GB953260A - Air-breathing solid propellant ducted rocket - Google Patents
Air-breathing solid propellant ducted rocketInfo
- Publication number
- GB953260A GB953260A GB43261A GB43261A GB953260A GB 953260 A GB953260 A GB 953260A GB 43261 A GB43261 A GB 43261A GB 43261 A GB43261 A GB 43261A GB 953260 A GB953260 A GB 953260A
- Authority
- GB
- United Kingdom
- Prior art keywords
- propellant
- rocket
- combustion
- air
- nozzle
- 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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/105—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Solid-Fuel Combustion (AREA)
Abstract
953,260. Self-propelled missiles. THIOKOL CHEMICAL CORPORATION. Jan. 4, 1961, No. 432/61. Heading F3A. In a solid propellant rocket the casing incorporates an air intake so as to introduce atmospheric air into the combustion space. As shown, Fig. 1, the rocket casing 11 contains the propellant charge 12, the gases from which are directed by nozzle 13 into the combustion chamber 14. The ducts 15 lead air into 14 to complete the combustion of the gases prior to discharge through nozzle 16. In the second embodiment, Fig. 3, the rocket is first accelerated by the high-thrust propellant 37. After a predetermined time, the charge 33 is ignited and the bulkhead 38 is burned. The partially oxidized gases from 33 are mixed with air supplied through duct 36 to produce further combustion in the space occupied by 37 and are then emitted through nozzle 39. In the third embodiment, Fig. 4, the oxidant rich propellant 43 first accelerates the rocket. Then, partial combustion of propellant 49 supplies fuel rich gas to the combustion chamber 47 where further burning occurs, with air supplied through duct 45, before discharge through 48. Organic polymer or copolymer fuels in conjunction with ammonium perchlorate or a nitrate salt as an oxidizer are used.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB43261A GB953260A (en) | 1961-01-04 | 1961-01-04 | Air-breathing solid propellant ducted rocket |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB43261A GB953260A (en) | 1961-01-04 | 1961-01-04 | Air-breathing solid propellant ducted rocket |
Publications (1)
Publication Number | Publication Date |
---|---|
GB953260A true GB953260A (en) | 1964-03-25 |
Family
ID=9704251
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB43261A Expired GB953260A (en) | 1961-01-04 | 1961-01-04 | Air-breathing solid propellant ducted rocket |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB953260A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2574480A1 (en) * | 1984-12-10 | 1986-06-13 | Matra | Device comprising a useable charge and a longitudinally displaceable jet propulsion unit |
FR2650341A1 (en) * | 1989-07-27 | 1991-02-01 | Messerschmitt Boelkow Blohm | GAS GENERATOR FOR STATUS-FUSEES |
DE3029495C1 (en) * | 1979-08-14 | 1995-09-28 | Poudres & Explosifs Ste Nale | Self-firing composition for generating thrust in air with an explosive as the oxidant and ramjet engines with the self-combusting composition as the fuel |
FR2863665A1 (en) * | 1988-10-12 | 2005-06-17 | Aerospatiale | Ramjet engine for propelling missile, includes tubular unit made up of composite material, whose lower volume is separated into two spaces by intermediate transversal partition wall |
CN111594344A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Small-scale two-stage rocket combined ramjet engine |
CN111734550A (en) * | 2020-06-15 | 2020-10-02 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
-
1961
- 1961-01-04 GB GB43261A patent/GB953260A/en not_active Expired
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3029495C1 (en) * | 1979-08-14 | 1995-09-28 | Poudres & Explosifs Ste Nale | Self-firing composition for generating thrust in air with an explosive as the oxidant and ramjet engines with the self-combusting composition as the fuel |
FR2574480A1 (en) * | 1984-12-10 | 1986-06-13 | Matra | Device comprising a useable charge and a longitudinally displaceable jet propulsion unit |
FR2863665A1 (en) * | 1988-10-12 | 2005-06-17 | Aerospatiale | Ramjet engine for propelling missile, includes tubular unit made up of composite material, whose lower volume is separated into two spaces by intermediate transversal partition wall |
FR2650341A1 (en) * | 1989-07-27 | 1991-02-01 | Messerschmitt Boelkow Blohm | GAS GENERATOR FOR STATUS-FUSEES |
CN111594344A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Small-scale two-stage rocket combined ramjet engine |
CN111734550A (en) * | 2020-06-15 | 2020-10-02 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
CN112627982B (en) * | 2020-12-15 | 2021-12-07 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
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