Aircraft track angle control method and system and storage medium

A control method and technology for an aircraft, applied in the field of aircraft track angle control, can solve problems such as engine vibration, aircraft control system failure, reduction of lift coefficient, etc., so as to avoid failure, improve flight quality and flight safety characteristics, and improve control accuracy. Effect

Active Publication Date: 2021-06-11
SHENZHEN INSTITUTE OF INFORMATION TECHNOLOGY
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Problems solved by technology

In addition, during the flight, when the angle of attack of the aircraft exceeds a certain critical value, the lift coefficient decreases with the increase of the angle of attack, which will cause the aircraft to produce uncontrolled dive and pitch motion, and the engine will vibrate, resulting in the failure of the aircraft control system.

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  • Aircraft track angle control method and system and storage medium
  • Aircraft track angle control method and system and storage medium
  • Aircraft track angle control method and system and storage medium

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Embodiment Construction

[0042] It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0043] At present, most of the controllers for aircraft are not constrained by the output state signal when designing the aircraft. In order to ensure that the aircraft has good flight quality and flight safety, the output attitude angle and attitude angular velocity must be controlled when the aircraft track angle is controlled. meet certain constraints. The present invention proposes an aircraft track angle neural network dynamic surface control method considering state constraints. Based on the backstepping method, adaptive control technology and neural control theory, it realizes fast and stable tracking of the aircraft track angle, and through the introduction of the barrier Li Yap The Nove function makes the angle of attack and pitch rate change within a certain range and meets the expected state constraints, wh...

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Abstract

The invention provides an aircraft track angle control method and system and a storage medium. The method comprises the steps of building an aircraft nonlinear system model according to the strong coupling and high nonlinear characteristics of an aircraft dynamic model; through variable substitution, converting the aircraft nonlinear system model into a feedback control model with model parameter uncertainty; and carrying out track angle constraint control on the aircraft feedback control model based on a barrier Lyapunov function and an RBF neural control theory. Compared with the prior art, failure of an aircraft control system can be avoided, so that the flight path angle control precision of the aircraft is improved, and the flight quality and the flight safety characteristic of the aircraft are improved.

Description

technical field [0001] The present invention relates to the technical field of aircraft track angle control, in particular to an aircraft track angle control method, system and storage medium. Background technique [0002] The aircraft has the characteristics of complex flight environment, high degree of parameter uncertainty, and strong model nonlinearity. With the complexity of the flight mission, the performance requirements of the aircraft control system are getting higher and higher, making the nonlinear control of the aircraft a control field. A hot spot, but also brings new challenges. [0003] Among many control modes, the track inclination tracking control is one of the most important control modes in the aircraft control system. The advantage of its control method is that it has good anti-wind disturbance characteristics and can effectively reduce the influence of turbulent airflow on the flight control law. Therefore, track tilt tracking control is widely used in...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/06G05D1/08G05D1/10G05D1/12G05B13/02
CPCG05B13/029G05D1/0607G05D1/0808G05D1/0825G05D1/101G05D1/12
Inventor 陈宝文程东升孙经广
Owner SHENZHEN INSTITUTE OF INFORMATION TECHNOLOGY
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