Closed-loop guidance on-line compensation method considering any-order earth non-spherical gravitational perturbation

Abstract

The invention provides a closed-circuit guidance on-line compensation method considering any-order earth non-spherical gravitational perturbation. The method comprises the following steps that 1, a disturbance gravity reconstruction model is off-line constructed along a trajectory; 2, a required speed vR is calculated on the basis of a binary dynamics model in each guidance period of a missile; 3,the shutdown point state predicted on the missile in real time is taken as an input condition, and a trajectory terminal state deviation delta Xc is rapidly calculated by adopting a trajectory deviation analysis and forecast model taking consideration of the earth non-spherical gravitational perturbation; 4, a required speed correction amount delta vR is analyzed and calculated according to the trajectory terminal state deviation delta Xc; and 5, a control quantity U considering the earth non-spherical gravitational perturbation is solved. The brand-new closed-circuit guidance on-line compensation method is provided on the basis of the trajectory deviation analysis and forecast model of a missile trajectory free section, and a method support is provided for further improving the precisionof the strategic missile guidance method in China.

Description

technical field [0001] The invention relates to the technical field of flight dynamics, in particular to an on-line compensation method for closed-circuit guidance considering any order of earth's aspheric gravitational perturbation. Background technique [0002] The performance of the missile guidance system is a key factor affecting the combat effectiveness of strategic missiles. Continuously improving the accuracy of the missile guidance system and adaptability to ballistic deviation is the fundamental way to meet the current needs of rapid mobile launch and high-precision hit of strategic missiles. Closed-circuit guidance is a guidance method that performs real-time calculation according to the function expression of the control functional (such as range deviation, required speed or orbital period, etc.) according to the target data and the real-time motion parameters of the missile. This method has high adaptability and robustness, and has become the first choice of th...

AI Technical Summary

Problems solved by technology

However, the closed-circuit guidance algorithm is usually relatively complicated, so it is difficult to take into account the influence of the earth's high-order non-spherical gravity when calculating the guidance command, and the compensation idea based on the correction of ballistic elements is poor in adapting to large-scale ballistic deviations, and It will increase the launch preparation time of strategic missiles, thereby reducing their pre-launch survivability

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