CS220148B1 - Two-slit flap extending mechanism - Google Patents

Abstract

The invention solves the possibility of extending the two-slot flap for takeoff as a single-slot flap and for landing as a double-slot flap. The essence of the invention lies in connecting the post-movement mechanism (lj) to one arm of a two-arm lever (3), rotatably mounted on the body of the front section (2) of the flap. The rear section (6) of the flap is hung in any way on the front section (2) of the flap and its movement is linked to the movement of the lever (3). The second arm of the lever (3) is provided with a guide element (4) slidably mounted in a guide (7), which consists of two parts. The first part (7'), the curvature of which corresponds to the curvature of the trajectory of the extension of the front section (2) of the flap, and the second part (7"), into which the guide (7) smoothly passes at its end and whose curvature corresponds to the path of the guide element (4) when the movement of the front section (2) of the flap stops. The invention can be used in all small transport aircraft.

Description

(54) Double-slot flaps ejection mechanism

The invention solves the possibility of extending the two-slot flap for starting as a single-slot and for landing as a two-slot.

SUMMARY OF THE INVENTION The principle of the invention consists in connecting the movement mechanism (11) to one arm of the two-arm lever (3) rotatably mounted on the body of the front section (2) of the flap. The second arm of the lever (3) is provided with a guide element (4) slidably mounted in a guide (7) consisting of two parts, the first part (7 ') of which the curvature corresponds to the curvature of the trajectory. extending the front section (2) of the flap and from the other part (7 "), in which the guide (7) passes continuously at its end and whose curvature corresponds to the path of the guide element (4) when stopping the movement of the front section (2).

The invention is applicable to all small airliners.

220

BACKGROUND OF THE INVENTION The present invention relates to a mechanism for disengaging double-slot flaps.

From the aerodynamics requirements it follows that in order to achieve a minimum drag coefficient with sufficient lift coefficient for take-off and increase in lift coefficient and drag for landing, it is preferable to extend the flap for start as a single slot and for landing as a double slot. Some aircraft do not meet this requirement at all, some achieve it by an autonomous system for ejection of the rear flap section, or so-called kinematic, that is using a kinematic mechanism, which extends the rear section for the start position relatively less than for landings, which significantly increases. rear flap section with a small increase in deflection of the front flap section. These mechanisms are very complex, heavy, or need more ejection force, which again results in more weight.

These disadvantages are eliminated by the mechanism of the double-slotted flap guided in the guide of curvature identical to the curvature of the trajectory of the front flap section according to the invention, which consists in that the two-arm lever is rotatably mounted on the front flap section. , with the movement of the rear section of the flap and one arm of which is connected to a movement mechanism, such as a rod or screw strut, while the other arm of the lever is provided with a guide element slidably mounted in a guide consisting of two parts with different curvature the curvature of the first part of the guide corresponds to the curvature of the trajectory of the front section of the flap and the curvature of the second part of the guide, in which the guide passes smoothly at its end, corresponds ideally to the curvature of the guide track.

The advantage of the proposed mechanism is to achieve a simple way of sliding the flap for the start as a single slot and for landing as a double slot.

An exemplary embodiment is schematically shown in the attached drawing.

On the body of the front flap section 2, a two-arm lever 3 is rotatably mounted, the movement of which is tied by a rod 5 with the movement of the rear flap section 6, hinged in any manner, e.g. One arm of the two-arm lever 3 is connected to a movement mechanism 1 formed by a screw strut, the other arm of the lever 3 is provided at its end with a guide element 4 slidably mounted in the guide 7. The guide 7 consists of two parts 7 ', 7' the curvature of the first part 7 'corresponds to the curvature of the trajectory of the extension of the front section of the flap 2 and the curvature of the second part 7', in which the guide 7 continuously passes at its end flaps and other movement of the movement mechanism.

To extend the start flap, where it is advantageous to achieve the flap ejection as a single-slot, the guide element 4 moves along the first part 7 'of the guide 7. The lever 3, the front section 2 of the flap and the rear section 6 maintain the same position 4 is guided by a guide of curvature identical to that of the front section 2 of the flap. In the event of a landing, by the action of the movement mechanism 1, the guiding element 4 is moved to the second part 7 of the guide 7 a. rear section 2, & flaps.

The invention is applicable to all small airliners.

Claims (1)

SUBJECT Mechanism of ejection of a two-slot flap guided in a guide of curvature identical to the curvature of the trajectory of the front section of a two-slot flap, characterized in that the body of the front section (2) of the flap is rotatably supported by a two-arm lever (-3). 5), with the movement of the back section (6) of the flap and whose one arm is connected to a movement mechanism [1], eg formed by a rod or screw strut, while the other arm of the lever (3) is provided with a guide element (4) ) slidably mounted in a guide (7) consisting of two parts (7 ', 7') with different trajectory curvature, the curvature of the first part [7'J of the guide (7) corresponding to the curvature of the front section extension flap (2j) and the curvature: the second part (7 ") of the guide (7), in which the guide (71 continuously passes at its end), corresponds in an ideal state of curvature of the path of the guide element (4) for stopping the drive the front section (Z) of the flap.