High-overload-resistant integrated guidance control system

Abstract

The invention discloses an integrated guidance control system capable of resisting high overload. According to the system, a navigation system, a guidance system and a control system are integrally designed; data are transmitted to a microprocessor module for processing, so that the influence of time lag of signal transmission between subsystems on aircraft control is eliminated. A sheet-shaped anti-high-overload antenna is specially designed; compared with a traditional conical antenna and an improved loop antenna, the sheet-shaped antenna not only has stronger satellite signal receiving capability but also has the characteristic of high overload resistance, and can stably work under the condition of high dynamic and high overload. Besides, because the sight line angular rates obtained bythe navigation module and the guidance module are not accurate enough and have errors, the microprocessor module uses the fused and calculated sight line angular rate to carry out navigation calculation, so that the hit precision can be further improved.

Description

technical field [0001] The invention relates to a guidance and control system of an aircraft, in particular to an integrated guidance and control system capable of resisting high overload. Background technique [0002] The guidance and control system is one of the irreplaceable core components of the high dynamic aircraft, and is the key to determine the performance of the high dynamic aircraft. The traditional guidance and control system usually consists of a space directional gyro, a platform laser seeker, and a pneumatic steering gear. However, the above components essentially determine that the designed high-dynamic aircraft cannot resist the destructive effects of high overload on the system. Many components no longer have theoretical working performance under high-dynamic conditions, and traditional guidance and control systems often require The navigation system, guidance system, and control system are designed separately according to the specific model, which not onl...

AI Technical Summary

Problems solved by technology

[0002] The guidance and control system is one of the irreplaceable core components of the high dynamic aircraft, and is the key to determine the performance of the high dynamic aircraft. The traditional guidance and control system usually consists of a space directional gyro, a platform laser seeker, and a pneumatic steering gear. However, the above components essentially determine that the designed high-dynamic aircraft cannot resist the destructive effects of high overload on the system. Many components no longer have theoretical working performance under high-dynamic conditions, and traditional guidance and control systems often require Design the navigation system, guidance system, and control system separately according to the specific model, which not only takes a lot of time and effort, but also has the problem of incoordination and mismatch between subsystems

Especially under the action of high overload, this traditional design scheme makes the transmission command lag between the navigation system, guidance system and control system more serious, resulting in serious consequences

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