Control method of hypersonic vehicle orienting uncertainty condition

A technology of hypersonic speed and control method, applied in attitude control, three-dimensional position/course control, etc., can solve problems such as slow convergence speed and chattering, and achieve the effect of ensuring rapidity and robustness

Active Publication Date: 2017-08-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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At the same time, the present invention provides a new solution for the shortcomings of the traditional reachin

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  • Control method of hypersonic vehicle orienting uncertainty condition
  • Control method of hypersonic vehicle orienting uncertainty condition
  • Control method of hypersonic vehicle orienting uncertainty condition

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[0138] In order to verify the control effect of the designed backstepping sliding mode controller, the hypersonic vehicle is simulated and analyzed, the command tracking signal is given, and the parameters of the designed controller are adjusted at the same time to obtain the corresponding command tracking effect. The robustness of the control method is verified by introducing the maximum parameter perturbation into the aircraft model, which shows that the control method greatly improves the stability and accuracy of the system.

[0139] The following is a simulation verification of the established hypersonic aircraft model from the perspective of simulation. In the Matlab simulation test, refer to the simulation verification conditions in the document "Backstepping Sliding Mode Control for Hypersonic Vehicle Trajectory Tracking" to select the flight height and flight speed of the aircraft The initial equilibrium states of are respectively the nominal parameters under the 33528...

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Abstract

The invention discloses a control method of a hypersonic vehicle orienting the uncertainty condition. The control method comprises the following steps that step S1, full state feedback linearization processing is performed on flight speed V and flight height h according to a hypersonic vehicle longitudinal dynamic equation so as to obtain a corresponding state equation; step S2, an anti-step sliding mode controller is designed according to the state equation, and the double exponential approximation law of the selected sliding mode surface is S<.>=-k<1>|S|<eta>sgn(S)-k<2>|S|<lambda>sgn(S), wherein k<1>>0, K<2>>2, eta>1 and 1>lambda>0 are parameters in the formula; and step S3, a test platform is established based on the anti-step sliding mode controller to perform performance simulation. According to the method, the double exponential sliding mode controller based on the backstepping method is adopted, and switching gain and the problem of buffeting existing in sliding mode control can be effectively reduced by the method.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft, in particular to a flight control method for hypersonic aircraft under uncertain conditions. Background technique [0002] Hypersonic aircraft mainly perform flight missions in the near-space area of ​​20-100km from the ground. Near space is a space that has not been well developed and utilized by humans so far. It has great potential in military and civilian applications. The concealment of the hypersonic vehicle is very high and the communication signal of the aircraft in this field is very strong. The flight of a hypersonic vehicle in close space determines that it has both the advantages of aviation technology and the advantages that spacecraft cannot have. In military applications, hypersonic aircraft can execute very fast and can reach the target in the first time, which will lead to the advent of the era of rapid and precise strike weapons. Especially in intelligence collectio...

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
Inventor 刘蓉姜定国高艳辉严昊李志宇郭剑东孙晓媛
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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