Medication maneuvering time selecting method for deep space detector approaching orbit

Abstract

The invention relates to a method for selecting time of deep space probe approach orbit correction maneuver, which belongs to the field of spaceflight and aviation and solves the problems of deep space probe approach orbit correction maneuvering time including low control precision, great calculation amount and poor independency in the prior method for selecting time of deep space probe approach section orbit correction maneuver. The method comprises: 1, determining miss distance rhof passing through the B plane of an object celestial body; 2, determining the acceptable maximum miss distance rhomax of a deep space probe; 3, judging whether the miss distance rhof is more than the acceptable maximum miss distance rhomax, if yes, executing step 4; otherwise, returning to step 1; and 4, executing deep space probe approach section orbit correction maneuver. The method not only can save fuel at a rate of 6m / s, but also can ensure that final passing-through precision is increased by more than 100m as compared with ground station designated maneuver time precision under the same condition and reaches within 250m.

Description

technical field The invention relates to a method for selecting a maneuvering moment for a deep-space probe approaching orbit correction, and belongs to the field of aerospace. Background technique With the increasing number of interplanetary exploration missions, probes flying over, orbiting and softly landing on target celestial bodies have become important tasks and topics for future deep space scientific exploration. In order to successfully complete scientific investigation missions, the orbit correction of the approaching probe must have high control accuracy, so that the probe can cross the B-plane of the target celestial body at the desired position to complete follow-up tasks such as fly-by, fly-by, and soft landing. At the same time, due to the constraints of the launch system's launch capability, the detector is required to consume as little fuel as possible, which puts forward two requirements for the control accuracy and fuel consumption of the orbit correction ...

AI Technical Summary

Problems solved by technology

The purpose of the present invention is to solve the existing method for selecting the maneuvering time of orbit correction in the approaching section of deep space detectors. Because a large number of Monte Carlo simulation methods are used, it not only consumes a lot of manpower and material resources, but also has low control accuracy and poor impact effect; iterative calculation is adopted The method of solving the optimal solution has the problems of large amount of calculation and poor autonomy. A method for selecting the maneuvering time of the deep space probe approaching the orbit correction is provided.

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