JPH0478697A - Aircraft wing - Google Patents

Abstract

PURPOSE:To prevent the generation of flow breakaway around a rudder face provided rotatably behind a wing body by providing movable skirts extended from the rear edge of the wing body toward the rudder face, and interlocking these skirts with the movement of the rudder face. CONSTITUTION:The wing (a general term for a main wing, a horizontal tail and a vertical tail) of an aircraft is provided with a wing body 6, a fixed part forming the most part of the wing, and a rudder face 1 rotatable around a rudder face rotational center 2 is provided behind the wing body 6. An upper and a lower movable skirts 3, rotatable around hinges 4, extended backward toward the rudder face 1, are fitted to the rear edge parts of the upper and lower faces of the wing body 6. The rear ends 43 of an upper and a lower rudder face rods 8, 8' are pivotally fixed into the upper and lower positions in the vicinity of the front edge of the rudder face 1. The respective rudder face rods 8, 8' are extended frontward inside the wing body 6, and their front ends are connected to an actuator. The movable skirts 3 are driven interlockingly with the movement of the rudder face 1 so as to diminish a gap between the movable skirts 3 and the rudder face 1 and thereby to prevent the breakaway of flow around the rudder face 1.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aircraft wing having a control surface such as a main wing, a horizontal stabilizer, or a vertical stabilizer.

[Prior Art] As will be explained below, a conventional aircraft wing having a control surface, such as a main wing, a horizontal stabilizer, or a vertical stabilizer, is provided with a skirt at the front portion where the control surface is fixed.

Figure 9 shows the entire aircraft. In order to control the aircraft 13, an aileron 16 is attached to the main wing 15, an elevator 18 is attached to the horizontal stabilizer 17, and a rudder 20 is attached to the vertical stabilizer 19. In this specification, the fixed majority of the main wing 15, horizontal stabilizer 17, and vertical stabilizer 19 will be collectively referred to as the wing body, and the aileron 16, elevator 18, rudder 20, etc. will be collectively referred to as the control surface. The cross section is shown in Fig. 10. In FIG. 10, the control surface 1 is connected to the rear of the wing body 6, and can be rotated around the control surface rotation center 2 by upper and lower control surface rods 8, 8' serving as a control surface changing mechanism. He is able to control the aircraft 13 by gaining the effectiveness of the control surface 1. At the rear of the wing body 6, upper and lower skirts 3 fixed in front of the control surface 1 are provided, and the wing body 6 and the control surface 1
A seal 5 is provided between the two so that there is no gap.

As shown in Fig. 11, the effect 23 when the control surface 1 takes the rudder angle 22 is the force that increases when the control surface 1 takes the rudder angle 22 (Fig. 11 shows an upward force). Yes, it is used to control the aircraft 13, and the maneuverability of the aircraft 13 is evaluated based on this size. The hinge moment 24 refers to the moment of the control surface 1 around the rotation center 2 of the control surface, which is connected to the pilot's control force and is a very important evaluation item in the case of manual control.

[Problem to be solved by the invention] As shown in FIG. 11, in the conventional aircraft wing,
When the control surface 1 assumes a rudder angle 22, a large difference in level is created between the control surface l and the skirt 3, where the flow 10 generates separation 21, and the effect changes with respect to the rudder angle. It may cause a non-linear part as shown by the symbol a in Figure 12,
Regarding the change in hinge moment with respect to the steering angle, the first
This resulted in non-linearity as shown in Figure 3.

When there is such a nonlinear part, it requires a lot of effort for the pilot to operate, and in some cases,
It may not affect the safe flight of aircraft 13.

SUMMARY OF THE INVENTION An object of the present invention is to provide an aircraft wing that solves the above problems of conventional aircraft wings and allows a pilot to safely and easily operate the aircraft.

[Means for Solving the Problems: - The present invention provides a movable skirt that extends rearward from the trailing edge of the wing body toward the control surface in an aircraft wing that is provided with a rotatable control surface behind a large main body; A driving device is provided which drives the movable skirt in conjunction with the movement of the control surface and controls the distance between the movable skirt and the control surface.

