GB722857A - Improvements relating to the construction of hollow bodies of streamline form - Google Patents
Improvements relating to the construction of hollow bodies of streamline formInfo
- Publication number
- GB722857A GB722857A GB2510452A GB2510452A GB722857A GB 722857 A GB722857 A GB 722857A GB 2510452 A GB2510452 A GB 2510452A GB 2510452 A GB2510452 A GB 2510452A GB 722857 A GB722857 A GB 722857A
- Authority
- GB
- United Kingdom
- Prior art keywords
- longitudinally divided
- stiffeners
- stringers
- construction
- parent specification
- 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
- 239000003351 stiffener Substances 0.000 abstract 2
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification 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 POWERÂ PLANTSÂ OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
722,857. Aircraft framework. HEAL, L. C. March 20, 1951, No. 25104/52. Divided out of and Addition to 702,981, [Group XXII]. Class 4. [Also in Group XXII] An improvement in or modification of the invention claimed in the parent Specification comprises a longitudinally divided hollow structure constituted by separately-made longitudinally curved sections which are subsequently joined together, each of said sections being a hollow body constructed as claimed in the parent Specification. An aircraft fuselage comprises longitudinally divided halves 1, 1A wherein profiled skin strips are secured to one another and to internally disposed permanently attached stiffeners and stringers. In a further embodiment Fig. 2 (not shown), the structure of an engine nacelle comprises longitudinally divided halves, each having inner and outer skins of interconnected strip form having stiffeners and stringers located in the annular cavity between the skins on the opposed faces thereof.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2510452A GB722857A (en) | 1951-03-20 | 1951-03-20 | Improvements relating to the construction of hollow bodies of streamline form |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2510452A GB722857A (en) | 1951-03-20 | 1951-03-20 | Improvements relating to the construction of hollow bodies of streamline form |
Publications (1)
Publication Number | Publication Date |
---|---|
GB722857A true GB722857A (en) | 1955-02-02 |
Family
ID=10222282
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2510452A Expired GB722857A (en) | 1951-03-20 | 1951-03-20 | Improvements relating to the construction of hollow bodies of streamline form |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB722857A (en) |
-
1951
- 1951-03-20 GB GB2510452A patent/GB722857A/en not_active Expired
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