Rotorcraft control system, associated rotorcraft, and corresponding control method

Patent metadata

Field	Value
Publication number	US-9915954-B2
Application number	US-201615146108-A
Country	US
Kind code	B2
Filing date	May 4, 2016
Priority date	May 4, 2015
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

A control system for a rotorcraft, which system includes at least one control unit allowing a rotor of a rotorcraft to be driven, with the rotorcraft including at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground, and with the control system being suitable for receiving information from the detection means. The invention also relates to the rotorcraft and to a control method corresponding to the control system.

First claim

What is claimed is:

1. A control system, which system includes at least one control unit allowing a rotor of a rotorcraft to be driven, with the rotorcraft including at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground, and with the control system being suitable for receiving information from the detection means, the control system comprising:
identification means allowing the identification of a current state of the rotorcraft from among at least two different states of the rotorcraft, namely, a state of “touching” the ground and an “in flight” state, by comparing the ground reaction forces F1, F2, F3, as measured by the detection means, against predetermined low (S B ) and high (S H ) threshold values;
with the “touching” state being identified when the following two conditions have been confirmed:
the ground reaction force F1, as measured by one of the detection means, is greater than the low threshold (S B ) value but lower than the high threshold (S H ) value; and
each of the ground reaction forces F2, F3, as measured by at least two other detection means, is lower than the low threshold (S B ) value;

and with the “in flight” state being identified when each of the ground reaction forces F1, F2, F3, as measured simultaneously by the at least three detection means, is lower than the low threshold (S B ) value;
control means for controlling the rotor of the rotorcraft according to at least two control laws that are separate from one another, depending on the current state of the rotorcraft as identified by the identification means, namely:
a first control law, implemented by the control means when the current state has been identified as the “in flight” state; and
a second control law, implemented by the control means when the current state has been identified as the “touching” state;

with the control system being characterized in that:
the low threshold (S B ) value is greater than zero;
the control means include a computer allowing the implementation of the first and second control laws by means of integrating adjusters that stay active, with the integrating adjusters enabling at least two different settings of an integral adjustment dynamic, with a first setting of the integral adjustment dynamic of the integrating adjuster corresponding to the first control law and a second setting of the integral adjustment dynamic of the integrating adjuster corresponding to the second control law, and with the second setting enabling the continuous active state of an integrated component located at the output of the integrating adjuster corresponding to the second control law; and
the second control law makes it possible to maintain full control authority over the control of the rotor of the rotorcraft.

2. The control system according to claim 1 , wherein the first setting of the integral adjustment dynamic of the integrating adjuster corresponding to the first control law generates control changes that are faster than the ones obtained with the second setting of the integral adjustment dynamic of the integrating adjuster corresponding to the second control law.

3. The control system according to claim 1 , wherein the first setting of the integral adjustment dynamic of the integrating adjuster corresponding to the first control law generates control changes that are twice as fast as the ones obtained with the second setting of the integral adjustment dynamic of the integrating adjuster corresponding to the second control law.

4. The control system according to claim 1 , wherein the high threshold (S H ) value is between 2,500 Newtons and 20,000 Newtons.

5. The control system according to claim 1 , wherein the low threshold (S B ) value is between 1,000 Newtons and 10,000 Newtons.

6. A rotorcraft comprising:
at least one rotor;
at least one control unit allowing the at least one rotor to be driven;
at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground; and
a control system including:
identification means allowing the identification of a current state of the rotorcraft from among at least two different states of the rotorcraft, namely, a state of “touching” the ground and an “in flight” state, by comparing the ground reaction forces F1, F2, F3, as measured by the detection means, against predetermined low (S B ) and high (S H ) threshold values;
with the “touching” state being identified when the following two conditions have been confirmed:
the ground reaction force F1, as measured by one of the detection means, is greater than the low threshold (S B ) value but lower than the high threshold (S H ) value; and
each of the ground reaction forces F2, F3, as measured by at least two other detection means, is lower than the low threshold (S B ) value;

and with the “in flight” state being identified when each of the ground reaction forces F1, F2, F3, as measured simultaneously by the at least three detection means, is lower than the low threshold (S B ) value;
control means in cooperation with the at least control unit for controlling the at least one rotor of the rotorcraft according to at least two control laws that are separate from one another, depending on the current state of the rotorcraft as identified by the identification means, namely:
a first control law, implemented by the control means when the current state has been identified as the “in flight” state; and
a second control law, implemented by the control means when the current state has been identified as the “touching” state;

with the control system being characterized in that:
the low threshold (S B ) value is greater than zero;
the control means include a computer allowing the implementation of the first and second control laws by means of integrating adjusters that stay active, with the integrating adjusters enabling at least two different settings of an integral adjustment dynamic, with a first setting of the integral adjustment dynamic of the integrating adjuster corresponding to the first control law and a second setting of the integral adjustment dynamic of the integrating adjuster corresponding to the second control law, and with the second setting enabling the continuous active state of an integrated component located at the output of the integrating adjuster corresponding to the second control law; and
the second control law makes it possible to maintain full control authority over the control of the at least one rotor of the rotorcraft.

7. A method for controlling a rotorcraft by means of at least one control unit allowing a rotor of the rotorcraft to be driven, the rotorcraft including at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground, the method comprising:
storing, in memory, predetermined low (S B ) and high (S B ) threshold values;
measuring the ground reaction forces F1, F2, F3 on each landing-gear unit;
comparing the ground reaction forces F1, F2, F3 against the predetermined low (S B ) and high (S H ) threshold values;
identifying a current state of the rotorcraft from among at least two different states of the rotorcraft, namely, a state of “touching” the ground and an “in flight” state;
with the “touching” state being identified when the following two conditions have been confirmed:
the ground reaction force F1, as measured by one of the detection means, is greater

Assignees

• Airbus Helicopters

Inventors

• Vallart Jean-Baptiste
• Byzery Romeo

Classifications

• G05D1/495

  to ensure stability · CPC title

• G05D1/439

  on the runway during take-off or landing · CPC title

• G05D1/0816 Primary

  to ensure stability · CPC title

• G05D1/0858 Primary

  specially adapted for vertical take-off of aircraft · CPC title

• B64C13/16

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