Aircraft control system, aircraft control method, and aircraft

Patent metadata

Field	Value
Publication number	US-11214358-B2
Application number	US-201816149801-A
Country	US
Kind code	B2
Filing date	Oct 2, 2018
Priority date	Nov 2, 2017
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.

First claim

The invention claimed is:

1. An aircraft control system comprising:
a flow control device configured to control a flow of air around an aircraft;
a control circuit configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft, the physical quantity relating to the air; and
a damage detection system configured to detect damage in the structure,
wherein the control circuit is configured to, when the damage is detected in the structure, set the control value of the pressure distribution by performing computational fluid dynamics analysis of the structure to which the damage has been reflected.

2. The aircraft control system according to claim 1 ,
wherein the flow control device is at least one of an actuator configured to control a moving surface or an actuator configured to control the flow of the air.

3. The aircraft control system according to claim 1 , further comprising:
a stress sensor configured to detect a stress distribution of the structure,
wherein the control circuit is configured to set the control value of the pressure distribution based on the stress distribution.

4. The aircraft control system according to claim 3 , wherein an optical fiber sensor is provided as the stress sensor.

5. The aircraft control system according to claim 1 ,
wherein the control circuit is configured to set the control value of the pressure distribution based on air data indicating a relationship between the aircraft and the air around the aircraft.

6. The aircraft control system according to claim 5 , wherein the control circuit is configured to control a plasma actuator as the flow control device.

7. The aircraft control system according to claim 1 , wherein the control circuit is configured to set the control value of the pressure distribution so as to minimize an air resistance in a part in which a plasma actuator as the flow control device is disposed.

8. The aircraft control system according to claim 1 , wherein the control circuit is configured to set the control value of the pressure distribution optimally so that an attitude of the aircraft becomes a desired attitude.

9. The aircraft control system according to claim 1 ,
wherein the damage detection system is configured to detect a position and a size of the damage using an ultrasonic inspection and,
the control circuit is configured to, when the damage is detected in the structure, set the control value of the pressure distribution by performing the analysis processing using the position and the size of the damage as a constraint.

10. The aircraft control system according to claim 1 ,
wherein the damage detection system comprises
an ultrasonic transducer configured to emit ultrasound toward an inspection area of the structure,
a sensor configured to detect a reflected wave of the ultrasound reflected by the inspection area or a transmitted wave of the ultrasound having transmitted through the inspection area; and
a signal generation circuit configured to generate a transmission signal and apply the generated transmission signal to the ultrasonic transducer, and
a power supply configured to operate the flow control device supplies electric power to the signal generation circuit.

11. An aircraft comprising:
the aircraft control system according to claim 1 .

12. An aircraft control method comprising:
controlling a flow control device configured to control a flow of air around an aircraft, using the aircraft control system according to claim 1 .

13. An aircraft control method comprising:
controlling a flow of air around an aircraft using a flow control device; and
controlling the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft, the physical quantity relating to the air; and
detecting damage in the structure via a damage detection system configured to detect damage in the structure; and
in response to detecting the damage in the structure, setting the control value of the pressure distribution by performing computational fluid dynamics analysis of the structure to which the damage has been reflected.

Assignees

• Subaru Corp

Inventors

• Miyawaki Takashi
• Abe Masakatsu
• Kato Hiroki

Classifications

• G01N29/245

  Ceramic probes, e.g. lead zirconate titanate [PZT] probes · CPC title

• G01N2291/2694

  Wings or other aircraft parts · CPC title

• G01N29/4472

  Mathematical theories or simulation · CPC title

• G01N29/043

  in the interior, e.g. by shear waves · CPC title

• B64D2045/0085

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