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Double-rotary table semi-physical simulation system and method for full strapdown missile guidance control system

A semi-physical simulation and control system technology, applied in the field of aerospace simulation, can solve problems such as high cost and difficult simulation implementation, and achieve the effect of reducing complexity and cost

Active Publication Date: 2019-04-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

On the one hand, this kind of simulation scheme requires a customized high-performance five-axis turntable, which is costly; For similar missiles, it is necessary to simulate the missile system on the inner two axes of the five-axis turntable, and simulate the body line of sight relative to the missile system on the outer two axes. The complex coordinate transformation relationship brings difficulties in simulation implementation.

Method used

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  • Double-rotary table semi-physical simulation system and method for full strapdown missile guidance control system
  • Double-rotary table semi-physical simulation system and method for full strapdown missile guidance control system
  • Double-rotary table semi-physical simulation system and method for full strapdown missile guidance control system

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Experimental program
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Embodiment 1

[0096] Taking the laser semi-active to attack the stationary armored vehicle with the full strapdown missile as an example, the implementation description of the method is carried out. The given initial simulation scenario is as follows:

[0097] x T (0) = 1500mV T (0)=0.0m / s x M (0) = 0m ω Mx (0)=2.0deg / s

[0098] the y T (0)=-2m, θ T (0)=0.0deg,y M (0) = 0m, ψ M (0) = 0.0deg, ω My (0)=2.0deg / s

[0099] z T (0)=0m ψ VT (0)=0.0deg z M (0) = 0m γ M (0)=0.0deg ω Mz (0)=2.0deg / s

[0100] V M (0) = 0.0m / s

[0101] θ M (0)=6.0deg

[0102] ψ VM (0) = 0.0deg

[0103] At the moment of simulation 2s, an instantaneous crosswind is applied to the missile with a wind speed of 2m / s; the aerodynamic parameters come from the engineering estimation results. The body parameters are as follows:

[0104] m=11.3,J x =0.0324,J y =0.8412,J z =0.8405, S=0.01327, L=1.042

[0105]

[0106]

[0107]

[0108] where m is the mass of the missile, J x ,J y ,J z is ...

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Abstract

The invention relates to a double-rotary table semi-physical simulation system and method for a full strapdown missile guidance control system. A guide head, body sight simulation rotary tables, a target simulator, an inertia group, a missile-borne computer, a posture simulation rotary table, a steering gear, a steering gear loading system, a real-time master control simulation machine, a data acquisition computer and a reflective memory network are included; one rotary table is used for simulating the attitude motion, and the other rotary table is used for simulating motion of a missile relative to the body sight. By means of the system, two three-axis rotary tables are used for replacing five-axis rotary tables required during semi-physical simulation of a traditional full strapdown missile guidance control system, and the complexity and cost of the simulation platform are effectively reduced.

Description

technical field [0001] The invention relates to a semi-physical simulation system and method of a full strapdown missile guidance control system, in particular to a semi-physical simulation method of a double turntable of a full strapdown missile. It belongs to the field of aerospace simulation. Background technique [0002] The semi-physical simulation of missiles refers to the process of inserting some real objects in the simulation test for simulation verification. It can be closer to the actual situation, and can greatly shorten the development cycle and compress the development funds. For the guidance and control system, it is usually necessary to provide the same working conditions as the real environment for the seeker, inertial group, missile-borne computer, steering gear and other hardware links in the hardware-in-the-loop simulation. [0003] At present, in the hardware-in-the-loop simulation system of the existing strapdown missile guidance and control system, mo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 赵斌周军卢晓东郭建国谭雁英
Owner NORTHWESTERN POLYTECHNICAL UNIV
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