Self-adaptation powered explicit guidance method

Abstract

The invention discloses a self-adaptation powered explicit guidance method which includes the steps of initializing powered explicit guidance, forming a guidance parameter related to mass, thrust and a specific impulse, forming a guidance parameter estimation algorithm based on acceleration measurement, applying the estimated guidance parameter, calculating the speed increment direction, the reference time and the thrust direction change rate, forecasting the state of a terminal, calculating the guidance target deviation and a correction parameter, repeating the steps for each control period till a convergence condition is met and calculation of a guidance command is completed, and under the condition that the convergence condition is not met, enabling the guidance command to inherit a prior value or an original value. According to the self-adaptation powered explicit guidance method, a PEG structure is improved, the adaptability and the robustness of a guidance law to uncertainties such as the mass, the thrust and the specific impulse are improved, meanwhile, the speed and height control accuracy of the powered process of a detector is improved, and the requirement of the detector for high-accuracy control over a terminal target is met.

Description

technical field [0001] The invention relates to an adaptive power descent guidance method, which is mainly applied to deep space landing and ascent detectors, and belongs to the technical field of spacecraft guidance, navigation and control. It can be applied to deep-space celestial body exploration missions such as the moon, Mars, and asteroids, and has extensive application value and market prospects. Background technique [0002] The soft landing of the celestial body and the dynamic guidance method of the ascending probe are important aspects of the GNC (guidance, navigation and control) scheme design of the landing probe. PEG (Powered Explicit Guidance, Powered Explicit Guidance) guidance is a guidance scheme proposed by the United States for the ascent of the space shuttle. Control of high-speed and three-dimensional speed of the guidance track. The article Space Shuttle Ascent Guidance, Navigation, and Control (The Journal of the Astronautical Science, Vol.XXVII, No...

AI Technical Summary

Problems solved by technology

The ascent process of the space shuttle is a process of getting higher and higher from the ground, and its ascent process does not have stricter precision requirements than the landing probe power descent process. Therefore, it does not consider the influence of the existing mass, thrust and specific impulse uncertainties. It can still meet the requirements of the space shuttle's ascent process for speed and altitude control accuracy

[0003] Considering that the power descent process of the landing probe requires higher speed and height control accuracy, and the ascending probe also requires higher and higher terminal control accuracy, it is required that the dynamic guidance method can adapt to the influence of mass, thrust and specific impulse uncertainties, Existing PEG guidance cannot realize these functions

Images