US1827181A - Aeroplane construction - Google Patents

Description

Oct. 13, 1931. H. ALFARO 1,827,181

AEROPLANE CONSTRUCTI ON Filed Oct. 30, 1930 3 Sheets-Sheet l V MW 5 u Wu 7 p Mn MAYA fig 3 6 j INVENTOR /4 BY 2 ATTORNEYE? Oct. 13, 1931. H. ALFARO 1,327,181

AEROPLANE CONSTRUCTION Filed Oct. 50, 1930 s Sheets-Sheet 2 INVENTOR ATTORNEY5 Oct. 13, 193 1. H, ALFARO 1,827,181

AEROPLANE CONSTRUCTION Filed Oct. 30, 1930 3 Sheets-Sheet 3 INVENTOR W ATTORNEY Patented Oct-.13; 1931 UNITED STATES nnnacnro AL-FARO, 01- EAST CLEVELAND, 01110 AEROPLAN E CONSTRUCTION Application filed October 30, 1930. Serial No. 492,235.

failure of one or more of the structural elements composing the frame work.

A further object is to provide an aeroplane especially suitable for military purposes by so constructing the frame work that if any structural member of the framework should be severed by the explosion of a shell or burst of machine gun bullets, the load will be car ried b the other frame members, so that continue flight is possible.

A further object is to=provide a fuselage frame so constructed as to provide maximum rigidity in the portion of the fuselage to which the wings are attached and to so construct the wings as to provide maximum rigidity at the inner ends thereof which are connected to the fuselage.

A further object is to provide a frame work i composed wholly of light structural members so in which the necessaryrigidity is supplied by systems of diagonal braces.

With the above and other objects in view, the invention may be said to comprise the construction as illustrated in the accompanying drawings hereinafter described and particularly set forth in the appended claims, together with such variations and modifications thereof as will be apparent to one skilled in the art to which the invention ap- 'pertains.

Reference should be had to the accompanying drawings forming a part of this specification in which:

Figure 1 is a top plan view of an aeroplane embodying the invention.

Fig. 2-is a side elevation of. the fuselage frame.

Fig. 3 is a transverse section through'the 10 fuselage frame on an enlarged scale.

' versely through one of the wings. 1

Fig. 4 is a transverse section through one of the side panels of the fuselage frame.

'Fi 5 is a p'ers ective view showing the I attac ment of the races to the longrons in the fuselage frame. F

Fig. 6 is a perspective view showing a slightly modified construction in which one piece angle shaped longrons are employed.

Fig. 7 is a perspective view showing the connection of the braces at a crossing point. no

Figs. 8 to 13, inclusive, are detail views showing various structural shapes which may be employed for the braces.

Fig. 14 is a vertical section taken trans- Fig. '15 is a plan view showing a wing with a slightly modified bracing system.

Fig. 16 is a perspective view of one of the wing beams. r F1 17 is a sectional view showing a modi- 7Q fied orm of wing having a controlling flap along its trailing edge. Fi 18 is a perspective view showing the flap ame work. I I

.Fig. 19 is a perspective view showing a 7 slightly modified flap construction. In the accompanying drawings, the fuse lage is indicated by the reference numeral 1 and the wings attached to the fuselage by the referencenumeral2. Thedrawingsshowonly an I the structural frame work of the aeroplane, since the present invention relates exclusively to the construction of the said structural frame work.

As best shown in Figs. 2 and 3, the fuselage as 1 has longrons 2 which extend the full length thereof at the intersections of the side walls with the top and bottom walls and these longrons are preferably each composed of two angle bars 4 which have flanges 5 and 6 9e disposed atan angle of approximately The edges of the flanges are preferably rolled oper to provide beads 7 along the edges there-: 0

The longrons are arranged with their as flanges 5 back to back and are rigidly secured together by a row of rivets 8. The flanges 6 of the bars 4 forming each of the longrons are disposed at right angles to each other and the longrons are connected by means of di we agonal braces 9 which are arranged in crossing relation. The braces 9 are preferably channel shaped structural members having curled flanges 10 which provide strengthening beads along the edges thereof. The braces 9 are arranged in crossing relation and, preferably, with the end of each brace joined to the end of an oppositely inclined bra'ce at its point of connection with the longrons.

As shown in Fig. 6, the braces 9 are flattened at their ends and oppositely inclined braces are attached together and to a flange 6 of the longron by any suitable means such as rivets 11.

The crossing braces are arranged back to back and secured together by any suitable means such as a rivet 12 at each crossing point, as shown in Fig. 7.

The use of two part longrons permits the separate fabrication of each of the four panels of the fuselage frame, the braces 9 being riveted together and to the flanges 6 of the angle bars 4, as shown in Fig. 4, after which the panels are assembled and the flanges 5 of the angle bars are riveted together at the corners of the frame to complete the assembly. lln some instances, it may be desirable to employ one piece longrons in which case a structural member of angle shape such as indicated by the numeral 13 in Fig. 6 is preferred, the member 13 having flanges 14 which are rolled over at their edges to provide beads 15. In this modification, the diagonal braces 9 are riveted to the flanges 14 of the longron 13, which are disposed at right angles to each other.

