Aerospace craft orbit planning method based on heaven and earth communication

Abstract

The invention relates to an aerospace craft orbit planning method based on heaven and earth communication. The aerospace craft orbit planning method comprises the following steps that after the condition that a trajectory needs to be planned again is confirmed, state information of an aerospace craft is started to receive; a new target orbit is calculated on the ground; a parameter of the new target orbit is uploaded; after the parameter of the target orbit is received by a rocket, an orbital transfer strategy is planned; the planned orbital transfer strategy is downloaded, if a ground measurement and control system considers the ignition time and the guidance law to be unreasonable, planning is conducted again, the uploaded parameter is sent again till the ground measurement and control system considers the ignition time to be reasonable, and confirmation information is sent; and orbital transfer is started, and the aerospace craft enters the new target orbit. According to the aerospace craft orbit planning method based on heaven and earth communication, the risks caused by basic level non-lethal faults are eliminated, and an effective load can be ensured, and the aerospace craft can further enters a working orbit; and optimal target orbit selecting under a fault state is achieved.

Description

technical field [0001] The invention relates to a space vehicle track planning method based on space-to-ground communication, which belongs to the field of space vehicle guidance and control. Background technique [0002] After the space vehicle is sent into the corresponding orbit (low orbit or suborbit) by the base-level launch vehicle, it completes the follow-up space mission. In the event of a non-fatal failure of the basic stage rocket (such as shutdown due to exhaustion of propellant, thrust drop, etc.), the spacecraft cannot be sent to the predetermined orbit or area, or due to special circumstances, it is necessary to change the target orbit of the spacecraft and change the original flight trajectory. [0003] For the launch vehicle, the ground measurement and control system can only passively receive the telemetry information of the launch vehicle, and cannot intervene in the flight process of the launch vehicle; after the launch vehicle fails, it can only use the f...

AI Technical Summary

Problems solved by technology

[0003] For the launch vehicle, the ground measurement and control system can only passively receive the telemetry information of the launch vehicle, and cannot intervene in the flight process of the launch vehicle; after the launch vehicle fails, it can only use the failure plan compiled before the launch vehicle to carry out protective flight, and cannot Optimal flight under failure conditions; and it is impossible to perform flight missions that temporarily change the target trajectory

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