Parameter perturbation inhibited instruction tracking control method of high-supersonic-speed aircraft

A technology of hypersonic speed and command tracking, which is applied in the direction of adaptive control, general control system, control/regulation system, etc., and can solve the problems of ensuring the command tracking performance of the control system

Active Publication Date: 2018-03-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

[0004] Purpose of the invention: In order to solve the problem that the existing nonlinear control technology is difficult to ensure the command tracking performance of the control system when the

Method used

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  • Parameter perturbation inhibited instruction tracking control method of high-supersonic-speed aircraft
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  • Parameter perturbation inhibited instruction tracking control method of high-supersonic-speed aircraft

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Embodiment 1

[0127] Embodiment one: in order to verify the effectiveness of the robust adaptive sliding mode controller (10)—(12), references (Xu H, Minmirani M D, Ioannou P A.Adaptive sliding mode control design for ahypersonic flight vehicle[J] .Journal of Guidance, Control, and Dynamics, 2004,27(5):829-838.) The aerodynamic coefficient of the hypersonic vehicle is shown in formula (19), and the atmospheric density and gravity acceleration are shown in formula (20). The parameters are shown in Table 1.

[0128]

[0129]

[0130] Table 1 Basic parameter data of hypersonic vehicle

[0131] parameter name

Numerical size

parameter name

Numerical size

quality

136820kg

Reference area

334.73m 2

y-axis moment of inertia

9490740kg·m 2

mean aerodynamic chord length

24.38m

[0132] The initial state of the aircraft is V=4590.3m / s, γ=0°, α=2.745°, q=0° / s, h=33528m, β=0.21, Using the flight controller described by formula (16-1...

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Abstract

The invention discloses a parameter perturbation inhibited instruction tracking control method of a high-supersonic-speed aircraft. The method comprises the steps that nondeterminacy modeling is carried out on the high-supersonic-speed aircraft to obtain a parameter nondeterminacy model; on the basis of a principle influential element analysis method, the established parameter nondeterminacy modelis simplified; a parameter nondeterminacy inhibited robust adaptive instruction tracking controller is designed; and the stability of the designed controlled is proved. Under the condition that greatparameter perturbation occurs in the high-supersonic-speed aircraft, the rapid instruction tracking capability and the stability of the aircraft can be also ensured, the problem that the instructiontracking performance of the high-supersonic-speed aircraft cannot be ensured in the preset control technology is solved, the operand of the controller is reduced, and the control method is convenientto realize.

Description

technical field [0001] The invention relates to hypersonic vehicle control technology, in particular to a hypersonic vehicle command tracking control method for suppressing parameter perturbation. Background technique [0002] Hypersonic aircraft refers to aircraft with a flight speed exceeding 5 times the speed of sound. It has the characteristics of extremely fast flight speed, flight envelope, and strong defense penetration ability, and has huge military application value and economic value. A controller with good performance is a necessary guarantee for a hypersonic vehicle to successfully complete its mission. Due to factors such as large flight envelope, fast fuel consumption, strong coupling between engine and fuselage, obvious aerodynamic heating effect, and incomplete test data, hypersonic vehicles have uncertainties that cannot be ignored. In order to ensure the effectiveness of the flight controller, these uncertain factors must be fully considered at the control...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 余朝军肖东周俊江驹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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