The invention discloses a sub-orbital carrier rocket with an end cover and first-stage integral recovery, which comprises a first-stage rocket body and a rocket sleeve cover, the rocket sleeve cover comprises a cylinder cover, an end cover shell section and the end cover, the cylinder cover is arranged at the front end of the first-stage rocket body, the interior of the cylinder cover is used for containing a suborbital load, and an adaptive load support is arranged at the bottom of the cylinder cover; a sliding rail combination is arranged on the inner wall of the barrel cover, an electric control locking device used for locking the suborbital load is arranged on the adaptive load support, and the sliding rail combination is connected with the suborbital load in a sliding fit mode. The end cover shell section is arranged at the front end of the barrel cover, the end cover is arranged at the front end of the end cover shell section, the end cover is composed of multiple petals hinged to the end cover shell section, the multiple petals of the end cover are in a hemisphere shape after being folded, and opening and closing of the end cover are controlled through the end cover actuator; a reverse thrust rocket is further arranged at the front end of the inner wall of the end cover shell section; the invention discloses a sub-orbital carrier rocket with an end cover and first-stage integral recovery, which can be integrally recovered by 100%, can be repeatedly used after detection and evaluation, and is higher in reuse value.

    本发明公开了一种端罩与一级整体回收的亚轨道运载火箭,包括一级箭体和火箭套罩,火箭套罩包括筒罩、端罩壳段和端罩,筒罩设置于一级箭体的前端,筒罩内用于放置亚轨道载荷,筒罩的底部设置适配载荷支座,筒罩的内壁上设置滑轨组合,适配载荷支座上设置用于锁定亚轨道载荷的电控锁紧装置,滑轨组合与亚轨道载荷滑动配合连接;端罩壳段设置于筒罩的前端,端罩设置于端罩壳段的前端,端罩由与端罩壳段铰接的多瓣组成,多瓣端罩合拢后为半球状,通过端罩作动器控制端罩的开合;端罩壳段的内壁前端还设置有反推火箭;本发明公开了一种端罩与一级整体回收的亚轨道运载火箭,能够100%整体回收,检测评定后可重复使用,复用价值更高。


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    Titel :

    Sub-orbital carrier rocket with end cover and first-stage integral recovery


    Weitere Titelangaben:

    一种端罩与一级整体回收的亚轨道运载火箭


    Beteiligte:
    SUI GUOFA (Autor:in)

    Erscheinungsdatum :

    2021-06-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS




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