Non-singular terminal sliding mode finite time convergence angle constraint guidance method

A non-singular terminal, finite-time technology, applied in the field of non-singular terminal sliding mode finite-time convergence angle-constrained guidance field, can solve the problems of singular buffeting and low landing precision of sliding mode surface

Inactive Publication Date: 2019-11-19
HARBIN INST OF TECH
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  • Abstract
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Problems solved by technology

[0004] The purpose of the present invention is to solve the problems of singular chattering on the sliding mode surface and low precision of landing point existing in the existing angle-constrained guidance method, and to provide a non-singular terminal sliding mode finite-time convergence angle-constrained guidance method. The technical solution is as follows:

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  • Non-singular terminal sliding mode finite time convergence angle constraint guidance method
  • Non-singular terminal sliding mode finite time convergence angle constraint guidance method
  • Non-singular terminal sliding mode finite time convergence angle constraint guidance method

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Embodiment 1

[0068] A non-singular terminal sliding mode finite-time convergence angle-constrained guidance method, wherein the non-singular terminal sliding-mode finite-time convergence angle-constrained guidance law includes the following steps:

[0069] Step 1: Establish the target-aircraft relative motion equation;

[0070] Step 2: The target-aircraft relative motion equation is combined with the non-singular terminal sliding mode surface and the terminal sliding mode approach law to design the non-singular terminal sliding mode finite-time convergence angle constraint guidance law;

[0071] Step 3: Stability analysis of the guidance law;

[0072] The process of establishing the target-aircraft relative motion equation described in step one is as follows:

[0073] The first step: establish the target-aircraft relative motion equation, take the state vector as

[0074] x=[r,λ,θ T ,θ M ] (1)

[0075] Among them, θ T and θ M are the ballistic inclination angles of the target and th...

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Abstract

The invention discloses a non-singular terminal sliding mode finite time convergence angle constraint guidance method and belongs to the technical field of guidance and control. According to the technical schemes of the invention, the non-singular terminal sliding mode finite time convergence angle constraint guidance method comprises the following steps that: step 1, a target-aircraft relative movement equation is established; step 2, a non-singular terminal sliding mode finite time convergence angle constraint guidance law is designed; and step 3, stability analysis is performed on the guidance law. The on-singular terminal sliding mode finite time convergence angle constraint guidance method of the invention is based on a non-singular terminal sliding mode surface and a terminal slidingmode reaching law. With the method adopted, a singular buffeting problem on a sliding mode surface can be avoided; finite time convergence is guaranteed; and landing precision is improved. The methodhas a bright application prospect.

Description

technical field [0001] The invention belongs to the technical field of guidance and control, and in particular relates to a non-singular terminal sliding mode finite time convergence angle constraint guidance method. Background technique [0002] Certain tasks require that the guidance law not only achieve high landing point accuracy, but also require a specific landing angle at the end of the trajectory to achieve complex mission requirements such as horizontal strike or vertical return. Therefore, it is necessary to study the angle-constrained guidance technology that achieves a limited time convergence of the landing angle. . [0003] For systems with uncertainties such as model errors, the robust adaptive ability of sliding mode control technology is better, so it has been more and more used in the design of guidance laws. Compared with the traditional linear sliding mode surface, the terminal sliding mode control method can make the system mode converge quickly in a li...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/02
CPCG05B13/024
Inventor 韦常柱许河川崔乃刚韩业鹏李源
Owner HARBIN INST OF TECH
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