Impact protection apparatus

• US 9,789,969 B2
• Filed: 11/11/2016
• Issued: 10/17/2017
• 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:
  US15/349,750
• Publication Number:
  US 20170057645A1
• Time in Patent Office: 340 Days
• 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: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• 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 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 (UAV), comprising:

one or more inflatable members configured to be coupled to the UAV and inflatable to reduce forces experienced by the UAV during an impact;

a container coupled to the one or more inflatable members and configured to hold compressed gas;

a control mechanism configured to cause the compressed gas to flow from the container into the one or more inflatable members; and

a controller in communication with the control mechanism,

wherein the controller is configured to control the control mechanism to selectively inflate an inflatable member of the one or more inflatable members based on a signal from a remote terminal, wherein the control mechanism is powered by a first power source separate from a second power source configured to provide power to one or more components of the UAV, and wherein the first power source is configured to be automatically recharged during operation of one or more propulsion units of the UAV.

2. The impact protection apparatus of claim 1, wherein the remote terminal is configured to remotely control the UAV.

3. The impact protection apparatus of claim 1, wherein the one or more components comprise at least one of (1) the one or more propulsion units, (2) a flight controller, (3) a guidance system, and (4) a communication system, of the UAV.

4. The impact protection apparatus of claim 1, wherein the controller is configured to be in communication with the remote terminal via a communication system powered by the first power source.

5. The impact protection apparatus of claim 1, wherein the first power source is configured to be recharged periodically based on the state of the first power source.

6. The impact protection apparatus of claim 1, wherein the control mechanism comprises a valve configured to control flow of the compressed gas into the one or more inflatable members.

7. The impact protection apparatus of claim 1, wherein the one or more inflatable members are disposed on an upward portion of the UAV, the upward portion being located along a direction of lift of the UAV opposite to a downward portion of the UAV.

8. The impact protection apparatus of claim 1, wherein the UAV comprises a hub and one or more arms extending from the hub, and wherein the one or more inflatable members are configured to deploy from the hub and/or the one or more arms of the UAV.

9. The impact protection apparatus of claim 1, wherein at least a portion of the one or more inflatable members are configured to protect a load from damage when the one or more inflatable members are inflated, and wherein the load is disposed on the UAV.

10. The impact protection apparatus of claim 9, wherein the load comprises a payload and a carrier configured to carry the payload.

11. The impact protection apparatus of claim 10, wherein the payload comprises one or more of a camera, an illumination device, an audio device, and a measurement or sensing equipment.

12. The impact protection apparatus of claim 1, wherein the one or more inflatable members are configured to deploy from the one or more propulsion units of the UAV.

13. The impact protection apparatus of claim 1, wherein the one or more inflatable members are configured to deploy from an area proximate to the one or more propulsion units of the UAV.

14. The impact protection apparatus of claim 1, wherein the one or more inflatable members comprise a plurality of inflatable members clustered around the one or more propulsion units of the UAV.

15. A UAV comprising:

a vehicle body;

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

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

16. A UAV comprising:

a vehicle body;

one or more inflatable members configured to be coupled to the vehicle body and inflatable to reduce forces experienced by the UAV during an impact;

a container coupled to the one or more inflatable members and configured to hold compressed gas;

a control mechanism configured to cause the compressed gas to flow from the container into the one or more inflatable members;

a controller in communication with the control mechanism; and

a remote control device configured to control a movement of the UAV,

wherein the controller is configured to control the control mechanism to selectively inflate an inflatable member of the one or more inflatable members based on a signal from the remote control device, wherein the control mechanism is powered by a first power source separate from a second power source configured to provide power to one or more components of the UAV, and wherein the first power source is configured to be automatically recharged during operation of one or more propulsion units of the UAV.

17. The UAV of claim 16, wherein the remote control device is further configured to control a movement of a carrier and/or a payload carried by the UAV.

18. A method for protecting a UAV from an impact, comprising:

providing one or more inflatable members that are coupled to the UAV, wherein the one or more inflatable members are selectively inflatable to reduce forces experienced by the UAV during the impact;

receiving a signal from a remote control device, wherein the remote control device is configured to control a movement of the UAV;

causing, in response to the signal from the remote control device and by means of a control mechanism, a compressed gas from a container to flow into an inflatable member of the one or more inflatable members to reduce the forces experienced by the UAV during the impact;

powering the control mechanism by a first power source separate from a second power source configured to provide power to one or more components of the UAV; and

automatically recharging the first power source during operation of one or more propulsion units of the UAV.