UA103537C2 - Detonation solid fuel rocket engine - Google Patents
Detonation solid fuel rocket engineInfo
- Publication number
- UA103537C2 UA103537C2 UAA201200283A UAA201200283A UA103537C2 UA 103537 C2 UA103537 C2 UA 103537C2 UA A201200283 A UAA201200283 A UA A201200283A UA A201200283 A UAA201200283 A UA A201200283A UA 103537 C2 UA103537 C2 UA 103537C2
- Authority
- UA
- Ukraine
- Prior art keywords
- fuse
- combustion chamber
- detonating
- circular
- section
- Prior art date
Links
Abstract
A detonation solid-fuel rocket engine is proposed, this includes a combustion chamber and a charge of detonating solid fuel placed there, this includes explosive substance as layers of detonating fuse separated one from another with damping pads that are gasified at passage of detonation wave by the fuse, supersonic nozzle connected to combustion chamber, and detonator placed at one of the ends of the fuse and connected to the system for control of start of the engine. Combustion chamber is arranged as circular, in toroidal shape, with cylindrical side walls, and connected to profiled cone-like central body, at that on the outer cylindrical side wall of the toroidal combustion chamber, in its lower section, a profiled ring is provided, this together with the cone-like central body forms a trans-sonic, with critical cross section, section of the circular supersonic nozzle with external expansion of gas flow; charge of detonating solid fuel is made circular, with sequential repetitive laying circular layers of detonating fuse to damping pads, with connection to the inner cylindrical side wall of the circular toroidal combustion chamber; the free end of detonating fuse that is placed at the last layer of the fuse is connected to detonator. Detonating fuse at its initial section that is connected to detonator has diameter of cross section that gradually increases from minimal admitted to rated one for the main mode of operation of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAA201200283A UA103537C2 (en) | 2012-01-10 | 2012-01-10 | Detonation solid fuel rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAA201200283A UA103537C2 (en) | 2012-01-10 | 2012-01-10 | Detonation solid fuel rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| UA103537C2 true UA103537C2 (en) | 2013-10-25 |
Family
ID=52283726
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| UAA201200283A UA103537C2 (en) | 2012-01-10 | 2012-01-10 | Detonation solid fuel rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| UA (1) | UA103537C2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109667684A (en) * | 2018-12-26 | 2019-04-23 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking airbreathing motor and aircraft of thruster vector control |
-
2012
- 2012-01-10 UA UAA201200283A patent/UA103537C2/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109667684A (en) * | 2018-12-26 | 2019-04-23 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking airbreathing motor and aircraft of thruster vector control |
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