Parameter simulation method for inertial navigation system of aircraft

Abstract

The invention relates to a parameter simulation method for an inertial navigation system of an aircraft. The method can effectively realize separation of dynamic calculation errors in the process of dynamic simulation of the inertial navigation system, eliminates influence of the dynamic calculation errors in simulation on inertial navigation simulation precision, corrects and compensates the dynamic calculation errors of navigation parameters in the navigation simulation process at a simulation output terminal of the inertial navigation system, improves navigation simulation precision of the inertial navigation system, provides bases for type selection of inertial navigation sensors and has a good engineering application value.

Description

technical field [0001] The invention relates to a parameter simulation method of an aircraft inertial navigation system. Background technique [0002] The inertial navigation system is an autonomous navigation system. Among them, the strapdown inertial navigation system replaces the mechanical platform inertial navigation system with a "mathematical platform", which has the characteristics of simple structure, low cost, small size, and low power consumption. With the continuous development of inertial components and the increasing level of computer technology, the application of strapdown inertial navigation systems is becoming more and more extensive, and the precision requirements for strapdown inertial navigation systems are also getting higher and higher. The error factors affecting the strapdown inertial navigation system mainly come from the error characteristics of the inertial measurement sensor. However, the existing simulation analysis methods for analyzing the inf...

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Problems solved by technology

The error factors affecting the strapdown inertial navigation system mainly come from the error characteristics of the inertial measurement sensor. However, the existing simulation analysis methods for analyzing the influence of the error characteristics of the inertial measurement sensor on the dynamic performance of the inertial system are still very lacking; There is still a lack of effective analysis and verification methods for the impact of the inertial measurement sensor on the dynamic performance of the inertial navigation system under the conditions of the selected index of the inertial measurement sensor. Usually, it is necessary to use the method of flying for verification, which requires a lot of manpower and material resources. And financial resources are large, and the acquisition of flight inertial navigation results will generate large dynamic calculation errors. If the dynamic calculation errors are not effectively separated, the accuracy of the inertial navigation system will be affected. At the same time, it is difficult to simulate the inertial measurement sensor error. Influence of characteristics on dynamic calculation error performance of inertial navigation system

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