Tree-shaped multi-satellite superposition co-position launching method
A co-location and tree-shaped technology, applied in the field of satellite launch, can solve the problems of increased launch costs, difficulty in docking coordination of satellites and rockets, and large occupancy, so as to improve work efficiency and performance of launch vehicles, and simplify the interface and docking process of satellites and rockets.
Inactive Publication Date: 2019-10-25
NAT UNIV OF DEFENSE TECH
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Each satellite is directly electromechanically connected to the rocket, which takes up a lot of resources on the rocket, including mechanical interfaces, electrical interfaces, and fairing space, which puts high demands on the launch vehicle and increases the launch cost and the coordination of the docking of the rocket. difficulty
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[0013] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with specific embodiments of the present invention and corresponding drawings. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts fall within the protection scope of the present invention.
[0014] The technical solutions provided by the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0015] A tree-shaped multi-satellite superposition co-location launching method, the method comprising: dividing a plurality of satellites into n levels, n being a positive integer greater than or ...
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The invention discloses a tree-shaped multi-satellite superposition co-position launching method. The method comprises the following steps that a plurality of satellites are divided into n stages, wherein n is a positive integer larger than or equal to 2, the ith-stage satellite is connected with the (i-1)th-stage satellite, and the first-stage satellite is connected with a carrier rocket; and after the first-stage satellite is launched into an orbit, the carrier rocket provides a separation control signal to the first-stage satellite, and the (i-1)th-stage satellite provides a separation control signal to the ith-stage satellite, wherein i belongs to the set of [ 2, n ]. In the tree-shaped multi-satellite superposition co-position launching method, each stage of satellite serves as a carrier and a signal source of a secondary satellite, and then a tree-shaped multilevel expansion structure is formed in sequence. By means of the topological structure, the multiple satellites with different scales and different functions can be integrated and then are launched in a co-position mode under a relatively simple cascade interface specification, a very simplified satellite-rocket interface and a butt joint process are realized, the working efficiency of a launching field and the efficiency of the carrier rocket are improved.
Description
technical field [0001] The invention relates to the technical field of satellite launching, in particular to a tree-shaped multi-satellite superposition co-location launching method. Background technique [0002] With the development of science and technology, satellites play an important role in production, life and scientific research. Satellites are generally launched into orbit by rockets. When the carrying capacity permits, in order to save launch costs, satellite clusters usually launch multiple satellites with one arrow. At present, the common method of multi-satellite launching in the world is that multiple satellites are connected to the rocket through a multi-satellite adapter or a multi-satellite distributor. Separate control signals. Each satellite is directly electromechanically connected to the rocket, which takes up a lot of resources on the rocket, including mechanical interfaces, electrical interfaces, and fairing space. difficulty. Therefore, it is nec...
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Login to View More IPC IPC(8): B64G1/00
CPCB64G1/002
Inventor 白玉铸庹洲慧赵勇陈小前陈利虎绳涛宋新杨磊
Owner NAT UNIV OF DEFENSE TECH