High-integration three-unit cubic satellite capable of maneuvering orbital transfer

A cube satellite, a highly integrated technology, applied in the direction of artificial satellites, aerospace vehicle guidance devices, etc., can solve the problems that cube satellites cannot achieve large-scale orbital maneuvering, solid rocket thruster thrust eccentric control, etc., to achieve high functional density, The effect of high module integration

Inactive Publication Date: 2021-01-05
NANJING UNIV OF SCI & TECH
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  • Description
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Problems solved by technology

[0004] The purpose of the present invention is to provide a highly integrated three-unit cube satellite that can maneuver and change orbits, which solves

Method used

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  • High-integration three-unit cubic satellite capable of maneuvering orbital transfer
  • High-integration three-unit cubic satellite capable of maneuvering orbital transfer
  • High-integration three-unit cubic satellite capable of maneuvering orbital transfer

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Embodiment Construction

[0024] to combine figure 1 , the three-unit CubeSat UV antenna 10 and the solar cell array 14 are arranged outside the main load-bearing structure 13, and the inside of the main load-bearing structure 13 is arranged in parallel and spaced intervals from the windward side to the leeward side. Centroid adjustment mechanism 12, attitude measurement and control System 11, mass moment actuator 9, star computer 8, UV communication machine 7, air-conditioning micro thruster and pulse modulation module 6, lithium battery pack 5, power control board 4, ignition control board 3, double pulse solid rocket thruster 1. The attitude measurement and control system 11 is an independent system, which is powered by the power supply system; the UV communicator 8, the air-conditioning micro thruster and the modulation module 6, and the ignition control board 3 are controlled by the star computer 7 and powered by the power control board 4 ; Power control board 4 is connected with lithium battery ...

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Abstract

The invention discloses a high-integration three-unit cubic satellite capable of maneuvering orbital transfer. The cubic satellite comprises a satellite basic platform, and the satellite basic platform comprises a main force bearing structure, a solar cell array, a satellite computer, a lithium battery pack, a power supply control panel, a UV antenna, a UV communication machine, an attitude measurement and control system, other related accessories and a propulsion and control system; and the control system comprises a double-pulse solid rocket thruster, an ignition control panel of the double-pulse solid rocket thruster, a cold air micro thruster, a pulse modulation module of the cold air micro thruster, a mass moment executing mechanism and a mass center adjusting mechanism. The three-unit cubic satellite has the thrust vector control capability and is high in integration degree, rapid orbital transfer and attitude orbit control of the cubic satellite can be conducted, large-range orbital maneuver of the satellite is achieved, and the application field of the cubic satellite is greatly expanded.

Description

technical field [0001] The patent of the present invention belongs to the technical field of cube satellites, and is a highly integrated three-unit cube satellite with maneuverable orbit change. Background technique [0002] CubeSat refers to a nanosatellite composed of one or more standard units (called 1U (one unit)) with a size of 10cm×10cm×10cm. Usually the launch runs in a low earth orbit of about 500-1000km. Compared with traditional large satellites, they have the characteristics of small size, light weight, good performance, rapid response, short development cycle, low cost, formation and networking, and reconfigurable functions. With the development of CubeSat technology, it has been able to partially undertake the tasks of large satellites, and its applications in communications, military affairs, remote sensing of the earth, deep space exploration, meteorological services, scientific research and technical experiments have grown rapidly, and are receiving more an...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/26B64G1/28
CPCB64G1/10B64G1/26B64G1/28
Inventor 邓寒玉韩戴如陆正亮
Owner NANJING UNIV OF SCI & TECH
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