JPH0640398A - Rudder plate of high-mobility aircraft - Google Patents

Abstract

PURPOSE:To enable steering of an aircraft at a low speed even if the speed is lower than stalling speed by providing rudder plate attaching portions rotatably provided around rotary shafts parallel to an axis and a plurality of rudder plates approximatery axial symmetrically provided on the rudder attaching portions so as to be able to move inresponse to the rotation, and respectively having the rotary shafts for steering. CONSTITUTION:When an aircraft 1 flies at a high attack angle, back wash 21 is generated because the air flow around the aircraft 1 is disturbed. Generally, since rudder plates do not effectively function in the back wash, rudder plates 7a, 7b are placed outside the back wash 21 on both upper and lower faces of the body of the aircraft by rotating rudder plate attaching portions 6. When the steering is performed in this state, sufficient stability and controllability can be obtained because the rubber plates 7a, 7b function without being affected by the back wash 21. However, in the range of low speed lower than stalling speed of a main wing 5, the rudder plates 7a, 7b are swung by the rotation of the rudder plate attaching portions 6, and the steering can be performed by generated aerodynamic force. So that, the steering can be performed by rotating the rudder plate attaching portions 6 around the rotary shaft 11, and the rudder plates 7a, 7b around the rotary shafts 8a, 8b.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a control surface of an aircraft, in particular, an aircraft having high mobility.

[0002]

2. Description of the Related Art A perspective view of a conventional aircraft is shown in FIG. As shown in the figure, the conventional aircraft 1 is provided with a canard wing 2 in front of the main wing, a vertical tail 3 is enlarged, and engine thrust is increased in order to ensure stability and maneuverability even at a high angle of attack or a main wing stall. High maneuverability is attempted by providing a thrust deflector 4 for tilting.

[0003]

The control surface of the conventional high-mobility aircraft has the following problems to be solved.

That is, the effect of the canard wing and the large vertical tail used in the conventional aircraft is significantly reduced in the low speed region near the stall speed. Therefore, it is necessary to make the area large enough to be effective even in the low-speed range, which causes a problem such as an increase in the body weight and an increase in the radar reflection area. Further, in order to control the attitude of the vehicle body by using the thrust deflector of the engine, an engine having a thrust larger than usual is required, so that there is a problem that economical efficiency at the time of cruising is deteriorated.

It is an object of the present invention to provide an aircraft control surface which is not affected by the wake of the airframe even at a high angle of attack and which can maintain maneuverability even at a stall speed or less.

[0006]

As a means for solving the above-mentioned problems, the present invention has a control surface mounting portion having a rotary shaft parallel to the axis of an aircraft and rotatably provided around the rotary shaft. A highly maneuvering control surface for a highly mobile aircraft, comprising: a plurality of control surfaces which are provided on the surface mounting portion substantially axially symmetrically and capable of responding to the rotation thereof and each independently have a rotation axis for steering. Is to provide.

[0007]

Since the present invention is constructed as described above, it has the following actions.

That is, a rudder surface mounting portion that is rotatable about an axis parallel to the machine axis, and a plurality of rudder surfaces that are substantially axisymmetrical to the rudder surface mounting portion and that are rotatable according to the rotation of the rudder surface mounting portion. Therefore, in the event of a high-angle-of-attack flight, when the airflow is disturbed by the wake of the aircraft and the effect of the control surface is reduced, the control surface mounting part is rotated around its axis to allow multiple control surfaces to interact with each other. When the steering is performed with the tip of the rudder face outside the wake, the steering can be performed without being affected by the turbulence of the air flow.

Further, when the effect of the control surface is reduced near the stall speed due to the small velocity of the air flow around the control surface, the control surface acts when the control surface is swung around an axis parallel to the machine axis. The attitude of the aircraft can be controlled by aerodynamic force.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. FIG. 1 is a perspective view of an aircraft provided with a highly maneuvering control surface for an aircraft, FIG. 2 is an enlarged vertical sectional view of a control surface mounting portion 6 of FIG. 1 (a sectional view parallel to the machine axis), and FIG. FIG. 3 is a perspective view of the A enclosure of FIG. 2.

