RU2549593C2 - Flap for short takeoff and landing aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. This flap comprises main link, deflector, carriages with support rollers and flap displacement guide rails. Main link top part has stiff panels articulated therewith whereto connected are tie-rods articulated with rotary board levers via panel drive rocker and mid tie-rods. Said panel is arranged at flap main link front while rotary board levers are articulated via turn tie-rods with release/retract mechanisms.

EFFECT: higher lift.

11 dwg

Description

The invention relates to aircraft, in particular to means of mechanization of the wing of a short take-off and landing aircraft, and can be used in the construction of aircraft.

A known wing design with a single-slot flap mounted on rotary rockers, rigidly connected to the flap and mounted on the brackets of the linkage mechanization [1].

The disadvantage of this design is the low efficiency of the flap itself, which provides a well-defined increment of lift, depending on the increment of the area and curvature of the wing obtained by deflecting the flap of a particular chord.

A known design of a double-slotted flap [2] with a system for installing on the wing and cleaning - release in the take-off and landing position.

The disadvantage of this technical solution is the relatively low efficiency, depending on the specific parameters of the flap links, aerodynamic gap parameters, the increment of the wing area (when the flap is released) and the installation angle in the take-off and landing position.

The closest but technical essence to the claimed object is a wing with a Fowler flap installed by means of carriages and rollers on rails, providing a significant exit of the flap into the note, significantly increasing the lifting force by increasing the area and curvature of the wing [3].

The disadvantage of this design is the low stiffness of the tail of the wing, due to the placement of the Fowler flap, and limited efficiency aerodynamic gap parameters.

The invention is aimed at improving the efficiency of the wing flap of a short take-off and landing aircraft.

This is achieved by the fact that in the upper part of the main link of the flap with a deflector rigid panels are movably mounted along the guides, to which the rods are articulated, and the rods themselves. through the rocker drives of the drive, the panels and intermediate rods are pivotally connected to the levers of the rotary flap, the latter being pivotally mounted in the bow of the main link of the flap, and the levers of the rotary flap, through the rotary rods, are pivotally connected to the cleaning-release mechanism.

The invention is illustrated by drawings, where figure 1 shows a wing when viewed from above on a cruising flight mode; figure 2 - section aa in figure 1 (the flap is removed); figure 3 is a section aa in figure 1 (the flap is released); figure 4 is a section bB in figure 1 (the flap is removed); figure 5 is a section bB in figure 1 (the flap is released); in Fig.6 - node K in Fig.4; in Fig.7 - node And in Fig.5; in Fig.8 is a section bb in Fig.1; figure 9 is a cross section GG in figure 5; figure 10 is a cross section DD in figure 5; Fig.11 is a cross-section EE in Fig.8.

The flap 1 of the wing 2 of the short take-off and landing aircraft consists of the main link 3 and the deflector 4. The bit mechanism 5 for cleaning and releasing the flap 1 through the rotary link 6 is movably connected to the rigid lever 7 of the rotary flap 8 pivotally mounted in the bow of the main link 3. When this lever 7, through the intermediate rod 9, is connected movably to the rocking arm 10 of the panel drive 11. The other rocking arm 10, through the rod 12 of the panel, is pivotally connected to the bow of the movable panel 11, which is installed along the rails in the upper part of the main link 3 flap 1 by vertical upper rollers 13 and lower 14 and the horizontal rollers 15. The flap 1 is mounted movably on rails 16 by means of the carriages 17 with the upper rollers 18 and lower rollers 19.

In the extreme position of the take-off and landing modes, the rotary flap 8 has a limit stop 20, which determines and fixes the required angle of rotation of the flap 8 and the offset value of the movable panel 11 (Fig. 5; 7).

In addition, the flap 1, in the extreme position of the take-off and landing modes, is limited in movement along the rails 16 by the stops 21 (Fig. 8) interacting with the carriages 17 of the flap 1.

Flap short take-off and landing works as follows.

In take-off and landing modes, the double-slotted flap 1 is extended by screw mechanisms 5 along the rails 16 to the extreme position limited by the stops 21 of the carriages 17 of the flap 1.

In this case, through the swing rods 6, the rigid levers 7 of the shield 8, the intermediate rods 9, the rockers 10 and the rods 12, the movable panel 11 (Fig. 5; 7) is advanced along the guides of the main link 3 of the flap 1, by means of the vertical upper rollers 13, the lower ones 14 (figure 9) and horizontal rollers 15 (figure 10), in the extreme (takeoff and landing) position, increasing the chord and curvature of the wing. At the same time, the rotary flap 8, pivotally mounted in the bow of the main link 3 of the flap 1, is deployed to the required position, opening the aerodynamic channel between the main link 3 and the deflector 4 of the flap 1, changing the geometry of this channel and increasing its efficiency. In this case, the flow rate at the exit from the aerodynamic channel between the main link 3 and the deflector 4 of the flap 1 is significantly increased.

Thus, in the take-off and landing modes, due to the extension of the movable panel 11 and the deviation of the rotary flap 8 to the required position, the chord and curvature of the wing are increased, and the flow velocity between the main link 3 and the deflector 4 is increased, which contributes to a significant increase in circulation speeds around wing 2, and consequently, a significant increase in the lifting force of wing 2 in these modes.

Information sources

1. Zhitomirsky G.I. "Aircraft Design". M .: Mechanical Engineering, 1991, p.134, Fig. 4.5 (g).

2. Patent RU 2187445 C1, 08/20/2002.

3. Zhytomyr G.I. "Aircraft Design". M.: Engineering, 1991, p.133, Fig. 4.4 (b).

Claims (1)

A flap of a short take-off and landing airplane containing a main link, a deflector, carriages with support rollers, flap guiding rails, cleaning-release mechanisms, characterized in that rigid panels are movably mounted in the upper part of the main flap link with a deflector along the guides, and the last the rods are pivotally fixed, and the rods themselves, through the rocker of the panel drive and the intermediate rods, are pivotally connected to the levers of the rotary flap, while the flap itself is movably installed in the nose of the main link a, a rotary flap levers, through rotating rod pivotally connected with the cleaning-release mechanisms.

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