DE414514C - plane - Google Patents

Description

Plane. The invention relates to an aircraft with a possible over the entire width of the aircraft continuous, self-supporting wing. - Such wings are usually composed of several boxes, you extend transversely to the direction of flight and so arranged side by side and with one another are connected that their abutting upper and lower walls form a continuous Outer surface of the supporting deck result in the desired profile. Man. but can also go through Spars and frames a shoring .ausbilden and the joyful Wing obtained by having such a support structure with a stiff Spanning the outer skin.

According to the invention, individual continuous parts of the wing are now (Spars or boxes) in their entirety to accommodate the engine and other parts cranked down in the middle to form a hollow. It can also at least some of the continuous load-bearing parts of the supporting deck at the cranking point indirectly or be extended directly to attach the landing gear.

The cranked parts to form a trough can also be used to accommodate the pilot's legs will be determined, and it will then be arched at least some durchgehedder load-bearing parts of the deck upwards. Also a seat for the pilot can be formed. A backrest for this seat of the The pilot can eventually be created by this. be that for example a bridge of its continuous load-bearing. Part of the supporting deck correspondingly far behind above is extended. The main body part can now be butted onto this backrest will. It is not necessary here that this extended web always also has one Backrest forms, but @ he can. , be intended solely for the purpose of creating a To give away end plate for the main body part.

Airplanes were already with through-cranking of the through structural parts formed; these cranks were not down, but on the contrary, led upwards. In addition, however, was never in these cranks: a Motor or other part installed that was subject to heavy loads on it Cranking point the compressive stresses which are caused on both sides of the same the connected parts of the wing are created, as it were in themselves ; cancel and thus the. @Relieve the cranking point from these pressure loads would. In addition, by installing the engine in the manner outlined in this trough achieves that the engine wilt is lowered and thereby the torque, which by the driving force and its distance from the center of resistance during flight arises, is reduced and, if necessary, completely eliminated.

In the drawing, Fig. I is a front view of the aircraft according to FIG of the invention, some forward boxes of the deck itself being omitted.

Fig. 2 is a side view in partial white section.

Finally, Figure 3 is a perspective view of part of a Aircraft which is designed according to the invention.

It is believed that a monoplane is made of strong and lightweight Building material, for example aluminum or an aluminum alloy, by formation from box @a to a1 °, which form the wing, and over the entire span run through the wing, should be made. The boxes themselves are made of Butt and lower sheets that are as continuous as possible, bent on both sides and between which vertical webs d are arranged. c are transverse webs, if applicable To stiffen the box, d are rivets that are arranged to be inside of the wing profile and, if possible, flanges two adjacent one-axis Simultaneously connect the outer sheets with the interposed web. The foremost Box a is conveniently obtained by bending a single sheet. The single ones After all, castes are so constructed that each one for himself has what is allotted to him Part of the total load is able to bear, and the box plates therefore have different thickness, depending on the position which the associated box in the profile. occupies and what burden he therefore has to bear. e are rivets with which the rearmost Box is held together.

A container is also finely built in one of the continuous boxes, that by staying open a cover sheet a0, which at the same time is the load-bearing outer surface forms, after loosening screws c00, which are sunk in trough-like depressions attached, can be lifted out.

In particular, the front boxes are now according to the invention bent at the bottom so that a space for the crankcase - the engine g . arises.

As: a look at Fig. R shows that the two lateral ones would now be Parts of the wing are curved upwards during flight, or it would become the cranking point right and left are heavily stressed in bending. -But because the lower Part of the engine is located between the two side parts of the wing this is kept apart by the engine lower part, it is vvir from the right and left under pressure from the wing parts during flight, and these pressure forces, which are practically the same are now identical in the lower part of the engine and with the relief of the l #, '- röpfungssbelle almost completely exhausted.

Some other boxes, for example, a ¢ and a5, are also bent downwards and thus form my hollow. those used to accommodate the Driver's legs which serves on one or more the box further back can sit.

In order not to have to make this hollow too deep if necessary, are boxes behind it, e.g. B. @ a6, a7, something at the appropriate point raised, so arched upwards, so that a seat h is formed for the pilot will.

To stiffen these points in the deck, special, expediently vertical webs are drawn in, so they veAaufien in the direction of flight and in the example shown of a single-engine monoplane, it is also symmetrical to the plane of symmetry of the engine or the supporting deck.

The middle part of the cranking point is now designed so that . it initially develops the lowest air resistance. So it becomes a horizontal drip cross-section with the longitudinal axis in the direction of flight. One would make a horizontal cut through it along the line il (section 2) and make this cut by 90 °. in the Drawing plane. fold around, you would see the dot-dashed line in Fig. 2 and also cross-section marked il at this point: received. A-in The box can also be developed into projections a ° to a7 at the cranking point to which one can directly or indirectly, as will be described later, the Can attach organs for landing and moving the aircraft on the ground or water.

The hull k is advantageously formed by a tube attached to its rear end is flattened and the rudder 1, the elevator m and the Has spur r. In the case of larger versions, this tube will be assembled from sheet metal, How to recognize this Fig. 3 without further ado. leaves. At the point where the fuselage joins is to be connected to the wing, the former is so blended that one has it can easily slide tightly over the wing and attach to it.

The landing frame, in the example for landing on the ground, is here indirectly attached to the crank of the fuselage and consists of an intermediate element o appropriate horizontal drip cross-section into which the wheel p from 'below. plugged in and is thus partially protected against drafts. Side extensions @oi, vertical Drip cross-section, are symmetrical to the center plane of the wheel, and formed feathers g are attached to them on both sides, which come with them first when landing come into contact with the ground and thereby braking on the one hand, and additionally on the other have a resilient effect and reduce the impact when the aircraft touches the ground. Of course, the wheel p is also resiliently mounted in a suitable manner. Obviously have the springs have the further effect of preventing the aircraft from tipping sideways Landing and taxiing on the ground is avoided, and load for this purpose the approaches o 'accordingly far to the side.

Finally, the backrest n for the pilot and the end plate for the tubular fuselage are designed in the simplest way as an organic game with the rest of the wing in that, for example, the rear web b of the box, a7 in the figure from Fig. 2, 3 evident way is continued upwards.

Claims (1)

PATENT CLAIMS: i. Plane with self-supporting, if possible over the entire wing span of the aircraft continuous wing, characterized in, that individual continuous parts of the wing (spars or boxes) in their entirety to accommodate the engine and other parts in the middle down to a trough are cranked. Aircraft according to claim i, characterized in that at least some of the continuous load-bearing parts of the supporting deck at the cranking section indirectly or are extended directly to attach the landing gear. 3rd plane Nasch claim i, characterized in that behind -den to 'take up the legs of the pilot to a hollow through cranked parts by curvature at least a seat (h) for the top of some continuous load-bearing parts of the deck deck Pilot is trained. q .. Aircraft according to claim i or the following, characterized gekennzeichhet that a web of a continuous load-bearing part of the supporting deck is extended so far upwards that this creates a backrest (s) or end plate is formed for the main body part (k).