Guidance control system for highly dynamic aircraft with strapdown seeker

Abstract

The invention discloses a guide control system of a high dynamic aircraft with a strapdown seeker. The system comprises a processor module used for calculating needed overload of the aircraft, a quasi-satellite guide solution module used for providing the aircraft position and speed information at the present needed by calculating of the needed overload by the processor module during satellite losing and an iterative module connected with the strapdown seeker and capable of directly obtaining a missile sight line angle rate needed by calculating of the needed overload through a missile sight line angle through detection of the strapdown seeker.

Description

technical field [0001] The invention relates to the control field of strapdown guided aircraft, in particular to a guidance control system for a highly dynamic aircraft with a strapdown seeker. Background technique [0002] In the prior art, in order to meet the objective needs of saving the space of the aircraft, increasing the amount of charge, and reducing the weight, the missile-borne platform was canceled, and the strap-down guidance method was used for guidance control. Therefore, this guidance control aircraft needs to calculate the guidance command. However, due to cost constraints and changes in the battlefield environment (temperature, humidity), the scale coefficient of the missile-borne sensor will fluctuate, that is, the angular rate gyro scale coefficient and the detector scale coefficient Changes occur, resulting in a mismatch between the angular rate gyro scale coefficient and the detector scale coefficient, resulting in incomplete decoupling of bullet-to-eye...

AI Technical Summary

Problems solved by technology

[0002] In the prior art, in order to meet the objective needs of saving the space of the aircraft, increasing the amount of charge, and reducing the weight, the missile-borne platform was cancelled, and the strap-down guidance method was used for guidance control. Therefore, this guidance control aircraft needs to calculate the guidance command. However, due to cost constraints and changes in the battlefield environment (temperature, humidity), the scale coefficient of the missile-borne sensor will fluctuate, that is, the angular rate gyro scale coefficient and the detector scale coefficient Changes occur, resulting in a mismatch between the angular rate gyro scale coefficients and the detector scale coefficients, resulting in incomplete decoupling of the line-of-sight information

Moreover, the cost of the angular rate gyro is relatively high. If possible, everyone hopes to remove the high-cost and low-reliability detection components such as the angular rate gyro, simplify the components carried on the aircraft to the greatest extent, and complete the project with a low-cost and high-performance solution. Design and manufacture of aircraft;

[0003] During the entire guidance process of the aircraft, it depends on the position and speed information provided by the satellite. For the high dynamic aircraft, the problem of losing the satellite is more serious, and it is easy to be interfered by various signals and geographical factors. The interference received will be greater, which may cause the satellite receiver on the aircraft to be unable to receive satellite signals. When the satellite is lost, the aircraft will lose control and cause irreparable consequences

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