Follow-up tracking type dynamic and static isolation double supersatellite platform and working mode realization method

Abstract

The invention discloses a follow-up tracking dynamic and static isolation type dual-super satellite platform and a working mode implementation method thereof. The follow-up tracking dynamic and static isolation type dual-super satellite platform is suitable for sensitive load spacecrafts with the ultra-precision and ultra-stability requirement. Dynamic and static isolation is used as the means, a satellite is divided into a load cabin and a service cabin, the load cabin can ensure that the effective load meets the expected ultra-precision and ultra-stability control requirement through a high-performance magnetic levitation flywheel arranged on the load cabin, the service cabin can resist environmental disturbance and track the load cabin in a follow-up mode through an external actuator mounted on the service cabin, and accordingly the two cabins can meet the expected relative pose requirement. The load cabin is connected with the service cabin through a suspension device in a non-contact mode, vibration disturbance of the service cabin can be effectively isolated, and the vibration isolation effect cannot be affected by the sensor performance. The satellite based on the dual-super satellite platform at least has the launching, ultra-precision and ultra-stability, anti-collision or mobility working mode. The dual-super satellite platform can be applied to high resolution sensitivity effective load spacecrafts such as a high resolution remote sensing satellite and a deep space exploration astronomical telescope.

Description

technical field [0001] The invention relates to the field of aerospace technology, and more specifically, relates to a follow-up tracking type dynamic and static isolation satellite platform and a working mode realization method thereof designed for a spacecraft with ultra-precision and ultra-stable requirements. Background technique [0002] The lightweight structure of large spacecraft is flexible, and the problem of dense low-frequency modes is becoming more and more obvious, which greatly restricts the bandwidth design of the control system; the periodic dynamic interference induced by moving parts such as flywheels, gyroscopes, and drive mechanisms is the main cause of load vibration. reason. With the improvement of spacecraft performance requirements, the problems of attitude control and flutter suppression caused by the large flexibility of lightweight structures and vibration interference of moving parts have become more and more prominent, and have become the main r...

AI Technical Summary

Problems solved by technology

The passive vibration isolation system has a simple structure, is stable and reliable, and does not require additional energy and measurement devices, but the low-frequency suppression effect is poor; the active vibration isolation system has better performance in theory, but the control system is complicated, the stability is poor, and it has a water bed effect

At the same time, based on voice coil motor technology, foreign countries have developed a non-contact non-disturbance vibration isolation platform, which can solve the problem of platform vibration interference, but it brings the complexity of the spacecraft attitude control system and makes it difficult for practical application

At present, both the traditional active and passive vibration isolation methods and the recent non-contact non-disturbance vibration isolation method are all based on the idea of ​​active control of the payload by the platform. The former has limited vibration isolation effect, while the latter has complex structure and control.

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