The invention discloses a recoverable rocket and a recovery deceleration method thereof, and relates to the field of aerospace. Comprising a rocket body and two deceleration side wings, the rocket body comprises a structural system, a propelling system, a control system and a foot stool, one end of each deceleration side wing is connected to a shell of the rocket body, and the other end of each deceleration side wing is connected with a deceleration mechanism; the turbine engine mechanism is connected with the rocket body through pipelines installed in the speed reduction side wings, the rocket body supplies energy needed by work to the turbine engine mechanism, the propeller mechanism is arranged below the turbine engine mechanism, and a propeller is connected with a transmission shaft of the turbine engine mechanism. The propeller mechanism is driven by the turbine engine to rotate and interacts with air to generate thrust opposite to the motion direction of the rocket so as to decelerate the rocket in the recovery process. The rocket recycling device has the beneficial effect that the rocket can be effectively recycled.

    本发明公开了一种可回收火箭及其回收减速方法,涉及航空航天领域。包括火箭主体和两只减速侧翼,火箭主体包括结构系统、推进系统、控制系统和脚架,减速侧翼的一端连接在火箭主体的外壳,另一端连接一个减速机构,减速机构包括一个涡轮发动机机构,涡轮发动机机构通过安装在减速侧翼内的管道与火箭主体连接,由火箭主体向涡轮发动机机构供应工作所需的能源,涡轮发动机机构的下方设置有螺旋桨机构,螺旋桨连接着涡轮发动机机构的传动轴,螺旋桨机构在涡轮发动机的带动下转动,与空气的相互作用产生与火箭运动方向相反的推力,为回收过程中的火箭减速。本发明的有益效果在于:能够有效实现火箭的回收再利用。


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    Title :

    Recoverable rocket and recovery deceleration method thereof


    Additional title:

    一种可回收火箭及其回收减速方法


    Contributors:

    Publication date :

    2023-07-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen / B64G Raumfahrt , COSMONAUTICS



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