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Finite time integral sliding mode terminal guidance law

A limited time, terminal guidance law technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problems of conservatism and difficulty in obtaining

Active Publication Date: 2019-04-02
SICHUAN AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, in practice, this information is often difficult to obtain. In order to ensure robustness and finite time convergence characteristics, it is often necessary to select larger design parameters, which will result in conservative

Method used

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specific Embodiment approach

[0093] The invention proposes a finite-time-integral sliding-mode terminal guidance law based on a super-twisting algorithm, which mainly includes the establishment of three-dimensional guidance equations, the design of a target maneuver acceleration observer, the design of a finite-time-integral sliding-mode terminal guidance law and its stability analysis. The specific embodiment of the present invention is as follows:

[0094] 1) Assume that the missile uses an active radar seeker, which can provide target-missile relative distance information r and its rate of change Line of sight angle information φ and θ, and line of sight angle rate information and

[0095] 2) From the output information of the seeker, calculate the target-missile relative approach velocity component V r , V φ and V θ . Use this as the input of the target acceleration observers (10) and (11) to obtain the estimated value of the target maneuver acceleration and

[0096] 3) Substitute the es...

Embodiment 1

[0098] Intercept drones. The initial position of the interceptor missile is (100, 1, 15) km, the initial velocity is 1600m / s, and the initial trajectory inclination and trajectory angle are -15° and -17° respectively. The initial position of the target is (120, 5, 12) km, the initial velocity is 900m / s, and the initial ballistic inclination and ballistic deflection angle are -2° and 180° respectively. The target is only implemented on the yaw channel a Tθ =-8g, t≥3s form of step maneuver.

Embodiment 2

[0100]Intercept ballistic missiles. The initial position of the interceptor missile is (45, 1, 6) km, the initial velocity is 1700m / s, and the initial trajectory inclination and trajectory angle are 10.5° and -18.5° respectively. The initial position of the target is (75, 5, 20) km, the initial velocity is 900m / s, and the initial ballistic inclination and ballistic deflection angle are -40° and 180° respectively. Ballistic missile implements spiral maneuver, as a Tφ =Acos(πt / 3)g and a Tθ =Asin(πt / 3)g, where the amplitude A varies with the altitude, as shown in Table 1.

[0101] Table 1 Target Maneuvering Amplitude A

[0102]

[0103] In the above two embodiments, the proposed finite-time integral sliding mode guidance law (SOSMG) based on the super-twisting algorithm is compared with the classic adaptive sliding mode guidance law (ASMG) to verify the performance of SOSMG.

[0104] from figure 1 with Figure 4 It can be seen that the proposed SOSMG can guarantee that t...

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Abstract

The invention discloses a finite time integral sliding mode terminal guidance law based on a super-twisting algorithm. The guidance law comprises the following steps: step 1, establishing a three-dimensional target-missile relative motion equation; step 2, designing a guidance law. A stability analysis is conducted on the guidance law. The invention provide the finite time integral sliding mode terminal guidance law based on the super-twisting algorithm by combining an integral sliding mode, a super-twisting algorithm and a finite time disturbance observer. According to the finite time integral sliding mode terminal guidance law based on the super-twisting algorithm, the finite time can be converged, the buffeting phenomenon can be eliminated, so that the maneuvering acceleration of a target can be better estimated, and the guidance accuracy is high; and the guidance law can be used for intercepting high-speed large-maneuvering targets such as unmanned aerial vehicles, ballistic missiles and the like, and has a wide application prospect.

Description

technical field [0001] The invention relates to a finite time integral sliding mode terminal guidance method based on a super-twisting algorithm, belonging to the technical field of guidance control. Background technique [0002] With the continuous advancement of science and technology, the target threat in modern and future warfare is developing towards high-speed and large-scale maneuvering. This poses a new challenge to the design of the guidance law, which requires the guidance to respond quickly and ensure convergence in a limited time. In addition, in order to completely destroy the target, the kinetic energy killing technology that requires direct collision has become a research hotspot, which puts forward higher requirements for guidance accuracy. [0003] Sliding mode control is robust to bounded uncertainties and disturbances that satisfy matching conditions. In addition, the sliding mode control algorithm has the advantages of simple structure, easy implementat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 孟克子王进黄鹏吴璋胡洲游金川刘红梅
Owner SICHUAN AEROSPACE SYST ENG INST
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