US1605036A

US1605036A - Flying machine

Info

Publication number: US1605036A
Application number: US665133A
Authority: US
Inventors: Junkers Hugo
Original assignee: Individual
Current assignee: Individual
Priority date: 1922-10-02
Filing date: 1923-09-27
Publication date: 1926-11-02
Anticipated expiration: 1943-11-02
Also published as: FR569926A; GB204687A; NL25049C

Description

Nov. 2 1926. 1,605,036

H. JUNKERS Sheets-Sheet 1 Nov'. 2 1926.

1,605,036 H. JUNKERS FLYING MACHINE Filed sept'. 27, 1923 2 sheets-sheet 2 .vio

i317 l f Patented Nov. 2 1926.

UNITED STATES PATENT.- OFFICE..

HUGO JUNKERS, F DESSAU', GERMANY. i

FLYING MACHINE.

Application led September 27, 1923, Serial No. 665,133, and in Germany October 2, 1922.

My invention refers to flying machines and its particular object is to provide means whereby more room is made available for useful loads without unduly interfering with the mechanical strength of the hull of the machine. f

In aircraft design great difliculties are experienced in giving sufficient strength to that part of the hull which is designed for lo the useful load, inasmuch as it requires large free spaces and openings in the wall whereby the necessary bracing of the walls is frequently rendered impossible. This dif'ii.v culty is enhanced in cases where the hull is only low in proportion to the dimensions of the loads to be accommodated. In such cases, it became necessary to enter the hull from above, inasmuch as, payingdue regard to the necessary strength, it proved impos? sible to provide lateral entrance apertures communicating with the large upper openin of the hull.

he present invention is designed to provide for especially large free spaces within the hull in combination with lateral openings by utilizing the struts connecting the hull with the wing, such struts being reinforced correspondingly, as well as that portion of the wing vwhich adjoins the hull, for bracing this latter. By this means essential parts of the usual supporting and bracing structure of the hull adjacent the wing can be dispensed with. Thus, for instance', the hull of an aeroplane having 'its win disposed high above and serving for bracing the .hull can have aspace for the useful ,load which is open on top and at the sides, the rigid system thus resenting gaps which allow entering the liull from the sides. My invention further includes particular features. embodied in the win Vand the braces formin part thereof an which are utilized for bracing the hullin such manner that the combination of these 65 parts furnishes the necessary rigidity.

In the drawings aixed to this specification and forming part thereof, several forms of an aeroplane embodying my invention are illustrated dia ammatically by way of example. In the' rawingsj Fi 1 is a diagram showing in vertical longitudinal section a high-winged aeroplane with the hull and wing arranged after the manner of a treble joint. f

Fig. 2 is a similar. view of an aeroplane having the hull and wing disposed after the manner of a double joint.

Fig. 3 is a perspective diagrammatic, view of a machine embodying the constructive features disclosed in Fig. 2.

Fig. 4 is a 'diagrammatic section of an aeroplane of a similar kind in which the strut bracing serves for stiiening the hull.

Fig. 5 is a perspective diagrammatic view of a machine embodying the constructive features disclosed in Fig. 4.

Figs. 6 and 7 are diagrammatic sections of two further modifications.

Referring first to Fig. 1 of the drawings, 1 is the front portion and 2 the rear portion of the hull which are united below the wing 3 by means of the joint 4, further joints 5 and 6 being formed between these parts of the hull and the wing. The

members

7 and 8 bridging the span between the hull and the wing may either be fins or strut bracings having rigid bases at the hull or at the wing or at both these parts. Thus, in Fig. 1 the forward end of the bracing is rigidly fixed to the rigid front portion of the wing,

while the rear portion of the wing,l which is less rigid, is connected by means of the 'oint 6 to the strut bracing 8 having its asis at the rigid rear portion of the hull.

As shown in4 the drawings, the. three parts 1, 2, 3 form in the vertical longitudinal plane a statically defined three-joint system which, in spite of the large opening in the hull, is capable of taking up all the forces acting in this plane, which originate from loads, from the air resistance yacting on the wing and rudders and from the motor.

In the modification illustrated in Fig. 2, the hull is not made in two separate parts, but has front and rear portions are directly connected with one another by a bottom portion 9. From a practical standpoint this arrangement is simpler, inasmuch as the assembling and handling of the body is simpliied. rlhe conditions of resistivity are not materially changed, because, in conseuence of the static'over-denition resulting from the bottom portion 9 which does not altogether act like a joint, no fundamental dis lacement of forces takes place.

n the machine disclosed in Fig. 3, the bottom 10 of the hull, which is triangular in cross-section only one side wall 1l is uninterrupted, while the cover is interruptbesides ed by a large opening, the other side wall by a triangular indenture designed for the door 12. The two forward strut bracings 7 which are rigid in all directions, are formed each of three struts arranged in pyramids having their bases on the wing, wh1le their points 5 form a rigid joint axis near the hull. The two I rearl strut bracings '8 -are formed by two triangles disosed in parallel longitudinal planes with t eir bases fixed to the hull, while their points 6 are linked to the wing in a transverse plane and ada t themselves to the wing Iwhich is already fixed relatively to 'the hull by the front struts 7. In this arrangement, wherein the weakened middle portion of Ithe hull can be regarded statically as a ball joint, the joint axes formed by the ends 5-5 and 6 6, respectively, of the struts connect the forward and rear portions of the hull with the middle wing portion, all of which are safe against torsional stresses, in a manner which renders also the structure resulting from their combination safe against torsional stresses. v

