DE674938C - Fixed bumper connection at the surface connection of collapsible aircraft surfaces - Google Patents

Description

GERMAN EMPIRE

ISSUED ON
APRIL 26, 1939

REICH PATENT OFFICE

PATENT LETTERING

CLASS 62 b GROUP 5o4

P83915X1162})

iff Heinz Hollstein in Kassel

has been named as the inventor.

Fieseler-Flugzeugbau G.m.b.H. in Kassel-Bettenhausen

Patented in the German Empire on November 5, 1937 Date of publication of the patent grant: April 6, 1939

The present invention relates to a fixed bumper connection at the surface joint of folding aircraft surfaces in the special training that the connection of the bumpers by two one or two-armed levers to which the bumpers are articulated is formed which are rotatably mounted at one point when the surface is folded in, and one of them is a lever

ίο on a sliding guide ο. like. on one Area, e.g. B. the collapsible surface is hinged, while the other lever is fixed on the other surface, e.g. B. the stationary surface, is rotatably mounted, and that In addition, both levers are articulated to one another at a common pivot point are.

'A design in which the bumpers do not work when the wings are folded down need to be separated is known. In this case, however, the areas in front of the Folding in must first be rotated around a pivot point. The bumper is through this Pivot point passed through. For the commonly used version where the On the other hand, aircraft surfaces are folded in by pivoting around a pivot point a fixed bumper connection has not yet become known, so that in sol-, chem FaE- before folding in, the bumpers always had to be separated 3 ».

The bumper connection according to the invention, however, not only provides a solid, inseparable coupling between the bumper part in the fixed surface part and between the bumper part in the collapsible surface part, but also allows through a corresponding:} Connection of the bumpers to the levers between the bumpers the production of any translation.

The invention is illustrated in the drawing, namely show

Fig. Ι a system drawing with the control stick in the middle position in the folded-in and folded-in position State of the surface, Fig. 2 a system drawing with "off"; struck joystick (end position) ';' 'ίίι

folded and folded state of the flat Fig. 3 is a schematic representation of the

Folding an aircraft wing and

Fig. 4 is a schematic representation of the ίο power transmission lovers.

The fixed surface α has a pivot point c, around which the surface b is arranged so that it can be folded up. The fixed surface «has a fixed bearing d and the foldable surface b has a sliding guide ί?. A lever is hinged to the bearing and a lever g is hinged to the sliding guide e. When the wing & is folded, the levers / and g can be rotated about the same point, ie the bearing and the sliding guide e are in this position of the wing b one above the other or one inside the other (in the latter case one of the levers had to be designed as a fork). The levers / and g are articulated to one another at the pivot point h. On the lever / is the bumper; and the bumper k is hinged to the lever g. By choosing the position of the connection point of the bumper I on the lever / any number of translations is possible.

The following is the operation of the subject invention described:

Control stick in middle position (see Fig. 1). When the surface d is folded around the pivot point, the other swivels at the same time. The same lever g mounted by means of the sliding guide e around the pivot point h on the circular arc /. The kinematic difference that occurs due to the distance between the fulcrum h from the ₊₀ fulcrum of the surfaces «and b when the surface b is folded in is compensated for by the sliding guide e. The further occurring difference m is compensated for by a corresponding deflection of the rudder actuated by the push rod k (Fig. 3). The rudder «as well as the control stick are blocked when the surfaces & are folded up.

Control stick deflected, levers / and g in rest position (Fig. 2).

If, with the control stick in this position, the area δ is folded in around the pivot point, the lever g pivots around the pivot point h. The sliding guide e moves on the circular arc / up to the point ■ At point 0 , the sliding guide e , which compensates for the kinematic "" difference of the system, encounters a movement limit (circular arc ;;). When the surface b is pivoted further, the lever / swings back around its pivot point at the fixed bearing d , and the sliding guide e moves around the pivot point h on the circular arc #. This position of the system then remains until the surface b is completely folded in. By then folding in the opposite surface, the lever / is pulled back into the central position, while the sliding guide e yields the same way. This end position corresponds to the process in Fig. I. The rudders and the joystick are blocked.

The distance (s) of the pivot points c and h from one another determines the size of the rudder deflection when the surface b is folded in and the size of the sliding guide e.

The most favorable case for the implementation of the object according to the invention would be if the distance m = 0 .

Claims (1)

Claim: Fixed bumper connection at the surface connection of folding aircraft surfaces, characterized in that the connection of the bumpers (i and k) is formed by two one or two-armed levers (/ and g) to which the bumpers (iuadk) are hinged, which when folded Surface (&) are rotatably mounted in one point and one of the levers (g) on a sliding guide (e) or the like. B. the foldable surface (&), while the other lever (/) is fixed to the other surface, e.g. B. the stationary surface (a), is pivotally mounted, and that both levers (/ and g ) are articulated to each other in a common pivot point (Ji). 1 sheet of drawings ßEfttt! *. GfebBUCKT lh tofeu M-ICHsbnUäKfertB