JP2016159737A - Flutter control device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve flutter limit occurring in wings of an air craft and expand a flight speed range.SOLUTION: A flutter control device has front control wings (22f) and rear control wings (22r) which are disposed at wing tip parts of wings (14) which move in a fluid and receive relative wind. Each front control wing (22f) is attached to the front side (an upstream direction of a mainstream) of a front end (EL) of the wing tip part. Each rear control wing (22r) is attached to the rear side (a downstream direction of the mainstream) of a rear end (ET) of the wing tip part.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a flutter control device disposed at a wing tip of an aircraft.

  Patent Document 1 (US Pat. No. 7,597,285) discloses a wing tip appendage that minimizes the induced resistance generated from the wing tip. The blade tip appendage described in Patent Document 1 controls the angle of attack of the blade tip appendage based on the detected deflection of the main wing.

US Pat. No. 7,597,285

  Improve flutter limits on aircraft wings and increase flight speed range.

  The means for solving the problem will be described below using the numbers used in the (DETAILED DESCRIPTION). These numbers are added to clarify the correspondence between the description of (Claims) and (Mode for Carrying Out the Invention). However, these numbers should not be used to interpret the technical scope of the invention described in (Claims).

  The flutter control device according to some embodiments includes a front control wing (22f) and a rear control wing (22r) disposed at the wing tip of the wing (14) that moves in the fluid and receives relative wind. . The front control blade wind pressure center (CPf) of the front control blade (22f) is disposed in front of the front edge (EL) of the blade tip. Further, the rear control blade wind pressure center (CPr) of the rear control blade (22r) is arranged behind the rear edge (ET) of the blade tip.

  In the flutter control device according to some embodiments, the direction of the lift generated by the front control blade (22f) and the direction of the lift generated by the rear control blade (22r) are the same direction.

  In the flutter control device according to some embodiments, the front control wing (22f) is disposed in front of the leading edge (EL) of the wing tip. The rear control blade (22r) is disposed behind the trailing edge (ET) of the blade tip.

  In the flutter control device according to some embodiments, the blade (14) has a bending vibration mode leading to the flutter and a torsional vibration mode leading to the flutter, and the frequency of the torsional vibration mode is the blade ( It shall increase according to the increase of the dynamic pressure acting on 14). Torsional vibration due to the direction of the torque to which the torsional deformation caused by the torsional vibration mode is to be restored and the lift generated at the wind pressure center of the front control blade (22f) and the rear control blade (22r) The front control blade (22f) and the rear control blade (22r) are arranged so that the direction of the dynamic pressure torque around the twist center of the mode is reversed.

  In the flutter control device according to some embodiments, the blade (14) has a bending vibration mode leading to the flutter and a torsional vibration mode leading to the flutter, and the frequency of the torsional vibration mode is the blade ( It shall decrease with the increase of the dynamic pressure acting on 14). Torsional vibration due to the direction of the torque to which the torsional deformation caused by the torsional vibration mode is to be restored and the lift generated at the wind pressure center of the front control blade (22f) and the rear control blade (22r) The front control blade (22f) and the rear control blade (22r) are arranged so that the direction of the dynamic pressure torque around the twist center of the mode is the same.

  In the flutter control device according to some embodiments, the flutter control device further includes a front support member (20f) and a rear support member (20r). The front support member (20f) is disposed at the blade tip and supports the front control blade (22f). The rear support member (20r) is disposed at the blade tip and supports the rear control blade (22r).

  In the flutter control device according to some embodiments, at least one of the front control wing (22f) and the rear control wing (22r) extends from the blade tip toward the outside of the wing (14). Yes.

  In the flutter control device according to some embodiments, at least one of the front control blade (22f) and the rear control blade (22r) extends from the blade tip toward the fuselage (12). .

  In the flutter control device according to some embodiments, the planar shape of at least one of the front control blade (22f) and the rear control blade (22r) is a swept blade shape.

  In the flutter control device according to some embodiments, the planar shape of at least one of the front control blade (22f) and the rear control blade (22r) is a delta blade shape.

  In the flutter control device according to some embodiments, at least one of the front control wing (22f) and the rear control wing (22r) includes a plurality of control wings.

  In the flutter control device according to some embodiments, the plurality of control blades are arranged in parallel to the cord direction (X-axis direction) and the span direction (Y-axis direction) of the blade (14).

  In the flutter control device according to some embodiments, the plurality of control blades are parallel to a cord direction (X-axis direction) of the blade (14), and one of the plurality of control blades and the blade (14) are arranged. The angle formed by the span direction is different from the angle formed by the other one of the plurality of control blades and the span direction of the blade (14).

  In the flutter control device according to some embodiments, the flutter control device further includes a forward linear motion guide portion (such as a linear guide LG) and a forward linear motion drive portion (such as a motor M and a worm gear WG). The front linear motion guide portion (linear guide LG or the like) guides the front support member (20f) so as to be movable in the cord direction (X-axis direction) of the blade tip. The forward linear drive unit (motor M, worm gear WG, etc.) drives the front support member (20f) in the cord direction (X-axis direction) of the blade tip.

  In the flutter control device according to some embodiments, the flutter control device further includes a rear linear motion guide unit (linear guide LG or the like) and a rear linear motion drive unit (motor M, worm gear WG, or the like). The rear linear motion guide unit (linear guide LG or the like) guides the rear support member (20r) so as to be movable in the cord direction (X-axis direction) of the blade tip. The rear linear drive unit (motor M, worm gear WG, etc.) drives the rear support member (20r) in the cord direction (X-axis direction) of the blade tip.

