Impact protection apparatus

Patent metadata

Field	Value
Publication number	US-9493250-B2
Application number	US-201514948220-A
Country	US
Kind code	B2
Filing date	Nov 20, 2015
Priority date	Feb 27, 2014
Publication date	Nov 15, 2016
Grant date	Nov 15, 2016

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.

First claim

What is claimed is:

1. An impact protection apparatus for an unmanned aerial vehicle, the apparatus comprising:
two or more inflatable members configured to be coupled to the unmanned aerial vehicle, and selectively inflatable to reduce forces experienced by the unmanned aerial vehicle during an impact; and
a control mechanism powered by a first power source that is separate from a second power that provides power to one or more propulsion units of the unmanned aerial vehicle,
wherein the control mechanism is configured to cause compressed gas to flow from a container into an inflatable member selected from the two or more inflatable members in response to (a) a first signal indicative of malfunction of the unmanned aerial vehicle, wherein the control mechanism is capable of selectively relaying the first signal such that at least one inflatable member does not inflate, and/or (b) a second signal indicative of one or more portions of the unmanned aerial vehicle that are likely to experience the impact, wherein the control mechanism is capable of selectively relaying the second signal such that at least one inflatable member does not inflate.

2. The impact protection apparatus of claim 1 , wherein the two or more inflatable members are disposed on an upward portion of the unmanned aerial vehicle, said upward portion being located along a direction of lift of the unmanned aerial vehicle opposite to a downward portion of the unmanned aerial vehicle.

3. The impact protection apparatus of claim 1 , wherein the second power source further provides power to a flight controller, a guidance system, and/or a communication system.

4. The impact protection apparatus of claim 3 , wherein the first signal is transmitted to the control mechanism when the second power source is no longer providing power to one or more of the propulsion units, flight controller, guidance system, and/or communication system of the unmanned aerial vehicle.

5. The impact protection apparatus of claim 3 , wherein the malfunction of the unmanned aerial vehicle comprises one or more of the following conditions: (1) abnormal orientation, speed, and/or acceleration of the unmanned aerial vehicle, (2) overheating of one or more components of the unmanned aerial vehicle, (3) a short circuit in the one or more components of the unmanned aerial vehicle, (4) an unintended fire in the unmanned aerial vehicle, (5) a state of charge of the second power source falling below a predetermined threshold, (6) loss of power to the one or more components of the unmanned aerial vehicle, or (7) loss of communication between the unmanned aerial vehicle and an external device.

6. The impact protection apparatus of claim 1 , further comprising: one or more sensors configured to collect data to predict a direction, angle, location, speed, and/or acceleration at which the one or more portions of the unmanned aerial vehicle are likely to experience the impact.

7. The impact protection apparatus of claim 6 , further comprising: a controller in communication with the one or more sensors and the control mechanism, wherein the controller is configured to control the control mechanism to inflate the inflatable member selected from the two or more inflatable members to protect the unmanned aerial vehicle, based on the collected data.

8. The impact protection apparatus of claim 6 , wherein the second signal is generated based on the collected data.

9. The impact protection apparatus of claim 1 , further comprising: one or more sensors configured to monitor a state of charge of the first power source.

10. The impact protection apparatus of claim 9 , wherein the first power source is configured to be recharged periodically based on the state of the first power source.

11. The impact protection apparatus of claim 9 , wherein the first power source is configured to be automatically recharged during operation of one or more propulsion units of the unmanned aerial vehicle.

12. The impact protection apparatus of claim 1 , further comprising: one or more additional power sources that serve as a back-up to the first power source.

13. The impact protection apparatus of claim 1 , further comprising: a deactivatable safety mechanism that, unless deactivated, prevents inflation of the two or more inflatable members, wherein the safety mechanism is configured to be automatically deactivated by a safety signal indicating that the aerial vehicle is airborne.

14. The impact protection apparatus of claim 13 , wherein the safety mechanism further comprises a pin, and wherein deactivation of the safety mechanism further comprises automatic removal of the pin caused by turning on or operating the unmanned aerial vehicle.

15. An unmanned aerial vehicle comprising:
a vehicle body to which one or more propulsion units are coupled; and
the impact protection apparatus of claim 1 coupled to the vehicle body and/or the one or more propulsion units.

16. The aerial vehicle of claim 15 , wherein the unmanned aerial vehicle is a rotorcraft.

17. A system comprising:
an unmanned aerial vehicle comprising a vehicle body to which one or more propulsion units are coupled;
the impact protection apparatus of claim 1 coupled to the vehicle body and/or the one or more propulsion units; and
an external device remote to the unmanned aerial vehicle, wherein the control mechanism is configured to cause the compressed gas to flow from the container into an inflatable member selected from the two or more inflatable members in response to a control signal received from the external device.

18. The system of claim 17 , wherein the external device is configured to transmit the control signal to activate the control mechanism of the impact protection apparatus.

19. The system of claim 17 , wherein the external device is in wireless communication with the unmanned aerial vehicle and the impact protection apparatus.

20. The system of claim 17 , wherein the control signal is transmitted from the external device upon receipt of a user input.

21. The system of claim 20 , wherein the control signal is transmitted from the external device when the unmanned aerial vehicle is experiencing the malfunction and/or when the one or more portions of the unmanned aerial vehicle are likely to experience the impact.

22. A method for protecting an unmanned aerial vehicle from an impact, the method comprising:
providing two or more inflatable members of claim 1 that are coupled to the unmanned aerial vehicle, wherein the two or more inflatable members are selectively inflatable to reduce forces experienced by the unmanned aerial vehicle during the impact;
receiving (a) a first signal indicative of malfunction of the unmanned aerial vehicle and/or (b) a second signal indicative of one or more portions of the unmanned aerial vehicle that are likely to experience the impact; and
causing, in response to the first and/or second signals and by means of the control mechanism, a compressed gas from a container to flow into an inflatable member selected from the two or more inflatable members.

23. The method of claim 22 , wherein the malfunction of the unmanned aerial vehicle is detected using one or more sensors on the vehicle, and wherein the malfunction comprises one or more of the following conditions: (1) abnormal orientation, speed, and/or acceleration of the unmanned aerial vehicle, (2) overheating of one or more components of the unmanned aerial vehicle, (3) a short circuit in the one or more co

Assignees

• Sz Dji Technology Co Ltd
• Sz Dji Technology Co Ltd

Inventors

• Wang Mingyu

Classifications

• B64U10/13

  Flying platforms · CPC title

• B64C25/56

  inflatable · CPC title

• B64C25/54

  Floats · CPC title

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C25/32

  characterised by elements which contact the ground or similar surface  (arrester hooks B64C25/68) · CPC title