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A Collision Angle Control Guidance Method Based on Observer and Global Sliding Mode

A technology of observer and collision angle, applied in adaptive control, general control system, control/adjustment system, etc., can solve the problem that missiles cannot complete accurate strikes, cannot guarantee limited time convergence characteristics, etc., and achieve large-scale collision angle control. , the effect of a wide range of applications

Active Publication Date: 2022-05-20
NANJING UNIV OF SCI & TECH
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Problems solved by technology

However, the above-mentioned methods all need to obtain the remaining flight time of the missile, and the remaining flight time of the missile is usually obtained by estimating, so it is inevitable to introduce estimation errors, so that the missile cannot complete the task of precise strike; on the other hand, the above-mentioned methods all There is no guarantee of finite-time convergence properties

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  • A Collision Angle Control Guidance Method Based on Observer and Global Sliding Mode
  • A Collision Angle Control Guidance Method Based on Observer and Global Sliding Mode
  • A Collision Angle Control Guidance Method Based on Observer and Global Sliding Mode

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Embodiment 1

[0090] combine figure 1 , the present invention is based on an observer and a global sliding mode collision angle control guidance method, comprising the following steps:

[0091] Step 1, establish the relative kinematics model of projectile and target, as follows:

[0092] The relative kinematics model of the missile-target in the two-dimensional plane can be established as:

[0093]

[0094] Among them, the subscripts T and M represent the target and the missile; a represents the acceleration, V represents the velocity, θ represents the line of sight angle, λ and δ represent the flight direction angles of the missile and the target relative to the line of sight (LOS) respectively; γ represents the flight path angle. and respectively represent the acceleration components of the missile and the target perpendicular to the LOS; V θ and V R denote the relative velocities perpendicular to the LOS and along the LOS, respectively. They can be calculated according to the f...

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Abstract

The invention discloses a collision angle control guidance method based on an observer and a global sliding model. The method is as follows: first establish the relative kinematics model of the missile and target; then obtain the motion parameters of the missile and the target through the missile-borne sensor; then estimate the target acceleration information; then design the guidance law; finally input the guidance command to the actuator to control the missile Flying; repeat steps to measure motion parameters and guide control until the end of guidance. The invention has the characteristic of finite time convergence and is suitable for stationary targets and maneuvering targets.

Description

technical field [0001] The invention relates to the technical field of missile guidance, in particular to a collision angle control guidance method based on an observer and a global sliding model. Background technique [0002] In order to achieve precise strike, the designed guidance law is required to ensure a small amount of miss. However, in some special application scenarios, such as anti-tank missiles and anti-ship missiles, it is also required that the designed guidance law can control the collision angle to enhance the damage effect. Scholars at home and abroad have proposed some solutions to this multi-constraint guidance law problem. For example, Dou L. (Dou, L., Dou, J.: The design of optimal guidance law with multi-constraints using blockpulse functions. Aerospace Science and Technology 23(1), 201-205(2012).) based on optimal control A guidance law is proposed that optimizes the drop angle and controls energy consumption. LeeC.H. et al. (Lee, C.H., Shin, H.S., ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042Y02T90/00
Inventor 易文俊张文广
Owner NANJING UNIV OF SCI & TECH
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