  In the flutter control device according to some embodiments, at least one of the front linear motion drive unit (motor M) and the rear linear motion drive unit (motor M) includes a front control blade (22f) and a rear control blade (22r). ) Is stored in at least one of the front storage part (40f) and the rear storage part (40r) formed on the front edge (EL) or the rear edge (ET) of the blade tip part. I do.

  In the flutter control device according to some embodiments, the flutter control device further includes a forward rotation guide portion (radial bearing RB, etc.) and a forward rotation drive portion (motor M, spur gear PG, etc.). The forward rotation guide portion (radial bearing RB) supports the front support member (20f) so as to be rotatable around the code axis (around the X axis) of the blade tip. The forward rotation drive unit (motor M, spur gear PG, etc.) rotationally drives the front support member (20f) around the code axis (X axis) of the blade tip.

  In the flutter control device according to some embodiments, the flutter control device further includes a rear rotation guide portion (radial bearing RB, etc.) and a rear rotation drive portion (motor M, spur gear PG, etc.). The rear rotation guide portion (radial bearing RB or the like) supports the rear support member (20r) so as to be rotatable around the cord axis of the blade tip (around the X axis). The backward rotation drive unit (motor M, spur gear PG, etc.) rotationally drives the rear support member (20r) around the code axis (X axis) at the blade tip.

  In the flutter control device according to some embodiments, the flutter control device further includes a relative speedometer (34) and a control device (30). According to the value of the relative speedometer (34), the control device (30) includes a front linear motion drive unit (motor M, worm gear WG, etc.) and a rear linear motion drive unit (motor M, worm gear WG, etc.). Or at least one of the forward rotation drive unit (motor M, spur gear PG, etc.) and the rear rotation drive unit (motor M, spur gear PG, etc.).

  In the flutter control device according to some embodiments, the flutter control device further includes a vibration meter (front vibration meter 32f, rear vibration meter 32r) and a control device (30). The vibrometers (front vibrometer 32f and rear vibrometer 32r) detect torsional vibrations of the wing (14). The control device (30) includes a front linear motion drive unit (motor M, worm gear WG, etc.) and a rear linear motion drive unit (motors M, M, etc.) according to the values of the vibration meter (front vibration meter 32f, rear vibration meter 32r). Drive control of at least one of the worm gear WG or the like, or at least one of the forward rotation drive unit (motor M, spur gear PG, etc.) and the rear rotation drive unit (motor M, spur gear PG, etc.). Drive control is performed.

  The flutter limit generated in the wing of an aircraft can be improved and the flight speed range can be expanded.

FIG. 1 is a plan view illustrating an embodiment in which a flutter control device having a front control wing and a rear control wing is arranged at both wing tips of an aircraft. FIG. 2 is a side view of the flutter control device observed from the side of the aircraft, as viewed from the direction indicated by the arrow A in FIG. FIG. 3 is a front view of the flutter control device observed from the front of the aircraft, as viewed from the direction indicated by the arrow B in FIG. FIG. 4 is a diagram showing the frequency of the bending vibration mode and the torsional vibration mode of the blade reaching the flutter when dynamic pressure is set on the horizontal axis and frequency is set on the vertical axis. is there. FIG. 5 is a side view of the flutter control device for explaining the improvement of the frequency in the torsional vibration mode shown in FIG. FIG. 6 is a diagram showing the frequency of the bending vibration mode and the frequency of the torsional vibration mode of the blades reaching the flutter when the dynamic pressure is set on the horizontal axis and the frequency is set on the vertical axis. is there. FIG. 7 is a side view of the flutter control device for explaining the improvement of the frequency in the torsional vibration mode shown in FIG. FIG. 8 is a side view of the blade tip portion showing an embodiment in which the front control blades are arranged in a double leaf. FIG. 9 is a front view of the blade tip portion illustrating the front control blade shown in FIG. FIG. 10 is a perspective view of a blade tip portion illustrating the front control blade shown in FIGS. 8 and 9. FIG. 11 is a front view of a blade tip portion showing an embodiment in which the front control blade is arranged in a V-shaped blade. FIG. 12 is a perspective view of a blade tip portion illustrating the front control blade shown in FIG. FIG. 13 is a plan view of a blade tip portion illustrating an embodiment in which the front control blade and the rear control blade are extended from the blade tip toward the body side. FIG. 14 is a front view of a blade tip portion illustrating an embodiment in which the front control blades of the flutter control device are arranged in a double-upper configuration. FIG. 15 is a front view showing an embodiment in which the front control blades of the flutter control device are arranged in a V-shaped blade. FIG. 16 is a diagram illustrating an embodiment in which the planar shapes of the front control blade and the rear control blade are delta blades. FIG. 17 is a diagram illustrating an embodiment in which the front control blade and the rear control blade are driven in the cord direction of the blade. FIG. 18 is a plan view illustrating an embodiment in which the front control blade and the rear control blade are independently driven in the cord direction of the blade. FIG. 19 is a diagram illustrating a cross section taken along the line CC shown in FIG. 18, and is a side sectional view illustrating a state in which the front control blade and the rear control blade are stored. FIG. 20 is a plan view illustrating an embodiment in which the front control wing and the rear control wing are driven to rotate around the code axis of the wing. FIG. 21 is a front view of the flutter control device shown in FIG. 20 observed from the front.

  A form for implementing a flutter control device will be described below with reference to the accompanying drawings.

