RU2012125857A - ROCKET ENGINE STAROVEROVA -9 (OPTIONS) - Google Patents
ROCKET ENGINE STAROVEROVA -9 (OPTIONS) Download PDFInfo
- Publication number
- RU2012125857A RU2012125857A RU2012125857/06A RU2012125857A RU2012125857A RU 2012125857 A RU2012125857 A RU 2012125857A RU 2012125857/06 A RU2012125857/06 A RU 2012125857/06A RU 2012125857 A RU2012125857 A RU 2012125857A RU 2012125857 A RU2012125857 A RU 2012125857A
- Authority
- RU
- Russia
- Prior art keywords
- combustion chamber
- hydrazine
- engine
- fed
- engine according
- Prior art date
Links
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 claims abstract 16
- 238000002485 combustion reaction Methods 0.000 claims abstract 16
- UORVGPXVDQYIDP-UHFFFAOYSA-N borane Chemical compound B UORVGPXVDQYIDP-UHFFFAOYSA-N 0.000 claims abstract 8
- 229910000085 borane Inorganic materials 0.000 claims abstract 4
- 239000007788 liquid Substances 0.000 claims abstract 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract 4
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims abstract 4
- 239000002760 rocket fuel Substances 0.000 claims abstract 4
- 239000007787 solid Substances 0.000 claims abstract 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract 2
- 239000003245 coal Substances 0.000 claims abstract 2
- 239000000839 emulsion Substances 0.000 claims abstract 2
- 229910002804 graphite Inorganic materials 0.000 claims abstract 2
- 239000010439 graphite Substances 0.000 claims abstract 2
- 239000000203 mixture Substances 0.000 claims abstract 2
- 239000004449 solid propellant Substances 0.000 claims abstract 2
- 239000004071 soot Substances 0.000 claims abstract 2
- 239000000126 substance Substances 0.000 claims abstract 2
Landscapes
- Testing Of Engines (AREA)
Abstract
1. Ракетный двигатель, содержащий камеру сгорания и отличающийся тем, что в камеру сгорания под давлением подается смесь борана и гидразина, или раствор или эмульсия борана в жидком гидразине.2. Двигатель по п.1, отличающийся тем, что в камеру сгорания подается 0,0001-1% от массы реагирующих веществ мелкодисперсного угля и/или сажи и/или графита и/или метана.3. Двигатель по п.1, отличающийся тем, что в камеру сгорания подается диборана 46,33+-10%, и гидразина 53,67+-10%.4. Двигатель по п.1, отличающийся тем, что в камеру сгорания направлена горелка или пиротехническая шашка, установленная на пусковой установке.5. Двигатель по п.1, отличающийся тем, что в центре и/или по краям камеры сгорания установлена шашка твердого ракетного топлива.6. Ракетный двигатель, содержащий камеру сгорания или корпус с соплом, работающий на жидком или твердом ракетном топливе и отличающийся тем, что в камеру сгорания или в корпус твердотопливного ракетного двигателя дополнительно подается выхлоп двигателя, работающего на диборане или тетраборане и гидразине.1. A rocket engine containing a combustion chamber and characterized in that a mixture of borane and hydrazine, or a solution or emulsion of borane in liquid hydrazine, is fed into the combustion chamber under pressure. The engine according to claim 1, characterized in that 0.0001-1% by weight of the reacting substances of finely divided coal and / or soot and / or graphite and / or methane are fed into the combustion chamber. The engine according to claim 1, characterized in that diborane 46.33 + -10% and hydrazine 53.67 + -10% are fed into the combustion chamber. The engine according to claim 1, characterized in that a burner or pyrotechnic checker mounted on the launcher is directed into the combustion chamber. The engine according to claim 1, characterized in that a checker of solid rocket fuel is installed in the center and / or along the edges of the combustion chamber. A rocket engine containing a combustion chamber or a housing with a nozzle operating on liquid or solid rocket fuel and characterized in that the exhaust chamber of an engine operating on diborane or tetraborane and hydrazine is additionally fed into the combustion chamber or into the housing of a solid propellant rocket engine.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012125857/06A RU2570910C2 (en) | 2012-06-20 | 2012-06-20 | Staroverv's rocket engine-9 (versions) |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012125857/06A RU2570910C2 (en) | 2012-06-20 | 2012-06-20 | Staroverv's rocket engine-9 (versions) |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2012125857A true RU2012125857A (en) | 2013-12-27 |
| RU2570910C2 RU2570910C2 (en) | 2015-12-20 |
Family
ID=49785920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2012125857/06A RU2570910C2 (en) | 2012-06-20 | 2012-06-20 | Staroverv's rocket engine-9 (versions) |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2570910C2 (en) |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2328519C2 (en) * | 1994-05-31 | 2008-07-10 | Уильям К. Орр | Enhanced combustion at vapour phase |
| RU2182163C2 (en) * | 1995-06-07 | 2002-05-10 | Уильям К. Орр | Fuel composition |
-
2012
- 2012-06-20 RU RU2012125857/06A patent/RU2570910C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2570910C2 (en) | 2015-12-20 |
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