The longrons are preferably formed of sheet metal such as an aluminum alloy stainless steel or other alloys and the braces 9 are preferably formed of the same material, although wooden members may be employed, if desired. i

It will be understood that the fastening I means employed for securing the braces to the longrons and to each other will be that best suited for the particular material of which these members are composed. For instance, when stainless steel or other easily weldable material is employed, the members may be joined by electrically welded spots instead of rivets.

Various structural shapes may be employed for the braces such as the shape 16 shown in Fig. 8, 17 shown in Fig. 9, 18 shown in Fig. 10, 19 shown in Fig. 11, 20 shown in Fig. 12, or 21 shown in Fig; 13.

The rivets 12 connecting the braces 9 at their crossing points are preferably made of a relatively soft metal such as aluminum while the rivets 11 connecting the braces to the longrons are preferably of a harder metal .such as an aluminum copper alloy or iron, this being desirable for simplicity of fabrication.

The braces 9 are preferably so arranged in saaiei the side walls of the fuselage as to provide maximum strength and rigidity in the portions of the fuselage where the stresses are highest. This result is obtained by spacing the braces closer together and at a greater angle with respect to the longrons in the portion of the fuselage to which the wings or other highly stressed members are attached and gradually increasing the spacing and decreasingthe angle of inclination toward the ends of the fuselage, as clearly shown in Fig.2.

The wings 2 are provided with two or more spaced longitudinal beams 22, each of which is of skeleton construction having top and bottom members each composed of two angle bars 23 secured together back to back and diagonal braces 24 which are arranged in crossing relation and secured between the flanges of the angle bars 23 by means of rivets 25. The angle members 23 and braces 24 are preferably made of a sheet metal composed of an aluminum alloy or rustless steel and the braces may be of the same shape as the braces 9 of the fuselage.

The braces 24 are arranged back to back and are attached at their crossing points by means of rivets 26. The beams 22, as shown in Fig. 14 are held against relative vertical movements by means of rigid cross members 27 extending through and connected to the beams .intermediate the tops and bottoms thereof. The top wall of the wing is reinforced by top braces 28 which extend diagonally across the tops of the beams in crossing relation from adjacent the forward; edge to adjacent the trailing edgeof the win The bottom wall of the wing is reinforce by diagonal braces 29 which extend across the bottoms of the beams 22 from adjacent the forward edge to adjacent the trailing edge of the wing and which are also disposed in crossing relation.

The top and bottom braces 28 and 29 are preferably inclined oppositely with respect to the beams and are rigidly attached to the beams. The braces 28 and 29 are so arranged that the ends of the top braces adjoin ends of oppositely inclined bottom braces along the front and rear edges of the wing. The top braces 28 are so arranged that the outenones incline in an inward direction from fore to aft in the wing while the outer diagonal braces of the lower face of the wing are inclined outwardly from the leading edge toward the trailing edge, the direction of the braces being in the general direction of the stream lines of flow along the upper and lower faces of the wing.

The braces of the wings are preferably so arranged as to provide maximum rigidity adjacent the inner ends of the wings which are attached to the fuselage. This result is accomplished by, spacing the braces closely together and at a high angle of inclination with respect to the beams 22, adjacent the inner ends of the wings and gradually decreasing the inclination and increasing the spacing of the braces toward the outer ends or tips of the wings. The differential spacing of the wing braces, while advantageous, is not essential to the invention and these braces may, if

desired, be arranged with uniform angularity and uniformspacing, as shown in Fig. of the drawings in which the top and bottom braces 31 and 32 are shown so arranged.

The wings may be provided with controlling flaps along their rear edges, as shown at r 33 in Fig. 17, in which case, the flap is preferplaced closer together and in crossing relation in both the top and bottom wall. As shown in Fig. 19, the top wall is provided witha system of crossing diagonal braces 40 and the bottom wall with a similar system of crossing braces 41.

It will be apparent that the present invention provides a structural framework for aeroplanes which can be quickly and easily fabricated, which is of low weight, but which nevertheless possesses great strength and rigidity and is capable of withstanding extreme stresses.

Furthermore it is to be understood that the particular "form of apparatus shown and described, and the particular procedure set forth, are presented for purposes of explanation and illustration and that various modifications of said apparatus and procedure can be made without departing from my inven-' tion as defined in the appended claims.

What I claim is:

1. An aeroplane having a fuselage, the frame work of which consists of longrons at the intersection ,of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an. oppositely inclined brace, and wings having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces and top and bottom walls having braces extending diagonally across the same and connected to the top and bottom members ofthe beams.

