Impact protection apparatus

• US 8,979,023 B1
• Filed: 04/21/2014
• Issued: 03/17/2015
• Est. Priority Date: 02/27/2014
• Status: Active Grant

• Current Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Original Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Inventors: Wang, Mingyu
• Primary Examiner(s): O'Hara, Brian M
• Assistant Examiner(s): KREINER, MICHAEL B
• Application Number:
  US14/257,930
• Time in Patent Office: 330 Days
• Field of Search: 244/100.A, 244/107, 244/139
• US Class Current: 244/100.A
• CPC Class Codes: B64C 25/32 characterised by elements which contact the ground or similar surface arrester hooks B64C25/68
• CPC Class Codes: B64C 25/54 Floats
• CPC Class Codes: B64C 25/56 inflatable
• CPC Class Codes: B64D 2201/00 Airbags mounted in aircraft for any use
• CPC Class Codes: B64D 25/00 Emergency apparatus or devices, not otherwise provided for parachutes B64D17/00, B64D19/00; jettisoning of fuel tanks or fuel per se B64D37/00; specially adapted for protection against criminal attack, e.g. anti-hijacking systems B64D45/0015 ; safety belts or body harnesses in general A62B35/00; safety belts or body harnesses for land vehicles B60R22/00; jettisonable parts of fuselage facilitating emergency escape B64C
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/30 for safety, e.g. with frangible components rotor guards B64U30/299
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/30 Supply or distribution of electrical power

Abstract

An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

Claims

1. An impact protection apparatus for an unmanned aerial vehicle, the apparatus comprising:

an inflatable member configured to be coupled to the unmanned aerial vehicle and inflatable to reduce forces experienced by the unmanned aerial vehicle during an impact;

a container coupled to the inflatable member, said container comprising compressed gas;

a control mechanism powered by a first power source separate from a second power source that provides power to the unmanned aerial vehicle, wherein the control mechanism is configured to cause the compressed gas to flow from the container into the inflatable member in response to a signal indicative of malfunction of the unmanned aerial vehicle; and

a deactivatable safety mechanism that, unless deactivated, prevents inflation of the inflatable member, wherein the safety mechanism is deactivated by a safety signal indicating that the unmanned aerial vehicle is airborne.

2. The impact protection apparatus of claim 1 wherein the compressed gas is carbon dioxide.

3. The impact protection apparatus of claim 1 wherein a volume of the container is less than or equal to 0.001 m³.

4. The impact protection apparatus of claim 1 wherein a pressure of the compressed gas when in the container is greater than or equal to 0.2×

10⁶ Pa.

5. The impact protection apparatus of claim 1 wherein the control mechanism comprises a valve configured to control flow of the compressed gas into the inflatable member.

6. The impact protection apparatus of claim 1 wherein the control mechanism comprises an accelerometer configured to detect an acceleration of the unmanned aerial vehicle that is outside a predetermined range and is indicative of the malfunction.

7. The impact protection apparatus of claim 6 wherein the accelerometer is configured to detect an acceleration of the unmanned aerial vehicle indicative of the unmanned aerial vehicle being in a free fall condition.

8. The impact protection apparatus of claim 1 wherein the signal indicative of malfunction is generated from the unmanned aerial vehicle.

9. The impact protection apparatus of claim 1 wherein the signal indicative of malfunction is generated from an external device in communication with the unmanned aerial vehicle.

10. An unmanned aerial vehicle, the vehicle comprising:

a vehicle body;

the impact protection apparatus of claim 1 coupled to the vehicle body; and

one or more propulsion units coupled to the vehicle body and configured to propel the vehicle body.

11. The aerial vehicle of claim 10, wherein the unmanned aerial vehicle is a rotorcraft.

12. A method for protecting an unmanned aerial vehicle from an impact, the method comprising:

providing an inflatable member coupled to the unmanned aerial vehicle;

receiving a safety signal indicating the unmanned aerial vehicle is airborne;

deactivating, in response to the safety signal, a deactivatable safety mechanism that, unless deactivated, prevents inflation of the inflatable member;

causing, in response to a signal indicative of malfunction of the unmanned aerial vehicle and by means of a control mechanism powered independently from the unmanned aerial vehicle, a compressed gas to flow into the inflatable member; and

effecting inflation of the inflatable member by the flow of the compressed gas to reduce forces experienced by the unmanned aerial vehicle during the impact.

