DE665082C - Swing plane propulsion with wings that automatically adapt to the resulting air flow - Google Patents

Description

The purpose of the invention is to achieve an even and good buoyancy Propulsion in swing aircraft known indispensable automatic adjustment S the wing and sash parts to the resulting air flow through an inevitable control the aileron flaps.

It is known in swing planes that the swing axes of the wings are parallel to the To arrange fuselage longitudinal center axis and this storage about a second axis transverse to To make flight direction adjustable. Here two axes are needed to support the wings of the to adapt the resulting air flow.

According to the invention, each wing is mounted only in a swing axis that with the Fuselage of the aircraft is firmly connected; the wings can also have a common axis of oscillation. A twist of the Wing around a transverse axis is only achieved in that the wing bearing with the fuselage longitudinal center axis in the vertical plane forms an acute angle which is open to the front. The wings are then raised backwards relative to the fuselage moved upwards and downwards when lowering, at the same time a lift resp. Shift in the center of gravity occurs and the aircraft's longitudinal axis merges with the wing movement synchronous vertical oscillation is brought. At the same time, the outer wing parts (aileron flaps) are supported by the Drive linkage of the sashes automatically in the same direction, more in the middle positions, in the Fewer end positions, swiveled; the type of pivoting can be determined by the pilot can be set differently on both sides by means of a known aileron control. Compared to the known measure of placing the wing oscillation axes so that their center lines intersect in front of the aircraft and so to lead the wing from the front up to the rear down during precipitation, whereby the wings a larger one when they are lifted

Have to cover distance than when lowering, with the swing axis arrangement according to the invention, the wing hits the air with greater speed a, ts | during precipitation ^: at the serve; also, the path of the NiS strike through the air is longer than the dfe | High impact. ^: ' ^:

Compared to the highly elastic swing wings, the subject of the invention has the

ίο advantage that the wings after experience can be carried out in rigid aircraft construction.

An example of the subject matter of the invention is shown in three figures. According to Fig. Ι the wings a, which are tensed with the fuselage in a known manner, are mounted in a swing axis c attached at an acute angle α to the fuselage center axis b of the aircraft, so that the wing moves slightly backwards when it is raised and slightly forwards when it is lowered . The resulting vertical oscillation of the longitudinal axis p of the aircraft is dependent on the size of the wing stroke, which is caused by known drive levers d by means of the rods e . At the highest wing position, the aircraft is forward-heavy and wing precipitation begins with a downward trajectory.

Fig. 2 shows the drive mechanism of the wings during precipitation. The rods e are pulled down at the same time by a force and bring the lever / to the stop at g , whereby the outer wing parts p are rotated in the same direction through the connection h upwards before the wings α flap downwards. At the bottom dead center of the wings, the aircraft is somewhat rearward due to the inclination of the wing oscillation axis c, and the trajectory is rising when the wing starts to flip. As soon as the driving force pushes the rods e upwards, the levers f are rotated so that they rest against the stops i by turning the outer wing parts p in the same direction downwards, whereupon the whole wings flap upwards.

In addition to the levers /, the bearing journals I each have a second lever k, which can be adjusted in opposite directions in a known manner by the aileron linkage ο. To also;. any adjustment of the outer wing 'rush, to enable the stops g "^ & i-i and springs are m, the Hebelf in the | attributed Littel location between g and i, • | ^$: i £ uf these levers k attached. The points of application η of the known aileron linkage ο on the levers k lie outside the wing oscillation axis c, which automatically counteracts the outer wing parts when the wings approach the upper or lower end position. Fig. 3 shows a wing according to the invention in plan. In order to allow the individual parts of the wings to cling even more closely to the air flow and to avoid vortex formation, they can also be designed to be elastic in a known manner with this automatic control.

Claims (2)

Patent claims: 1. Swing aircraft drive with wings automatically adapting to the resulting air flow, the swing axes of which form an acute angle with the longitudinal central axis of the fuselage, characterized in that the acute angle (μ) between the central longitudinal axis of the fuselage and the two wings common swing axis is open at the front in a vertical plane and the connecting rod (e) each wing (ß) of a crank mechanism common to both wings (d) simultaneously controls an aileron (p) via a (g, i) linkage (f, I, h) that is limited in its movement so that it moves upwards when the wings are down , swings down when the wing is upstroke. 2. Swing drive according to claim 1, characterized by a fork-shaped and oscillatable design of the limiting members (g, i) and the articulation of their inner ends located at a lateral distance from the swing axis to a lever (n, 0), which differentiate the limiting members on both sides allowed to set. 1 sheet of drawings