(Flutter control device installation example)
A mounting example of the flutter control device will be described with reference to FIGS. FIG. 1 is a plan view illustrating an embodiment in which a flutter control device having a front control wing 22f and a rear control wing 22r is arranged (fixed) at both wing ends of a wing 14 of an aircraft 10. 2 is a side view of the flutter control device observed from the side surface of the aircraft 10 as viewed from the direction indicated by the arrow A in FIG. FIG. 3 is a front view of the flutter control device observed from the front of the aircraft 10 as viewed from the direction indicated by the arrow B in FIG.

  The aircraft 10 shown in FIG. 1 flies in the FD direction. The aircraft 10 includes a fuselage 12, a pair of left and right wings 14 (main wings), a horizontal tail wing 16, a vertical tail wing 18, and a flutter control device including a front control wing 22f and a rear control wing 22r. A wing 14 (main wing) is disposed near the center of the fuselage 12 in the aircraft 10. A horizontal tail 16 and a vertical tail 18 are arranged at the rear of the fuselage 12 in the aircraft 10.

  The wing 14 lifts the aircraft 10 by generating lift during flight. A flutter control device including a front control blade 22f and a rear control blade 22r is disposed at the blade tip of the blade 14. The front control blade 22f is a small blade having a front control blade area Sf, and generates a front control blade lift Lf (see FIGS. 5 and 7 described later). The rear control blade 22r is a small blade having a rear control blade area Sr and generates a rear control blade lift Lr (see FIGS. 5 and 7 described later).

  The horizontal tail 16 stabilizes the posture in the pitch direction (the direction around the Y axis shown in FIG. 1) during the flight of the aircraft 10. The vertical tail 18 stabilizes the attitude in the yaw direction (the direction around the Z axis shown in FIG. 1) during the flight of the aircraft 10.

  Referring to FIG. 2, the front control blade 22 f and the rear control blade 22 r of the flutter control device are disposed in front of and behind the blade tip at an angle of attack that generates lift in the same direction as the blade 14. The front control blade wind pressure center CPf (see FIGS. 5 and 7 described later) of the front control blade 22f is disposed in front of the front edge EL of the blade tip. In the embodiment shown in FIG. 2, the front control blade 22f is attached in front of the front edge EL at the blade tip of the blade 14 (+ X axis direction shown in FIG. 1: upstream in the main flow direction).

  The rear control blade wind pressure center CPr (see FIGS. 5 and 7 described later) of the rear control blade 22r is disposed behind the rear edge ET of the blade tip. In the embodiment shown in FIG. 2, the rear control blade 22 r is attached to the rear (−X axis direction: downstream in the main flow direction shown in FIG. 1) behind the trailing edge ET at the blade tip portion of the blade 14. In the embodiment shown in FIGS. 2 and 3, the front control blade 22f and the rear control blade 22r of the flutter control device are in the X-axis direction (the cord direction of the blade 14) and the Y-axis direction (span direction), which are the mainstream directions. (In addition, in the present specification, “parallel” includes being substantially parallel). .

  In the embodiment shown in FIGS. 1 to 3, the front control blade 22 f is attached to the blade tip portion of the blade 14 via a front support member 20 f. The rear control blade 22r is attached to the blade end portion of the blade 14 via a rear support member 20r. Note that the front control blade 22f and the rear control blade 22r may be disposed directly on the blade tip portion of the blade 14 without the front support member 20f and the rear support member 20r. In the embodiment shown in FIG. 1, an embodiment in which the front control wing 22f and the rear control wing 22r are arranged at the wing end of the wing 14 (main wing) is shown. It can also be arranged at the tip of the horizontal tail 16.

  In the embodiment shown in FIGS. 1 to 3, the front control blade 22f and the rear control blade 22r are arranged or fixed in a state of extending from the blade tip toward the outside of the blade. Conversely, it may be arranged or fixed (see FIG. 13) in a state extending from the blade tip toward the fuselage 12 side.

(In the case where the torsional vibration mode increases from a low frequency to the bending vibration mode of the blade 14 to reach coupled vibration)
Next, the case where the torsional vibration mode increases from a lower frequency than the bending vibration mode of the blade 14 and reaches a coupled vibration (resonance) will be described with reference to FIGS. In FIG. 4, when the dynamic pressure DP (for example, corresponding to the speed of relative wind) is set on the horizontal axis and the frequency freq is set on the vertical axis, the frequency fb of the bending vibration mode of the blade 14 reaching the flutter is set. And the frequency ft0 and ft1 of the torsional vibration mode leading to the flutter. FIG. 5 is a side view of the flutter control device for explaining the improvement state of the frequency ft1 in the torsional vibration mode shown in FIG. In addition, about the site | part which has the same function as the site | part shown in FIG. 1 thru | or FIG. 3, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  Referring to FIG. 4, the frequency ft0 of the torsional vibration mode is a schematic variation of the frequency with respect to the dynamic pressure DP in a state where the flutter control device is not attached (in the case of a single torsional vibration mode). And a case where a plurality of torsional vibration modes are summarized.). The frequency ft1 in the torsional vibration mode is a schematic variation of the frequency with respect to the dynamic pressure DP in a state after the flutter control device is attached (in the case of a single torsional vibration mode or in a plurality of torsional vibration modes). (Including the case where the torsional vibration modes are summarized).

  Since the frequency fb of the bending vibration mode of the blade 14 is a vibration mode in which the change in the angle of attack of the blade 14 is small, the frequency fb of the bending vibration mode is the presence or absence of the dynamic pressure DP and the flutter control device as shown in FIG. It takes almost the same value regardless. On the other hand, the torsional vibration mode is a vibration mode in which the change in the angle of attack of the blade 14 with respect to the dynamic pressure DP is large.

