GB1394401A - Solid-fuel rocket propulsion unit - Google Patents
Solid-fuel rocket propulsion unitInfo
- Publication number
- GB1394401A GB1394401A GB159773A GB159773A GB1394401A GB 1394401 A GB1394401 A GB 1394401A GB 159773 A GB159773 A GB 159773A GB 159773 A GB159773 A GB 159773A GB 1394401 A GB1394401 A GB 1394401A
- Authority
- GB
- United Kingdom
- Prior art keywords
- solid
- air
- envelope
- propulsion unit
- jan
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Thermal Insulation (AREA)
Abstract
1394401 Solid-fuel propulsion units BAYERN-CHEMIE GES FUR FLUGCHEMISCHE ANTRIEBE mbH 11 Jan 1973 [28 Jan 1972] 1597/73 Heading F3A A thermally insulated, solid-fuel propulsion unit for air-to-air missiles comprises a combustion chamber 4 separated from an outer envelope 1, to which stabilizing fins 18 are attached, by a gas-impermeable, annular gap 7 and thermal insulation 10, 11. The annular gap is either evacuated or filled with a gas of low thermal conductivity, e.g. air. The chamber 4 is formed of high-tensile steel and the envelope 1 is formed of titanium alloy or berylliumaluminium alloy. A threaded portion 16 of the envelope is provided for receiving a warhead. The insulation 10, 11 is formed of glass fibre impregnated with phenol resin.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19722204006 DE2204006C3 (en) | 1972-01-28 | Solid rocket engine, especially for missiles of the military type launched from high-speed aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1394401A true GB1394401A (en) | 1975-05-14 |
Family
ID=5834312
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB159773A Expired GB1394401A (en) | 1972-01-28 | 1973-01-11 | Solid-fuel rocket propulsion unit |
Country Status (2)
Country | Link |
---|---|
FR (1) | FR2169067B3 (en) |
GB (1) | GB1394401A (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2500149B1 (en) * | 1981-02-17 | 1985-12-06 | Poudres & Explosifs Ste Nale | PROPULSIVE LOADING BIREGIME WITH TRUMPET HAVING A STAR SECTION |
-
1973
- 1973-01-11 GB GB159773A patent/GB1394401A/en not_active Expired
- 1973-01-15 FR FR7301336A patent/FR2169067B3/fr not_active Expired
Also Published As
Publication number | Publication date |
---|---|
FR2169067B3 (en) | 1976-01-16 |
DE2204006B2 (en) | 1975-10-09 |
DE2204006A1 (en) | 1973-08-09 |
FR2169067A1 (en) | 1973-09-07 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PCNP | Patent ceased through non-payment of renewal fee |