Air-to-air missile direct force/aerodynamic finite time anti-saturation control method

A limited-time, air-to-air missile technology, applied in non-electric variable control, three-dimensional position/course control, vehicle position/route/altitude control, etc., can solve problems such as control force offset, and achieve the effect of closed-loop system stability

Active Publication Date: 2018-12-25
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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Problems solved by technology

[0005] For control systems with multiple actuators, a control system design withou

Method used

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  • Air-to-air missile direct force/aerodynamic finite time anti-saturation control method
  • Air-to-air missile direct force/aerodynamic finite time anti-saturation control method
  • Air-to-air missile direct force/aerodynamic finite time anti-saturation control method

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specific Embodiment approach

[0062] Specific implementation: Firstly, the longitudinal short-period model of the missile is given, and an integral sliding mode controller that can deal with bounded disturbance and input saturation is designed according to the longitudinal motion model of the missile, and the virtual control torque required to establish the missile overload is obtained. Control distribution is used to map desired control torques to aerodynamic rudder surfaces and direct force devices. Theoretical analysis and numerical simulation both show that the proposed controller can make the compound control missile track overload command signal in finite time, and the closed-loop system is stable.

[0063] In order to avoid the singular phenomenon existing in the traditional terminal sliding mode, a new integral sliding mode surface is proposed, which can make the system state converge to the equilibrium position in a given finite time. According to the longitudinal motion model of the missile, an i...

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Abstract

The invention relates to an air-to-air missile direct force/aerodynamic finite time anti-saturation control method. In order to avoid the singularity of the traditional terminal sliding mode, a new integral sliding surface is proposed, which can converge the system state to the equilibrium position for a given finite time. An integral sliding mode controller that can deal with the bounded disturbance and the input saturation problem is designed,, and the virtual control torque needed to build a missile overload is obtained based on the longitudinal motion model of the missile. Controlled distribution is used to map the desired control torque to the aerodynamic rudder surface and direct force device. Both theoretical analysis and digital simulation show that the proposed controller enablesthe composite control missile to track an overload command signal for a limited time, and the closed loop system is stable.

Description

technical field [0001] The invention belongs to the technical field of aircraft attitude control, and relates to an air-to-air missile direct force / aerodynamic force limited time anti-saturation control method. Background technique [0002] The goal of air warfare is gradually becoming a new type of aircraft with high altitude, high speed, great maneuverability, intelligent escape and stealth technology, which puts forward new requirements for the response speed and maneuverability of air-to-air missiles. In this situation, the traditional aerodynamic control scheme is difficult to meet the development needs of air-to-air missiles, and a new composite control technology emerges as the times require. Different from the direct force device of general anti-aircraft missile, the direct force device suitable for air-to-air missile has its particularity. Strictly limited by the volume of air-to-air missiles, the direct force device for engine drainage is more suitable for air-to-...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 郭永李雨涛李爱军王长青
Owner NORTHWESTERN POLYTECHNICAL UNIV
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