CN-121973929-A - Control surface-free aircraft control system based on synthetic jet flow and momentum wheel

Abstract

The invention relates to the technical field of aircraft control, in particular to a control system of an aircraft without a control surface based on synthetic jet flow and momentum wheels, which comprises a lift force and gesture control subsystem, a steering control subsystem, a propulsion subsystem, a cooperative control unit and a gesture and navigation sensor. The lift force and attitude control subsystem independently controls different areas through a synthetic jet generator matrix integrated on the surface so as to generate local lift force difference, and roll and pitch control is realized. The steering control subsystem changes the angular momentum direction of the flywheel through a control moment gyroscope arranged inside, and generates reaction moment to control yaw. The propulsion subsystem provides a primary forward thrust. And the cooperative control unit receives the sensor signals, generates instructions according to a preset strategy, coordinates the subsystems to cooperatively work, and realizes full airspace flight control without an exposed control surface.

Inventors

• Xia Yechen

Assignees

• 夏叶宸

Dates

Publication Date

20260505

Application Date

20260304

Claims (8)

1. 1. The control system of the aircraft without the control surface based on the synthetic jet flow and the momentum wheel is characterized by comprising a lift force and gesture control subsystem, a steering control subsystem, a propulsion subsystem, a cooperative control unit and gesture and navigation sensors: The lift force and attitude control subsystem comprises a synthetic jet generator matrix integrated on the surface of the aircraft body, wherein the synthetic jet generator matrix consists of a plurality of miniature synthetic jet generators, each synthetic jet generator comprises a resonant cavity, a vibrating membrane and a nozzle, and the synthetic jet generators are used for changing the airflow distribution on the surface of the aircraft to generate local lift force differences by independently controlling the actuation states of the synthetic jet generators in different areas so as to control the roll and pitch of the aircraft; The steering control subsystem comprises at least one control moment gyro arranged in the aircraft, wherein the control moment gyro comprises a flywheel and a driving mechanism for driving the rotation axis direction of the flywheel to change, and the control moment gyro is used for generating a reaction moment by changing the direction of the angular momentum of the flywheel so as to control the yaw of the aircraft; The propulsion subsystem comprises a main propeller arranged at the tail of the aircraft and used for providing main forward thrust of the aircraft; the cooperative control unit is in communication connection with the lift force and gesture control subsystem, the steering control subsystem and the propulsion subsystem, is connected with the gesture and navigation sensor, is used for receiving signals from the gesture and navigation sensor, generates a control instruction according to a preset control strategy, and coordinates the synthetic jet generator matrix, the control moment gyro and the main propulsion to cooperatively work.
2. 2. The control surface-free aircraft control system based on synthetic jets and momentum wheels of claim 1 wherein the matrix of synthetic jet generators is integrated on the upper surface of the aircraft wing and/or on both side surfaces of the fuselage.
3. 3. The synthetic jet and momentum wheel based control system of claim 1, wherein the number of control moment gyroscopes is at least two, wherein at least one control moment gyroscope is used to control yaw of the aircraft and at least one other control moment gyroscope is used to control pitch of the aircraft.
4. 4. The control surface-free aircraft control system based on synthetic jet and momentum wheel of claim 1, wherein the main propeller is a vector propeller, and the direction of the nozzle is adjustable.
5. 5. The control surface-free aircraft control system based on synthetic jet and momentum wheel of claim 1, wherein the preset control strategy comprises: Preferentially distributing roll and pitch control instructions of the aircraft to the lift and attitude control subsystem for execution; And distributing yaw control instructions of the aircraft to the steering control subsystem for execution.
6. 6. The synthetic jet and momentum wheel-based control system of claim 5, wherein said step of preferentially assigning roll and pitch control commands to said lift and attitude control subsystem for the aircraft comprises: Generating a roll control instruction and a pitch control instruction according to the expected flight attitude and real-time attitude feedback from the attitude and navigation sensor; Preferentially sending the roll control command and the pitch control command to the lift and attitude control subsystem; The lift force and attitude control subsystem responds to the received instruction and independently controls the actuation states of the micro synthetic jet generators in corresponding areas in the synthetic jet generator matrix to generate corresponding local lift force differences so as to control the aircraft to execute rolling and pitching motions.
7. 7. The control surface-less aircraft control system of claim 5, wherein the step of assigning yaw control commands to the steering control subsystem for the aircraft comprises: Generating a yaw control instruction according to the expected flight heading and real-time heading feedback from the gesture and navigation sensor; Transmitting the yaw control command to the steering control subsystem; the steering control subsystem responds to the received yaw control command, and changes the direction of the rotation axis of the flywheel through the driving mechanism so as to generate reaction moment acting on the aircraft body, thereby controlling the aircraft to execute yaw motion.
8. 8. The synthetic jet and momentum wheel based control system of claim 1, wherein said attitude and navigation sensor comprises an inertial measurement unit and a global navigation satellite system receiver.

