In-orbit identification and correction method of stasis position of one-dimensional drive mechanism of spacecraft panel

Abstract

The invention provides an in-orbit identification method of a stasis position of a one-dimensional drive mechanism of a spacecraft panel. The in-orbit identification method comprises the steps that (1), the actual solar vector Sm of a system is determined by a sun sensor; (2), the theory sun vector Sb of the system is solved by integrating satellite attitude information, orbit information and solar ephemeris model information; and (3), the pitch stasis angle theta of the one-dimensional drive mechanism of the spacecraft panel is determined by Sb and Sm. The invention further relates to a correction method of the stasis position of the one-dimensional drive mechanism of the spacecraft panel, the correction method comprises the steps that S1, the pitch stasis angle is determined by the in-orbit identification method; and S2, a one-dimensional sun pointing guidance law of a satellite is designed, and by correcting the pitch stasis angle theta, the spacecraft panel after a failure can be realigned to the sun by correcting the attitude of the satellite. The in-orbit identification and correction method of the stasis position of the one-dimensional drive mechanism of the spacecraft panelhave the beneficial effects that the measurement is reliable and the safety is high, the cost is saved in the design of panel drive mechanism and whole star system, and in-orbit fault treatment measures are added to guarantee satellite energy.

Description

technical field [0001] This application belongs to the field of aerospace technology, and specifically relates to an on-orbit identification and correction method for the stagnation position of a one-dimensional sailboard drive mechanism of a spacecraft, which can be applied to a spacecraft with a one-dimensional sailboard drive mechanism for position identification and monitoring after its sailboard drive fails. On-orbit emergency treatment, supplementary energy and rescue of satellites. Background technique [0002] Spacecraft solar array drive mechanism (abbreviated as SADA, solar array drive assembly) is an essential and important part of long-life stable satellites. Electrical signals are transmitted into the astral body. Since it cannot be backed up, the solar panel drive mechanism is one of the few single-point sources of failure on the star. Once it fails, it will directly cause the entire star to lose all energy and fail. [0003] The sun sensor is a measurement c...

AI Technical Summary

Problems solved by technology

[0006] In the prior art, it is not proposed that after the failure of the sailboard drive mechanism of the spacecraft, other auxiliary sensors can be used to confirm the current position of the drive mechanism when the telemetry parameters of the rotation mechanism cannot accurately determine the current rotation position of the sailboard. At the same time, the current technology does not provide After detecting that the driving mechanism of the solar panel is not operating normally, how to make the panel go to the sun and ensure the energy of the whole star

[0007] The current technology only improves the reliability of the sailboard drive mechanism, which makes the sailboard drive mechanism expensive and difficult to adapt to the rapid development of commercial aerospace

In addition, if there is a lag in troubleshooting through ground intervention after a failure occurs, failure to deal with it in time will lead to the exhaustion of satellite energy and bring fatal consequences

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