[Effect]

In the present invention, when the control surface is operated, the movable skirt is driven in conjunction with the movement of the control surface to narrow the distance between the control surface and the movable skirt, thereby reducing the level difference between the control surface and the movable skirt. Separation of flow around the surface is prevented from occurring.

Therefore, the effect of the control surface on the rudder angle and the non-linearity of the hinge moment are eliminated, linearity is maintained, and the pilot can easily and safely operate the aircraft.

〔Example〕

A first embodiment of the present invention will be explained with reference to FIGS. 1 to 7.

6 is a wing main body which is a movable part that constitutes most of the wing (the main wing, horizontal stabilizer, vertical stabilizer, etc. are collectively referred to as the wing), and as shown in Fig. 1, there is a rotating control surface behind it. A control surface 1 (as described above, the aileron, elevation rudder, direction rudder, etc. are collectively referred to as the control surface) 1 is provided that can rotate around a center 2.

A vertically movable skirt 3 that is rotatable around a hinge 4 and extends rearward toward the control surface 1 is attached to the trailing edges of the upper and lower surfaces of the wing body 6 by the hinge 4.

Further, a seal 5 is provided between the front end of the control surface 1 and the center portion of the trailing edge of the wing body 6 in the vertical direction.

As shown in FIG. 4, a wiring 33 for transmitting signals from a control device 40 such as a control stick, stick, or pedal provided in the cockpit of the aircraft 13 is connected to a hydraulic system or an electric motor 32 (see FIG. 4). (shows the case where control surface 1 is an aileron)
. The rear ends 43 of the upper and lower control surface rods 8.8' are pivotally attached to upper and lower positions near the leading edge of the control surface 1, and the upper and lower control surface rods 8.8' move forward within the wing body G. It extends and its front end is connected to an actuator 30, 31 which is connected to said hydraulic or electric motor 32, respectively. As shown in FIG. 3, a small hole 36 extending in the axial direction of each control surface rod 8.8' is provided in front of the rear end 43 of each control surface rod 8.8', and each small hole 36 has a skirt rod 7. One end 39 of the same is slidably attached to the same skirt.

The other end 40 of the door is pivotally attached to the upper and lower skirts 3.

In this embodiment, as shown in FIG. 5, when the pilot 39 operates the control device 40, an electric signal is transmitted to the hydraulic device or electric motor 32 via the wiring 33, and the hydraulic device or electric motor 32 is activated. actuator 30.31
is activated, the control surface rods 8 and 8' move in opposite directions, and the control surface 1 takes a steering angle. As shown by arrows 42 and 37 in FIG. 3, the control surface rod 8 moves to the push side, and the rudder loft 8
' moves to the pulling side and operates so that the trailing edge of the control surface 1 is lowered, one end 39 of the upper skirt rod 7 slides in the small hole 36, and one end 39 of the lower skirt rod 7 slides in the small hole 36. It engages the rear end of the small hole 36 and moves with the control surface rod 8' in the direction of the arrow 37, the upper skirt 3 maintains its position, and the lower skirt 3 engages with the hinge 4 as shown by the arrow 38. It rotates around and the rear end is pulled up. As a result, as shown in FIG. 2, the control surface 1 and the lower skirt 3
The difference in level between the two is eliminated, and the airflow flows along the lower skirt 3 and the lower surface of the control surface 1 without causing separation, as shown by the arrow in FIG.

When operating to raise the trailing edge of the control surface 1, the position of the lower skirt 3 does not change, but the rear end of the upper skirt 3 rotates to lower the control surface 1 and the upper skirt 3. The difference in level is eliminated, and the airflow flows along the upper skirt 3 and the upper surface of the control surface 1 without causing separation.

Therefore, in this embodiment, as shown in FIGS. 6 and 7, linearity is maintained in the effect of the control surface and changes in hinge moment with respect to the rudder angle, making it possible to easily and safely maneuver the aircraft. .

A second embodiment of the present invention will be described with reference to FIG.

In this embodiment, the operation '41 of the control surface 1 and skirt 3 in the first embodiment is changed as follows.

