Spacecraft observation station guidance calculation method based on combined deviation orbit forecast

Abstract

The invention discloses a spacecraft observation station guidance calculation method based on combined deviation orbit forecast, which specifically comprises the following steps of: 1, performing orbit forecast on an autonomous control spacecraft according to an autonomous control program and an orbit dynamics model, and recording a forecast result as a spacecraft nominal ephemeris, and calculating nominal guide data by using the nominal ephemeris; 2, converting errors of the space environment model and the dynamic model into control deviation, and forecasting and generating a plurality of deviation ephemeris according to the range of the control deviation; 3, calculating deviation guiding data according to the deviation ephemeris, and calculating an angle difference value and a time difference value between the deviation guiding data and a nominal station entering point; and 4, according to the guiding data of the deviation ephemeris, comprehensively calculating guiding information. When the guidance data calculated by the method is captured, waiting is only needed at a theoretical waiting point, the waiting time is a determined interval, the observation station operation is simple, and the tracking condition and the spacecraft state can be judged easily.

Description

technical field [0001] The invention belongs to the technical field of spacecraft station tracking and guidance, and provides a spacecraft station guidance calculation method based on combined deviation orbit prediction. Background technique [0002] Autonomous control of spacecraft refers to the process in which a spacecraft independently completes specified actions or tasks in space by relying on its own sensors and control devices without using control instructions from the ground, including on-orbit autonomous control, spacecraft reentry and return, etc. During or after the autonomous control of the spacecraft, in order to receive its telemetry data and judge the working status, it is sometimes necessary for the ground station to track the spacecraft to obtain relevant data. In order to provide tracking and guidance for the ground station, the ground system needs to simulate the autonomous movement process of the spacecraft, forecast the spacecraft ephemeris, and then co...

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Problems solved by technology

[0003] The purpose of the present invention is to provide a kind of space vehicle survey station guidance calculation method based on combined deviation orbit forecast, which solves some problems of ground station tracking guidance under the condition of spacecraft autonomous control deviation

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