Novel spinning missile control method taking spinning missile spin cycle as control reference

A technology of control benchmarks and control methods, which is applied in the direction of self-propelled projectiles, weapon types, projectiles, etc., and can solve the problems of difficult implementation of control systems.

Inactive Publication Date: 2018-03-30
INST OF ELECTRONICS ENG CHINA ACAD OF ENG PHYSICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Even if the control point is determined according to the position of the rudder surface, it will be difficult to realize the control system in engineering because the rudder deflection cannot realize the complete cycle control.

Method used

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  • Novel spinning missile control method taking spinning missile spin cycle as control reference
  • Novel spinning missile control method taking spinning missile spin cycle as control reference
  • Novel spinning missile control method taking spinning missile spin cycle as control reference

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Embodiment Construction

[0030] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0031] Any feature disclosed in this specification (including any appended claims, abstract and drawings), unless expressly stated otherwise, may be replaced by alternative features which are equivalent or serve a similar purpose. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0032] The present invention comprises the following steps:

[0033] a. Use the roll angle measuring device to test the roll angle position signal γ of the projectile, as the basis for forming the control signal, and use this signal as the control reference signal;

[0034] The guidance command obtained by solving the GPS signal is the pitch equivalent rudder deflection angle δ in the quasi-missile coordinate system eqz and yaw equivalent ru...

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Abstract

The invention provides a novel spinning missile control method taking a spinning missile spin cycle as a control reference. According to the scheme, guide instructions obtained by resolving GPS signals are a pitching equivalent rudder deflection angle and a yaw equivalent rudder deflection angle under a quasi missile body coordinate system, wherein the pitching equivalent rudder deflection angle and the yaw equivalent rudder deflection angle need to be converted into an actual pitching rudder deflection angle and an actual yaw rudder deflection angle under a missile body coordinate system respectively; and when a rudder surface is deflected to a reference position, the actual rudder deflection angles are half of the pi times of the equivalent rudder deflection angles in respective guide instructions, rudder deflection reversing is carried out when the rudder surface is deflected to the reference position, and then a gyroscope preassembling angle is set to realize compensation decoupling on a spinning missile double-channel control system.

Description

technical field [0001] The present invention relates to a novel control method of a rotary bomb, especially a novel rotary bomb control method which takes the spin period of the rotary bomb as the control reference. Background technique [0002] Rotary missiles refer to a type of missile aircraft that continuously rolls around its own longitudinal axis during flight. It has a series of advantages such as simplifying the structure and composition of the control system, improving penetration capabilities, relaxing processing and manufacturing error tolerances, and avoiding asymmetrical ablation. , widely seen in artillery shells, rockets, tactical missiles, strategic missile reentry warheads, etc., represents an important direction in the development of weapons and equipment, such as the XM982 and other guided artillery shells in the United States, and the Tornado rocket in Russia. The reentry warheads of the latest RAM air defense missiles of the United States, Patriot-3 miss...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 叶海福牟东彭波把余玺程祥利汪能
Owner INST OF ELECTRONICS ENG CHINA ACAD OF ENG PHYSICS
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