Small celestial body high-speed impact terminal guidance method based on speed increment corridor

Abstract

The invention discloses a small celestial body high-speed impact terminal guidance method based on a speed increment corridor, and belongs to the technical field of deep space exploration. The methodaims at the problem of low high-speed impact terminal guidance accuracy of a big-quality impactor, and a terminal guidance process is designed into multiple times of orbit correction maneuvering of aprediction-correction form. The implementation method of the method comprises the following steps that: an on-board computer carries out coarse prediction for one time on the speed increment of a current moment in every one fixed time interval according to a navigation measurement result, and determines the position of the prediction increment in the speed increment corridor; according to a coarseprediction result, an orbit maneuvering starting moment and starting frequency can be adaptively determined; and accurate prediction is carried out on the speed increment of the current moment, orbitmaneuvering is implemented, circular judgment is carried out until impact is finished, and the small celestial body high-speed impact terminal guidance based on the speed increment corridor is realized. The method has the following advantages that the method is high in impact accuracy (1); the method is low in sensitivity of impact accuracy for system noise (2); and the method exhibits universality for a high-speed impact task under different conditions (3).

Description

technical field [0001] The invention relates to a terminal guidance method for asteroid defense, in particular to a terminal guidance method for high-speed impact of a large-mass impactor, belonging to the technical field of deep space exploration. Background technique [0002] Planetary defense technology is an important research direction in the field of deep space exploration. Among the currently proposed planetary defense schemes, the kinetic energy impact scheme is the most direct and effective method that is most in line with the current state of aerospace technology. The key to the success of the kinetic energy impact scheme is to provide high enough impact kinetic energy, so that the impact can change the orbit of the target small celestial body significantly enough to eliminate the risk of impacting the earth. In order to improve the impact kinetic energy of the impactor, it is necessary to increase the mass of the impactor. Due to the insufficient carrying capacity...

AI Technical Summary

Problems solved by technology

Under the current technical conditions, the implementation of this scheme faces the problem of insufficient terminal guidance accuracy. The reasons for this problem are as follows: First, the mass of the kinetic energy impactor carrying the small celestial body is too large, which is responsible for the correction of the terminal guidance trajectory. The thrust of the engine is limited, the orbit control takes a long time, and the control window time at the end of the high-speed impact is short, and the orbit control ability is insufficient

Second, the target small celestial body is small in size, with a diameter of less than 200 meters, and it cannot be successfully hit if the terminal guidance deviates slightly

Third, the deep space environment is complex, the distance is long, the ground measurement and control is difficult, and there are errors in the autonomous navigation on the star, so it is difficult to provide real-time and accurate position and velocity information for the guidance system

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