The invention relates to the technical field of spaceflight, in particular to a lander which comprises a main body part, a cold air injection assembly and a plurality of injection engines, the cold air injection assembly comprises a cooling high-pressure air source and an annular injector, and the annular injector is arranged at one end, in the first direction, of the main body part; the multiple injection engines are all arranged on the side, where the annular injector is located, of the main body part and evenly distributed in the circumferential direction of the annular injector, and injection openings of the injection engines face the side, where the annular injector is located, of the main body part. The annular ejector is provided with at least one circle of nozzles around the annular ejector, and the cooling high-pressure gas source is communicated with the annular ejector, so that cooling gas can be ejected at a preset speed under the ejection action of the annular ejector to form a cooling gas film wrapping the main body part. According to the lander provided by the invention, the cooling gas film performs heat insulation protection on the main body part. And an outer side heat insulation material of the main body part is reduced, the invalid mass ratio of the lander is reduced, and the coating difficulty of the main body part is reduced.
本申请涉及航天技术领域,尤其是涉及一种着陆器,着陆器包括主体部、冷气喷射组件和多个喷射发动机,冷气喷射组件包括冷却高压气源和环射器,环射器设置于主体部在第一方向上的一端,多个喷射发动机均设置于主体部的环射器所在的一侧,且多个喷射发动机围绕环射器的周向均布,喷射发动机的喷射口朝向环射器在的一侧设置。环射器设置有围绕环射器设置至少一周的喷口,冷却高压气源与环射器连通,以使冷却气体能够在环射器的喷射作用下,达到预定速度喷出形成包裹主体部的冷却气膜。根据本申请提供的着陆器,冷却气膜对主体部进行隔热保护。减少主体部的外侧隔热材料,减小了着陆器的无效质量占比,降低主体部的包覆难度。
Lander
着陆器
2024-01-09
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
Online Contents | 2003
|NTRS | 2015
|NTIS | 1993
|Elsevier | 2002
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