That is, a skirt actuator 4849 connected to the hydraulic system or electric motor 32 is provided, and the front ends of the upper and lower skirt actuating rods 12.12' pivotally connected to the upper and lower skirts 1-3.3L are connected to the skirt actuators, respectively. Connected to 48.49.

In this embodiment, as in the first embodiment, the control surface 1 takes a steering angle as shown in FIG. 9 by the pilot's operation of the control device. The skirt actuators 48, 49 are actuated, and the skirt actuating rods 12, 12' move as indicated by arrows 5050' in FIG. Rotate 51 around 4 to eliminate the level difference between the skirt 3 and the control surface 1.
Separation of the flow along the upper and lower skirts 3 and the upper and lower surfaces of the control surface 1 can be prevented.

Therefore, in this embodiment as well, linearity can be maintained in the change in the effect of the control surface and the hinge moment with respect to the rudder angle, and the aircraft can be easily and safely operated. In addition, in this embodiment, by operating the upper and lower skirts 3 simultaneously, the gap between the front part of the control surface 1 and the skirt 3 can be reduced even when the control surface 1 is not at a steering angle. Furthermore, even when the steering angle is adjusted, the skirt 3 and the control surface 1 can be brought closer to each other to reduce the gap, so air resistance can be reduced.

[Effects of the Invention] As explained above, in the present invention, the movable skirt that extends rearward from the trailing edge of the wing body toward the control surface is driven by the drive device in conjunction with the movement of the control surface, and the movable skirt and By reducing the distance between the control surface and the control surface, separation of the flow around the control surface can be prevented, and linearity can be maintained in the effect of the control surface relative to the rudder angle and changes in the hinge moment 24, resulting in good aerodynamics. It can be a characteristic.

Therefore, it is possible to solve the problems of conventional wings with control surfaces and provide an aircraft that can be safely and easily operated by a pilot.

[Brief explanation of the drawing]

Fig. 1 is a schematic diagram of the first embodiment of the present invention, Fig. 2 is a schematic diagram of the same embodiment when the control surface takes a steering angle, and Fig. 3 is a schematic diagram of the skirt, skirt rod and An explanatory diagram of the control surface lot part, FIG. 4 is a plan view of an aircraft equipped with the same embodiment, FIG. 5 is an operational block diagram of the same embodiment, and FIGS. 6 and 7 show the same implementation with respect to the rudder angle, respectively. A graph showing the relationship between the effectiveness of the control surface and the hinge moment in the example, No. 8V is the overall view of the second embodiment of the present invention, and FIG. 9 is a perspective view showing the entire aircraft.
Fig. 10 is an explanatory diagram of the wing body and control surface of the aircraft, Fig. 11 is an explanatory diagram showing the control surface of a conventional aircraft, and Fig. 12 is an explanatory diagram showing the control surface of a conventional aircraft.
1 and 13 are graphs showing the relationship between the effectiveness of a conventional control surface and the hinge moment with respect to the steering angle, respectively. 1... Control surface 3 2... Control surface rotation center 3...
Skirt, 4... Hinge 5... Seal 1
6...Wing body 7...Skirt lot, 8.8
'... Control surface lot 12.12 '... Skirt actuation rondo l3... Aircraft 15... Main wing 16
...Aileron, 17...Horizontal stabilizer 18...Elevator,
19... Vertical stabilizer 20... Rudder, 22... Rudder angle 23... Effect, 24... Hinge moment 3031... Actuator 32... Hydraulic device or electric motor 39... Pyro 7) , 40... control device 48
49...Skirt actuator. Agent Patent attorney Sakama 2 outside hospitals Figure 1 ¥ 2 doctors Figure 3 Figure 6 Figure 7 Figure 49 Skirt actuator Figure 9 Figure 10

Claims (1)

[Claims] In an aircraft wing having a rotatable control surface behind the wing body, a movable skirt extends rearward from the trailing edge of the wing body toward the control surface, and the movable skirt is driven in conjunction with the movement of the control surface. An aircraft wing comprising a drive device for controlling a distance between a movable skirt and the control surface.