Small satellite structure suitable for medium and high orbits

Abstract

The invention provides a small satellite structure suitable for medium and high orbits. The small satellite structure comprises a top panel, a front panel, a right panel, a left panel, a rear panel, abottom panel, a laser communication load, a solar wing driving mechanism, a solar wing driving mounting bracket, a nano star sensor and a GNSS antenna mounting bracket. The top panel, the front panel, the right panel, the left panel, the rear panel and the bottom panel define a parallelepiped; the outer side of the front panel is connected with the laser communication load, the inner side of thefront panel is provided with the solar wing driving mounting bracket, and the solar wing driving mechanism is installed on the solar wing driving mounting bracket and penetrates through the right panel and the left panel; The nano star sensor and the GNSS antenna mounting bracket are mounted on the outer side of the top panel; and the rear panel is provided with a propulsion system mounting interface. The laser communication load is installed on the outer side of the satellite body defined by the six panels, heat dissipation of the load can be effectively improved, and a problem that heat dissipation in the satellite body is not facilitated when the load is placed in the satellite is solved.

Description

technical field [0001] The invention relates to the technical field of satellite design, in particular to a small satellite structure suitable for medium and high orbits. Background technique [0002] At present, the structural design of small satellites mostly adopts the design of aluminum-skinned honeycomb sandwich panels, which are used in low orbits. The honeycomb panels are used as the installation panels of each stand-alone unit, and there are partitions inside to increase the structural bearing strength. For this reason, for the small satellite structural panels in the prior art, many embedded beams are designed in the honeycomb panels to form a continuous load-bearing support path, or the star body uses a frame to form a satellite load-bearing frame, and the honeycomb panels are installed on the outside of the frame. The structural design is used as the installation panel of the stand-alone machine, and most of the stand-alone machines and loads are installed inside ...

AI Technical Summary

Problems solved by technology

[0003] The shortcomings of the existing technology are: the frame design of the honeycomb panel or too many beams embedded in the honeycomb panel, the frame structure design adds a frame structure, which is not easy to install, and the installation process is complicated

This patent document improves the rigidity adaptability to different launch vehicles, reduces the stress on the star-rocket connection interface structure, and improves the utilization rate of space for equipment installation in the star; however, in order not to affect the cooling effect of the internal load of the star, a lot of thermal The control board makes the satellite structure complex and the mass increased

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