Unmanned aerial vehicle for logistical delivery

• US 7,059,566 B2
• Filed: 05/27/2004
• Issued: 06/13/2006
• Est. Priority Date: 06/20/2003
• Status: Expired due to Fees

• Current Assignee: The United States of America As Represented By The Secretary of The Navy Chief of Naval Research
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Milgram, Judah H., Strickland, Jason D., Macander, Aleksander B., Hall, Gary A., Kennell, Colen G., Byers, David W., Hunter, Graham D.
• Primary Examiner(s): Luu, Teri Pham
• Assistant Examiner(s): Holzen, Stephen A.
• Application Number:
  US10/856,360
• Publication Number:
  US 20050006525A1
• Time in Patent Office: 747 Days
• Field of Search: 244/137.1, 244/136, 244/137.2, 244/137.3, 244138-141, 244/117.R, 244/118.1, 244/118.2, 244/119, 244/125, 244/118.5
• US Class Current: 244/119
• CPC Class Codes: B64C 1/061 Frames
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 1/22 Other structures integral with fuselages to facilitate loading , e.g. cargo bays, cranes
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 3/58 provided with fences or spoilers adjustable for control purposes B64C9/00
• CPC Class Codes: B64C 31/02 Gliders, e.g. sailplanes hang-gliders B64C31/028
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 5/00 Aircraft transported by aircraft, e.g. for release or reberthing during flight flying units formed by separate aircraft B64C37/02
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 2101/69 the UAVs provided with means for airdropping goods, e.g. deploying a parachute during descent
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 50/15 using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
• CPC Class Codes: B64U 70/20 for releasing or capturing UAVs in flight by another aircraft
• CPC Class Codes: B64U 70/60 Take-off or landing of UAVs from a runway using their own power
• CPC Class Codes: B64U 70/70 Launching or landing using catapults, tracks or rails launching from storage containers B64U70/50
• CPC Class Codes: B64U 70/83 using parachutes, balloons or the like

Abstract

A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

Claims

1. An aircraft comprising a fuselage, said fuselage including a shell and a container, said shell approximately describing a cylindrical shape, said container approximately describing a box shape, said fuselage being characterized by a fuselage length and a fuselage geometric axis, said shell and said container each being symmetrical with respect to said fuselage geometric axis, said shell defining an outside shell surface and an inside shell surface, said inside shell surface delimiting an interior shell void, said container including four longitudinal container faces and two end container faces, said four longitudinal container faces and said two end container faces defining an exterior container surface and an interior container surface, said interior container surface delimiting an interior container space, said four longitudinal container faces forming four longitudinal container edges in said exterior container surface, each said longitudinal container edge being formed by two adjoining said longitudinal container faces, said container being situated in said interior shell void so that said four longitudinal container edges contact said interior shell surface, said aircraft further comprising plural compartments, each said compartment approximately describing a box shape, each said compartment including four longitudinal compartment faces and two end compartment faces, said four longitudinal compartment faces and two end compartment faces defining an exterior compartment surface and an interior compartment surface, said exterior compartment surface being conformal with respect to said interior container surface, said compartments being capable of situation in said interior container space so that said compartments are arranged sequentially and so that the combination including said shell, said container and said compartments has an integral structure characteristic, said aircraft further comprising a nose, a tail and a pair of wings, said fuselage having a front fuselage end and a back fuselage end, said aircraft nose being connectable to said fuselage at said front fuselage end, said aircraft tail being connectable to said fuselage at said back fuselage end, said wings being connectable to said fuselage at opposite locations alone a portion of said fuselage length, said tail including a tail casing and three tail stabilizers, said wings being extendable from said fuselage, said wings including plural inflatable spars, each said wing including at least one said inflatable spar.

2. The aircraft according to claim 1, the combination including said shell and said container having an integral structure characteristic.

3. The aircraft according to claim 1, said shell approximately describing an elliptical cylindrical shape.

4. The aircraft according to claim 1, said compartments being capable of situation in said interior container space so that said compartments are arranged adjacently so as to at least substantially occupy said interior container space.

5. The aircraft according to claim 1, said aircraft further comprising at least one compartment analogue member, each said compartment analogue member being capable of situation in said interior container space so that said compartments and said at least one compartment analogue member together are arranged sequentially and so that the combination including said shell, said container, said compartments and said at least one compartment analogue member has an integral structure characteristic.

6. The aircraft according to claim 5, said compartments and said compartment analogue members being capable of situation in said interior container space so that said compartments and said compartment analogue members are arranged adjacently so as to at least substantially occupy said interior container space.

7. The aircraft according to claim 1, one said end container face being attachable and detachable for facilitating ingress and egress of said compartments with respect to said interior container space, said interior compartment surface of each said compartment delimiting an interior compartment space, each said compartment including a said longitudinal compartment face that is attachable and detachable for facilitating ingress and egress of cargo with respect to said interior compartment space.

8. The aircraft according to claim 7, said compartments being capable of situation in said interior container space so that the combination including said shell, said container, said compartments and said cargo has an integral structure characteristic.