  As shown in FIG. 4, it is assumed that the frequency ft0 in the torsional vibration mode when the flutter control device is not attached approaches the frequency fb in the bending vibration mode as the dynamic pressure DP increases. In this case, in the dynamic pressure DP0, the bending vibration mode and the torsional vibration mode are coupled at the frequency FP0 to generate flutter. Therefore, by attaching a flutter control device to the blade tip of the blade 14, the change in the frequency with respect to the dynamic pressure DP is reduced (frequency ft 1 in the torsional vibration mode) to delay the coupling, and the dynamic pressure at which flutter is generated. DP1 can be moved out of practical speed (frequency FP1).

  As shown in FIG. 4, when the frequency ft0 of the torsional vibration mode increases from a lower frequency than the frequency fb of the bending vibration mode of the blade 14 and approaches the coupled vibration (frequency FP0). If the torsional rigidity Kt (N · m / rad) of the blade 14 can be lowered, the change in the frequency with respect to the dynamic pressure DP can be reduced and the coupling can be delayed.

  Next, the lift generated by the front control blade 22f and the rear control blade 22r will be described with reference to FIG. Referring to FIG. 5, the direction (upward) of the front control blade lift Lf generated in the front control blade 22f is the same as the direction (upward) of the rear control blade lift Lr generated in the rear control blade 22r. In FIG. 5, Lw indicates the lift force generated at the blade tip of the blade 14.

  Next, dynamic pressure torque generated by the front control blade 22f and the rear control blade 22r will be described with reference to FIG. For example, as shown in FIG. 5, the torsional center MRC having the frequency ft0 in the torsional vibration mode leading to the flutter exists behind (−X axis direction) from the structural virtual center MC (for example, the mass point) of the blade 14. If there is, a flutter control device including the front control blade 22f and the rear control blade 22r is disposed at the blade tip of the blade 14. In the embodiment shown in FIG. 5, the positions of the front control blade wind pressure center CPf of the front control blade 22f and the rear control blade wind pressure center CPr of the rear control blade 22r are arranged in front of the twist center MRC. As a result, the front control blade 22f and the torsional deformation (torsion angle α) applied to the blade 14 with respect to the torque direction (torsional rigidity Kt × torsion angle α) to return to the original state. The direction of the dynamic pressure torque (Xf × Lf + Xr × Lr) generated by the front control blade lift Lf and the rear control blade lift Lr generated by the rear control blade 22r is reversed (the sign is reversed). As a result, the dynamic pressure torque acts to apparently reduce the torsional rigidity Kt.

  Then, the same effect as the torsional rigidity Kt of the blades 14 is reduced, and the change in the frequency with respect to the dynamic pressure DP is reduced.

  A mechanism for reducing the torsional rigidity Kt will be described using mathematical expressions. It should be noted that the mathematical formula used in the explanation is not a detailed mathematical formula taking all elements into consideration, but a simple mathematical formula for explaining the mechanism.

For example, a general equation of motion of torsional vibration motion is represented by (Equation 1). The frequency ft of a general torsional vibration mode is expressed by (Expression 2). The addition of the front control blade 22f and the rear control blade 22r illustrated in FIG. 5 to a general torsional vibration system means that (Xf × Lf + Xr × Lr) is added to the right side of the equation of motion represented by (Expression 1). Generally means to add. Lf is approximately proportional to the twist angle α, and Lr is approximately proportional to the twist angle α. From the above, it is understood that (Xf × Lf + Xr × Lr) functions to apparently reduce the torsional rigidity Kt that is the coefficient of α in (Expression 1).

ｆｔ：一般的な捩じり振動モードの振動数
Ｋｔ：捩じり剛性
Ｌｆ：前方制御翼２２ｆが発生する前方制御翼揚力
Ｘｆ：捩じれ中心ＭＲＣから、前方制御翼風圧中心ＣＰｆまでの距離
Ｌｒ：後方制御翼２２ｒが発生する後方制御翼揚力
Ｘｒ：捩じれ中心ＭＲＣから、後方制御翼風圧中心ＣＰｒまでの距離
Ｊ：捩じり振動系の慣性モーメント
なお、各風圧中心は、例えば、対応する各翼に働く揚力の作用点を意味する。

ft: Frequency in a general torsional vibration mode Kt: Torsional rigidity Lf: Front control blade lift generated by the front control blade 22f Xf: Distance Lr from the twist center MRC to the front control blade wind pressure center CPf: Rear control blade lift Xr generated by rear control blade 22r: Distance from torsion center MRC to rear control blade wind pressure center CPr J: Inertia moment of torsional vibration system Note that each wind pressure center is, for example, each corresponding blade It means the point of action of lift that works on.

  As described above, when the front control blade 22f and the rear control blade 22r are disposed at the blade tip, the torsional deformation (torsion angle α) in the blade 14 returns from the torsional rigidity Kt to the front. A value based on the dynamic pressure torque (Xf × Lf + Xr × Lr) generated by the control blade lift Lf and the rear control blade lift Lr is subtracted. By arranging the front control blade 22f and the rear control blade 22r at the blade tip, an effect similar to that obtained when the torsional rigidity Kt of the blade 14 is reduced is produced, and the change in the frequency with respect to the dynamic pressure DP is reduced.

  In the example shown in FIG. 5, the front control blade 22 f of the flutter control device is attached in front of the front edge EL of the blade tip portion of the blade 14, and the rear control blade 22 r is the blade tip portion of the blade 14. It is attached behind the rear edge ET. For this reason, the change of the wind pressure center of the whole blade (the whole blade including the front control blade 22f, the blade 14, and the rear control blade 22r) due to the addition of the flutter control device is effectively suppressed.

