Attitude control method for satellite-to-satellite communication of orbit return re-entry vehicle

Abstract

A method for controlling the attitude of an orbiting return and reentry aircraft to satellite communication, involving the field of on-orbit and relay satellite measurement and control; including the following steps: Step 1, establishing a fixed coordinate system connected to the earth o 1 x 1 the y 1 z 1 ;According to the longitude L, latitude B and height H of the aircraft; put the corresponding geocentric vector of the aircraft in the earth fixed coordinate system o 1 x 1 the y 1 z 1 expressed as r ed ; Step 2, calculating the semi-centered angle δ corresponding to the earth area covered by a single relay satellite; Step 3, placing the earth-centered vectors corresponding to n relay satellites in the earth's fixed coordinate system o 1 x 1 the y 1 z 1 expressed as r esi Step 4, select the relay satellite corresponding to the aircraft from n relay satellites; Step 5, after selecting the relay satellite, adjust the attitude of the aircraft, so that the measurement and control antenna on the aircraft is aligned with the selected relay satellite; Following the two-way communication of satellites; the present invention avoids the repeated binding caused by the change of the launch window and the problem of lost satellites caused by the deviation of the actual flight trajectory, and ensures the continuous space-based measurement and control capability in the orbit segment.

Description

technical field [0001] The invention relates to the field of on-orbit and relay satellite measurement and control, in particular to a satellite-to-satellite communication attitude control method for an orbit return reentry aircraft. Background technique [0002] Orbital re-entry vehicles include various types such as satellites, spacecraft, space shuttles, and intercontinental missiles. Typical ballistics are generally divided into three stages: active section, in-orbit section, and re-entry section. The active section and the re-entry section are generally in China. In flight area flight, the measurement and control tasks are guaranteed by the ground-based measurement and control system. Due to the needs of the flight mission, the on-orbit segment needs to fly around the earth several times. Therefore, the development of the ground-based measurement and control system can no longer meet the needs of the on-orbit segment measurement and control tasks, mainly in the following ...

AI Technical Summary

Problems solved by technology

Due to the small number of overseas measurement and control stations and ocean-going survey ships in my country, it is difficult to meet the demand for high coverage of measurement and control arcs

[0004] 2. The real-time performance of load data transmission is not high. The load data of the orbital section can only be received by the domestic ground-based measurement and control station, and the timeliness of the data will be greatly reduced. In some cases, the data may be outdated

[0005] 3. It is difficult to realize the emergency measurement and control of the aircraft

[0007] Regarding the way of staring at the star, the traditional method is to generate time-varying attitude commands and bind them in the aircraft based on the launch window and ballistic information, but this method has a great influence on the launch window time and ballistic deviation, especially when the launch window changes Each time the binding information is updated accordingly, resulting in a more cumbersome launch process

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