RU2010126470A - LOW-THROUGH LIQUID ROCKET ENGINE CAMERA - Google Patents
LOW-THROUGH LIQUID ROCKET ENGINE CAMERA Download PDFInfo
- Publication number
- RU2010126470A RU2010126470A RU2010126470/06A RU2010126470A RU2010126470A RU 2010126470 A RU2010126470 A RU 2010126470A RU 2010126470/06 A RU2010126470/06 A RU 2010126470/06A RU 2010126470 A RU2010126470 A RU 2010126470A RU 2010126470 A RU2010126470 A RU 2010126470A
- Authority
- RU
- Russia
- Prior art keywords
- insert
- chamber
- mixing head
- gap
- camera
- Prior art date
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- Combustion Methods Of Internal-Combustion Engines (AREA)
- Studio Devices (AREA)
Abstract
1. Камера жидкостного ракетного двигателя малой тяги, состоящая из смесительной головки с форсунками, корпуса камеры с докритической и сверхзвуковой частями сопла, с концентрично и с зазором установленной внутри него вставки с образованием полости зазора, сообщающейся с полостью камеры, отличающаяся тем, что вставка выполнена в виде тонкостенной оболочки из жаростойкого материала, например иридия, и плотно закреплена в месте соединения смесительной головки и корпуса камеры. ! 2. Камера по п.1, отличающаяся тем, что вставка заканчивается вблизи критической части сопла и повторяет ее контур. ! 3. Камера по п.1 или 2, отличающаяся тем, что смесительная головка выполнена с двумя струйными форсунками, оси которых пересекаются. ! 4. Камера по п.1, отличающаяся тем, что зазор между вставкой и корпусом камеры имеет величину одного порядка с толщиной оболочки. 1. The chamber of a liquid propulsion thruster, consisting of a mixing head with nozzles, a chamber body with subcritical and supersonic parts of the nozzle, with an insert concentrically and with a gap installed inside it with the formation of a gap cavity communicating with the chamber cavity, characterized in that the insert is made in the form of a thin-walled shell made of heat-resistant material, such as iridium, and is tightly fixed at the junction of the mixing head and the camera body. ! 2. The camera according to claim 1, characterized in that the insert ends near the critical part of the nozzle and repeats its contour. ! 3. The chamber according to claim 1 or 2, characterized in that the mixing head is made with two jet nozzles, the axes of which intersect. ! 4. The camera according to claim 1, characterized in that the gap between the insert and the camera body is of the same order of magnitude as the shell thickness.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010126470/06A RU2465482C2 (en) | 2010-06-28 | 2010-06-28 | Low-thrust liquid-propellant engine chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010126470/06A RU2465482C2 (en) | 2010-06-28 | 2010-06-28 | Low-thrust liquid-propellant engine chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2010126470A true RU2010126470A (en) | 2012-01-10 |
| RU2465482C2 RU2465482C2 (en) | 2012-10-27 |
Family
ID=45783294
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2010126470/06A RU2465482C2 (en) | 2010-06-28 | 2010-06-28 | Low-thrust liquid-propellant engine chamber |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2465482C2 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2581756C2 (en) * | 2013-12-17 | 2016-04-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт машиностроения" (ФГУП "НИИМаш") | Low-thrust liquid-propellant engine chamber |
| RU2704518C1 (en) * | 2018-07-31 | 2019-10-29 | Акционерное общество "Государственный космический научно-производственный центр имени М.В. Хруничева" | Low-thrust liquid-propellant engine chamber |
| RU2727736C1 (en) * | 2019-04-18 | 2020-07-23 | Акционерное общество "НАУЧНО-ИССЛЕДОВАТЕЛЬСКИЙ ИНСТИТУТ МАШИНОСТРОЕНИЯ" (АО "НИИМаш") | Low-thrust liquid-propellant engine chamber |
| RU2726862C1 (en) * | 2019-04-18 | 2020-07-16 | Акционерное общество "НАУЧНО-ИССЛЕДОВАТЕЛЬСКИЙ ИНСТИТУТ МАШИНОСТРОЕНИЯ" (АО "НИИМаш") | Low-thrust liquid-propellant engine chamber |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3353359A (en) * | 1966-01-26 | 1967-11-21 | James E Webb | Multislot film cooled pyrolytic graphite rocket nozzle |
| RU2100636C1 (en) * | 1993-03-01 | 1997-12-27 | Научно-исследовательский институт машиностроения Министерства промышленности России | Liquid-propellant rocket engine chamber |
| RU2219363C2 (en) * | 1999-03-22 | 2003-12-20 | Государственное предприятие Научно-исследовательский институт машиностроения | Chamber of liquid propellant thruster |
| FR2836699B1 (en) * | 2002-03-04 | 2005-02-11 | Eads Launch Vehicles | ENGINE OF ROCKET |
| DE102005036137A1 (en) * | 2005-07-26 | 2007-02-01 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Combustion chamber and method for producing a combustion chamber |
-
2010
- 2010-06-28 RU RU2010126470/06A patent/RU2465482C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2465482C2 (en) | 2012-10-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20190629 |