It' the front andV rear portions of thc hull are connected with each other in the above manner, for instance after the manner of a transversely disposed jointaxle, one of them can be connected with the wing after the manner of a ball joint, that is by means of a single triangle of struts. Bending stresses acting on the hull in the horizontal plane are also transmitted by the `oints, partly in combination with torsional forces, onto the middle wing portion. Y,

The door 12 has a top-beam 13 adapted to be rigidly connected with the side wall b y means of fixation not shown in the drawing, the closed door thus forming a continuation of the hull structure and transmitting tensile and compressive forces. During flight the elastic changes of form of the hull, quite especially those occasioned by forces arising from lateral steering, are lessened, while at the bottom the hull can vbe handled after the wing has been completely dismounted. During normal service the middle portion 3 of the wing is permanently connected to the hull, onl the lateral wing portions 14, l5 being arranged to be removed forl transport. j

In order to safeguard the hull against heavy tensile stresses, the carriage is so designed that the forces transmitted through 1t are directly transferred onto the joints connecting the wing and the hull. end the carria e struts 16 carrying the load extend from t e wheel axle 17 directly to the joints 5 of the strut bracings 7. The links 18 which are merely placed under minor stresses and the struts 19 serving to support the middle portion of the axle are `connected with other parts of the hull structure.

meedoen `available in its interior and su ciently wide openings in the side walls. The wing 3 is either merely provided with the necessary means of connection in at least three points, for instance by adding a transverse trianle of struts 21, or it can be utilized foir urther bracing the hull more especially against torsional stresses, by arranging further strut bracings.

Without departing from the spirit of this invention, the joints above mentioned can be designed after the manner of rigid bracings, such as used in framework asse'mbla e points, as is the case for instance at 9 1n s shown in Fig. 6, the new type of aeroplane above described can also be provided with several wings, for instance by arranging a lower bearing plane 25 below the bottom of the hull.

The carriage may as well be replaced by lfhlpats726 as shown by way of example in l wish it to be understood that' I do not desire to be limited to the exact details of construction shown and described, for obvious modifications will occur to a person skilled in the art.

ll claim:-

1. Flying machine comprising a lhull and a wing placed across and ata distance from said hull, aside wall of said hull h aving a large indentation, and a` strut bracing connecting saidy hull and said wing and forming a rigid connection of the parts of the hull structure which are interrupted by said indentation.

2. Flying machine comprising a* hull, a side wall of said hull having a large indentation open on to a wing and a strut bracing connecting t e middle portion of said wing with the front portion and with the rear portion of said hull, while leaving the middle portion of said hull practically unobstruc d.

3. Flying machine comprising a hull, a side wall of said hull having a large indentation open on top, a wing and a strut bracing connecting the middle portion of said wingA with the front portion and with the rear portion of said hull, while leaving the middle portion of said hull practically unobstructed, said front and reark portions and said strut bracing constituting a rigid threejoint structure.

no, a

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4.-. Flying machine comprising a hull, a

ing connecting themiddle portion of said wing with the front portion and with the` rear portion of said hull, while leaving the middle portion of said hullipractically unobstructed, said front and rear portions, said .wing and said strut bracing constituting a rigid three-joint structure. A

5. An aeroplane comprising a hull, a side wall of said hull having a large indentation open on top,and a wing, the front and rear portions of said hull being formed rigid against torsional stresses, and a front and a rear system ol" strut 'bracings connecting said wing to said hull and arranged to form a member rigid against torsional stresses.

6. An aeroplane comprising a hull, a side wall of said hull having a large indentation open on top; and a wing, the front and rear portions of said hull being formed rigid against torsional stresses and a pair of strut bracings which are arranged in a transverse joint axle and connect each portion with said wing.

7. An aeroplane comprising a hull, a side wall of said hull having` a large indentation open on top, and a wing, the front and rear portion of said hull having triangular cross section and being formed rigid against'. tor-i sional stresses, and a front and a rear system of strut bracings connecting said wing to said hull and arranged to form a member rigid against torsional stresses.

8. An aeroplane comprising a hull and a wing, the front and rear portions of said hull being Jformed rigid against torsional stresses and being connected at least in one point, two strut bracings rigid in all direc'- tionsconnecting the wing with one of said portions and two strut bracings rigid in the longitudinal direction connecting with the other portion.

9. An aeroplane comprising a hull and a wing, the frontandrear portions of said hull being formed .rigid against torsional stresses and being connected at least in one said wing point, two strut bracings rigid in all directions connecting the wing with one of said portions and two strut bracings rigid in the longitudinal direction connecting said wing with the other portion, said forward strut bracings being rigidly fixed by their bases to the wing, their points being linked to the front portion of the hull, while the rear strut bracings have their bases rigidly connected to the rear portion of the hull, their points being linked to said Wing.

10. Flying machine comprising a hull and .a wing placed across and at a distance from portion and with the rear portion of said hull while leaving the middle portion of said 11u11 practically unobstructed, 'a carriage below said hull and struts connecting said carriage with the strut bracings connecting the hull with the middle portion of said wing.

12. Flying machine comprising a hull, a wing and a strut bracing connecting the middle portion of said wing with the front portion and with the rear portion of said hull while leaving the middle portion ot said hull practically unobstructed, a carriage below said hull and struts connecting said carriageJ with the strut bracings connecting the middle portion of said wing with said hull.

ln testimony whereof ll aiix my signature.

nneo JUNKERS.