Integrated design method for guidance and control of hypersonic aerocraft

A technology of hypersonic speed and design method, applied in the field of aircraft control, can solve the problem of mismatch between the guidance loop and the control loop, and achieve the effect of easy hypersonic aircraft engineering application, improved robustness, good control performance and robust performance.

Active Publication Date: 2019-05-03
BEIJING AEROSPACE TECH INST
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, and propose a hypersonic aircraft guidance and control integrated design method based on the traject

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  • Integrated design method for guidance and control of hypersonic aerocraft
  • Integrated design method for guidance and control of hypersonic aerocraft
  • Integrated design method for guidance and control of hypersonic aerocraft

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Embodiment Construction

[0042] Trajectory Linearization Control (TLC) method is an effective nonlinear tracking and decoupling control method, which can well solve the problems of the guidance loop and control loop of hypersonic aircraft under the condition of large external perturbation and interference. mismatch problem.

[0043] The basic principle of the TLC method is to first obtain the nominal controller according to the dynamic equation of the aircraft and based on the dynamic inverse idea, and secondly, linearize the tracking error along the nominal trajectory, and then transform the trajectory tracking problem into the tracking error adjustment problem. A linear time-varying feedback controller is designed to eliminate the tracking deviation, and then realize the tracking of the trajectory. In the integrated design of the guidance control strategy, the reference command [V c θ c ] T , design the guidance loop tracking controller, and generate the input control instructions of the control...

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Abstract

The invention discloses an integrated design method for guidance and control of a hypersonic aerocraft. The method comprises steps that firstly, a nonlinear dynamic model of the hypersonic aerocraft is established, based on the singular perturbation theory, the nonlinear dynamic model is divided into a slow time-varying guidance loop and a fast time-varying control loop, secondly, a nominal controller and a linear time-varying feedback controller of the two loops are designed separately, actual control input of the two loops is calculated, and lastly, control output of the two loops is calculated based on the mapping relationship. The method is advantaged in that aiming at the complex flight mission profile of the hypersonic aerocraft and a flight control problem along the trajectory, thecharacteristics of the hypersonic vehicle with strong coupling, strong nonlinearity and fast time-varying are considered, in the case of large system perturbation and external disturbance in the model, based on the trajectory linearization control method, integrated strategy design of guidance control is completed, the method is simple for realization and easy for engineering application in the hypersonic aircraft, and the method has better control performance and robust performance.

Description

technical field [0001] The invention belongs to the technical field of aircraft control, in particular to an integrated design method for guidance and control of a hypersonic aircraft based on a trajectory linearization method. Background technique [0002] Different from traditional aircraft, hypersonic aircraft has the characteristics of flight trajectory across large airspace and large speed range, which makes its flight state parameters and dynamic characteristics change rapidly, and is more sensitive to changes in environmental parameters; the body / engine integration technology makes the body of hypersonic aircraft. , the coupling between the propulsion systems is stronger, which makes the matching between the force systems show strong nonlinear characteristics; in addition, the flight environment of hypersonic aircraft is complex, and the aircraft is affected by large disturbances and disturbances during flight, and It is difficult to accurately simulate the complex fl...

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Application Information

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IPC IPC(8): G05D1/10
Inventor 姚德清魏振岩杨志红柳青彭寿勇
Owner BEIJING AEROSPACE TECH INST
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