LIGHTER-THAN-AIR VERTICAL LOAD LIFTING SYSTEM

• US 20090134268A1
• Filed: 11/26/2007
• Published: 05/28/2009
• Est. Priority Date: 11/26/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kulesha, Richard L.
• Granted Patent: US 8,141,814 B2
• Time in Patent Office: Days
• US Class Current: 244/2
• CPC Class Codes: B64B 1/06 Rigid airships; Semi-rigid airships B64B1/58 takes precedence
• CPC Class Codes: B64B 1/08 Framework construction
• CPC Class Codes: B64U 10/30 Lighter-than-air aircraft, e.g. aerostatic aircraft

Abstract

An aerial load lifting system features a non-rigid or blimp-type dirigible providing a lighter-than-air envelope that is placed within a structural shell. The system is designed so that the envelope provides essentially neutral buoyancy for the structure, leaving only the cargo weight to be lifted by the rotors. The structural shell supports the engine, fuel tank, rotors, and transmission system that power the lift and vectoring of the aircraft, in addition to supporting the cargo load. The structural shell transfers the weight of the load directly to the location of the rotors, thus avoiding stress on the envelope.

Claims

1. An aerial load lifting system for transporting a load, comprising:

an envelope filled with a lighter-than-air gaseous substance;

a structural shell for supporting the load, wherein the envelope is surrounded at least in part by the structural shell; and

a power train system including at least one engine and at least one rotor supported by the structural shell, wherein the envelope provides a buoyant force essentially to offset the weight of the structural shell and the power train system, and wherein the power train system provides a lifting force capable of lifting the load.

2. The system of claim 1, wherein the structural shell has an opening through which the envelope may be inserted.

3. The system of claim 1, wherein the envelope has a plurality of internal bladders which maintain the lighter-than-air gaseous substance at a constant pressure.

4. The system of claim 1, wherein the gaseous substance is helium.

5. The system of claim 1, wherein the structural shell is primarily formed of aluminum, titanium, or a composite material.

6. The system of claim 1, wherein the structural shell supports a cockpit for housing a pilot.

7. The system of claim 6, wherein the cockpit is located to provide a pilot with an unobstructed view of the load during a loading or unloading process.

8. The system of claim 1, wherein the system is operated using a radio control system.

9. The system of claim 1, wherein the structural shell includes plurality of fixtures located on a bottom side of the structural shell to which cargo cables may be attached.

10. The system of claim 1, wherein the power train system includes a combining transmission.

11. The system of claim 1, wherein the structural shell has a top side, and wherein the rotors are located on the top side of the structural shell.

12. The system of claim 11, wherein the system is controllable like a helicopter.

13. The system of claim 1, wherein the power train includes two motors, each being equipped with at least one rotor.

14. The system of claim 1, wherein the structure shell further supports retractable landing gear.

15. An aerial transportation system, comprising:

an envelope filled with a lighter-than-air gaseous substance;

a structural shell surrounding the envelope at least in part; and

a power train system including at least one engine and at least one rotor;

wherein the envelope provides a buoyant force essentially to offset the weight of the structural shell and the power train system and wherein the power train system provides a lifting force.

16. The system of claim 15, wherein the envelope has a plurality of internal bladders which maintain the lighter-than-air gaseous substance at a constant pressure.

17. The system of claim 15, wherein the structural shell is primarily formed of aluminum, titanium, or a composite material.

18. The system of claim 15, wherein the structural shell supports a cockpit for housing a pilot.

19. The system of claim 18, wherein the cockpit is located to provide a pilot with an unobstructed view of the load during a loading or unloading process.

20. The system of claim 15, wherein the structure shell further supports retractable landing gear.