Interference-compensated tracking control method for hypersonic-speed variable-swept-wing aircraft

A hypersonic, tracking control technology, applied in non-electric variable control, vehicle position/route/altitude control, control/regulation system, etc., can solve problems such as difficulty in ensuring the stability of hypersonic aircraft regardless of state and input constraints , to achieve the effect of improving stability and robustness

Pending Publication Date: 2021-12-10
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

However, most of the existing methods model the deformation process of the aircraft as a hard switching of a multi-switching system, ignoring factors such as additional disturbances in the deformation process

Method used

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  • Interference-compensated tracking control method for hypersonic-speed variable-swept-wing aircraft
  • Interference-compensated tracking control method for hypersonic-speed variable-swept-wing aircraft
  • Interference-compensated tracking control method for hypersonic-speed variable-swept-wing aircraft

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Example Embodiment

[0080] Example 1:

[0081]Step 1: Considering the flight state constraints, the influence of input saturation, the additional disturbances generated by the continuous deformation process, and the uncertainty of aerodynamic parameters, the longitudinal dynamics model of the hypersonic variable-sweep wing aircraft is established.

[0082] Taking the aerodynamic and structural data of the Variable-sweep-wing Morphing Waverider (VMW) as an example, the longitudinal dynamic model is established as follows:

[0083]

[0084] Among them, H is the flight height, X is the forward flight distance, V is the flight speed, γ is the ballistic inclination angle, θ is the pitch angle of the body, α is the flight angle of attack, q is the pitch angular velocity, and Λ is the wing sweep angle. The total mass of the aircraft is m=600kg, is the moment of inertia of the body to the body's center of mass, is the moment of inertia of the wing to the center of mass of the body, specifically: ...

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Abstract

The invention discloses an interference-compensated tracking control method for hypersonic-speed variable-swept-wing aircraft, and belongs to the technical field of hypersonic speed aircraft control. The implementation method comprises the following steps: an aircraft longitudinal dynamic model is established by considering flight state constraint, input saturation influence, additional interference generated in a continuous deformation process and aerodynamic parameter uncertainty; a deformation additional force, a torque and a pneumatic uncertain item are regarded as unknown composite interference, and an uncertain strict feedback nonlinear tracking control system is established; a nonlinear interference observer is designed to realize accurate estimation of unknown interference; a Backstepping control method is adopted to gradually design a tracking control law, an interference compensation mechanism is introduced to counteract composite interference, an instruction filtering auxiliary system is designed to compensate state constraint and input saturation influence, an instruction filtering tracking control law based on interference compensation is designed, so that the stability and robustness of a closed-loop system are improved, stable flight of the hypersonic-speed variable swept wing aircraft in a cross-speed domain and multi-mode flight working condition is realized.

Description

technical field [0001] The invention belongs to the technical field of hypersonic vehicle control, and relates to a tracking control method for a hypersonic variable-sweep wing vehicle. Background technique [0002] Due to the advantages of fast flight speed, wide airspace coverage, and strong maneuverability, hypersonic vehicles have become a hot spot for the development of aerospace science and technology around the world. Traditional fixed-configuration hypersonic vehicles are designed for specific flight conditions, which limits their ability to perform multi-tasks in high-speed and high-dynamic environments. In response to changes in the flight environment and mission scenarios, the hypersonic variable-sweep wing aircraft dynamically adjusts its flight performance by changing the wing sweep angle to achieve stable flight in the cross-speed domain and multi-mode flight conditions. However, drastic changes in aerodynamic and structural parameters in the process of flying...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 龙腾李俊志孙景亮王仰杰周桢林
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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