Ballistic deviation analysis and prediction algorithm considering high-order disturbance gravitation influence

Abstract

The invention provides a ballistic deviation analysis and prediction algorithm considering the high-order disturbance gravitation influence. The method comprises the steps of high-order disturbance gravitation vector decomposition and state deviation analysis forecasting model derivation, wherein the decomposition of the disturbance gravitation vector of any order comprises the following processesof firstly obtaining a function expression of a disturbance gravitation vector sigma g at any point P on a two-body trajectory with respect to a true short-point angle, then obtaining an expression of a disturbance gravitation three-component, and finally obtaining the expression; and the state deviation analysis and prediction model derivation specifically comprises the following steps of obtaining an integral solution expression of the trajectory deviation of the free flight section of the missile according to a state space perturbation theory, and substituting and integrating the integralsolution expression to obtain an expression of a trajectory deviation analysis solution of the free section considering the influence of disturbance gravitation. The resolving efficiency of the methodis 10 -3 s magnitude, the calculation error of any downward position is smaller than 5 meters, the calculation result is expressed in an inertial system, and the method can directly participate in missile-borne guidance calculation without extra coordinate conversion.

Description

technical field [0001] The invention relates to the technical field of flight dynamics, in particular to an analytical prediction algorithm of ballistic deviation considering the influence of high-order disturbance gravitational force. Background technique [0002] The free flight segment is the longest flight time in the entire flight segment of the ballistic missile, accounting for more than 90% of the total flight time. Due to the high flight altitude, the ballistic missile is mainly affected by the gravitational force of the center of the earth during the free flight period, and its flight trajectory is approximately a part of the elliptical orbit. , its true trajectory will deviate from the standard elliptical orbit. In order to ensure the hitting accuracy of the ballistic missile, it is necessary to quickly predict the ballistic deviation of the free flight segment under perturbed conditions when the engine is shut down. In fact, orbit prediction of extra-atmospheric...

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Problems solved by technology

The classic theories for this problem mainly include: flat root number method, fg series decomposition method, middle orbit method, non-orthogonal decomposition method and adaptive variable step size numerical integration method, etc., but the flat root number method, fg series decomposition method , middle track method, and non-orthogonal decomposition method are mainly used to deal with the consideration of J 2 、J 3 、J 4 The problem of orbit prediction under the perturbation of low-order spherical harmonics, but the problem of orbit prediction under the high-order Earth's non-spherical gravitational perturbation cannot be solved

Although the adaptive variable step size numerical integration method can calculate the orbit prediction problem under the influence of high-order disturbance gravity, the calculation efficiency decreases rapidly with the increase of the spherical harmonic order, and it cannot be applied to the real-time calculation on the projectile

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