Aircraft attitude control method and aircraft

A technology of attitude control and aircraft, applied in the field of aircraft, can solve problems such as limited nozzle angle, influence on the control effect of aircraft aerodynamic performance, complex thrust vector nozzle structure, etc., achieve high precision, avoid low rudder efficiency, and improve stealth performance Effect

Active Publication Date: 2022-05-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
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  • Application Information

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Problems solved by technology

Thrust-vectoring nozzles are complex and have limited angles for adjusting the nozzles
The jet circulation technology is based on the Coanda effect and is often applied at subsonic speeds. At...

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  • Aircraft attitude control method and aircraft
  • Aircraft attitude control method and aircraft

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Embodiment Construction

[0035] The present invention will be described in more detail below. While the present invention has provided preferred embodiments, it should be understood that the invention can be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0036] Please refer to Figure 1 to Figure 2 , an embodiment of the present invention provides an attitude control method for an aircraft, including:

[0037] Real-time monitoring of the pressure at the pressure measuring points through a plurality of pressure measuring points arranged on the aircraft;

[0038] Predicting the flight parameters of the aircraft based on the flight parameter model and the real-time pressure at the pressure measuring point;

[0039] Predicting the aerodynamic force and aerodynamic moment of the aircraft bas...

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Abstract

The invention discloses an aircraft attitude control method and an aircraft, and the control method comprises the steps: monitoring the pressure of pressure measurement points in real time through a plurality of pressure measurement points arranged on the aircraft; predicting flight parameters of the aircraft based on a flight parameter model and the real-time pressure of the pressure measuring point; predicting aerodynamic force and aerodynamic moment of the aircraft based on an aerodynamic force prediction model and the aircraft flight parameters; based on the aerodynamic torque, a layout scheme for generating protrusions on the surface of the aircraft is given through a protrusion position prediction model; the moment increment generated by the generated bulge meets the balancing requirement of the aircraft, and the aerodynamic force increment generated by the bulge is minimum; and forming corresponding bulges on the surface of the aircraft according to the layout scheme of the bulges so as to adjust the attitude of the aircraft. The attitude of the aircraft can be well controlled, the stealth performance of the aircraft is improved, and the influence on the aerodynamic performance is small.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to an attitude control method of an aircraft and the aircraft. Background technique [0002] Aircraft attitude control is usually mainly achieved through the deflection of aerodynamic rudder surfaces such as ailerons, rudders, and elevators. However, the aerodynamic rudder surface will limit the further improvement of the aerodynamic performance of the aircraft. When flying at low speed and large angle of attack, the rudder surface efficiency is low; when flying at high speed, the resistance of the aircraft will be increased, and the rudder surface will face severe aerodynamic heating problems. In addition, the rudder surface is a radar reflection source that cannot be ignored, which seriously restricts the stealth ability of the aircraft. Therefore, control with reduced rudder surfaces or even no rudder surfaces has become an important development direction of future ...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/106Y02T90/00
Inventor 覃建秀杨武兵朱德华
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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