Analytical Method of State Deviation in Ballistic Boosting Section Under Disturbed Gravity

Abstract

The invention provides a method for analyzing the state deviation of the ballistic boosting section under the action of disturbing gravity, specifically taking the ballistic missile as the research object, aiming at the problem of quickly solving the state deviation of the ballistic missile boosting section, the specific method is: first, according to the launching task Design and generate a standard trajectory; secondly, use the state deviation analysis method derived from the perturbation idea to solve the state deviation of each point in the boost section; after that, calculate the apparent acceleration deviation of the corresponding point based on the state deviation of each point in the boost section trajectory, and The deviation is regarded as a high-order item of the disturbance gravity, and the compensation is performed at the same time; finally, the state deviation result is corrected by using the Newton iteration method. This method can realize the rapid calculation of the state deviation along the boosting section of any flight trajectory, and its calculation accuracy can meet the requirements of trajectory calculation.

Description

technical field [0001] The invention relates to the field of aircraft dynamics modeling, in particular to a method for analyzing 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 maneuverability and rapid launch performance before launch and the 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 disturbance gra...

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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

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