# US 10,371,098 B2 · Device for pressurizing a propellant tank of a rocket engine

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- Number: US 10,371,098 B2
- Document ID: US10371098B2
- Status: Granted
- Kind: B2
- Application number: 14/909,945
- Filed: 2014-07-25
- Published: 2016-06-16
- Granted: 2019-08-06
- Earliest claimed: 2013-08-06
- Assignees: Arianegroup SAS
- Applicants: Snecma
- Inventors: Gérard Roz; David Hayoun; Didier Vuillamy; François Lassoudiere
- Web page: https://patentgrep.com/patent/US10371098B2

## CPC

- F02K 9/44: Feeding propellants
- B64G 1/401: {Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415)}
- B64G 1/402: {Propellant tanks; Feeding propellants}
- F02K 9/425: {Propellants}
- F02K 9/50: using pressurised fluid to pressurise the propellants
- F02K 9/605: {Reservoirs}
- F02K 9/48: driven by a gas turbine fed by propellant combustion gases {or fed by vaporized propellants or other gases}
- F02K 9/56: Control
- F02K 9/64: having cooling arrangements
- F02K 9/95: characterised by starting or ignition means or arrangements (safety devices F02K9/38)
- F02K 9/972: {Fluid cooling arrangements for nozzles (F02K9/64 takes precedence)}
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR

## Abstract

The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.

## Claims

### Claim 1

A pressurization device for pressurizing a propellant tank of a rocket engine, the device comprising a pressurization loop having a primary heater suitable for heating the propellant coming from the tank prior to it being reintroduced into the tank, the primary heater using the heat of combustion from the engine, the device further including a secondary heater having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater to heat the propellant between the propellant leaving the primary heater and being reintroduced into the tank, the propellant being put under pressure in the pressurization loop.

### Claim 2 (depends on 1)

A device as claimed in claim 1, wherein the secondary heater is an electric heater.

### Claim 3 (depends on 1)

A device as claimed in claim 1, wherein the outlet from the secondary heater is suitable for being connected to an ejection pipe.

### Claim 4 (depends on 1)

A device as claimed in claim 1, including a motor-driven pump arranged upstream from the primary heater.

### Claim 5 (depends on 1)

A propulsion assembly including a device as claimed in claim 1 for pressurizing a first tank containing a first propellant, a rocket engine fed by said first propellant and by a second propellant coming from a second tank, and a regenerator circuit for said second propellant, this circuit including a regenerative heat exchanger that co-operates with the engine to heat the second propellant prior to being reintroduced into the second tank, the primary heater co-operating with an outlet pipe of the regenerative heat exchanger.

### Claim 6 (depends on 5)

An assembly as claimed in claim 5, wherein the primary heater comprises at least one tube immersed in the outlet pipe.

### Claim 7 (depends on 5)

An assembly as claimed in claim 5, including an auxiliary circuit for pressurizing the second tank without using the heat of combustion from the engine.