Novel commercial remote sensing satellite configuration layout

Abstract

The invention relates to a novel commercial remote sensing satellite configuration layout. The novel commercial remote sensing satellite configuration layout comprises a hollow satellite structure (4) in a regular pentagon stand column manner, a body-mounted solar wing (3) and unfolding solar wings (2,6 and 7); and the satellite structure (4) further comprises a base plate (402), five same side plates (403-407), a camera installation plate (409) and a truss structure (408). According to the novel commercial remote sensing satellite configuration layout, factors such as a main load camera machine connector, the satellite main structure manner, the solar wing installation layout and the electronic equipment installation layout are comprehensively considered, and comprehensive optimization design is carried out, miniaturization, light weight, small rotational inertia and good final assembly operation of a satellite can be achieved on the basis that the effective load and the platform equipment installation layout requirement are met, and the satellite in-orbit application requirement is met.

Description

technical field [0001] The invention relates to a configuration layout of a satellite. Background technique [0002] High-resolution commercial remote sensing satellites are an inevitable trend to promote the development of satellite and application industrialization. Based on the commercial needs of the service market, they provide support for the digitalization of satellite remote sensing and the development of international services. The main payload of commercial remote sensing satellites is a multispectral camera, which has the characteristics of highly integrated platform, small size, and high agile maneuverability, and can realize fast and maneuverable high-resolution imaging tasks. [0003] The task of satellite configuration and layout design is to meet the installation and pointing requirements of payload equipment, meet the pointing and installation requirements of satellite subsystem equipment, and at the same time, the whole star must have good stiffness charact...

AI Technical Summary

Problems solved by technology

This traditional configuration layout method has the following problems: 1) The structural weight accounts for a large proportion of the entire satellite, about 15%; 2) The entire satellite has a large moment of inertia, and does not use the satellite to maneuver quickly in orbit; 3) The equipment installation space is small , the operability of the final assembly is poor; 4) The design, installation, and ground deployment process of the two stacks of deployable solar wings are complicated; 5) The envelope size of the whole star is large, and the space utilization rate in the star is low

Therefore, the traditional configuration and layout methods cannot meet the mission requirements of rapid assembly, light weight, and rapid maneuvering of satellites.

Images