Multiple-constraint multi-spacecraft flight interval indicating and collision avoidance method

Abstract

A multiple-constraint multi-spacecraft flight interval indicating and collision avoidance method includes the following steps: (1) confirming magnitude of attitude control average force according to telemeasuring data value of propellant consumed by attitude control of launched spacecrafts on an orbit under the cruising attitude, (2) conducting high-accuracy orbit prediction according to initial ephemeris information of each spacecraft and the attitude control average force confirmed in the step one, calculating ephemeris of each spacecraft in an inertial frame at any time and relative distance between each spacecraft at any time, and confirming the minimum relative distance between the spacecrafts, (3) changing the direction of the attitude control average force, repeating the step one and the step two, calculating the minimum value of the minimum relative distance between each spacecraft, namely, the direction of the attitude control average force corresponding to the minimum value is the worst situation, (4) comparing the minimum value confirmed in the step three with the minimum safe distance, when the minimum value is greater than the minimum safe distance, the spacecrafts has no risk of collision, otherwise, within a first circle observation and controlling track segmental arc, one spacecraft which is selected conducts orbital maneuver, and thereby the distance between the spacecrafts is widened and the collision risk of the spacecrafts is avoided.

Description

technical field [0001] The invention relates to multi-constraint multi-spacecraft flight distance prediction and collision avoidance measures. Background technique [0002] For medium and high-orbit spacecraft launched with one rocket and multiple satellites, the launch vehicle is often required to send multiple spacecraft into the same orbital plane. Due to the limitation of measurement and control conditions, multiple spacecraft separated from the launch vehicle need to use a ground measurement and control antenna to complete the measurement and control task at the same time, which requires that the angles of the spacecraft to the ground are all smaller than the beam coverage of the ground measurement and control antenna. The separation time of each spacecraft and the launch vehicle should be limited within a certain range, which directly leads to a small flight distance between the spacecraft and the separated objects. During the flight, due to various external disturbanc...

AI Technical Summary

Problems solved by technology

[0003] my country’s medium and high-orbit spacecraft need to complete operations such as solar panel deployment as soon as possible after separation from the launch vehicle. This is usually completed within the first circle after separation. Many measurement and control operations

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