(When the torsional vibration mode is decreased from a high frequency with respect to the bending vibration mode of the blade 14 to reach coupled vibration)
Next, the case where the torsional vibration mode is decreased from a high frequency with respect to the bending vibration mode of the blade 14 to reach coupled vibration will be described with reference to FIGS. 6 and 7. In FIG. 6, when the dynamic pressure DP (e.g., corresponding to the speed of relative wind) is set on the horizontal axis and the frequency freq is set on the vertical axis, the frequency fb of the bending vibration mode of the blade 14 reaching the flutter is set. And the frequency ft0 and ft1 of the torsional vibration mode leading to the flutter. FIG. 7 is a side view of the flutter control device for explaining the improvement state of the frequency ft1 in the torsional vibration mode shown in FIG. In addition, about the site | part which has the same function as the site | part shown in FIG. 4 thru | or FIG. 5, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  As shown in FIG. 6, it is assumed that the frequency ft0 in the torsional vibration mode without the flutter control device approaches the frequency fb in the bending vibration mode as the dynamic pressure DP increases. In this case, in the dynamic pressure DP0, the bending vibration mode and the torsional vibration mode are coupled at the frequency FP0 to generate flutter. Therefore, by attaching a flutter control device to the blade tip of the blade 14, the change in the frequency with respect to the dynamic pressure DP is reduced (frequency ft 1 in the torsional vibration mode) to delay the coupling, and the dynamic pressure at which flutter is generated. DP1 can be moved out of practical speed (frequency FP1).

  As shown in FIG. 6, when the frequency ft0 of the torsional vibration mode decreases from a high frequency with respect to the frequency fb of the blade 14 in the bending vibration mode and approaches the coupled vibration (frequency FP0). If the torsional rigidity Kt (N · m / rad) of the blade 14 can be increased, the change in the frequency with respect to the dynamic pressure DP can be reduced and the coupling can be delayed.

  Next, the lift generated by the front control blade 22f and the rear control blade 22r will be described with reference to FIG. Referring to FIG. 7, the direction (upward) of the front control blade lift Lf generated in the front control blade 22f is the same as the direction (upward) of the rear control blade lift Lr generated in the rear control blade 22r. In FIG. 7, Lw indicates the lift force generated at the blade tip portion of the blade 14.

  Next, dynamic pressure torque generated by the front control blade 22f and the rear control blade 22r will be described with reference to FIG. For example, as shown in FIG. 7, the torsional center MRC having the frequency ft0 in the torsional vibration mode leading to the flutter exists forward (in the + X-axis direction) from the structural virtual center MC (for example, the mass point) of the blade 14. In this case, a flutter control device including the front control blade 22f and the rear control blade 22r is disposed at the blade tip portion of the blade 14. In the embodiment shown in FIG. 7, the positions of the front control blade wind pressure center CPf of the front control blade 22f and the rear control blade wind pressure center CPr of the rear control blade 22r are arranged behind the twist center MRC. Thereby, the direction of the torque (torsional rigidity Kt × torsion angle α) in which the torsional deformation (torsion angle α) applied to the blade 14 is to be restored, the front control blade 22f and the rear control. The direction of the dynamic pressure torque (Xf × Lf + Xr × Lr) generated by the front control blade lift Lf and the rear control blade lift Lr generated by the blade 22r is the same (the same sign). As a result, the dynamic pressure torque apparently acts to increase the torsional rigidity Kt.

  Then, an effect similar to that obtained by increasing the torsional rigidity Kt of the blade 14 is produced, and the change in the frequency with respect to the dynamic pressure DP is reduced.

  A mechanism for increasing the torsional rigidity Kt will be described using mathematical expressions. It should be noted that the mathematical formula used in the explanation is not a detailed mathematical formula taking all elements into consideration, but a simple mathematical formula for explaining the mechanism.

  For example, a general equation of motion of torsional vibration motion is represented by (Equation 3). The frequency ft of a general torsional vibration mode is expressed by (Expression 4). The addition of the front control blade 22f and the rear control blade 22r illustrated in FIG. 7 to a general torsional vibration system is based on the equation (Xf × Lf + Xr × Lr) on the left side of the equation of motion. Generally means to add. Lf is approximately proportional to the twist angle α, and Lr is approximately proportional to the twist angle α. From the above, it is understood that (Xf × Lf + Xr × Lr) functions to apparently increase the torsional rigidity Kt that is the coefficient of α in (Expression 1).

ｆｔ：一般的な捩じり振動モードの振動数

Ｋｔ：捩じり剛性
Ｌｆ：前方制御翼２２ｆが発生する前方制御翼揚力
Ｘｆ：捩じれ中心ＭＲＣから、前方制御翼風圧中心ＣＰｆまでの距離
Ｌｒ：後方制御翼２２ｒが発生する後方制御翼揚力
Ｘｒ：捩じれ中心ＭＲＣから、後方制御翼風圧中心ＣＰｒまでの距離
Ｊ：捩じり振動系の慣性モーメント
なお、各風圧中心は、例えば、対応する各翼に働く揚力の作用点を意味する。

ft: Frequency of general torsional vibration mode

Kt: Torsional rigidity Lf: Front control blade lift force generated by front control blade 22f Xf: Distance from twist center MRC to front control blade wind pressure center CPf Lr: Rear control blade lift force Xr generated by rear control blade 22r: Distance J from torsion center MRC to rear control blade wind pressure center CPr: Inertia moment of torsional vibration system Note that each wind pressure center means, for example, an action point of lift acting on each corresponding blade.

