Full-electric-push satellite platform configuration based on one-rocket two-satellite self-series-connection launching mode

Abstract

The invention disclose a full-electric-push satellite platform configuration based on a one-rocket two-satellite self-series-connection launching mode. The full-electric-push satellite platform configuration comprises two sub-satellite platforms with the same structure and a connecting and separating device (61), the connecting and separating device (61) is installed at one end of a center force bearing cylinder (121) and penetrates through a -Z plate (122) of one sub-satellite platform to be connected to a +Z plate (111) of the other sub-satellite platform. According to the full-electric-pushsatellite platform configuration, through the structure optimization design and the connecting and separating device, one-rocket two-satellite self-series-connection launching is realized; meanwhile,the two-cabin configuration, the load and platform equipment comprehensive layout and the storage battery and electric thruster innovative layout are adopted, so that on-satellite resource sharing isrealized, the testing process is simplified, the satellite weight and power requirements are reduced, and the satellite load bearing carrying capability is further improved.

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 ...

AI Technical Summary

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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