Solid carrier rocket injection correction method

Abstract

The invention discloses a solid carrier rocket injection correction method which comprises the following steps: when a three-stage engine is shut down, acquiring the speed position state quantity of the rocket body; determining a sliding attitude instruction and fourth-stage ignition time according to the speed position state quantity and the orbit parameter information; adjusting the attitude of the rocket according to the sliding attitude instruction in the sliding attitude adjusting section until the rocket is adjusted to the four-stage fixed-axis attitude; when the fourth-stage ignition time is up, sending out a fourth-stage ignition instruction so that the rocket enters a fourth-stage active section; calculating the number of predicted injection orbits in the whole process of the four-stage active section at intervals of delta t4 according to an inner ballistic curve of an engine and engine state parameters; calculating to obtain a compensation value of the four-stage attitude angle instruction by predicting the number of injection orbits and the number of target orbits; and updating the fourth-stage attitude angle instruction according to the compensation value until the fourth-stage engine is used up and shut down. According to the method, the solid rocket engine is accurately shut down, and the injection cost is reduced due to the fact that the thrust terminating device does not need to be arranged.

Description

technical field [0001] The present disclosure generally relates to the technical field of rockets, and in particular relates to a correction method for orbiting a solid launch vehicle. Background technique [0002] The launch vehicle is generally composed of multiple stages. Through the thrust of the booster engines at each stage, it continuously overcomes the gravity of the earth to reach the height and speed required for orbiting, and thus enters the corresponding earth orbit. In this process, the guidance system mainly calculates and obtains the command attitude angle required by the rocket by comparing the current position and speed state of the rocket with the position and speed state required for orbit entry, and the attitude is adjusted by the actuator of the control system. state, send timing commands such as ignition, shutdown, and separation, and guide the rocket step by step to fly according to the command attitude angle to the position and speed state required fo...

AI Technical Summary

Problems solved by technology

[0008] Adding a thrust termination device requires installing a reverse nozzle and pyrotechnics on the top of the engine casing, which will affect the original structure of the casing and reduce the reliability of the product

At the same time, for engine casings such as carbon fiber that meet the known material winding, the installation process is more difficult to realize;

[0009] Adding a liquid orbit control engine requires adding a serie

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