  As described above, the dynamic pressure torque generated by the front control blade lift Lf and the rear control blade lift Lr with respect to the torsional rigidity Kt to which the torsional deformation (torsion angle α) of the blade 14 is to be restored. A value based on (Xf × Lf + Xr × Lr) is added. By arranging the front control blade 22f and the rear control blade 22r at the blade tip, an effect similar to that obtained by increasing the torsional rigidity Kt of the blade 14 is produced, and the change in the frequency with respect to the dynamic pressure DP is reduced.

  In the example shown in FIG. 7, the front control blade 22 f of the flutter control device is attached in front of the front edge EL of the blade tip portion of the blade 14, and the rear control blade 22 r is the blade tip portion of the blade 14. It is attached behind the rear edge ET. For this reason, the change of the wind pressure center of the whole blade (the whole blade including the front control blade 22f, the blade 14, and the rear control blade 22r) due to the addition of the flutter control device is effectively suppressed.

(Embodiment of multileaf arrangement)
Next, an embodiment in which at least one of the front control blade 22f and the rear control blade 22r is arranged in a multi-leaf arrangement of two or more leaves will be described with reference to FIGS. FIG. 8 is a side view of a blade tip portion showing an embodiment in which the front control blade 22f is arranged in a double leaf. FIG. 9 is a front view of the blade tip portion for explaining the front control blade 22f arranged in a compound leaf form as shown in FIG. FIG. 10 is a perspective view of a blade tip portion illustrating the front control blade 22f shown in FIGS. FIG. 11 is a front view of a blade tip portion showing an embodiment in which the front control blade 22f is arranged in a V-shaped blade. FIG. 12 is a perspective view of a blade tip portion for explaining the front control blade 22f shown in FIG. In addition, about the site | part which has the same function as the site | part shown in FIG. 1 thru | or FIG. 3, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  With reference to FIGS. 8 to 10, the front control blade 22f of the flutter control device has the multi-leaf attachment material 24 parallel to the cord direction (X-axis direction) and span direction (Y-axis direction) of the blade 14. The biplane is arranged up and down. The multi-leaf attachment member 24 is attached to the blade tip portion of the blade 14 via the front support member 20f. In the embodiment shown in FIGS. 8 to 10, the embodiment in which two front control blades 22f are arranged is shown, but three or more front control blades 22f can be arranged. Further, the rear control blade 22r can be arranged in a multi-leaf arrangement. When the front control blades 22f or the rear control blades 22r are arranged in a multi-leaf arrangement, the blade areas of the plurality of front control blades 22f or the plurality of rear control blades 22r may be different. Further, the attachment positions of the plurality of front control blades 22f or the plurality of rear control blades 22r can be attached while being shifted in the cord direction (X-axis direction) or span direction (Y-axis direction) of the blades 14.

  As shown in FIGS. 8 to 10, by shifting the mounting positions of the front control blade 22f and the rear control blade 22r arranged in the multi-leaf direction in the Z-axis direction, the wake and the blade 14 of the front control blade 22f or the front control blade are controlled. Interference between the wake 22f and the rear control blade 22r can be reduced. And the fall of the lift of the back control blade 22r resulting from interference can be suppressed, and the effect as a flutter control device can be maintained. Further, by arranging the front control blade 22f (or the rear control blade 22r) in a multi-leaf arrangement, the front control blade lift Lf (or the rear control blade lift Lr) can be increased. As a result, even when the length of the front support member 20f or the rear support member 20r is limited, the flutter limit (limit dynamic pressure or limit speed at which flutter does not occur) is effectively increased, and the flight speed region is increased. Can be spread.

  11 and 12, the two front control blades 22f of the flutter control device are parallel to the cord direction (X-axis direction) of the blade 14 (in addition, the parallel includes being substantially parallel). Arranged). In addition to this, they are arranged at different angles (V-shaped blade arrangement) with respect to the span direction (Y-axis direction) (one of a plurality of control blades and the span direction). The angle formed is different from the angle formed by the other one of the plurality of control blades and the span direction.) The plurality of front control blades 22f are attached to the blade tip portion of the blade 14 via the front support member 20f. In the embodiment shown in FIG. 11 and FIG. 12, an embodiment in which two front control blades 22f are arranged is shown, but three or more front control blades 22f can be arranged. Further, the plurality of rear control blades 22r can be arranged radially (V-shaped blade arrangement) with respect to the cord direction (X axis).

  As shown in FIGS. 11 and 12, the wake of the front control blade 22f and the blade 14 are arranged by shifting the angle between the front control blade 22f and the rear control blade 22r with respect to the cord direction (Y-axis direction). Or, the interference between the wake of the front control blade 22f and the rear control blade 22r can be reduced. And the fall of the lift of the back control blade 22r resulting from interference can be suppressed, and the effect as a flutter control device can be maintained. Further, by arranging the front control blade 22f (or the rear control blade 22r) in a multi-leaf arrangement, the front control blade lift Lf (or the rear control blade lift Lr) can be increased. As a result, even when the length of the front support member 20f or the rear support member 20r is limited, the flutter limit (limit dynamic pressure or limit speed at which flutter does not occur) is effectively increased, and the flight speed region is increased. Can be spread.

(Embodiment of control wing extending from wing tip toward fuselage 12 side)
1 to 3 and 8 to 12, the embodiment has been described in which the front control blade 22 f and the rear control blade 22 r of the flutter control device extend from the blade tip toward the outside of the blade 14. On the other hand, FIGS. 13 to 15 describe an embodiment in which the front control blade 22f and the rear control blade 22r of the flutter control device extend from the blade tip toward the fuselage.

