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Full-profile adaptive control method for hypersonic aircraft

An adaptive control, hypersonic technology, applied in the field of aircraft control, can solve the problems of high difficulty and multiple constraints in the control design of hypersonic aircraft

Active Publication Date: 2019-11-22
BEIHANG UNIV
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Problems solved by technology

However, due to the special structure of the re-entry hypersonic vehicle and the unique flight conditions (need to span the three stages of subsonic, transonic and supersonic), the attitude control of the vehicle has problems such as strong coupling, strong nonlinearity, fast time Variable, multiple constraints and other features
All these factors make the control design of hypersonic vehicles very difficult

Method used

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  • Full-profile adaptive control method for hypersonic aircraft
  • Full-profile adaptive control method for hypersonic aircraft
  • Full-profile adaptive control method for hypersonic aircraft

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Embodiment Construction

[0055] Such as figure 1 As shown, a hypersonic vehicle full profile adaptive control method. The first step is to establish a standard six-degree-of-freedom model of a re-entry hypersonic vehicle; the second step is to transform the six-degree-of-freedom model into a strict feedback form through coordinate transformation; the third step is to introduce a neural network to estimate the The nonlinear part of ; the fourth step is to design the adaptive law and the control law through the backstepping method. The invention can solve the problem of full-section attitude tracking control of the reentry vehicle, avoids switching of controllers between different task stages, and is suitable for hypersonic vehicle attitude tracking control. Its specific implementation method is as follows:

[0056] The first step is to establish a six-degree-of-freedom model of the re-entry hypersonic vehicle:

[0057]

[0058]

[0059]

[0060]

[0061]

[0062] Among them, V, θ, ψ ...

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Abstract

The invention relates to a full-profile adaptive control method for a hypersonic aircraft. Aiming at the problem of the controller switching during the full-profile flight of a reentrant hypersonic aircraft, an adaptive control method based on a neural network is designed. Firstly, a six-degree-of-freedom model of the reentrant hypersonic aircraft is established. Secondly, the six-degree-of-freedom model is converted into a strict feedback form by a coordinate transformation. Then, a neural network is introduced to estimate a nonlinear part of a system. Finally, an adaptive law and a control law are designed through a backstepping method. According to the method, the problem of the full-profile attitude tracking control of the reentrant hypersonic aircraft can be solved, the switching of acontroller during the full-profile flight is avoided, and the method is suitable for the attitude tracking control of the hypersonic aircraft.

Description

technical field [0001] The invention relates to a full-profile self-adaptive control method of a hypersonic aircraft, which is mainly applied to the full-profile attitude tracking control of a re-entry hypersonic aircraft, and belongs to the technical field of aircraft control. Background technique [0002] Ballistic missiles have a good long-range strike capability, but their trajectory is relatively fixed. With the rapid development of missile defense systems, the missile defense systems of major countries in the world have the ability to intercept ballistic missiles in the booster, middle, and terminal stages. The penetration capability and survivability of ballistic missiles are greatly threatened. Although cruise missiles can maneuver in the atmosphere, their range is short and their long-range strike capability is not strong. Therefore, major countries in the world are currently stepping up the development of a re-entry hypersonic vehicle that can combine the long-ran...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/107
Inventor 王陈亮李梓明郭雷乔建忠
Owner BEIHANG UNIV
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