Method for improving full-dynamic ground simulation authenticity in inertial navigation

Abstract

The invention relates to a method for improving full-dynamic ground simulation authenticity in inertial navigation. The method for improving the full-dynamic ground simulation authenticity in the inertial navigation comprises the steps of sampling an original property signal of a sensor of an inertial navigation accelerometer, and generating a digital signal comprising an original acceleration signal of the accelerometer and a position signal characteristic; and converting the digital signal into an analogue signal through a hardware control card, and sending the control analogue signal to an inertial navigation system in a pulse manner. When a missile is launched, a sent escape signal is manually controlled through hardware collection. A fixed time interval is set by the signal according to a working state of actual inertial navigation; and an order of converting inertial navigation into navigation is sent to the inertial navigation at certain time interval. With the adoption of the method provided by the invention, the inertial navigation system is more similar to an actual flight working state, so that the confidence of a semi-physical simulation test of a missile guidance system can be improved.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation semi-physical simulation test, specifically, it is a method for improving the authenticity of inertial navigation full-dynamic ground simulation, the method of the invention can improve the authenticity of inertial navigation system in semi-physical simulation test, so that The inertial navigation system is closer to the real flight working state, thereby improving the confidence of the hardware-in-the-loop simulation test of the missile guidance system. Background technique [0002] During the missile development process, a large number of semi-physical simulation tests must be carried out to verify the performance of the missile guidance system, so that the missile can implement a real flight test. The inertial navigation system, referred to as the inertial navigation system, is the main component of the missile guidance system. After the missile is launched, the inertial navigation ...

AI Technical Summary

Problems solved by technology

In the ground simulation test, the "missile off-board signal" is sent out under human control, while the "inertial navigation to navigation command" is issued by the carrier aircraft itself according to the "launch command". At this time, the "missile off-board signal" and the "inertial navigation There is a random error in the time interval of the guidance and navigation command (the time of launching the command)". When the error is large, the inertial navigation will enter the navigation working state in advance to perform navigation calculations, and its position, speed and other information and the information of the departure time may occur. Larger changes will cause inaccurate initial navigation calculations of inertial navigation, which will eventually cause certain errors in simulation results