Distributed acceleration sensing for robust disturbance rejection

Patent metadata

Field	Value
Publication number	US-10919617-B2
Application number	US-201715788434-A
Country	US
Kind code	B2
Filing date	Oct 19, 2017
Priority date	Oct 21, 2016
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.

First claim

What is claimed is:

1. An aerial vehicle comprising:
an airframe;
an aircraft flight controller to provide an output control signal; and
a sensor package positioned on the airframe, the sensor package comprising a rate gyroscope, a plurality of accelerometers, and a processor, wherein the sensor package is configured to measure collectively at least nine independent axial acceleration measurements,
wherein each of the plurality of accelerometers is positioned a predetermined distance from the center of gravity of the airframe,
wherein the processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and said plurality of accelerometers,
wherein the processor is configured to communicate the actuation signal to said aircraft flight controller,
wherein the aircraft flight controller is configured to adjust the output control signal as a function of said actuation signal, and
wherein the plurality of accelerometers is arranged in a circle with the rate gyroscope positioned substantially at the center of said circle.

2. The aerial vehicle of claim 1 , wherein the rate gyroscope, the plurality of accelerometers, and the processor are positioned on a printed circuit board.

3. The aerial vehicle of claim 1 , wherein the aircraft flight controller is configured to provide the output control signal to a propulsor or a flight control surface actuator.

4. The aerial vehicle of claim 1 , wherein the rate gyroscope is positioned substantially at the center of gravity of the airframe.

5. The aerial vehicle of claim 1 , wherein the at least nine independent axial acceleration measurements comprise three sets of three axial measurements, each of the three sets measured at a different location on the aerial vehicle, each of the three axial measurements within one of the three sets of three axial measurements measured along a different axis.

6. The aerial vehicle of claim 5 , wherein the plurality of accelerometers comprises a tri-axial linear accelerometer to generate one of the three sets of three axial measurements.

7. The aerial vehicle of claim 1 , wherein the processor is configured to estimate translational and rotational acceleration of the airframe based at least in part on the feedback signal to generate the actuation signal.

8. The aerial vehicle of claim 1 , wherein the processor is configured to receive a second feedback signal from a strain gauge or a pressure sensor embedded within the aerial vehicle.

9. The aerial vehicle of claim 8 , wherein the strain gauge or the pressure sensor is embedded in a wing of the aerial vehicle.

10. The aerial vehicle of claim 9 , wherein the strain gauge is embedded at a leading edge of the wing.

11. The aerial vehicle of claim 1 , wherein the processor is configured to calibrate the feedback signal using an estimation algorithm.

12. The aerial vehicle of claim 11 , wherein the estimation algorithm is selected from the group consisting of: least squares; maximum likelihood estimation; and linear quadratic estimation.

13. The aerial vehicle of claim 1 , wherein each of said plurality of accelerometers is a microelectromechanical system accelerometer.

14. A distributed acceleration sensing system for an aerial vehicle comprising:
a planar printed circuit board;
a rate gyroscope coupled to the planar printed circuit board;
a plurality of accelerometers coupled to the planar printed circuit board, wherein each of the plurality of accelerometers is spaced a predetermined distance from the rate gyroscope and configured to collectively measure at least three axial acceleration measurements taken at three different locations for each axis to yield at least nine independent axial acceleration measurements; and
a processor coupled to the planar printed circuit board,
wherein the processor is operatively coupled with the rate gyroscope and each of the plurality of accelerometers and configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and said plurality of accelerometers,
wherein the processor communicates the actuation signal to an aircraft flight controller of said aerial vehicle.

15. The distributed acceleration sensing system of claim 14 , wherein the plurality of accelerometers includes a tri-axial linear accelerometer to generate one of said three sets of three axial measurements.

16. The distributed acceleration sensing system of claim 14 , wherein the processor is configured to estimate translational and rotational acceleration of the aerial vehicle based on the feedback signal to generate the actuation signal.

17. The distributed acceleration sensing system of claim 14 , wherein the processor is configured to receive a second feedback signal from a strain gauge or a pressure sensor embedded within the aerial vehicle.

18. The distributed acceleration sensing system of claim 14 , wherein the rate gyroscope is positioned substantially at the center of gravity of the aerial vehicle.

19. An aerial vehicle comprising:
an airframe;
an aircraft flight controller to provide an output control signal; and
a sensor package positioned on the airframe, the sensor package comprising a rate gyroscope, a plurality of accelerometers, and a processor, wherein the sensor package is configured to measure collectively at least nine independent axial acceleration measurements,
wherein the rate gyroscope and the plurality of accelerometers are positioned in substantially the same plane and arranged such that a distance between each of the plurality of accelerometers and the rate gyroscope is the same,
wherein the processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and said plurality of accelerometers,
wherein the processor is configured to communicate the actuation signal to said aircraft flight controller, and
wherein the aircraft flight controller is configured to adjust the output control signal as a function of said actuation signal.

Assignees

• Aurora Flight Sciences Corp

Inventors

• Griffin Riley
• Scott Edward
• Humbert Sean

Classifications

• G01C21/166

  Mechanical, construction or arrangement details of inertial navigation systems · CPC title

• B64U2201/10

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

• B64U10/00

  Type of UAV · CPC title

• G01B11/18

  using photoelastic elements · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title