  FIG. 13 is a plan view of a blade tip portion illustrating an embodiment in which the front control blade 22f and the rear control blade 22r are extended from the blade tip toward the fuselage. FIG. 14 is a front view of a blade tip portion illustrating an embodiment in which the front control blades 22f of the flutter control device are arranged in a double-upper configuration. FIG. 15 is a front view showing an embodiment in which the front control blade 22f of the flutter control device is arranged in a V-shaped blade. In addition, about the site | part which has the same function as the site | part shown in FIG. 1 thru | or FIG. 3 and FIG. 8 thru | or FIG. 12, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  Referring to FIG. 13, the front control blade 22f is fixed to the blade tip portion via a front support member 20f. The rear control blade 22r is fixed to the blade tip portion via the rear support member 20r. As shown in FIG. 13, by moving the front control blade 22f and the rear control blade 22r from the blade tip toward the fuselage, the movement of the blade wind pressure center of the entire blade due to the addition of the flutter control device is also achieved. The flutter limit can be improved while suppressing. Further, since the increase in the wing width due to the addition of the flutter control device is small, it is suitable for an application for improving the flutter limit of an aircraft in which the wing width is limited.

  Referring to FIG. 14, a plurality of front control blades 22f (or rear control blades 22r) are arranged in a double-upper configuration parallel to the cord direction (X-axis direction) and span direction (Y-axis direction) of blade 14. ing. As shown in FIG. 14, a plurality of front control blades 22f (or rear control blades 22r) are arranged in parallel with each other, and a flutter control device is also added by extending the blades from the blade tip toward the fuselage. While suppressing the movement of the wing wind pressure center of the entire wing and the increase in the wing width, the flutter limit can be improved and the flight speed range can be expanded. Further, by arranging the front control blade 22f (or the rear control blade 22r) in a multi-leaf arrangement, the front control blade lift Lf (or the rear control blade lift Lr) can be increased, and the flutter limit can be improved more effectively. .

  Referring to FIG. 15, the plurality of front control blades 22f (or rear control blades 22r) are arranged in parallel to the cord direction (X-axis direction) of the blades 14 and in the span direction (Y-axis direction). On the other hand, they are arranged to form different predetermined angles (V-shaped wing arrangement). As shown in FIG. 15, the movement of the blade wind pressure center of the entire blade and the movement of the blade due to the addition of the flutter control device by arranging a plurality of front control blades 22f (or rear control blades 22r) as V-shaped blades. While suppressing the increase in width, the flutter limit can be improved and the flight speed region can be expanded. Further, by arranging the front control blade 22f (or the rear control blade 22r) in a multi-leaf arrangement, the lift generated when the blade 14 is twisted can be increased, and the flutter limit can be effectively improved. In the embodiment shown in FIG. 14 and FIG. 15, an embodiment in which two front control blades 22f are arranged has been shown. However, three or more front control blades 22f can be arranged, and rear control blades 22r are arranged in multiple leaves. You can also

(Example of planar shape of the front control blade 22f and the rear control blade 22r)
In FIG. 1, FIG. 10, FIG. 12, and FIG. 13, the embodiment in which the front control blade 22f and the rear control blade 22r have the planar shape formed in the backward blade shape (or the forward blade shape) has been described. On the other hand, in FIG. 16, an embodiment in which the planar shapes of the front control blade 22f and the rear control blade 22r are delta blade shapes will be described. The plane shape of the front control wing 22f and the rear control wing 22r is changed into a rectangular wing shape, a tapered wing shape, a swept wing shape, a forward wing shape, a delta wing shape, and a clipped delta wing shape according to the use speed range and application of the aircraft. Alternatively, other shapes can be used. The critical Mach number can be increased by providing a receding angle to the front control blade 22f and the rear control blade 22r.

(Embodiment in which the front control blade 22f and the rear control blade 22r are driven in the cord direction)
1 to 3 and 8 to 16, the embodiment in which the front control blade 22 f and the rear control blade 22 r are fixed to the blade tip of the blade 14 has been described. On the other hand, FIG. 17 is a plan view illustrating an embodiment in which the front control blade 22f and the rear control blade 22r are integrally driven in the cord direction of the blade 14 (X-axis direction shown in FIG. 17). In addition, about the site | part which has the same function as the site | part shown in FIG. 1 thru | or FIG. 3, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  With reference to FIG. 17, an embodiment of the front control blade 22f and the rear control blade 22r that can be driven in the cord direction of the blade 14 will be described. The flutter control device shown in FIG. 17 includes a front control blade 22f, a rear control blade 22r, a front support member 20f, a rear support member 20r, a linear guide LG, a motor M, an encoder E, and a control device 30 ( For example, an information processing apparatus such as a computer can be used. Further, the flutter control device may be provided with a front vibrometer 32f, a rear vibrometer 32r, and a relative speedometer 34.

  In the embodiment shown in FIG. 17, the front support member 20f and the rear support member 20r are integrally connected. A front control blade 22f having a front control blade area Sf is attached to the front support member 20f which is one member. A rear control blade 22r having a rear control blade area Sr is attached to the rear support member 20r.

  Referring to FIG. 17, the linear guide LG (front linear motion guide portion, rear linear motion guide portion) moves the front support member 20f and the rear support member 20r in the cord direction of the blade 14 (X-axis direction shown in FIG. 17). Guide to move. The stator of the motor M (front linear motion drive unit, rear linear motion drive unit) is fixed to the blade tip of the blade 14. The rotor of the motor M rotates the worm gear WG and the rotor of the encoder E. The encoder E measures the rotation angle of the rotor of the motor M (corresponding to the position of the front control blade 22f and the rear control blade 22r in the code direction (X-axis direction)) and sends a measurement value (to the measurement value) to the control device 30. Corresponding signal). The control device 30 controls the rotation and stop of the motor M. The worm gear WG meshes with a worm rack formed on the side surfaces of the front support member 20f and the rear support member 20r.

