Agile satellite configuration

Abstract

The invention provides an agile satellite configuration in the field of spacecraft. The agile satellite configuration comprises a propulsion cabin, a service cabin and a load cabin; the propulsion cabin comprises a first force bearing cylinder and a first supporting plate, wherein the first supporting plate is parallel to the axis direction of the force bearing cylinder, the first supporting plateis connected to the inner wall of the force bearing cylinder, the force bearing cylinder comprises a force bearing cylinder A and a force bearing cylinder B, the force bearing cylinder A is columnar,the force bearing cylinder B is conical, and a partition plate is connected to the junction of the force bearing cylinder A and the force bearing cylinder B; the service cabin comprises a second force bearing cylinder, a second supporting plate and a second bottom plate, wherein the second bearing cylinder is connected to the second bottom plate, the second supporting plate is connected to the inner wall of the second force bearing cylinder, and the second bottom plate is connected to the end, away from the partition plate, of the bearing cylinder A; and the load cabin comprises a bottom plate, a top plate and a supporting assembly connected between the bottom plate and the top plate. According to the agile satellite configuration, the propellant carrying capacity is large, the layout iscompact, the inertia is small, the orbit maneuvering capability is high, the pointing agile stability is high, and the bearing performance is excellent.

Description

technical field [0001] The invention relates to the field of spacecraft, in particular to an agile satellite configuration. Background technique [0002] At present, the typical satellite platforms in my country mostly adopt a cuboid configuration. The central load-bearing cylinder is designed inside the star as the main load-bearing component, and it is combined with honeycomb panels such as laminates, partitions, and side panels to form a box-type structure. Arrange stand-alone units on each structural board in the box, and design an expanded solar cell array and antenna outside the box. [0003] Agile satellites need to have strong orbital maneuvering and pointing maneuvering capabilities. For agile satellites, the traditional configuration has some disadvantages: (1) Since orbital maneuvering needs to consume a large amount of propellant, the propulsion system is generally equipped with multiple large-capacity storage tanks. The satellite platform is required to provide...

AI Technical Summary

Problems solved by technology

[0006] The invention utilizes an external force cylinder, an eight-link pointing mechanism, and a body-mounted solar cell array to form a satellite configuration, which effectively solves the problems of large propellant carrying capacity, compact layout, small inertia, quick pointing maneuvering, and excellent load-carrying performance. Meets the high mobility needs of agile satellites

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