Spacecraft intelligent predictive control entry guidance method

Abstract

The invention discloses a spacecraft intelligent predictive control entry guidance method. Firstly, constraint conditions of spacecraft atmosphere entry are considered, a nonlinear model prediction control method is adopted to design a guidance system, an attenuation memory filter is introduced, a prediction model correction method based on error information estimation is provided, and a variableprediction time domain strategy is combined to enhance robustness of a control system to model errors. Then, the guidance system is used as a guidance template, a sample data set is generated, offlinetraining of a multi-layer neural network is conducted, and the mapping relation between the real-time flight state of the spacecraft and a guidance instruction is approximated. Finally, in the guidance process, the trained neural network is used for replacing the process of solving the complex optimization problem and integral prediction, and the time for online solving the guidance instruction is shortened. Simulation results show that the guidance precision and real-time performance of the guidance method provided by the invention can meet task requirements under the condition that errors such as relatively large model uncertainty exist.

Description

technical field [0001] The invention relates to the technical field of spacecraft guidance, in particular to a spacecraft intelligent predictive control entry guidance method. Background technique [0002] Atmospheric entry guidance is the prerequisite for a spacecraft to successfully land on a planet and conduct various scientific research and experiments. As the planet most similar to the Earth in the solar system, Mars has become an important target object for human deep space exploration. The atmosphere of Mars is very thin, with great uncertainty, and weather such as strong winds and dust often occurs. In the process of spacecraft entry, descent and landing, the atmospheric entry period lasts the longest, the working conditions are the worst, the state of the spacecraft changes rapidly, and the requirements for deceleration performance are also high. As the "Curiosity" Mars rover successfully achieved a soft landing on the surface of Mars by using a closed-loop guidan...

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a spacecraft intelligent predictive control atmosphere entry guidance method, to solve the problem that the high-precision guidance and the fast solution of the command are difficult to meet simultaneously in the current guidance technology

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