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A Non-singular Roll Command Generation Algorithm for BTT Missile

A command generation, non-singular technology, applied to self-propelled missiles, offensive equipment, projectiles, etc., can solve problems affecting missile stability, lift surface adjustment disorder, missile out of control, etc., to achieve easy implementation, simple calculation, and avoid singularity The effect of the phenomenon

Active Publication Date: 2020-12-18
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This phenomenon will cause the adjustment of the lift surface to be disordered, and the missile will be out of control, which will seriously affect the stability of the missile. Therefore, the non-singular processing of the roll command of the roll channel is particularly important.

Method used

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  • A Non-singular Roll Command Generation Algorithm for BTT Missile
  • A Non-singular Roll Command Generation Algorithm for BTT Missile
  • A Non-singular Roll Command Generation Algorithm for BTT Missile

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Embodiment Construction

[0015] The flow of a non-singular roll command generation algorithm for BTT missiles in the embodiment of the present invention is as follows: figure 1 shown.

[0016] S1 calculates the normal and lateral overload command N y , N z , the calculation method is given by the designed guidance and control system; the expression is

[0017]

[0018] Where χ is the roll angle (the angle between the lift surface and the horizontal plane) instruction, N′ y is the normal overload after dead zone processing, N′ z It is the lateral overload after hysteresis processing.

[0019] S2 determines the form and width of the dead zone, the form of the dead zone is as follows figure 2 As shown in , where the x-axis represents the input of the overload command, the y-axis represents the output of the overload command, [-z, z] is the dead zone, and the size of z depends on the needs of the project, generally around 0.05. The mathematical description of the dead zone is

[0020]

[002...

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Abstract

The invention discloses a nonsingular rolling command generating algorithm for a BTT guided missile. The nonsingular rolling command generating algorithm comprises the steps that (1) a normal overloadcommand and a side direction overload command are calculated; (2) a dead zone is designed nearby the zero value for the normal overload command; (3) a hysteresis zone is designed nearby the zero value for the side direction overload command; and (4) a rolling angle command is calculated according to the normal overload command and the side direction overload command obtained in the step (2) and the step (3). According to the algorithm, the dead zone is designed for the normal overload command, the hysteresis zone is designed for the side direction overload command, the rolling command is calculated according to the processed overload commands, and control disorders caused by sign mutation of the rolling angle command due to pneumatic interference is avoided.

Description

technical field [0001] The invention relates to a non-singular roll instruction generation algorithm for BTT missiles, the main application field is the generation of tactical weapon roll instructions controlled by BTT, and a special nonlinear region is designed around zero by using the pitch and yaw overload instructions. Background technique [0002] The characteristic of BTT (Bank-To-Turn) control is that in the process of intercepting the target, the missile quickly turns the maximum lift surface of the missile to the ideal maneuvering direction through rolling control, and the pitch control system controls the missile at the maximum lift. Generate the required maneuvering acceleration in the plane. BTT control is generally carried out in polar coordinates, and there are two general processing methods, one is to calculate in the rectangular coordinate system first, and then transfer to the polar coordinate system; the second is to directly perform in the polar coordinate...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 奚勇陈光山彭继平冯昊廖幻年王璐田野
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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