Compact satellite configuration for multi-band detection payloads

Abstract

The present invention provides a compact satellite configuration suitable for multi-band detection load, including satellite body, biplane solar cell components, relay antenna, multi-frequency band detection load antenna component, communication load component, data transmission antenna component, measurement and control antenna As well as the thruster, the left-wing solar cell array and the right-wing solar cell array in the double-wing solar cell assembly are respectively installed on the left side and right side of the satellite body; the relay antenna and the multi-band detection load antenna assembly are respectively installed on the back of the satellite body , the front; the communication load assembly and the thruster are all installed on the satellite body; the left data transmission antenna and the right data transmission antenna in the data transmission antenna assembly are respectively installed on the left side and the right side of the satellite body; the measurement and control antenna is installed on the The front and / or back of the satellite body. The invention has a compact configuration, realizes good manufacturability and high integration of the satellite, and satisfies the requirement of satellite on-orbit application.

Description

technical field [0001] The invention relates to the technical field of overall satellite design, in particular to a compact satellite configuration suitable for multi-band detection loads. Background technique [0002] With the development of earth remote sensing technology in application fields such as meteorology, environment, and detection, satellite missions and functional requirements are increasing, especially for earth remote sensing spectrum monitoring satellites, a single frequency band or type of load can no longer meet user needs, and satellites often need to carry multiple Loads with different frequency bands, systems, types and functions, but limited by the envelope of the launch fairing, mutual compatibility between multi-band loads, large-scale deployment and many moving parts, and large heat flux density of a single load, so the compact structure of the satellite is limited. Type design presents a formidable challenge. Based on this, the present invention pr...

AI Technical Summary

Problems solved by technology

[0003] At present, there are many satellite configurations available for reference at home and abroad, but most of them carry a single type of payload, such as a satellite configuration with an embedded compound eye camera payload disclosed in patent document CN104309824A, including: configuration body, compound eye camera payload , star sensor and solar wing, the configuration body is a regular quadrilateral hexahedron configuration, the configuration body includes a bottom plate, a side plate, a top plate, a layer plate, a tapered bearing barrel and an adapter ring, and the top plate and the bottom plate are respectively connected to the side plates The upper and lower ends of the upper and lower ends, the laminate is set above the bottom plate to connect with the side plate, the conical load-bearing barrel is set between the bottom plate and the laminate, and the conical load-bearing barrel is connected to the laminate, and the adapter ring is set on the other side of the laminate. The side is connected to the conical load-bearing barrel; the solar wing is connected to the side plate; the compound eye camera load part is set on the inner side of the top plate and connected to the adapter ring, and the star sensor is connected to the part of the compound eye camera load on the outer side of the top plate. type of payload

[0004] Another example is the satellite configuration disclosed in the patent document CN105501471A, which is equipped with a large-scale deployable antenna with double reflectors. By ensuring the relative positional relationship between the feed array, the main reflector and the secondary reflector in the orbital flight state, it meets the requirements of the launch vehicle fairing. Envelope and large deployable antenna can be properly deployed constraints, by designing the load bay in the form of a truss structure, but the design still carries a single type of payload

For the compact satellite configuration of the multi-band detection load, no description or report of similar technology has been found, and similar data at home and abroad have not been collected yet

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