Trajectory boosting segment state deviation parsing and calculating method under action of disturbance gravitation

Abstract

The invention provides a trajectory boosting segment state deviation parsing and calculating method under the action of disturbance gravitation. In particular, a ballistic missile serves as a research object, and the problem of rapidly working out the ballistic missile boosting segment state deviation is solved. The method includes the specific steps that firstly, a standard trajectory is designed and generated according to a launch mission; secondly, the state deviation of each point of the boosting segment is worked out through a state deviation parsing method induced by the perturbation thought; then, the apparent acceleration deviation of the corresponding point is calculated based on the state deviation of each point of the boosting trajectory, the deviation is regarded as a high-order item of disturbance gravitation, and meanwhile compensation is conducted; finally, the state deviation result is amended through a Newton iteration method. By means of the method, fast calculation of the state deviation of the boosting segment of any flight trajectory can be achieved, the calculation accuracy can meet the requirement for trajectory calculation, the calculation method is far superior to that of an existing method, and a foundation is laid for achieving fast mobile lunching of the trajectory.

Description

technical field [0001] The invention relates to the field of aircraft dynamics modeling, in particular to a method for analyzing and calculating the state deviation of the ballistic boosting section under the action of disturbance gravity. Background technique [0002] It is an inevitable trend in the development of my country's new generation of ballistic missiles to continuously improve the performance of pre-launch maneuvering and rapid launch and hit accuracy. At present, the main factors restricting the hit accuracy of my country's ballistic missiles are the error of the guidance tool and the error of the guidance method. With the improvement of the hardware level of the inertial measurement system, part of the error of the guidance tool can be effectively corrected, so that the error of the guidance tool of the ballistic missile is gradually reduced. At the same time, the influence of the error of the guidance method is becoming more and more prominent, and the disturb...

AI Technical Summary

Problems solved by technology

[0003] At present, scholars in the field of missile flight mechanics have also done in-depth research on the error propagation model of missiles in the atmosphere, but they mainly focus on the modeling and analysis of guidance tool errors, and the impact of model errors such as gravity models and atmospheric models on missile state deviations. There are very few studies, and the ballistic difference method is usually used to analyze the influence characteristics of the disturbance gravity on the state deviation of the shutdown point in the boost phase

Although the ballistic difference method can accurately obtain the state deviation of the shutdown point of the boost stage under the action of disturbance gravity, this method is based on the ballistic integral, which takes a long time to calculate and requires a large amount of storage, which is not conducive to the rapid launch of missiles under the new situation. sexual demands

[0004] Therefore, it is urgent to establish a method for calculating the state deviation of the boost phase of ballistic missiles for fast maneuvering launch applications. The difficulties in this problem are as follows: First, the complex nonlinear dynamic deviation equation of the missile can be reasonably simplified under the premise of ensuring the accuracy of the solution In order to derive the form of a complete analytical solution expression; secondly, it is necessary to consider the influence of the coupling characteristics between the disturbance gravitation and the apparent acceleration on the state deviation of the boost phase. The apparent acceleration changes, therefore, the state deviation of the missile boost phase caused by the apparent acceleration deviation must be corrected

Images