JPH01289799A - Active aerodynamic elastic tailoring - Google Patents

Abstract

PURPOSE:To enable the twisting angle of a wing to be changed to an optimum value by providing a rudder face capable of producing an aerodynamic force in the up-and- down direction in accordance with the steering angle, at least on one side of the front and rear of the wing in the vicinity of the wing end of an air-craft, and controlling the steering angle as the function of the angle of incidence, Mach number, or the like at the time of flight. CONSTITUTION:A missile launcher 5 is provided to the wing end of the main wing 1 of an aircraft, and also at the front and rear thereof, small rudder faces 2, 3 are provided so as to be turnable around axes in the right and left direction. Further, in the same way as before, a small rudder face 4 and a propeller fan 8 are provided on the rear peripheral side of the main wing 1, and they are intended to be used at the time of normal flight as well as taking off and landing. And it is constituted so that the small rudder faces 2, 3 can be inclined or elevated by an actuator 6 which is operated by the command from a computer 7 in which calculation is carried out making a function of the angle of incidence alpha, Mach number M, and dynamic pressure q at the time of flight. Thus, an optimum main wing twisting angle can be obtained in a relatively wide range of flight, enabling the enhancement in the flight performance to be achieved.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a device that optimizes the torsion angle of a main wing according to flight conditions.

[Conventional technology]

In an aircraft, there is an aerodynamically optimal wing twist angle (difference between the angle between the wing tip and the wing root) depending on the angle of attack and the number of blades. It is desirable to maintain this twist angle at an optimum level during flight.

Although optimization of the main wing torsion angle has not previously been performed on a commercial aircraft, similar research has been conducted. However, in this case as well, for example, as shown in Fig. 6, the characteristics of the main wing 1 made of composite material and the torsional moment of the missile launch 5 with a protruding wing tip can be utilized to find the optimum flight condition for a given flight condition. It is not necessarily close to optimal under other conditions.

[Problem to be solved by the invention]

The above-mentioned conventional wing for controlling the twist angle of the wing had the following problems to be solved.

That is, since the conventional wing is deformed passively due to its structure, the range of optimal flight conditions is narrower than that under active control.

(Means for Solving Problem 11) As a means for solving the above problems, the present invention provides an aerodynamic force in the vertical direction depending on the steering angle on at least one side of the front and rear sides near the tip of the wing of an aircraft. a control surface provided to enable the generation of
Active aerodynamics characterized by comprising means for controlling the rudder angle of the control surface as a function of the angle of attack, Matsuha number and dynamic pressure during flight, and changing the torsion angle of the wing to the optimum value for flight. It is intended to provide elastic tailoring.

[For production]

Since the present invention is configured as described above, it has the following effects. That is, when looking at the wing section near the wing tip, the control surface that generates vertical aerodynamic force is provided at the front or rear of the wing section, or at both front and rear sides.

An upward or downward force is generated at a position near the center of the radius of rotation of the blade cross section (center of torsional moment).

Gives twist to the wing. That twist! The 11 degree angle is controlled to be the optimum value for the flight conditions at the time, so the aircraft can always fly with the most desirable wing twist angle.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 5.

In Figure 1, a missile launcher 5 is mounted on the wing tip of the main wing 1.
is provided, and small control surfaces 2 and 3 are provided in front and rear thereof so as to be rotatable around an axis in the left and right direction. In addition, a small control surface 4 and a control surface 40 8 having the same purpose and structure as the conventional aircraft are provided on the trailing edge side of the main wing 1, and are configured to perform normal flight, takeoff and landing. As shown in FIG. 2, the minor control surfaces 2 and 3 are raised and raised by an actuator 6 that operates in response to a command from a combiator 7 that is calculated as a function of the angle of attack α, Matsuha number M, and dynamic pressure q during flight. It is configured like this. In the above configuration, for example, the third
As shown in the figure, when the minor control surface 2 is steered downward by δT and the minor control surface 3 is steered by δT upward, a downward force is generated on the minor control surface 2 and an upward force is generated on the minor control surface 3 aerodynamically. , the missile launcher 5 receives a counterclockwise couple at the front and rear, and generates a moment as shown by M in the figure. Missile launcher 5 is the main 'fiL'
1, the blade tip is twisted, and a twist angle θ is created between the Wt tip and the root of the blade as shown in FIG. 4. Combiator 7 has an angle of attack α.

Using the Matsuha number M and the dynamic pressure q as inputs, the actuator 6 is given a command necessary to generate a corresponding moment at the blade tip in order to realize the torsion angle θ. FIG. 5 shows a conceptual diagram of calculations and commands when the shape and structure of the main wing 1 are constant. Note that FIG. 4(a) is a left side view qualitatively showing the case where the twist angle θ is small, and FIG. 4(b) is a left side view qualitatively showing the case when the twist angle θ is large.

Although the embodiment has been described above as an example in which the small control surfaces are provided at the front and rear ends of the missile launcher, the invention is not limited to this.
It may be provided directly at the wing tip, via an appropriate structure, slightly inward from the wing tip, or in any other suitable configuration.

However, the wing tip is better for imitation efficiency.

〔Effect of the invention〕

Since the present invention is configured as described above, it has the following effects. In other words, by driving the control surfaces attached to the front or the rear near the wing tips, or both, in a function of the angle of attack, Matsuh number, and dynamic pressure, the optimum main wing torsion angle can be achieved over a wider flight range than by mere passive tailoring. This significantly improves flight performance.

[Brief explanation of the drawing]

FIG. 1 is a plan view of the right wing of an aircraft equipped with an embodiment of the present invention, FIG. 2 is a schematic configuration diagram of an embodiment of the control surface drive logic, and FIG. 3 is a ■A diagram illustrating the steering of the small control surface in a cross section in the direction of arrows. FIG. 4 is a left side view of the aircraft illustrating the magnitude of the torsion angle of the main wing 1 according to the above embodiment, and (a) shows the case where the torsion angle is small. , (b) are diagrams each showing a case where the twist angle is large. The fas diagram is a conceptual diagram when calculating and transmitting a driving actuator signal for steering the small control surface of the above embodiment, and is the sixth diagram.
The figure is a plan view of the right wing of a conventional example. l...Main wing 2.3.4...Small control surface 5.
... Missile launcher 6... Actieator 7... Combiator 8...
・Flaperon

Claims (1)

[Claims] A control surface is provided on at least one of the front and rear sides near the tip of an aircraft wing so that an aerodynamic force can be generated in the vertical direction according to the rudder angle, and the rudder angle of the same control surface is controlled during flight. active aeroelastic tailoring, characterized in that it comprises: means for controlling the angle of attack of the wing, the Mach number and the dynamic pressure of the wing and changing the torsion angle of the wing to an optimum value for flight;