An integrated ultra-low orbit constellation carrying platform comprises an air inlet cabin section, a middle cabin section and a tail cabin section, an air inlet channel is arranged in the air inlet cabin section, a radio frequency ionization chamber, an electric control solid propeller storage cabin and a satellite storage cabin are arranged in the middle cabin section, and a magnetic spraying accelerating tube, a propellant supplementing mechanism and an electric control solid rocket upper stage are arranged in the tail cabin section. The air inlet channel, the radio frequency ionization chamber and the magnetic spraying accelerating pipe are communicated to form a carrying platform air suction type electric propulsion system. The satellites are connected with the upper stages of the corresponding electronic control solid rockets in the launching channels. In the satellite transportation orbit injection networking stage, the upper stage of the electronic control solid rocket carrying the satellite goes out of a cabin, the upper stage of the electronic control solid rocket adopts an electronic control solid propellant as a propelling working medium and can be repeatedly ignited and started, and after reaching a target orbit, the satellite is separated from the upper stage of the electronic control solid rocket and is automatically unfolded for networking; and the upper stage of the electronic control solid rocket returns to the carrying platform by relying on the remaining fuel for fuel supplementation and prepares to start the next satellite transportation task.

    一体化超低轨星座运载平台,包括进气舱段、中间舱段以及尾部舱段,所述进气舱段内包括进气道,中间舱段内包括射频电离室、电控固体推进器储舱和卫星储舱,尾部舱段内包括磁喷加速管、推进剂补充机构以及电控固体火箭上面级,进气道、射频电离室以及磁喷加速管联通组成运载平台吸气式电推进系统。卫星在发射通道内与相应的电控固体火箭上面级进行连接。卫星运送入轨组网阶段,搭载卫星的电控固体火箭上面级出舱,电控固体火箭上面级采用电控固体推进剂作为推进工质,可重复点火启动,待到达目标轨道后,卫星脱离电控固体火箭上面级并自行展开组网,电控固体火箭上面级则依靠剩余的燃料返回运载平台进行燃料补充,准备开始下一次卫星运送任务。


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    Titel :

    Integrated ultra-low orbit constellation carrying platform


    Weitere Titelangaben:

    一体化超低轨星座运载平台


    Beteiligte:
    HU ZEJUN (Autor:in) / HE ZHICHENG (Autor:in) / WU JIANJUN (Autor:in) / ZHANG YU (Autor:in) / ZHENG PENG (Autor:in) / ZHONG YUXUAN (Autor:in) / PENG QINHUI (Autor:in) / CHE BIXUAN (Autor:in) / LI JIAN (Autor:in) / OUYANG (Autor:in)

    Erscheinungsdatum :

    2023-11-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS