GB468281A - Fluid reaction propelling apparatus - Google Patents
Fluid reaction propelling apparatusInfo
- Publication number
- GB468281A GB468281A GB35826/35A GB3582635A GB468281A GB 468281 A GB468281 A GB 468281A GB 35826/35 A GB35826/35 A GB 35826/35A GB 3582635 A GB3582635 A GB 3582635A GB 468281 A GB468281 A GB 468281A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzles
- wings
- chambers
- communicate
- discharge
- 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
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
Abstract
468,281. Propelling aircraft. ENDRES, H., and BACHMANN, E. Dec. 27, 1935, No. 35826. Convention date, Nov. 28. [A Specification was laid open to inspection under Sect. 91 of the Acts, July 1, 1936.] [Class 4] In a reaction-propulsion unit as described in Specification 424,546, the discharge nozzles 26 are arranged separately from the compression devices 17 and communicate with the vacuumcylinder spaces of the compression devices. As shown, the compressor 18 delivers air into the chambers 22 from which it passes under the pilot's control to the nozzles. The nozzles disposed in the aircraft wings are controlled singly or in pairs by cams carried by a camshaft 31 and which operate piston valves 25 against the action of springs 27. The devices 17 are arranged around a circle in the fuselage and communicate through non-return valves with the chambers 22. A suction chamber 33 communicates through non-return valves with the vacuum-cylinder spaces. The wings and the fuselage frames may be formed as lightmetal castings. The nozzles discharge through apertures 23 in the wings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE468281X | 1935-11-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB468281A true GB468281A (en) | 1937-06-28 |
Family
ID=6540826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB35826/35A Expired GB468281A (en) | 1935-11-28 | 1935-12-27 | Fluid reaction propelling apparatus |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB468281A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2553443A (en) * | 1947-06-16 | 1951-05-15 | Oscar N Davis | Wing-mounted jet propulsion system for aircraft |
-
1935
- 1935-12-27 GB GB35826/35A patent/GB468281A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2553443A (en) * | 1947-06-16 | 1951-05-15 | Oscar N Davis | Wing-mounted jet propulsion system for aircraft |
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