GB733830A - Improvements in or relating to the fuselages of aerodynes - Google Patents
Improvements in or relating to the fuselages of aerodynesInfo
- Publication number
- GB733830A GB733830A GB8924/53A GB892453A GB733830A GB 733830 A GB733830 A GB 733830A GB 8924/53 A GB8924/53 A GB 8924/53A GB 892453 A GB892453 A GB 892453A GB 733830 A GB733830 A GB 733830A
- Authority
- GB
- United Kingdom
- Prior art keywords
- girder
- fuselage
- floor
- aeroplane
- secured
- 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
- 230000003014 reinforcing effect Effects 0.000 abstract 3
- 235000000396 iron Nutrition 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Devices Affording Protection Of Roads Or Walls For Sound Insulation (AREA)
- Sampling And Sample Adjustment (AREA)
Abstract
733,830. Aircraft framework. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-EST. March 31, 1953 [April 9, 1952], No. 8924/53. Class 4. An aeroplane fuselage is provided along the greatest part of its bottom from the nose toward the rear with a floor dividing the fuselage into an upper compartment and a substantially smaller lower compartment, and, secured to the floor and fuselage, a reinforcing central girder in the lower compartment disposed in the longitudinal plane of symmetry to act as a reinforcing member for said fuselage with a view to allow the use of aeroplane conveying devices bearing under said girder at any point or points of its length. The girder 7 is shown in Figs. 2 and 4, extending from the bottom of the shell to a floor 1 dividing the fuselage into two compartments. The girder may be made in sections of varying height to accommodate different heights of the floor 1. Transverse reinforcing plates 25, 26 are used, or flanged angle pieces where equipment is stowed, e.g. a ski-landing gear similar to that of Specification 726,573. The girder is secured to the fuselage ring frames, especially the stronger ones near the wing roots. An external portion 24 may be provided to slide on rollers or the like. The girder may consist of two plates 14, 15 (Fig. 7) internally braced and fastened down by angle irons 22, 23.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR733830X | 1952-04-09 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB733830A true GB733830A (en) | 1955-07-20 |
Family
ID=9126992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8924/53A Expired GB733830A (en) | 1952-04-09 | 1953-03-31 | Improvements in or relating to the fuselages of aerodynes |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB733830A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993856A1 (en) * | 2012-07-30 | 2014-01-31 | Airbus Operations Sas | AIRCRAFT FUSELAGE STRUCTURE ELEMENT HAVING AN EVOLVING SECTION |
-
1953
- 1953-03-31 GB GB8924/53A patent/GB733830A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993856A1 (en) * | 2012-07-30 | 2014-01-31 | Airbus Operations Sas | AIRCRAFT FUSELAGE STRUCTURE ELEMENT HAVING AN EVOLVING SECTION |
| EP2692631A1 (en) * | 2012-07-30 | 2014-02-05 | Airbus Operations | Aircraft fuselage frame with tapered section |
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