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A trajectory tracking control method for hypersonic aircraft based on output information

A hypersonic, trajectory tracking technology, applied in vehicle position/route/altitude control, attitude control, control/regulation systems, etc., can solve the problems of complex algorithm, unestimable tracking time, poor robust performance, etc., to eliminate the system jitter effect

Active Publication Date: 2022-07-15
QUFU NORMAL UNIV
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  • Description
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AI Technical Summary

Problems solved by technology

[0005] The present invention solves the problems of complex control algorithms, poor robustness and unestimable tracking time of the existing aircraft.

Method used

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  • A trajectory tracking control method for hypersonic aircraft based on output information
  • A trajectory tracking control method for hypersonic aircraft based on output information
  • A trajectory tracking control method for hypersonic aircraft based on output information

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Embodiment Construction

[0052] like figure 1 As shown, the specific implementation steps of the present invention are as follows (the following takes the longitudinal model of the hypersonic aircraft as an example to illustrate the specific implementation of the method):

[0053] 1) Using the input-output linearization technology, the longitudinal model of the hypersonic vehicle is transformed into an input-output model containing lumped disturbances (the sum of external disturbances and parameter uncertainties);

[0054] The longitudinal model of the hypersonic vehicle system is:

[0055]

[0056] Among them, V, h, α, γ, q represent the speed, altitude, attack angle, track angle and pitch angle rate of the aircraft respectively; μ is the earth’s gravitational constant, r=h+R, R is the earth’s radius, M yy is the control torque, I yy is the moment of inertia, C L =0.6203α,C D =0.6450α 2 +0.0043378α+0.003772,C M (δ E )=c e (δ E +d 2 (t)-α),

[0057] The second-order dynamic model o...

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Abstract

A hypersonic vehicle trajectory tracking control method based on output information, comprising the following steps: Step 1: Using an input-output linearization technique, transform the longitudinal model of the hypersonic vehicle into a system containing lumped disturbances (the sum of external disturbances and parameter uncertainties) ) input and output model; Step 2: According to the input and output model established in Step 1, design a fixed time dilation state observer to estimate the state of the unknown disturbance and the input and output model; Step 3, based on the fixed time dilation state observer and the output value of the system , design the fixed-time continuous terminal sliding mode surface, and further obtain the fixed-time continuous terminal sliding mode trajectory tracking control scheme of the hypersonic aircraft system; the method of the invention can make the system output track the reference trajectory in the fixed time. The invention is suitable for the field of hypersonic aircraft control.

Description

technical field [0001] The invention relates to a track tracking control method for a hypersonic aircraft based on output information, which is mainly applied to the technical field of hypersonic aircraft control. Background technique [0002] Hypersonic vehicle is an aircraft that flies in near space and has a speed greater than Mach 5. It has both the functions of spacecraft and aircraft, and is the main force to realize space operations and global operations in the future. It can be seen that the research on hypersonic aircraft has important military significance and is becoming the focus of research by various military powers. It can also directly strike the enemy or serve as a weapon launching platform for long-distance raids, which greatly improves the ability of long-range combat. In addition, due to its extremely fast flight speed, high flight altitude and strong of lateral mobility, no anti-aircraft weapons currently can hit it. In short, hypersonic aircraft has u...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 孙海滨侯林林宗广灯杨东
Owner QUFU NORMAL UNIV
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