In these figures, 1 is an aircraft, 5 is a main wing, and 6 is a rudder surface mounting portion for mounting the rudder surfaces 7a and 7b on the main wing 5 so as to be rotatable around an axis parallel to the axis of the aircraft 1.
Reference characters a and 7b are rotatable surfaces around the rotary shaft 11 of the control surface mounting portion 6, and the rotary surfaces 8a and 8b are rotatable (steerable) within a predetermined range. Rotating shafts of the rudder surfaces 7a and 7b, 9 is a rotating portion for steering the rudder surface 7b, 10 is a rotating portion for steering the rudder surface 7a, 11 is a rotating shaft (axis center) provided parallel to the machine axis, 12 is the rotating unit 1
0 is a non-rotating portion for moving (sliding) 0 in the required range in the direction of the rotating shaft 11, 13 is a non-rotating portion for similarly moving the rotating portion 9 in the required direction in the direction of the rotating shaft 11, 14 is the rotating portion 9 A rack having a key-like protrusion, the main part of which is parallel to the rotary shaft 11 and teeth for engraving the bevel gear 15 to rotate in a pinion fashion, 15 is the direction of the rotary shaft 11 of the rack 14. Is a bevel gear that rotates in a pinion shape when moving to a bevel gear 1 at the base end of the rotating shaft 8b.
5, receives the rotation, and rotates the control surface 7 around the rotary shaft 8b.
This is a bevel gear for rotating (steering) b.

As shown in FIGS. 1 and 2, the rudder surfaces 7a and 7b are provided substantially symmetrically with respect to the rotary shaft 11, and the mechanism for steering them is the same except for some sizes. In order to avoid redundancy, the structure will be described representatively on the control surface 7b side, and detailed description of the control surface 7a side will be omitted.

Next, the operation of the above configuration will be described. In FIG. 1, when the aircraft 1 flies at a high angle of attack, the aircraft 1
The flow of the surrounding air is disturbed and a wake 21 is generated. Generally, since the rudder surface does not function effectively in the wake, in this embodiment, the rudder surface mounting portion 6 is rotated to bring the rudder surface 7a and the rudder surface 7b out of the wake 21 on the fuselage and the lower surface, respectively. If steering is performed in this state, the rudder face 7a, without being affected by the wake 21
Since 7b functions, sufficient stability and maneuverability can be obtained. Further, in the low speed range below the stall speed of the main wing 5, the rudder surface attachment portion 6 rotates to swing the rudder surfaces 7a and 7b, and the generated aerodynamic force is used for steering. Steering is performed by rotating the control surface mounting portion 6 around the rotary shaft 11 and rotating the control surfaces 7a and 7b around the rotary shafts 8a and 8b, respectively.

Steering of the rudder surface 7b is performed by sliding the non-rotating portion 13 of FIG. 2 back and forth along the rotary shaft 11. When the non-rotating part 13 is slid back and forth, the rotating part 9 connected through the bearing slides back and forth, and this movement causes the control surface 7b to rotate around the rotating shaft 8b through the rack 14 and the bevel gears 15 and 16. Let Similarly, the movement of the non-rotating portion 12 moves the rotating portion 10 to rotate the control surface 7a around the rotating shaft 8a via the rack and the bevel gear.

Rotation about the rotary shafts 11, 8a, 8b,
Sliding and the like can be controlled independently.

As described above, according to the present embodiment, since the rudder surface mounting portion 6 is rotated around the axis of the rotary shaft 11 to make the rudder surfaces 7a and 7b substantially vertical and the steering can be performed, the rudder effect can be obtained even at a high angle of attack. Has the advantage of not decreasing.

Further, there is an advantage that the attitude control can be performed by swinging the control surface mounting portion 6 even at a low speed and in a state close to a stall.

[0018]

Since the present invention is constructed as described above, it has the following effects.

That is, since the rudder surface mounting portion can be rotated about its axis and the rudder surface provided symmetrically can be made substantially vertical, the rudder surface is brought out of the wake at a high angle of attack. Steering is possible, and the effectiveness of the rudder does not deteriorate depending on the angle of attack.

Further, even at a low speed equal to or lower than the stall speed, the aerodynamic force generated by swinging the control surface can be utilized for steering.

[Brief description of drawings]

FIG. 1 is a perspective view of an airframe including a control surface for a highly mobile aircraft according to an embodiment of the present invention.

FIG. 2 is an enlarged vertical sectional view of a control surface mounting portion 6 of FIG.

3 is a perspective view of the A enclosure of FIG. 2. FIG.

FIG. 4 is a perspective view of a conventional example.

[Explanation of symbols]

 1 Aircraft 6 Rudder surface mounting part 7a, 7b Rudder surface 8a, 8b Rotating shaft 9,10 Rotating part 11 Rotating shaft 12,13 Non-rotating part 14 Rack 15,16 Bevel gear

Claims (1)

[Claims] 1. A control surface mounting portion having a rotation axis parallel to an aircraft axis and rotatably provided around the axis.
A high maneuvering aircraft, characterized in that it is provided with a plurality of control surfaces which are provided in the control surface mounting portion substantially in axial symmetry and are capable of responding to the rotation thereof and each independently has a rotation axis for steering. Control surface.