2. An aeroplane having a fuselage, the frame work of which consists of longrons at the intersection of the side walls with the top and bottom walls and'a, system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, and wings having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces and top and bottom walls having braces extending diagonally across the same and connected to the top and bottom members of the beams, the outer braces of the top wall of each wing being oppositely inclined with respect to th outer braces of the bottom wall. I

3. An aeroplane having a fuselage, the framework of'which consists of longrons at the .intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longe'rons across the top, bottom and sides of the frame, each brace being. connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, the braces at the sides of the fuselage frame being closely spaced and at relatively high angles of inclination in the portion of the fuselage to which the wings are attached and of progressively less inclination towardthe ends of the frame, and wings having longitudinal beams which have top and bottom members and web-s composed of crossing diagonal braces and top and bottom walls having braces extending diagonally across the same and connected to the top and bottom members of the beams.

4. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longerons and to oppositely inclined braces and intermediate its ends to an oppositely in-.

clined brace, the braces at the sides of the fuselage frame being closely spaced and at relatively high angles of inclination in the portion of the fuselage to which the wings are attached and of progressively less inclination toward the ends of the frame, and wings having longitudinal beams which have top and framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, and wings having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces and top and bottom walls having braces extending diagonally across the same and connected to the top and bottom members of the beams, the frame members of the fuselage and wings being all in the form of flanged sheet metal structural shapes.

6. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons "and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace. I

7. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across thetop, bottom and sides of the frame, each brace being connected at its ends tothe longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace,-said longrons and braces being flanged sheet metal members, the braces of each fuselage wall being arranged back to back and attached together at their crossing points, oppositely inclined braces having their ends riveted together and to the longrons.

8. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, said longrons and braces being flanged sheet metal members, the braces of each fuselage wall being arranged back to back and attached together at their crossing points, oppositely inclined braces having their ends attached together and to the longrons, the inclination of the braces with respect to the longrons gradually decreasing toward the rear end of the fuselage.

9. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal aeemsi pair of angle members having flanges attached together back to back.

10. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and intermediate its ends to an oppositely inclined brace, said longrons and braces being flanged sheet metal members, the braces of each fuselage wall being arranged back to back and attached together at their crossing points, oppositely inclined braces having their ends attached together and to the longrons, each of said longrons consisting of a pair of angle members having flanges attached together back to back.

11. An aeroplane having a fuselage, the framework of which consists of longronsvat the intersection of the side walls with the top and bottom walls anda system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and intermediate its ends to an oppositely inclined brace, said longrons and braces being flanged sheet metal members, the braces of each fuselage wall being arranged back to back and riveted together at their crossing points, oppositely inclined braces having their ends riveted together and to the longrons, the rivets'connecting the braces at their crossing points being formed of a relatively soft metal. Y

12. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, said longrons and braces being flanged sheet metal members, the braces of each fuselage wall being arranged back to back and riveted together at their crossing points, oppositely inclined braces having their ends riveted together and to the longrons, the rivets connecting the braces at their crossing points being formed of a relatively soft metal, the rivets joining the braces to the longrons being formed of a harder metal.

13. An aeroplane having a fuselage, the framework of which consists of longrons at the intersection of the side walls with the top and bottom walls and a system of diagonal iIO braces connecting the longrons across the top, bottom and sides of the frame, each brace being connected at its ends to the longrons and to oppositely inclined braces and intermediate its ends to an oppositely inclined brace, said longrons and braces being flanged sheet metal members, the braces of of each fuselage wall being arranged back to back and riveted together at their crossing points, oppositely inclined braces having their ends riveted together and to the longrons, the inclination of the braces with respect to the longrons gradually decreasing toward the rear end of the fuselage, the rivets connecting the braces at their crossing points being formed of a relatively soft metal and the rivets joining the braces to the longrons being of a harder metal.

14. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined braces extending across the top and bottom of the wing and joined to said beams.

15. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined 'braces extending across the top and bottom of the wing and joined to said beams, the outer braces at the top of the wing being inclined at an angle opposite that of the outer brace members at the bottom of the wing.

, 16. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined braces extending across the top and bottom of the wing an aimed to said beams, said members and braces ing all in the form of flanged sheet metal bars.

17. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined braces extending across the top and bottom of the wing and joined to said beams, the outer braces at the top of the wing being inclined at an angle opposite that of the outer brace members at the bottom of the wing, the ends of oppositely inclined braces of the top and bottom walls adjoining near the front and rear edges of the wing.

18. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined braces extending across the top and bottom of the wing and joined to said beams, the outer braces at the top of the wing being inclined at an angle opposite that of the outer brace members at the bottom of the wing, inclination of said braces with respect to the beams gradually decreasing toward the outer ends of the wings and the spacing of said braces gradually decreasing toward the inner end of the wing.

19. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces connecting the top and bottom members, inclined braces extending across the top and bottom of the wing and joined to said beams, and cross members connecting the beams intermediate the top and bottom members thereof.

20. In an aeroplane, a wing having longitudinal beams which have top and bottom members and webs composed of crossing diagonal braces, connecting the top and bottom members, and inclined braces extending across the top and bottoms of the wing and joined to said beams, the outer braces at the top of the wing extending inwardly from fore to aft in the wing and the outer braces at the bottom of the wing having an opposite inclination.

In testimony whereof I aflix my signature.

HERACLIO ALFARO.

Images