13. The method of claim 12 further comprising powering the control mechanism by a power source separate from that providing power to the one or more propulsion units of the unmanned aerial vehicle.

14. The method of claim 12 further comprising powering the control mechanism by a power source separate from that providing power to a flight control system of the unmanned aerial vehicle.

15. The method of claim 12 wherein the control mechanism comprises an accelerometer configured to detect an acceleration of the unmanned aerial vehicle that is outside a predetermined range and is indicative of the malfunction.

16. The method of claim 12 further comprising detecting, using a motion sensor from an inertial measurement unit, a loss of stability of the unmanned aerial vehicle that is indicative of the malfunction.

17. The method of claim 12 further comprising responding, with aid of the control mechanism, to a loss of power of the unmanned aerial vehicle that is indicative of the malfunction.

18. An impact protection apparatus for an unmanned aerial vehicle, the apparatus comprising:

an inflatable member configured to be coupled to the unmanned aerial vehicle, wherein said inflatable member is inflatable to reduce forces experienced by the unmanned aerial vehicle during an impact;

a container coupled to the inflatable member, said container comprising compressed gas;

a control mechanism is configured to cause the compressed gas to flow from the container into the inflatable member, in response to a signal indicative of malfunction of said unmanned aerial vehicle; and

a deactivatable safety mechanism that, unless deactivated, prevents inflation of the inflatable member, wherein the safety mechanism is deactivated by (1) an automated electronic signal provided by a flight control system of the unmanned aerial vehicle or (2) an electronic signal from a remote terminal configured to accept a user input.

19. The impact protection apparatus of claim 18 wherein the signal is indicative of malfunction of a member selected from the group consisting of one or more propulsion units of the aerial vehicle, a flight control system of the aerial vehicle, and a power source providing power to the aerial vehicle.

20. The impact protection apparatus of claim 18 wherein the safety mechanism comprises a pin and deactivation of the safety mechanism comprises removal of the pin.

21. The impact protection apparatus of claim 20 wherein the pin is configured to be removed by a user prior to operation of the unmanned aerial vehicle.

22. The impact protection apparatus of claim 18 wherein the safety mechanism is deactivated by a safety signal indicating that the unmanned aerial vehicle is in operation.

23. The impact protection apparatus of claim 22 wherein the safety signal is provided by a flight control system of the unmanned aerial vehicle.

24. An unmanned aerial vehicle, the vehicle comprising:

a vehicle body;

the impact protection apparatus of claim 18 coupled to the vehicle body; and

one or more propulsion units coupled to the vehicle body and configured to propel the vehicle body.

25. A method for protecting an unmanned aerial vehicle from an impact, the method comprising:

providing an inflatable member coupled to the unmanned aerial vehicle;

receiving a safety signal from (1) a flight control system of the unmanned aerial vehicle or (2) a remote terminal configured to accept a user input;

deactivating, in response to the safety signal, a deactivatable safety mechanism that, unless deactivated, prevents inflation of the inflatable member;

causing, in response to a signal indicative of a malfunction of the aerial vehicle, a compressed gas to flow from said container into the inflatable member; and

effecting inflation of the inflatable member by the flow of the compressed gas to reduce forces experienced by the unmanned aerial vehicle during the impact.

26. The method of claim 25 wherein the compressed gas is caused to flow using a valve.

27. The method of claim 26 further comprising powering the valve by a power source separate from that providing power to one or more propulsion units of the unmanned aerial vehicle.

28. The method of claim 26 further comprising powering the valve by a power source separate from that providing power to a flight control system of the aerial vehicle.

29. The method of claim 25 wherein the safety mechanism comprises a pin and deactivation of the safety mechanism comprises removal of the pin.

30. The method of claim 29 further comprising removing the pin by a user prior to operation of the unmanned aerial vehicle.