Temporarily-installed aircraft observer door plug, chair, sonotube ejection and control system

• US 9,567,058 B2
• Filed: 01/10/2013
• Issued: 02/14/2017
• Est. Priority Date: 10/15/2007
• 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:
  US13/738,935
• Publication Number:
  US 20140077034A1
• Time in Patent Office: 1,496 Days
• Field of Search: 244/118.2, 244/137.1, 244/118.1, 244/129.1, 244/129.5, 244/137.4, 89/15.4, 89/15.8, 89/15.9, 89/371.6, 89/371.7, 89/372.1, 89/372.2
• US Class Current: 1/1
• CPC Class Codes: B64C 1/1407 Doors; surrounding frames
• CPC Class Codes: B64C 1/1484 Windows B64C1/1492 takes precedence
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64C 1/20 specially adapted for freight
• CPC Class Codes: B64D 1/02 Dropping, ejecting, or releasing articles jettisonable fuel reservoirs B64D37/12
• CPC Class Codes: B64D 11/00 Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• CPC Class Codes: B64D 11/06 Arrangements of seats, or adaptations or details specially adapted for aircraft seats crew seat constructions for emergency purposes B64D25/04
• CPC Class Codes: B64D 11/0616 with ejection means
• CPC Class Codes: B64D 11/062 Belts or other passenger restraint means for passenger seats
• 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

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.

Claims

1. An apparatus comprising a mounting plate connecting one or more line-replaceable unit (LRU) racks to a floor of an aircraft, wherein:

the mounting plate is connected to an adaptive floor plate via one or more restraint bolts or adjustable CAM locks; and

the adaptive floor plate is connected to the floor of the aircraft, wherein the adaptive floor plate comprises aircraft type-specific bolt patterns corresponding to;

one or more cargo floor tie down rings of the aircraft;

or

one or more tie down ring bolt socket patterns of the aircraft.

2. The apparatus of claim 1, wherein one or more of the LRU racks are contoured, wherein the contour complies with a fuselage curvature of the aircraft.

3. The apparatus of claim 1, wherein the LRU racks comprise a reduced-height LRU rack and a full-height mission LRU rack.

4. The apparatus of claim 3, further comprising a workstation operable to connect to an upper surface of the reduced-height LRU rack.

5. The apparatus of claim 4, wherein one or more of the workstation or the LRU racks are electronically interfaced to one or more of:

a data bus of the aircraft;

or

a modified ditching hatch plug.

6. The apparatus of claim 4, further comprising a control interface connected to an observer chair connected to the aircraft, wherein the control interface is connected to the work station via at least power and data cables.

7. The apparatus of claim 4, wherein the workstation comprises a plurality of physically connected modules.

8. The apparatus of claim 7, wherein two or more of the physically connected modules are physically connected at least by one or more locking hinges.

9. The apparatus of claim 8, further comprising one or more module hinge release actuators operable to release one or more of the module locking hinges.

10. The apparatus of claim 7, wherein the plurality of physically connected modules comprises one or more of:

an overhead module;

an upper display module;

a lower display module;

or

a tactile interface module.

11. The apparatus of claim 10, further comprising:

an oxygen cylinder housed within a frame of the tactile interface module; and

one or more oxygen controls connected to the tactile interface module.

12. The apparatus of claim 10, further comprising:

one or more wrist pads connected to the tactile interface module at least by one or more hinges; and

one or more wrist pad bins connected to the tactile interface module, each wrist pad bin located under one of the wrist pads.

13. The apparatus of claim 12, further comprising a joystick that is operable to interface with the tactile interface module and fit within one or more of the wrist pad bins.

14. The apparatus of claim 10, wherein one or more of a forward edge of the overhead module or a forward edge of the tactile interface module comprise a chamfered foam edging.

15. The apparatus of claim 1, wherein one or more of the LRU racks are operable to connect to a litter bar connected to a fuselage of the aircraft.

16. The apparatus of claim 1, wherein the mounting plate is further operable to connect the LRU racks to a fuselage of the aircraft via one or more seat belt sockets.

17. The apparatus of claim 16, wherein the mounting plate is further operable to connect the LRU racks to the fuselage of the aircraft via the seat belt sockets and one or more of:

one or more multiple restraint bolts;

or

one or more self-tightening chocks.

18. The apparatus of claim 1, wherein the mounting plate is further operable to connect the one or more LRU racks to the floor of the aircraft via an upper surface of an Air Deployment System (ADS) rail connected to the floor of the aircraft.

19. The apparatus of claim 18, wherein one or more of the LRU racks are contoured, and wherein the contour accommodates fitment outboard the ADS rail.

20. The apparatus of claim 18, wherein the hinges are operable to enable collapse of the work station such that the work station would fit outboard the ADS rail, between the ADS rail and a fuselage of the aircraft.

21. The apparatus of claim 18, wherein the mounting plate is further operable to connect to the floor of the aircraft via the upper surface of the ADS rail and one or more CAM locks.