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A configuration of all-electric push satellite platform based on self-tandem launching mode of one rocket and two satellites

A satellite platform and dual-satellite technology, which is applied in the field of satellite platform configuration, can solve the problems of difficulty in realizing the self-tandem launch of one arrow and two satellites, the incompatibility of the working mode of all-electric satellites, and the inability to realize the self-tandem of two satellites. The difficulty of research and development, the effect of saving the cost of launch and launch, and improving the economy and market competitiveness

Active Publication Date: 2021-06-11
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

If the adaptive modification of the propulsion system is carried out for the existing communication satellite platform, it will be difficult to achieve its goal of self-tandem launch of two satellites with one arrow. huge waste of resources
First of all, in order to accommodate a sufficiently large propellant storage tank, the load-bearing cylinder of the traditional satellite platform adopts a combination of a cone section and a straight cylinder. The upper and lower star interfaces are not uniform and cannot realize double-star self-connection.
Secondly, the traditional satellite platform propulsion equipment is arranged in the platform cabin, which is physically isolated from the load cabin and independently dissipates heat. After the electric propulsion high-power orbit change, in order to ensure the temperature of the platform cabin, a large number of compensation heaters need to be turned on additionally, and the load will be turned off during the orbit change. , it is necessary to arrange a large number of heaters in the load compartment to maintain the temperature of the load compartment, resulting in a great waste of energy for the whole star

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  • A configuration of all-electric push satellite platform based on self-tandem launching mode of one rocket and two satellites
  • A configuration of all-electric push satellite platform based on self-tandem launching mode of one rocket and two satellites

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Embodiment Construction

[0025] The present invention will be further described below in conjunction with accompanying drawing.

[0026] For the convenience of description, first establish the body coordinate system (O-XYZ) of the satellite, which is defined as follows:

[0027] Coordinate origin O: the theoretical center of the lower end frame of the central bearing tube 121 and the separation surface of the star and arrow;

[0028] Z axis: along the origin of the coordinates pointing towards the direction of the star;

[0029] Y axis: perpendicular to the direction of the Y plate, with the installation direction of the +Y partition 114 as positive;

[0030] X-axis: right-handed system with Z and Y axes.

[0031] Such as figure 1 , 2 As shown, an all-electric push satellite platform configuration based on the self-tandem launch method of one arrow and two satellites, including: two sub-satellite platforms with the same structure, connected and separated device 61; the sub-satellite platform inclu...

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Abstract

An all-electric push satellite platform configuration based on the self-tandem launch method of one arrow and two satellites: including: two sub-satellite platforms with the same structure, and a connection and separation device (61); the connection and separation device (61) is installed in the central load-bearing cylinder ( 121) one end, passing through the -Z board (122) of the sub-satellite platform is connected with the +Z board (111) of another sub-satellite platform. The invention realizes the self-tandem launch of one arrow and two satellites through structural optimization design and connection and separation device. At the same time, the two-chamber configuration, comprehensive layout of load and platform equipment, and innovative layout of batteries and electric thrusters are adopted to realize on-board resource sharing, simplify the test process, reduce satellite weight and power requirements, and further improve satellite load-carrying capacity .

Description

technical field [0001] The invention relates to a satellite platform configuration. Background technique [0002] The competition of communication satellites in geosynchronous orbit is becoming increasingly fierce, and taking measures to reduce the comprehensive cost of satellite development and launch is an important way to win the market. Using electric propulsion instead of chemical propulsion to complete orbit change and position maintenance tasks is currently the most effective way to significantly reduce the launch weight of high-orbit communication satellites or significantly increase satellite payload carrying capacity and reduce satellite development costs. [0003] Full electric propulsion satellite refers to the use of electric propulsion system to achieve GTO orbit change and GEO on-orbit position maintenance, which can greatly reduce the amount of propellant carried, and reduce the launch weight of satellites by 40% while maintaining the same payload weight, so ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64B64G1/44B64G1/58
CPCB64G1/645B64G1/641B64G1/443B64G1/58B64G1/643
Inventor 王敏韩绍欢胡照彭真王伟李友遐李修峰
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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