Propeller impact detection and force reduction

Patent metadata

Field	Value
Publication number	US-12157560-B2
Application number	US-202318381994-A
Country	US
Kind code	B2
Filing date	Oct 19, 2023
Priority date	Dec 7, 2017
Publication date	Dec 3, 2024
Grant date	Dec 3, 2024

Abstract

A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

First claim

What is claimed is:

1. An aircraft, comprising:
a rotor; and
a motor controller configured to generate a plurality of phase-shifted sinusoidal signals, wherein the motor controller includes:
a rotor strike detector configured to detect a rotor strike including by comparing a commanded control signal and an adaptive control signal, wherein:
the adaptive control signal is associated with controlling the rotor and includes the plurality of phase-shifted sinusoidal signals;
a rotor strike is detected based at least on a change in a plurality of sinusoidal signals;
a first signal of the plurality of sinusoidal signals has a phase offset compared with a second signal of the plurality of sinusoidal signals; and
at least one of: increased magnitude and increased frequency of the plurality of sinusoidal signals corresponds to increased rotor rotation;
wherein the plurality of phase-shifted sinusoidal signals is generated in response to detecting the rotor strike including by setting values of the plurality of phase-shifted sinusoidal signals to at least one of:

brake the rotor or exert no additional torque on the rotor; and
a drive and control unit coupled to the rotor and the motor controller, the drive and control unit being configured to in response to detecting the rotor strike, set a value of the adaptive control signal to reduce a striking force applied to an object being struck by the rotor.

2. The aircraft recited in claim 1 , wherein the plurality of phase-shifted sinusoidal signals indicates a directionality of rotation of the rotor.

3. The aircraft recited in claim 2 , wherein the directionality of rotation of the rotor includes a direction associated with default operation and another direction associated with braking the rotor in response to the detection of the rotor strike.

4. The aircraft recited in claim 1 , wherein the plurality of phase-shifted sinusoidal signals includes a first signal, a second signal with a 120 degree phase offset from the first signal, and a third signal with a 240 degree offset from the first signal.

5. The aircraft recited in claim 1 , wherein the plurality of phase-shifted sinusoidal signals is generated by the drive and control unit based on at least one of: the commanded control signal, state information from sensors, and a strike indication signal from the rotor strike detector.

6. The aircraft recited in claim 1 , wherein the change in the phase-shifted sinusoidal signals includes at least one of a change corresponding to an increase in an amount of torque or a reduction in rotations per minute.

7. The aircraft recited in claim 6 , wherein the comparison of the commanded control signal and the adaptive control signal includes the change in the phase-shifted sinusoidal signals not matching the commanded control signal.

8. A method, comprising:
generating a plurality of phase-shifted sinusoidal signals;
detecting a rotor strike including by comparing a commanded control signal and an adaptive control signal, wherein:
the adaptive control signal is associated with controlling the rotor and includes the plurality of phase-shifted sinusoidal signals;
a rotor strike is detected based at least on a change in a plurality of sinusoidal signals;
a first signal of the plurality of sinusoidal signals has a phase offset compared with a second signal of the plurality of sinusoidal signals;
at least one of: increased magnitude and increased frequency of the plurality of sinusoidal signals corresponds to increased rotor rotation;
the plurality of phase-shifted sinusoidal signals is generated in response to detecting the rotor strike including by setting values of the plurality of phase-shifted sinusoidal signals to at least one of: brake the rotor or exert no additional torque on the rotor; and

in response to detecting the rotor strike, setting a value of the adaptive control signal to reduce a striking force applied to an object being struck by the rotor.

9. The method recited in claim 8 , wherein the plurality of phase-shifted sinusoidal signals indicates a directionality of rotation of the rotor.

10. The method recited in claim 9 , wherein the directionality of rotation of the rotor includes a direction associated with default operation and another direction associated with braking the rotor in response to the detection of the rotor strike.

11. The method recited in claim 8 , wherein the plurality of phase-shifted sinusoidal signals includes a first signal, a second signal with a 120 degree phase offset from the first signal, and a third signal with a 240 degree offset from the first signal.

12. The method recited in claim 8 , wherein the plurality of phase-shifted sinusoidal signals is generated based on at least one of: the commanded control signal, state information from sensors, and a strike indication signal.

13. The method recited in claim 8 , wherein the change in the phase-shifted sinusoidal signals includes at least one of a change corresponding to an increase in an amount of torque or a reduction in rotations per minute.

14. The method recited in claim 13 , wherein the comparison of the commanded control signal and the adaptive control signal includes the change in the phase-shifted sinusoidal signals not matching the commanded control signal.

15. A computer program product, the computer program product being embodied in a non-transitory computer readable storage medium and comprising computer instructions for:
generating a plurality of phase-shifted sinusoidal signals;
detecting a rotor strike including by comparing a commanded control signal and an adaptive control signal, wherein:
the adaptive control signal is associated with controlling the rotor and includes a plurality of phase-shifted sinusoidal signals;
a rotor strike is detected based at least on a change in a plurality of sinusoidal signals;
a first signal of the plurality of sinusoidal signals has a phase offset compared with a second signal of the plurality of sinusoidal signals;
at least one of: increased magnitude and increased frequency of the plurality of sinusoidal signals corresponds to increased rotor rotation;
the plurality of phase-shifted sinusoidal signals is generated in response to detecting the rotor strike including by setting values of the plurality of phase-shifted sinusoidal signals to at least one of: brake the rotor or exert no additional torque on the rotor; and

in response to detecting the rotor strike, setting a value of the adaptive control signal to reduce a striking force applied to an object being struck by the rotor.

16. The computer program product recited in claim 15 , wherein the plurality of phase-shifted sinusoidal signals indicates a directionality of rotation of the rotor, the directionality including a direction associated with default operation and another direction associated with braking the rotor in response to the detection of the rotor strike.

Assignees

• Kitty Hawk Corp

Inventors

• Saunders Christopher Scott

Classifications

• B64D17/80

  in association with aircraft, e.g. for braking thereof · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64D31/10

  for preventing asymmetric thrust · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64U2201/00

  UAVs characterised by their flight controls · CPC title