GB574795A - Improvement in or relating to aeroplane construction - Google Patents
Improvement in or relating to aeroplane constructionInfo
- Publication number
- GB574795A GB574795A GB3198/44A GB319844A GB574795A GB 574795 A GB574795 A GB 574795A GB 3198/44 A GB3198/44 A GB 3198/44A GB 319844 A GB319844 A GB 319844A GB 574795 A GB574795 A GB 574795A
- Authority
- GB
- United Kingdom
- Prior art keywords
- relating
- improvement
- supercharger
- radiators
- hood
- 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
- 238000010276 construction Methods 0.000 title 1
- 239000002826 coolant Substances 0.000 abstract 1
- 238000005192 partition Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
574,795. Aircraft fuselages ; air inlets. MAAG, G. A. Feb. 21, 1944, No. 3198. [Class 4] The cockpit hood 1 of an aeroplane is extended forwardly of the windscreen 2 to form an airscoop 3 from which air is distributed to the engine, supercharger, radiator or cabin. The rear end of the scoop is closed by a partition 5 in which is a central opening to a conduit 8 leading to the supercharger and two openings to honeycomb radiators for the engine coolant. Conduits 14 from the radiators lead to discharge openings 15 in the walls of the fuselage. The hood 1. is preferably transparent.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3198/44A GB574795A (en) | 1944-02-21 | 1944-02-21 | Improvement in or relating to aeroplane construction |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3198/44A GB574795A (en) | 1944-02-21 | 1944-02-21 | Improvement in or relating to aeroplane construction |
Publications (1)
Publication Number | Publication Date |
---|---|
GB574795A true GB574795A (en) | 1946-01-21 |
Family
ID=9753800
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3198/44A Expired GB574795A (en) | 1944-02-21 | 1944-02-21 | Improvement in or relating to aeroplane construction |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB574795A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0743247A2 (en) * | 1995-05-15 | 1996-11-20 | The Boeing Company | Passive cooling device and method for cooling an auxiliary power unit on an airoplane |
-
1944
- 1944-02-21 GB GB3198/44A patent/GB574795A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0743247A2 (en) * | 1995-05-15 | 1996-11-20 | The Boeing Company | Passive cooling device and method for cooling an auxiliary power unit on an airoplane |
EP0743247A3 (en) * | 1995-05-15 | 1998-01-07 | The Boeing Company | Passive cooling device and method for cooling an auxiliary power unit on an airoplane |
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