A space vehicle trajectory planning method based on space-ground communication

Abstract

The invention relates to a method for orbit planning of a space vehicle based on space-to-ground communication, comprising the following steps: after confirming the need for ballistic re-planning, start to receive state information of the spacecraft; calculate a new target track on the ground; upload new target track parameters; receive the target on the arrow After the orbit parameters, plan the orbit change strategy; download the planned orbit change strategy, if the ground measurement and control system thinks that the ignition time and guidance law are unreasonable, re-plan and send the uploaded parameters again, until the ground measurement and control system thinks that the ignition time is reasonable, and send Confirm the information; start orbit change and enter the new target orbit. The invention realizes the elimination of the risk brought by non-fatal faults at the basic level, ensures that the payload can still enter the working track, and realizes the selection of the optimal target track under the fault state.

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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