Method for attitude control of orbital return and reentry air vehicle over satellite communication

Abstract

The invention provides a method for attitude control of an orbital return and reentry air vehicle over satellite communication, and relates to the field of measurement and control of in-orbit segmentsand relay satellites. The method comprises the following steps that step 1, an earth-fixed coordinate system o1x1y1z1 is established; according to the longitude L, latitude B and height H of the aircraft; the geocentric radius vector corresponding to the air vehicle is represented as red in the earth-fixed coordinate system o1x1y1z1; step 2, the semi-geocentric-angle delta corresponding to the earth area covered by a single relay satellite is calculated; step 3, the geocentric radius vectors corresponding to n relay satellites in the earth-fixed coordinate system o1x1y1z1 are represented as resi; step 4, the relay satellite corresponding to the air vehicle is selected from the n relay satellites; step 5, after the relay satellite is selected, the attitude of the air vehicle is adjusted toachieve that a measurement and control antenna on the air vehicle is aligned with the selected relay satellite and achieve bidirectional communication between the air vehicle and the relay satellite.The method for attitude control of the orbital return and reentry air vehicle over the satellite communication avoids the problems of repeated binding caused by the change of a launch window and thestar loss caused by the deviation of an actual flight trajectory, and ensures the continuous space-based measurement and control capability of the in-orbit segments.

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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