Guidance system reconstruction method for coping with one-time ignition fault

Abstract

The invention relates to a guidance system reconstruction method for coping with a one-time ignition fault. For an upper stage, the working mode of satellite orbit injection is guaranteed through two-time active section orbital transfer; when one-time ignition fails, second-time ignition can be started immediately, it is guaranteed that the upper stage can reach the enough height in a sub-orbit orbital transfer section; a second active section adopts an engine extrusion working mode to push an upper stage / satellite assembly to an orbit injection point; a first active section adopts an iterative guidance method, and the second active section changes the guidance method and aims at various elements, so that the orbit injection precision is ensured. According to the guidance system reconstruction method for coping with the one-time ignition fault, when the one-time ignition fault occurs, the engine extrusion working mode is fully utilized, autonomous online judgment and reconstruction are carried out, it is guaranteed that the satellite orbit injection precision meets the requirement under the fault condition, and the system reliability is improved.

Description

technical field [0001] The invention relates to a guidance system reconfiguration method for dealing with an ignition failure, and belongs to the technical field of guidance and control. Background technique [0002] When the upper stage launches a Low Earth Orbit (LEO) satellite mission, the main engine is generally ignited twice to change the orbit, and the iterative guidance method is used for the two orbit changes. However, since the orbit change thrust of the upper stage is provided by a single main engine, and the ignition of the two active stages of the main engine is a single-point trigger, there is a risk of ignition failure. According to the existing guidance scheme, if the engine fails to ignite once, the upper stage / satellite The assembly will fall into the atmosphere and burn up after a short flight in suborbit. At the same time, because the engine is not ignited but the combustion agent and oxidizer continue to be discharged, the pressure of the engine tank wil...

AI Technical Summary

Problems solved by technology

However, since the orbit change thrust of the upper stage is provided by a single main engine, and the ignition of the two active stages of the main engine is a single-point trigger, there is a risk of ignition failure. According to the existing guidance scheme, if the engine fails to ignite once, the upper stage / satellite The assembly will fall into the atmosphere and burn up after a short flight in suborbit. At the same time, because the engine is not ignited but the combustion agent and oxidizer continue to be discharged, the pressure of the engine tank will rise rapidly, and eventually exceed the threshold and there is a risk of direct explosion

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