US1889294A - Triangular plane girder for aeroplanes - Google Patents
Triangular plane girder for aeroplanes Download PDFInfo
- Publication number
- US1889294A US1889294A US501711A US50171130A US1889294A US 1889294 A US1889294 A US 1889294A US 501711 A US501711 A US 501711A US 50171130 A US50171130 A US 50171130A US 1889294 A US1889294 A US 1889294A
- Authority
- US
- United States
- Prior art keywords
- girder
- aeroplanes
- triangular plane
- plane girder
- openings
- 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 - Lifetime
Links
- 238000010276 construction Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Images
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
- B64C1/08—Geodetic or other open-frame structures
Definitions
- the accompanying drawing shows diagrammatically by way of example a girder construction for an aeroplane fuselage, in which the apertures for the entrance doors are formed without the necessity of employing special means for reinforcing the girder and without effecting the stability of said girder.
- Figure 1 shows diagrammatically a part of the girder forming the side wall of the fuselage.
- Figure 2 is a general view of an aeroplane, of which the fuselage is constructed with the girder shown in Fig. 1.
- a and A denote the two fully free large pentagonal apertures in correspondence with which the doors .9 and s, (Fig. 2) shall be fitted.
- the above described system may be applied in cases other than that mentioned above without departing from the spirit of this invention.
Description
Nov, 29, 1932.. c, RQSA'TELLHI 1 889394 TRIANGULAR PLANE GIRDER FOR AEROPLANES Filed Dec. 11, 1950 Patented Nov. 29, 1932 UNITED STATES PATENT oFFIcE CELESTINO ROSATELLI, or roam, ITALY, ASSIGNOR TO FIAT SOGIETA ANOLN'IMA, 0F
TURIN,
ITALY Application filed December 11, 1930, Serial No. 501,711, and. in Italy September 23, 1930.
10 the braced girder which is in'accordance with the known statical graphical law expressed by the formula wherein X is the number of members and Y the number of knots of the girder.
As it is well known the above mentioned formula expresses the necessary and sufficient condition enabling a braced girder to be statically determined and undeformable.
The accompanying drawing shows diagrammatically by way of example a girder construction for an aeroplane fuselage, in which the apertures for the entrance doors are formed without the necessity of employing special means for reinforcing the girder and without effecting the stability of said girder.
Figure 1 shows diagrammatically a part of the girder forming the side wall of the fuselage.
Figure 2 is a general view of an aeroplane, of which the fuselage is constructed with the girder shown in Fig. 1.
Referring to the drawing: A and A denote the two fully free large pentagonal apertures in correspondence with which the doors .9 and s, (Fig. 2) shall be fitted. The apertures A and A divide the girder into three sections; considering'in such section thepartsBGFED,EGHILMand M N O P Q and referring to the members as a and to the connections as 9bit will be found that a=33 and n 18 The said values fulfill the necessary and suflicient condition for obtaining a statically determined and undeformable girder. In fact 33=2 18-3 Of course the above described system may be applied in cases other than that mentioned above without departing from the spirit of this invention.
What I claim is: a
In an aircraft body having lateral openings for the doors extending a substantial portion of the height of the body, a longi tudinal truss at a side of the body and having openings corresponding with the body openings, said truss comprising upper and lower beams extending continuously throughout the portion of the body in which said door openings are located, uprights connecting said beams between said openings, a horizontal member for connecting intermediate points of said uprights, diagonal struts between said uprights converging towards the connecting point of this horizontal member with one of said uprights, and struts between the connecting points of said horizontal member and the lower beam.
In testimony that I claim the foregoing as my invention, I have signed my name.
CELESTINO ROSATELLI.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT1889294X | 1930-09-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US1889294A true US1889294A (en) | 1932-11-29 |
Family
ID=11434796
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US501711A Expired - Lifetime US1889294A (en) | 1930-09-23 | 1930-12-11 | Triangular plane girder for aeroplanes |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US1889294A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2827251A (en) * | 1952-04-02 | 1958-03-18 | Doman Helicopters Inc | Aircraft frame with large side openings |
-
1930
- 1930-12-11 US US501711A patent/US1889294A/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2827251A (en) * | 1952-04-02 | 1958-03-18 | Doman Helicopters Inc | Aircraft frame with large side openings |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US1656810A (en) | Hollow girder for light structures | |
| US1889294A (en) | Triangular plane girder for aeroplanes | |
| US2083051A (en) | Airship | |
| US2136265A (en) | Construction of wings, surfaces, and fuselages for aircraft | |
| US1419827A (en) | Construction member | |
| US1943256A (en) | Light weight girder for aircraft | |
| US1894011A (en) | Construction of fuselage or other bodies of aircraft | |
| US1698849A (en) | Airplane | |
| US1801344A (en) | Aeroplane | |
| US1727293A (en) | Joint for structural-steel columns and girders | |
| GB620863A (en) | Improvements in or relating to aircraft | |
| US2140558A (en) | Airplane fabric attachment | |
| US1792890A (en) | Airplane | |
| SU1048A1 (en) | Beam for wings of metal airplanes | |
| GB520249A (en) | Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft | |
| US1446528A (en) | Ambulance aircraft fuselage | |
| DE414906C (en) | Butt connection for airship frame | |
| DE655936C (en) | Hollow bodies for aircraft | |
| US2222981A (en) | Beam grid for roof or floor construction | |
| SU9922A1 (en) | Monoplane Wing | |
| GB462390A (en) | Improved construction of wings, aerofoils and the like for aeronautical machines | |
| GB388438A (en) | Improvements in or connected with the construction of fuselage or other bodies of aircraft | |
| SU2780A1 (en) | Beams for aircraft support surfaces | |
| GB392447A (en) | Single spar aircraft wing with auxiliary spars | |
| GB332568A (en) | Improvements in or relating to light metal structures |