GB721962A - Improvements in or relating to propellant supply systems for jet reaction rocket motors - Google Patents
Improvements in or relating to propellant supply systems for jet reaction rocket motorsInfo
- Publication number
- GB721962A GB721962A GB295652A GB295652A GB721962A GB 721962 A GB721962 A GB 721962A GB 295652 A GB295652 A GB 295652A GB 295652 A GB295652 A GB 295652A GB 721962 A GB721962 A GB 721962A
- Authority
- GB
- United Kingdom
- Prior art keywords
- oxidant
- valve
- fuel
- supplied
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
721,962. Jet-propulsion plant. MINISTER OF SUPPLY. Feb. 4, 1953 [Feb. 4, 1952], No. 2956/52. Class 110 (3). In a rocket in which two propellants are supplied to the combustion chamber, by pumps driven by one or more turbines, oxidant is supplied initially to a catalyst chamber supplying working fluid to the turbines, so that fuel is supplied under pressure to the combustion chamber through a fuel valve which opens under pressure and oxidant is supplied under pressure to the combustion chamber through a first oxidant valve which is opened by the pressure in the fuel line downstream of the fuel valve so that fuel reaches the combustion chamber before the oxidant and the pressure of the oxidant downstream of its valve is used to open a second oxidant valve so that oxidant is supplied to the catalyst chamber to drive and increase the speed of the turbine or turbines. In the arrangement shown, hydrogen peroxide passes through a non-return valve 13, an idling throttle valve 14, a pipe line 12 and a main throttle valve 15 to a catalyst chamber 16 where it is dissociated into steam and oxygen and then fed to a turbine 18 driving the fuel pump 19 and oxidant pump 20. When the fuel pump reaches a predetermined speed, the solenoid valve 26 is opened and the pressure in the fuel pipe 26 opens the fuel valve 24 and fuel is fed to the combustion chamber 22. Fuel under pressure downstream of the valve 24 acting through the pipe 29 opens the oxidant valve 28 and oxidant is pumped into the chamber 22 at a higher pressure than that of the first-mentioned oxidant. Oxidant from the pipe line 27 downstream of the valve 28 passes through a pipe line 31, a second oxidant valve 33 and pipe line 12 to the generator 16 and also closes the non-return 13 so that the rocket continues to run independently of the first-mentioned oxidant. In a modification, the oxidant supplied to the generator 16 is hydrogen peroxide and the oxidant supplied by the pump 20 is nitric acid. In this arrangement, a further pump for hydrogen peroxide is driven by the turbine 18. This pump is connected to the pipe line 12 through a valve which is opened by the pressure in the pipe line 27.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB295652A GB721962A (en) | 1952-02-04 | 1952-02-04 | Improvements in or relating to propellant supply systems for jet reaction rocket motors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB295652A GB721962A (en) | 1952-02-04 | 1952-02-04 | Improvements in or relating to propellant supply systems for jet reaction rocket motors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB721962A true GB721962A (en) | 1955-01-19 |
Family
ID=9749210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB295652A Expired GB721962A (en) | 1952-02-04 | 1952-02-04 | Improvements in or relating to propellant supply systems for jet reaction rocket motors |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB721962A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1159695B (en) * | 1960-12-02 | 1963-12-19 | United Aircraft Corp | Propellant control system for a liquid rocket |
| CN104792233A (en) * | 2015-04-29 | 2015-07-22 | 北京航天发射技术研究所 | Supercharging device and supercharging method for low-temperature rocket ground redundancy |
| CN113204206A (en) * | 2021-04-25 | 2021-08-03 | 北京航天动力研究所 | PLC-based multi-test-bed extrusion type medium supply control system and method |
-
1952
- 1952-02-04 GB GB295652A patent/GB721962A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1159695B (en) * | 1960-12-02 | 1963-12-19 | United Aircraft Corp | Propellant control system for a liquid rocket |
| CN104792233A (en) * | 2015-04-29 | 2015-07-22 | 北京航天发射技术研究所 | Supercharging device and supercharging method for low-temperature rocket ground redundancy |
| CN113204206A (en) * | 2021-04-25 | 2021-08-03 | 北京航天动力研究所 | PLC-based multi-test-bed extrusion type medium supply control system and method |
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