公开(公告)号：US20160341362A1

公开(公告)日：2016-11-24

申请号：US15111989

申请日：2014-12-31

Applicant: SNECMA

Inventor： Didier VUILLAMY ,  Nicolas RAVIER ,  David HAYOUN

IPC: F17C13/00

CPC classification number: F17C13/001 ,  F17C13/088 ,  F17C2201/0104 ,  F17C2201/032 ,  F17C2201/054 ,  F17C2205/0115 ,  F17C2205/0126 ,  F17C2205/0176 ,  F17C2205/018 ,  F17C2221/012 ,  F17C2221/08 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2227/0341 ,  F17C2227/0386 ,  F17C2260/031 ,  F17C2260/032 ,  F17C2270/0197 ,  Y02E60/321

Abstract: An assembly including a cryogenic fluid tank for a space vehicle and a thermal protection system for a cryogenic fluid tank of the space vehicle, the system including: a shell adapted to surround the cryogenic fluid tank, the shell being dimensioned to define an inside space between the shell and the tank; and an injector for injecting a cooling fluid spray into the inside space; the cooling fluid being injected into the inside space in the liquid state at a temperature that is adapted to ensure that the cooling fluid picks up the heat flux reaching the cryogenic fluid tank, thereby causing the cooling fluid to vaporize, the shell having a plurality of orifices adapted to allow the cooling fluid in gaseous form to leave inside space through the shell.

Abstract translation: 一种组件，包括用于空间飞行器的低温流体箱和用于空间载体的低温流体箱的热保护系统，所述系统包括：适于围绕低温流体箱的壳体，壳体的尺寸被设计成在 壳和油箱; 以及用于将冷却流体喷射注入到所述内部空间中的喷射器; 冷却流体以适于确保冷却流体拾取到达低温流体箱的热通量从而导致冷却流体蒸发的温度而以液态注入到内部空间中，壳体具有多个 适于允许气体形式的冷却流体通过壳体离开内部空间的孔。

公开(公告)号：US20160222918A1

公开(公告)日：2016-08-04

申请号：US15024466

申请日：2014-09-18

Applicant: SNECMA

Inventor： Gérard ROZ ,  David HAYOUN ,  Nicolas RAVIER

IPC: F02K9/42 ,  F02K9/44

CPC classification number: F02K9/425 ,  F02K9/44 ,  F02K9/50 ,  F02K9/94

Abstract: A propulsion assembly (1, 201) for a rocket, comprising a tank (2) configured to contain a propellant, an engine having a combustion chamber (9), a propellant feed pipe (11) extending between the tank (2) and the combustion chamber (9) and having an isolation valve (24) arranged therein, and a heater (15) having an inlet connected to the feed pipe (11) and an outlet connected to the tank (2). The inlet of the heater comprises an inlet pipe (13a) connected firstly to the feed pipe (11) downstream from the isolation valve (24) and secondly to a neutral fluid feed (31).

Abstract translation: 一种用于火箭的推进组件（1,201），包括构造成容纳推进剂的罐（2），具有燃烧室（9）的发动机，在所述罐（2）和所述燃料室 燃烧室（9）并且具有布置在其中的隔离阀（24），以及具有连接到进料管（11）的入口和连接到罐（2）的出口的加热器（15）。 加热器的入口包括入口管（13a），其首先连接到隔离阀（24）下游的进料管（11），其次连接到中性流体进料（31）。

公开(公告)号：US20160177874A1

公开(公告)日：2016-06-23

申请号：US14909894

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard ROZ ,  Lauren NGUYEN DUC ,  Stéphanie DREYER ,  Nicolas RAVIER

IPC: F02K9/50 ,  F02K9/94

Abstract: The device comprises two heat exchangers (74, 90) suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (16, 18). The heat exchangers co-operate respectively with first and second gas generators (60, 84) suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator (84) being suitable for being fed at least in part by the exhaust from the first gas generator (60).

Abstract translation: 该装置包括两个热交换器（74,90），它们分别适于在将第一和第二推进剂以气态重新引入其储罐（16,18）之前蒸发。 所述热交换器分别与适于供给燃料混合物的第一和第二气体发生器（60,84）配合以产生燃烧，所述第二气体发生器（84）适于至少部分地由 来自第一气体发生器（60）的排气。