Description

Control surface-free aircraft control system based on synthetic jet flow and momentum wheel Technical Field The invention relates to the technical field of aircraft control, in particular to a control surface-free aircraft control system based on synthetic jet flow and momentum wheels. Background The attitude and heading control of the existing aircraft mainly depends on mechanical movable components such as a pneumatic control surface or rotor rotation speed difference. For example, the fixed wing unmanned aerial vehicle generates control moment by changing air flow through deflection of control surfaces such as ailerons, elevators and rudders, and the multi-rotor unmanned aerial vehicle realizes gesture adjustment by adjusting the rotation speed difference of a plurality of propellers. In addition, some advanced aircraft employ mechanical vector propulsion technology to provide control forces by deflecting engine jets. However, the control method of the prior art is severely dependent on interaction with external air, and the inherent defects of poor stealth performance, rapid decline of control efficiency or failure in low-speed and high-altitude lean atmosphere are exposed under the condition that the mechanical movable part is exposed or the atmosphere environment is changed. The control surface control force based on the pneumatic effect can be greatly attenuated in the environment of low-speed flight or high-altitude air rarefaction, and the multi-rotor control mode based on the rotating speed difference can be difficult to maintain stability due to the reduction of the blade efficiency, so that the control capability of the aircraft is seriously insufficient or even out of control. Disclosure of Invention In order to make up for the defects, the invention provides a control surface-free aircraft control system based on synthetic jet flow and momentum wheels, which aims to solve the problems that the stealth performance is poor and the efficiency of the existing aircraft is seriously reduced or even fails under the low-speed and high-altitude lean atmospheric environment due to the fact that the existing aircraft depends on an exposed movable control surface or rotor wing. The invention provides a control surface-free aircraft control system based on synthetic jet flow and momentum wheel, the system comprises a lift force and gesture control subsystem, a steering control subsystem, a propulsion subsystem, a cooperative control unit and gesture and navigation sensors: The lift force and attitude control subsystem comprises a synthetic jet generator matrix integrated on the surface of the aircraft body, wherein the synthetic jet generator matrix consists of a plurality of miniature synthetic jet generators, each synthetic jet generator comprises a resonant cavity, a vibrating membrane and a nozzle, and the synthetic jet generators are used for changing the airflow distribution on the surface of the aircraft to generate local lift force differences by independently controlling the actuation states of the synthetic jet generators in different areas so as to control the roll and pitch of the aircraft; The steering control subsystem comprises at least one control moment gyro arranged in the aircraft, wherein the control moment gyro comprises a flywheel and a driving mechanism for driving the rotation axis direction of the flywheel to change, and the control moment gyro is used for generating a reaction moment by changing the direction of the angular momentum of the flywheel so as to control the yaw of the aircraft; The propulsion subsystem comprises a main propeller arranged at the tail of the aircraft and used for providing main forward thrust of the aircraft; the cooperative control unit is in communication connection with the lift force and gesture control subsystem, the steering control subsystem and the propulsion subsystem, is connected with the gesture and navigation sensor, is used for receiving signals from the gesture and navigation sensor, generates a control instruction according to a preset control strategy, and coordinates the synthetic jet generator matrix, the control moment gyro and the main propulsion to cooperatively work. Preferably, the matrix of synthetic jet generators is integrated on the upper surface of the wing and/or on both sides of the fuselage of the aircraft. Preferably, the number of control moment gyroscopes is at least two, wherein at least one control moment gyroscope is used for controlling yaw of the aircraft and at least one other control moment gyroscope is used for controlling pitch of the aircraft. Preferably, the main propeller is a vector propeller, and the nozzle direction of the main propeller is adjustable. Preferably, the preset control strategy includes: Preferentially distributing roll and pitch control instructions of the aircraft to the lift and attitude control subsystem for execution; And distributing yaw control instructions of the aircraft to the stee