMS plate and extend inboard from the AMS plate to interface to a floor of the aircraft, wherein;

the one or more LTBs are hinged to the AMS plate via one or more flanges; and

the one or more LTBs can be rotated to a vertical position via the one or more flanges upon disconnection of the inboard interface to the floor of the aircraft.

2. The apparatus of claim 1, wherein the strut extends from the interior of the aircraft to the exterior of the aircraft via a pressurized door plug that interfaces to the aircraft.

3. The apparatus of claim 2, wherein the pressurized door plug comprises:

a single piece door plug;

or

a combined door plug upper panel and a door plug lower panel.

4. The apparatus of claim 1, wherein the strut is coupled to the AMS plate via:

coupling a bolt assembly to the strut;

coupling a flange to the AMS plate; and

coupling the bolt assembly to the flange.

5. The apparatus of claim 1, wherein the strut is capable of being rotationally actuated.

6. The apparatus of claim 4, wherein the strut is capable of being rotationally actuated by:

one or more electric drive motors;

or

one or more hand wrenches.

7. The apparatus of claim 5, further comprising a shoulder armature assembly coupled to a first end of the strut, wherein the strut is coupled to the AMS plate via the shoulder armature assembly.

8. The apparatus of claim 7, further comprising a wrist armature assembly, wherein the wrist armature assembly is couple to a second end of the strut.

9. The apparatus of claim 8, wherein the wrist armature assembly is mechanically connected to the shoulder armature assembly.

10. The apparatus of claim 9, wherein the wrist armature assembly is further capable of being maintained in a vertical position while the strut is rotationally actuated through a range of angles.

11. The apparatus of claim 10, wherein the vertical position is vertical in relation to the aircraft.

12. The apparatus of claim 10, wherein the strut is capable of being articulated to a position below a lower periphery of the aircraft.

13. The apparatus of claim 1, wherein a first end of the one or more LTBs is interfaced to the floor of the aircraft via one or more cargo tie down “

D”

rings and one or more adjustable cam locks secured by one or more adjustment bolts.

14. The apparatus of claim 1, wherein the AMS plate is milled to accommodate one or more restraint and bolt devices specific to the ADS rails, wherein the restraint and bolt devices are operable to interface the AMS plate and the ADS rails.

15. The apparatus of claim 1, further comprising an ordinance rack attached to a portion of the strut on the exterior of the aircraft.

16. The apparatus of claim 15, wherein the ordinance rack further comprises one or more adjustable sway braces adapted for one or more payloads attached to the ordinance rack.

17. The apparatus of claim 1, wherein the AMS plate, the strut, and the one or more LTBs are housed in a strut transport and alignment case that is temporarily attached to the floor of the aircraft for installing the apparatus to the aircraft.

18. A method of installing a mission payload mounting apparatus to an aircraft comprising:

attaching an adaptive mounting system (AMS) plate to one or more Air Deployment System (ADS) rails of an aircraft via one or more restraint and bolt devices;

coupling a strut to the AMS plate, wherein the strut extends from an interior of the aircraft to an exterior of the aircraft; and

connecting one or more removable load transfer braces (LTBs) to the AMS mounting plate, wherein;

the one or more LTBs extend inboard from the AMS mounting plate to interface to a floor of the aircraft;

the one or more LTBs are hinged to the AMS via one or more flanges; and

the one or more LTBs can be rotated to a vertical position via the one or more flanges upon disconnection of the inboard interface to the floor of the aircraft.

19. The method of claim 18, wherein:

the strut extends from the interior of the aircraft to the exterior of the aircraft through a doorway on a side of a fuselage of the aircraft; and

the doorway is sealed by a pressurized door plug, the pressurized door plug being adapted to allow the extension of the strut through the pressurized door plug.

20. The method of claim 18, wherein coupling the strut to the AMS plate comprises:

coupling a bolt assembly to the strut;

coupling a flange to the AMS plate; and

coupling the bolt assembly to the flange.