Airplane

Description

[0001] Airplane. The invention relates to an airplane with a self-supporting structure extending as far as possible over the entire width of the airplane. Wing. - Such wings are usually made up of several boxes that extend perpendicular to the direction of flight and thus are arranged side by side and connected to each other, such that their abutting upper and lower walls form a continuous The outer surface of the supporting deck should have the desired profile. This can also be achieved using spars and frames. to form a supporting frame and to obtain the free-bearing wing by enclosing such a supporting frame with a rigid outer skin.

[0002] According to the invention, individual continuous parts of the wing (spars or box) are now used in their entirety to accommodate the The engine and other parts are bent downwards in the middle to form a recess. Furthermore, at least some of the continuous load-bearing components may be... Parts of the support deck at the bend point may be extended, either directly or indirectly, to accommodate the landing gear.

[0003] The parts that are bent to form a recess can also be designed to accommodate the legs of the pilot, and it is then By curving at least some of the continuous load-bearing parts of the wing upwards, a seat for the pilot can also be formed. can. A backrest for this pilot's seat can ultimately be created by, for example, a bridge of its continuous load-bearing section. Part of the support deck is extended upwards accordingly. The main fuselage section can then be attached to this backrest. It can be attached bluntly. It is not necessary for this extended bridge to always form a backrest; it can. (This is solely for the sake of...) Its purpose is to provide a finishing plate for the main fuselage section.

[0004] Although aircraft had already been designed with cranks in the continuous load-bearing parts, these cranks were not not downwards, but on the contrary, upwards. Furthermore, no motor or other part was ever installed in these bends. at this inherently highly stressed bending point, the pressure stresses which are exerted on both sides of it by the connected Parts of the wing are created, as it were, within themselves; canceling out and thus relieving the crank point of these compressive stresses. would. Furthermore, by installing the engine in this recess in the manner described, the engine compartment is lowered. and thereby reduces the torque that arises during flight due to the driving force and its distance from the center of resistance, and will be completely eliminated if necessary.

[0005] In the drawing, Fig. i is a front view of the aircraft according to the invention, showing some forward boxes of the wing deck itself omitted.

[0006] Fig. 2 is a side view with partial section.

[0007] Fig. 3 is finally a perspective view of a part of an aircraft designed according to the invention.

[0008] It is assumed that a monoplane made of durable and lightweight construction material, for example aluminum or a Aluminium alloy, by forming boxes @a to a1°, which form the wing and extend over the entire span of the wing, The boxes themselves are made of outer and lower sheets of metal that are as continuous as possible and are bent on both sides. between which vertical webs d are arranged. c are transverse webs, possibly for stiffening the box, d are rivets arranged in such a way, that they lie within the airfoil profile and, if possible, flanges of two closely spaced outer sheets with the intermediate one Connect the bridge simultaneously. The foremost box a is conveniently obtained by bending over a single sheet of metal. The individual boxes are finally designed in such a way that each one is able to bear its own share of the total load, and the box plates have Therefore, different thicknesses exist, depending on the position the corresponding box occupies in the profile and the load it must therefore bear. Rivets that hold the rearmost box together.

[0009] In one of the continuous boxes, a container is also finely constructed, which is formed by the addition of a cover plate a0, which simultaneously The load-bearing outer surface is formed after loosening screws c00, which are countersunk in trough-like recesses, and can be lifted out. can.

[0010] In particular, the front boxes are now cranked downwards according to the invention, so that a receiving space for the crank housing - of the engine g . is created.

[0011] As a glance at Fig. r shows, the two lateral parts of the wing would now be bent upwards during flight, or it would The crank point on the right and left is subjected to strong bending stress. - However, because the lower part of the engine is located between the two The lateral parts of the wing are held apart by the lower engine section, which is separated from the right and left by the Wing sections are subjected to pressure during flight, and these pressure forces, which are practically equal to each other, are now balanced in the lower engine compartment. immediately and almost completely relieves the l#,'-röpfungssbelle.

[0012] Some further boxes, for example a¢ and a5, are likewise bent downwards and thus form my trough, which to Accommodation for the driver's legs It serves as a seat on one or more of the boxes located further back.

[0013] In order to avoid having to make this recess too deep, boxes behind it, e.g. @a6, a7, are attached to the The corresponding area is slightly raised, i.e., curved upwards, so that a seat h is formed for the pilot.

[0014] To stiffen these areas in the supporting deck, special, suitably vertical webs can now be inserted, which are therefore in the Flight direction veAaufien and, in the illustrated example of a single-engine monoplane, also symmetrical to the plane of symmetry of the engine or the The support decks are lying.

[0015] The central part of the crank point is now designed such that it initially develops the least air resistance. It is therefore a horizontal droplet cross-section with the longitudinal axis in the direction of flight is obtained. If one were to make a horizontal section through it along line 11 (Dept. 2) Make this cut and fold it 90° into the plane of the drawing. This would create the line shown in dashed lines in Fig. 2, which is also shown in Fig. 2. The cross-section designated il is preserved at this point. At the point of offset, the boxes can also be further formed into projections a° to a7. to which, directly or indirectly, as will be described later, the organs for landing and moving the aircraft on the ground are connected. or can apply water.

[0016] The fuselage k is advantageously formed by a tube which is flattened at its rear end and which houses the rudder control 1, the elevator control m and the spur r. In larger versions, this tube will be assembled from sheets, as shown in Fig. 3. It is recognizable. At the point where the fuselage is to be joined to the wing, the former is cut in such a way that it can be easily seen. It can be slid tightly over the wing and attached to it.

[0017] The landing gear, in this example for landing on the ground, is here indirectly attached to the crank of the fuselage and consists of an intermediate element o with a suitably horizontal drip cross-section, into which the wheel p is inserted from below and thus partially protected against drafts. is protected. Lateral extensions @oi, vertical drip cross-section, are symmetrically formed to the central plane of the wheel and attached to them. Springs are attached to both sides, which first come into contact with the ground upon landing and thus act as brakes, On the other hand, they also act as a spring and cushion the impact when the aircraft touches down. Of course, the wheel p is also suitable. The springs are mounted in a spring-like manner. The springs evidently have the further effect of preventing the aircraft from tilting sideways during landing and taxiing. on the ground is avoided, and - for this purpose the approaches o' extend outwards accordingly to the sides.

[0018] Finally, the backrest n for the pilot and the end plate for the tubular fuselage are designed in the simplest way as organic game with the rest of the wing is formed by, for example, the rear web b of the box, a7 in the one shown in Fig. 2, 3. continues upwards in an evident manner.

Claims

[0019] PATENT CLAIMS: i. Aircraft with a self-supporting wing extending, if possible, over the entire wingspan of the aircraft, characterized in that individual continuous parts of the wing (spars or box) in their entirety serve to accommodate the engine and other parts are bent downwards in the middle to form a recess. Aircraft according to claim i, characterized in that at least some the continuous load-bearing parts of the support deck at the crank point directly or indirectly for the attachment of the landing gear are extended.

3. Aircraft claim i, characterized by the fact that behind -den for the 'accommodation of the pilot's legs to a The trough of cranked parts forms a seat (h) for the upward curvature of at least some continuous load-bearing parts of the deck by means of the curvature of at least some continuous load-bearing parts of the deck. The pilot is trained. q.. Aircraft according to claim i or following, characterized in that a web of a continuous load-bearing part of the supporting deck is extended upwards to such an extent that it forms a backrest (n) or end plate for the main fuselage part (k).