公开(公告)号：US20160237952A1

公开(公告)日：2016-08-18

申请号：US15031484

申请日：2014-10-21

Applicant: SNECMA

Inventor： Antoine CARATGE ,  Jean Michel SANNINO ,  Stephanie DREYER ,  Jean-Luc BARTHOULOT

IPC: F02K9/58 ,  F02K9/60 ,  F02K9/42

CPC classification number: F02K9/58 ,  F02K9/425 ,  F02K9/50 ,  F02K9/605 ,  F05D2220/80

Abstract: An autogenous pressurizer device for a main propellant tank, the device includes a pressurizer pipe connected to the main tank to inject propellant into the main tank, a pressurizer valve arranged on the pressurizer pipe, and a heater for heating the propellant upstream from the pressurizer valve. The pressurizer device includes a buffer tank connected to the pressurizer pipe upstream from the pressurizer valve.

Abstract translation: 一种用于主推进剂罐的自生加压装置，该装置包括连接到主罐的加压管，用于将推进剂喷入主罐中，加压阀布置在加压管上，加热器用于加热来自加压阀上游的推进剂 。 加压装置包括连接到加压阀上游的加压管的缓冲罐。

公开(公告)号：US20150308384A1

公开(公告)日：2015-10-29

申请号：US14648411

申请日：2013-11-28

Applicant: SNECMA ,  CENTRE NATIONAL D'ETUDES SPATIALES CNES

Inventor： Jean-Luc BARTHOULOT ,  Jean-Marie CONRARDY ,  Gaelle LE BOUAR

IPC: F02K9/48 ,  F02K9/58 ,  F02K9/44

Abstract: A propulsion assembly for a rocket including a tank for liquid oxygen, an engine having a combustion chamber, and a “heater” heat exchanger suitable for vaporizing liquid oxygen. The assembly has a vaporized oxygen circuit suitable for directing the oxygen vaporized by the heater either to the combustion chamber or to the tank. When the vaporized oxygen is directed to the combustion chamber, the engine advantageously develops low thrust.

Abstract translation: 一种用于包括用于液氧的罐的火箭的推进组件，具有燃烧室的发动机和适于蒸发液氧的“加热器”热交换器。 组件具有适于将由加热器蒸发的氧气引导到燃烧室或罐的蒸发氧气回路。 当蒸发的氧气被引导到燃烧室时，发动机有利地产生低推力。