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Aircraft track angle control method, system and storage medium

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

Active Publication Date: 2021-11-23
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, system and storage medium
  • Aircraft track angle control method, system and storage medium
  • Aircraft track angle control method, system and storage medium

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Embodiment Construction

[0043] It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0044] 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, system and storage medium. The method includes the following steps: according to the strong coupling and highly nonlinear characteristics of the aircraft dynamic model, the aircraft nonlinear system model is established; through variable substitution, the The nonlinear system model of the aircraft is transformed into a feedback control model with model parameter uncertainty; the flight path angle constraint control is performed on the feedback control model of the aircraft based on barrier Lyapunov function and RBF neural control theory. Compared with the prior art, the invention can avoid failure of the control system of the aircraft, thereby improving the control precision of the flight path angle of the aircraft, and improving the flight quality and flight safety characteristics of the aircraft.

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 Patents(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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