Method of regulating the pressure within a first rocket engine propellant tank
US-10415507-B2 · Sep 17, 2019 · US
Device for self-pressurization of a tank
US2016222918A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016222918-A1 |
| Application number | US-201415024466-A |
| Country | US |
| Kind code | A1 |
| Filing date | Sep 18, 2014 |
| Priority date | Sep 30, 2013 |
| Publication date | Aug 4, 2016 |
| Grant date | — |
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Abstract
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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 ( 13 a ) connected firstly to the feed pipe ( 11 ) downstream from the isolation valve ( 24 ) and secondly to a neutral fluid feed ( 31 ).
First claim
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1 . A propulsion assembly for a rocket, comprising a tank configured to contain a propellant, an engine having a combustion chamber, a propellant feed pipe extending between the tank and the combustion chamber and having an isolation valve arranged therein, and a heater having an inlet connected to the feed pipe and an outlet connected to the tank, wherein the inlet of the heater comprises an inlet pipe connected firstly to the feed pipe downstream from the isolation valve and secondly to a neutral fluid feed. 2 . A propulsion assembly according to claim 1 , comprising means configured to maintain the neutral fluid in the neutral fluid feed at a pressure that is not less than the critical pressure of the propellant. 3 . A propulsion assembly according to claim 1 , wherein the neutral fluid feed comprises a check valve allowing fluid to flow in the feed only in the direction going towards the heater. 4 . A propulsion assembly according to claim 1 , comprising means for sweeping an injection head of the combustion chamber with the neutral fluid. 5 . A propulsion assembly according to claim 1 , wherein the neutral fluid is helium. 6 . A propulsion assembly according to claim 1 , wherein the propellant is oxygen. 7 . A propulsion assembly according to claim 1 , wherein the heater is a heat exchanger that co-operates with a pipe transporting another propellant. 8 . A propulsion assembly according to claim 1 , wherein the heater is a heat exchanger that co-operates with a pipe transporting combustion gases.
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- What does patent US2016222918A1 cover?
- 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 …
- Who is the assignee on this patent?
- Snecma
- What technology area does this patent fall under?
- Primary CPC classification F02K9/425. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Aug 04 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).