9. The aircraft according to claim 1, said inflatable spars being inflatable by gas.

10. The aircraft according to claim 1, said inflatable spars being inflatable by liquid.

11. The aircraft according to claim 10, said liquid being potable liquid.

12. The aircraft according to claim 10, said liquid being carried as a payload.

13. An aircraft comprising a fuselage, said fuselage including a shell and a container, said shell approximately describing a cylindrical shape, said container approximately describing a box shape, said fuselage being characterized by a fuselage length and a fuselage geometric axis, said shell and said container each being symmetrical with respect to said fuselage geometric axis, said shell defining an outside shell surface and an inside shell surface, said inside shell surface delimiting an interior shell void, said container including four longitudinal container faces and two end container faces, said four longitudinal container faces and said two end container faces defining an exterior container surface and an interior container surface, said interior container surface delimiting an interior container space, said four longitudinal container faces forming four longitudinal container edges in said exterior container surface, each said longitudinal container edge being formed by two adjoining said longitudinal container faces, said container being situated in said interior shell void so that said four longitudinal container edges contact said interior shell surface, said aircraft further comprising plural compartments, each said compartment approximately describing a box shape, each said compartment including four longitudinal compartment faces and two end compartment faces, said four longitudinal compartment faces and two end compartment faces defining an exterior compartment surface and an interior compartment surface, said exterior compartment surface being conformal with respect to said interior container surface, said compartments being capable of situation in said interior container space so that said compartments are arranged sequentially and so that the combination including said shell, said container and said compartments has an integral structure characteristic, said aircraft further comprising a nose, a tail and a pair of wings, said fuselage having a front fuselage end and a back fuselage end, said aircraft nose being connectable to said fuselage at said front fuselage end, said aircraft tail being connectable to said fuselage at said back fuselage end, said wings being connectable to said fuselage at opposite locations along a portion of said fuselage length, said tail including a tail casing and three tail stabilizers, said wings being extendable from said fuselage, said wings being inflatedly extendable wings, said nose describing a truncated ellipsoidal shape, said tail casing describing a truncated conical shape, said aircraft being characterized by an aircraft length and an aircraft geometric axis, said fuselage geometric axis and said aircraft geometric axis being coincident, said shell, said container, said nose and said tail casing being symmetrical with respect to said aircraft geometric axis.

14. The aircraft according to claim 13, said aircraft being a glider aircraft suitable for un-powered controlled flight, said glider aircraft being characterized by an aspect ratio in the range between approximately eight and approximately twenty, each said stabilizer including at least one control surface.

15. The aircraft according to claim 14, each said wing including at least one control surface.

16. The aircraft according to claim 13, said cylinder and said tail casing each including a composite laminate, said nose including a composite skin and a foam core, said nose thereby being capable of absorbing some energy so as to mitigate the impact associated with the landing of said glider aircraft.

17. The aircraft according to claim 13, said tail casing having an opening, said tail casing thereby being adaptable to coupling with means for producing thrust.

18. An aircraft comprising a fuselage, said fuselage including a shell and a container, said shell approximately describing a cylindrical shape, said container approximately describing a rectangular prism shape, said fuselage being characterized by a fuselage length and a fuselage geometric axis, said shell and said container each being symmetrical with respect to said fuselage geometric axis, said shell defining an outside shell surface and an inside shell surface, said inside shell surface being characterized by an elliptical cross-section perpendicular to said fuselage geometric axis, said inside shell surface delimiting an interior shell void, said container including four longitudinal container faces and two end container faces, said four longitudinal container faces and said two end container faces defining an exterior container surface and an interior container surface, said exterior container surface being characterized by a rectangular cross-section perpendicular to said fuselage geometric axis, said interior container surface delimiting an interior container space, said four longitudinal container faces forming four longitudinal container edges in said exterior container surface, each said longitudinal container edge being formed by two adjoining said longitudinal container faces, said container being situated in said interior shell void so that said four longitudinal container edges contact said interior shell surface and so that said four longitudinal container faces do not contact said interior shell surface, said aircraft further comprising plural compartments, each said compartment approximately describing a rectangular prism shape, each said compartment including four longitudinal compartment faces and two end compartment faces, said four longitudinal compartment faces and two end compartment faces defining an exterior compartment surface and an interior compartment surface, said exterior compartment surface being conformal with respect to said interior container surface, said compartments being capable of situation in said interior container space so that said compartments are arranged sequentially and so that the combination including said shell, said container and said compartments has an integral structure characteristic, said aircraft further comprising a nose, a tail and a pair of wings, said fuselage having a front fuselage end and a back fuselage end, said aircraft nose being connectable to said fuselage at said front fuselage end, said aircraft tail being connectable to said fuselage at said back fuselage end, said wings being connectable to said fuselage at opposite locations along a portion of said fuselage length, said tail including a tail casing and three tail stabilizers, said wings being extendable from said fuselage, said nose describing a truncated ellipsoidal shape, said tail casing describing a truncated conical shape, said aircraft being characterized by an aircraft length and an aircraft geometric axis, said fuselage geometric axis and said aircraft geometric axis being coincident, said shell, said container, said nose and said tail casing being symmetrical with respect to said aircraft geometric axis.

19. The aircraft according to claim 18, said aircraft being a glider aircraft suitable for un-powered controlled flight, said glider aircraft being characterized by an aspect ratio in the range between approximately eight and approximately twenty, each said stabilizer including at least one control surface.

20. The aircraft according to claim 19, each said wing including at least one control surface.

21. The aircraft according to claim 18, said cylinder and said tail casing each including a composite laminate, said nose including a composite skin and a foam core, said nose thereby being capable of absorbing some energy so as to mitigate the impact associated with the landing of said glider aircraft.

22. The aircraft according to claim 18, said tail casing having an opening, said tail casing thereby being adaptable to coupling with means for producing thrust.