Unmanned aerial vehicle flight control system

Patent metadata

Field	Value
Publication number	US-10001776-B2
Application number	US-201615075933-A
Country	US
Kind code	B2
Filing date	Mar 21, 2016
Priority date	Mar 21, 2016
Publication date	Jun 19, 2018
Grant date	Jun 19, 2018

Abstract

An onboard system for controlling flight of an unmanned aerial vehicle. The system comprises: a flight management system configured for controlling flight of the unmanned aerial vehicle; a mission control module configured to send commands to the flight management system for guiding the unmanned aerial vehicle to perform a mission; a safety module configured to communicate commands to the flight management system for guiding the unmanned aerial vehicle to fly in a safe mode; a communication control component which is switchable between a mission state in which the flight management system receives commands from the mission control module and a safety state in which the flight management system receives commands from the safety module; and a monitor module configured to determine whether a trigger condition warranting a change in mode is present or not and to cause the communication control component to switch from the mission state to the safety state when the trigger condition is present.

First claim

The invention claimed is:

1. An onboard system for autonomous operation of an unmanned aerial vehicle, comprising:
a flight management system configured for controlling flight of the unmanned aerial vehicle;
an autonomous mission control module configured to manage the mission by issuing commands addressed to the flight management system for guiding the unmanned aerial vehicle to perform a mission;
a safety module configured to issue commands addressed to the flight management system for guiding the unmanned aerial vehicle to continue flying safely in a safe mode;
a communication control component which is switchable between a mission state in which the flight management system receives communication of commands from the mission control module and a safety state in which the flight management system receives communication of commands from the safety module; and
a monitor module configured to determine whether a trigger condition warranting a change in mode from a mission mode to a safe mode is present or not and to cause the communication control component to switch from the mission state to the safety state when the trigger condition is present,
wherein the flight management system, mission control module, safety module, communication control component and monitor module are all located onboard the unmanned aerial vehicle to enable autonomous operation of the unmanned aerial vehicle.

2. The system as recited in claim 1 , wherein the monitor module is further configured to cause the communication control component to switch from the safety state to the mission state when normal operation of the mission module and aircraft are restored.

3. The system as recited in claim 1 , wherein the trigger condition is that a command issued by the mission control module is determined to be invalid or that a parameter of a valid command issued by the mission control module violates a constraint.

4. The system as recited in claim 3 , wherein the monitor module is further configured to reboot the mission control module when the command issued by the mission control module is determined to be invalid.

5. The system as recited in claim 1 , further comprising a health status sensor, wherein the trigger condition is that the health status sensor has detected a fault or failure onboard the unmanned aerial vehicle.

6. The system as recited in claim 1 , further comprising a flight status sensor, wherein the trigger condition is that the flight status sensor has detected an unsafe flight condition.

7. The system as recited in claim 1 , wherein the trigger condition is that a parameter of a valid command issued by the mission control module has a value that violates the constraint, wherein the parameter is one of the following group: a rate of turn, a rate of climb, a rate of descent, a roll rate, a pitch rate, and a yaw rate.

8. The system as recited in claim 1 , further comprising:
a plurality of flight status sensors; and
a sensor connected to send data to the monitor module regarding a position of an object,
wherein the flight management system comprises a vehicle state estimator that receives data from the flight status sensors and communicates vehicle state estimates, including at least a vehicle position and speed, to the monitor module, the monitor module is further configured to calculate a position of the object relative to the unmanned aerial vehicle, and to determine that a trigger condition is present when a position of an object relative to the unmanned aerial vehicle violates a distance constraint.

9. The system as recited in claim 8 , wherein the sensor comprises an object proximity sensor connected to communicate data to the monitor module regarding proximity of the object.

10. The system as recited in claim 9 , wherein the constraint is a minimum separation distance from the unmanned aerial vehicle to the object.

11. The system as recited in claim 10 , wherein the safety module is further configured to send commands to the flight management system for guiding the unmanned aerial vehicle away from the object.

12. The system as recited in claim 1 , wherein the safety module is further configured to send commands to the flight management system for guiding the unmanned aerial vehicle to fly to a specified position.

13. A method for autonomous operation of an unmanned aerial vehicle, comprising:
(a) sending commands from a mission control module onboard the unmanned aerial vehicle to a flight management system onboard the unmanned aerial vehicle for guiding the unmanned aerial vehicle to perform a mission;
(b) monitoring validity of the commands sent from the mission control module to the flight management system to determine when a trigger condition is present based on whether the commands sent from the mission control module to the flight management system are valid or invalid; and
(c) guiding the unmanned aerial vehicle in accordance with the validated commands sent from the mission control module to the flight management system,
wherein steps (a) through (c) are performed onboard the unmanned aerial vehicle.

14. The method as recited in claim 13 , further comprising:
(d) determining that a command sent from the mission control module to the flight management system is invalid;
(e) discontinuing the communication of commands from the mission control module to the flight management system; and
(f) communicating commands from a safety module onboard the unmanned aerial vehicle to the flight management system for guiding the unmanned aerial vehicle to operate in a safe mode,
wherein steps (d) through (f) are performed onboard the unmanned aerial vehicle.

15. The method as recited in claim 14 , further comprising rebooting the mission control module when the command issued by the mission control module is invalid.

16. The method as recited in claim 13 , wherein step (b) comprises monitoring whether a value of a parameter included in the command issued by the mission control module violates a constraint or not.

17. The method as recited in claim 16 , wherein the monitored parameter is one of the following group: a heart-beat rate of commands output from the mission control module, a rate of turn, a rate of climb, a rate of descent, a roll rate, a pitch rate, and a yaw rate.

18. A method for autonomous operation of an unmanned aerial vehicle, comprising:
(a) communicating commands from a mission control module onboard the unmanned aerial vehicle to a flight management system onboard the unmanned aerial vehicle for guiding the unmanned aerial vehicle to perform a mission in a mission mode;
(b) monitoring whether a trigger condition warranting a change in mode from the mission mode to a safe mode is present or not; and
(c) communicating commands from a safety module onboard the unmanned aerial vehicle to the flight management system instead of communicating commands from the mission control module for guiding the unmanned aerial vehicle to operate in the safe mode when the trigger condition is present,
wherein steps (a) through (c) are performed onboard the unmanned aerial vehicle.

19. The method as recited in claim 18 , wherein the trigger condition is that a command issued by the mission control module is invalid or that a parameter of a valid command issued by the mission control module violates a constraint.

20. The method as recited in claim 18 , wherein the trigger condition is that a health status sensor has detected a fault or failure onboard the unmanned aerial vehicle.

21. The method as

Assignees

• Boeing Co

Inventors

• Rangarajan Murali

Classifications

• B64U2201/10

  autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] · CPC title

• B64F5/60 Primary

  Testing or inspecting aircraft components or systems · CPC title

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64C2201/141

  Operations & Transport · mapped topic

• G05D1/0055 Primary

  with safety arrangements · CPC title