Embedded satellite configuration

Abstract

The invention provides an embedded satellite configuration. The embedded satellite configuration comprises a platform cabin, a loading cabin, a docking locking-unlocking mechanism, a non-contact magnetic suspension direct force control mechanism and a solar cell array. The platform cabin is in a hollow annular structure; the loading cabin is arranged in the platform cabin; the docking locking-unlocking mechanism and the non-contact magnetic suspension direct force control mechanism are arranged between the platform cabin and the loading cabin respectively; the solar cell array is arranged on the side of the platform cabin. Ultrahigh-precision ultrahigh-stability control requirements of satellites are met, quality characteristics and agile mobility performances of the satellites are improved, a loading space environment is improved, and influences of platform disturbance and thermal cycling on satellite loading are reduced. According to a design conception of non-contact split design and centralized control, the embedded satellite configuration has advantages of structural configuration compactness, high control precision, high environmental adaptability, low development risk, short cycle and simplicity and feasibility in integration and final assembly.

Description

technical field [0001] The invention relates to a configuration design method of a built-in "double super" satellite, specifically relates to a satellite with ultra-high pointing accuracy and ultra-high stability, which can be applied to future space science exploration, high-quality high-resolution remote sensing, and deep-distance laser communication , deep space and cosmic exploration and other mission fields. Background technique [0002] An ultra-high pointing accuracy and ultra-high stability satellite under development, the whole star weighs about 2500kg, its detection load weighs 680kg, the detection load envelope is Φ1600mm×3500mm, and the pointing accuracy requirement is 5×10 -4 degree, attitude stability is 5×10 -6 degrees / second. [0003] Most of the existing satellite platform configurations are designed for the fixed connection between the payload and the satellite platform, and the disturbance of the satellite platform is not fully isolated during the design...

AI Technical Summary

Problems solved by technology

[0003] Most of the existing satellite platform configurations are designed for the fixed connection between the payload and the satellite platform, and the disturbance of the satellite platform is not fully isolated during the design. The structure design is mostly installed with an external or fixed mounting surface, and it is difficult to reduce the height and center of mass of the entire satellite. Location

Moreover, the load is exposed to the space environment, requiring special protection and poor adaptability

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