Intelligent Ballistic Parachute System with Fuel Discharge

• US 20100176244A1
• Filed: 01/13/2009
• Published: 07/15/2010
• Est. Priority Date: 01/13/2009
• Status: Active Grant

• Current Assignee: Cirrus Design Corporation (Aviation Industry Corporation of China, Ltd.)
• Original Assignee: Hoyt A Fleming
• Inventors: Fleming III, Hoyt A.
• Granted Patent: US 8,056,861 B2
• Time in Patent Office: Days
• US Class Current: 244/135.R
• CPC Class Codes: B64C 13/04 actuated personally
• CPC Class Codes: B64D 17/00 Parachutes non canopied parachutes B64D19/00
• CPC Class Codes: B64D 17/34 adapted to control direction or rate of descent
• CPC Class Codes: B64D 17/343 by reefing means
• CPC Class Codes: B64D 17/72 by explosive or inflatable means
• CPC Class Codes: B64D 17/725 by explosive means
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof
• CPC Class Codes: B64D 37/26 Jettisoning of fuel
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A method performed by an aircraft, the aircraft including a wing, aircraft fuel, and a whole-aircraft parachute that is coupled to the aircraft. The method comprises: deploying the whole-aircraft parachute while the aircraft is in flight; and after deploying the parachute, but before the aircraft contacts the earth or any object coupled to the earth, discharging at least a portion of the aircraft fuel from the wing of the aircraft.

Claims

1. A method performed by an aircraft, the aircraft including a wing, aircraft fuel, and a whole-aircraft parachute that is coupled to the aircraft, the method comprising:

deploying the whole-aircraft parachute while the aircraft is in flight; and

after deploying the parachute, but before the aircraft contacts the earth or any object coupled to the earth, discharging at least a portion of the aircraft fuel from the wing of the aircraft.

2. The method of claim 1, wherein the aircraft includes a processor and retractable landing gear, wherein the processor is coupled to the retractable landing gear, and wherein the method further comprises, the processor outputting data that causes the retractable landing gear to extend.

3. The method of claim 1, wherein the discharging at least a portion of the aircraft fuel includes:

creating a fuel discharge passageway for discharging the at least a portion of the aircraft fuel from the wing of the aircraft.

4. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin, and wherein the discharging the at least a portion of the aircraft fuel from the wing of the aircraft includes creating a fuel discharge passageway between the lower wing skin and the panel.

5. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin and wherein the method further includes:

during the deployment of the whole-aircraft parachute, tensioning a strap that couples the aircraft to the parachute, and tensioning a cable, which is coupled to the strap and the panel.

6. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin and wherein the method further includes:

during the deployment of the whole-aircraft parachute, tensioning a strap that couples the aircraft to the parachute and tensioning a cable, which is coupled to the strap and the panel; and

then creating a fuel discharge passageway for discharging the at least a portion of the aircraft fuel from the wing of the aircraft.

7. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin and wherein the method further includes:

during the deployment of the whole-aircraft parachute, rotating the panel with respect to at least a portion of the lower wing skin.

8. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin and wherein the method further includes:

during the deployment of the whole-aircraft parachute, translating the panel with respect to at least a portion of the lower wing skin.

9. The method of claim 1, wherein the aircraft includes a lower wing skin and a panel coupled to the lower wing skin by a joint that includes epoxy and wherein the method further includes:

during the deployment of the whole-aircraft parachute, breaking at least a portion of the epoxy joint between the panel and the lower wing skin.

10. The method of claim 1, wherein the aircraft includes anti-icing fluid and wherein the method further includes;

after deploying the whole-aircraft parachute, but before the aircraft contacts the earth or any object coupled to the earth, discharging at least a portion of the anti-icing fluid from the aircraft.

11. An aircraft including:

a parachute;

a harness containing a plurality of straps that couple the parachute to a plurality of locations on the aircraft;

aircraft fuel; and

a fuel discharge system operative to discharge at least a portion of the aircraft fuel, after deployment of the parachute while the aircraft is in flight, but before the aircraft contacts the earth or any object coupled to the earth.

12. The aircraft of claim 11, wherein the fuel discharge system includes:

a wing that contains a fuel tank that stores the aircraft fuel, a first portion of the fuel tank being formed by a lower wing skin, a second portion of the fuel tank being formed by a panel that is coupled to the lower wing skin and separately coupled to at least one of the plurality of straps.

13. The aircraft of claim 12, wherein the panel is separately coupled to the at least one of the plurality of straps by a first cable, a pass-through assembly and a second cable.

14. The aircraft of claim 13, wherein the pass-through assembly includes a tube, a pass-through, and an o-ring that is located between the tube and the pass-through.

15. The aircraft of claim 14, wherein the tube is coupled to a wing rib that forms a third portion of the fuel tank.

16. The aircraft of claim 12, wherein the panel is coupled to the lower wing skin via an epoxy joint that includes micro.

17. The aircraft of claim 11, wherein the fuel discharge system creates a fuel discharge passageway after deployment of the parachute while the aircraft is in flight, but before the aircraft contacts the earth or any object coupled to the earth.

18. The aircraft of claim 11, further comprising:

anti-icing fluid; and

an anti-icing fluid discharge system operative to discharge at least a portion of the anti-icing fluid, after deployment of the parachute while the aircraft is in flight, but before the aircraft contacts the earth or any object coupled to the earth.

19. The aircraft of claim 11, further comprising a processor coupled to a sensor that provides the processor with data that indicates whether the parachute has been deployed.

20. The aircraft of claim 11, further comprising a ballistic parachute activation interface and a processor coupled to the ballistic parachute activation interface via a communication interface.