A solid launch vehicle elliptical transfer orbit iterative guidance control method

Abstract

The invention discloses an iteration guidance control method of a solid carrier rocket elliptical transfer orbit and relates to the technical field of guidance control. The iteration guidance controlmethod comprises the following steps: prefabricating a numerical table of an elliptical reference trajectory; calculating the velocity vector Vic and position vector Rec of the solid carrier rocket ata forecast shutdown moment; according to Rec and the numerical table of the elliptical reference trajectory, calculating the standard velocity vector (refer to the Specification) of the solid carrierrocket under the target point orbital coordinate system; within one calculation period, sequentially carrying out iterative computations on the work remaining time adjustment quantity delta T, the pitch angle adjustment quantity delta phi and the yawing program angle adjustment quantity delta psi until the absolute value of each of the delta T, the the pitch angle adjustment quantity delta phi and delta psi is equal to or less than a preset value; and within the rest each calculation period, continuously carrying out iterative computations on the delta T, delta phi and delta psi, updating T,updating phi-(refer to the Specification) and updating psi-(refer to the Specification) until the rest working time is equal to or less than the preset value, and keeping the current pitch program angle and the yawing program angle unchanged until T becomes zero. The iteration guidance control method is high in practicality and guidance precision and simple in algorithm.

Description

technical field [0001] The invention relates to the technical field of guidance control, in particular to an iterative guidance control method for an elliptical transfer orbit of a solid launch vehicle. Background technique [0002] Iterative guidance is a guidance method applied to solid launch vehicles. As a guidance rate, it runs on the rocket-borne computer and is a real-time algorithm that guides the solid launch vehicle to the target orbit according to the real-time flight status during the flight of the solid launch vehicle. Its guidance function is mainly realized through the program angle and other auxiliary information. [0003] The traditional iterative guidance scheme is aimed at the situation where the thrust of the solid-carrying main engine is not adjustable. Usually, five terminal constraints are considered, including position constraints in two directions and speed constraints in three directions. The main control means are to change the direction of the thr...

AI Technical Summary

Problems solved by technology

However, when the flight time is shortened, the adjustment angle required for the correction of the same position deviation is quite large (20°~40°), and the error of the method formed by the approximate processing increases sharply, which makes the algorithm difficult to converge

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