  The front vibration meter 32f and the rear vibration meter 32r of the flutter control device measure the displacement, speed, or acceleration of the blade 14 in the vertical direction (Z-axis direction) at the blade tip, and the measurement result (corresponding to the measurement value). Signal) to the control device 30. The control device 30 calculates the torsion center MRC in the torsional vibration mode of the blade 14 from the results detected by the front vibrometer 32f and the rear vibrometer 32r and the installation position information of the front vibrometer 32f and the rear vibrometer 32r. The frequency and amplitude can be detected. The control device 30 moves the front control blade 22f and the rear control blade 22r in a direction to prevent the occurrence of flutter according to the torsion center MRC, the vibration frequency, the amplitude, and the like detected by the front vibration meter 32f and the rear vibration meter 32r. A command for drive control can be output to the motor M.

  The relative speedometer 34 detects the relative wind speed of the wing 14 (aircraft 10) moving in the fluid, and outputs the result (a signal corresponding to the detected relative wind speed) to the control device 30. When the control device 30 determines that the relative wind speed has approached the flutter generation speed, the control device 30 instructs the motor M to drive and control the front control blade 22f and the rear control blade 22r in a direction to prevent flutter generation. Can be output.

  When control device 30 outputs a command to rotate the rotor of motor M, motor M rotates in the direction in which the command is received. Then, the worm gear WG rotates around the X axis, and the worm rack moves in the X axis direction. Then, the front control blade 22f attached to the front support member 20f and the rear control blade 22r attached to the rear support member 20r are aligned and move in the cord direction (X-axis direction) of the blade 14. The amount of movement of the front control blade 22f and the rear control blade 22r is indirectly detected by the encoder E. The control device 30 can control the positioning of the front control blade 22f and the rear control blade 22r at predetermined positions in the cord direction (X-axis direction) of the blade 14 by referring to the output value of the encoder E.

  The control device 30 performs positioning control of the front control blade 22f and the rear control blade 22r in the cord direction (X-axis direction) of the blade 14, and thereby the front control blade lift Lf generated by the front control blade 22f and the rear control blade 22r. In addition, the dynamic pressure torque (Xf × Lf + Xr × Lr) can be adjusted by changing the moment arm lengths Xf and Xr of the rear control blade lift Lr (see FIGS. 4 to 7). Then, the dynamic pressure torque generated when the wing 14 is twisted can be adjusted to improve the flutter limit and widen the flight speed region.

  In the embodiment shown in FIG. 17, the front control blade 22f and the rear control blade 22r extend from the blade tip portion of the blade 14 toward the outside, but the front control blade 22f and the rear control blade 22r. At least one of the wings 22r can be extended from the wing end of the wing 14 toward the fuselage 12 side. Moreover, an electric power source, a hydraulic power source, a pneumatic power source, or other power sources can be used as the front linear motion drive unit or the rear linear motion drive unit. The encoder E can also use an optical encoder, resolver, inductin, RVDT (Rotary variable differential transformer), and other detectors.

(Embodiment in which at least one of the front control blade 22f and the rear control blade 22r is driven in the cord direction)
In FIG. 17, the embodiment in which the front control blade 22f and the rear control blade 22r are simultaneously driven in the same direction has been described. On the other hand, in FIG. 18 and FIG. 19, an embodiment will be described in which the front control blade 22f and the rear control blade 22r independently drive in the cord direction of the blade 14 (X-axis direction shown in FIG. 18). . FIG. 18 is a plan view of a flutter control device for explaining an embodiment in which the front control blade 22f and the rear control blade 22r are independently driven in the cord direction of the blade. FIG. 19 is a side sectional view for explaining the CC section shown in FIG. 18, and is a side sectional view for explaining a state in which the front control blade 22f and the rear control blade 22r are stored. In addition, about the site | part which has the same function as the site | part shown in FIG. 17, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  Referring to FIG. 18, a front control blade 22f is attached to the front support member 20f. A rear control blade 22r is attached to the rear support member 20r. The front support member 20f is guided by the front linear motion guide portion (linear guide LG) so as to be movable in the cord direction of the blade 14 (X-axis direction shown in FIG. 18). The rear support member 20r is guided by the rear linear motion guide portion (linear guide LG) so as to be movable in the cord direction of the blade 14 (X-axis direction shown in FIG. 18).

  The front linear motion drive unit (motor M) drives the front control blade 22 f in the cord direction of the blade 14. The rear linear motion drive unit (motor M) drives the rear control blade 22r in the cord direction of the blade 14. The control device 30 (for example, an information processing device such as a computer can be used) controls the front linear motion drive unit (motor M) and the rear linear motion drive unit (motor M) independently by controlling the front. The support member 20f and the rear support member 20r can be independently controlled in the cord direction of the blade 14 (X-axis direction shown in FIG. 18).

  When the control device 30 outputs a command to rotate the rotor of the motor M that drives the front support member 20f, the motor M rotates in the direction in which the command is received, and the worm gear WG rotates about the X axis to support the front. The worm rack of the material 20f moves in the X-axis direction. Then, the front control blade 22f attached to the front support member 20f is driven in the cord direction (X-axis direction) of the blade 14.

  Similarly, when the control device 30 outputs a command to rotate the rotor of the motor M that drives the rear support member 20r, the motor M rotates in the received direction, and the worm gear WG rotates around the X axis. The worm rack of the rear support member 20r moves in the X-axis direction. Then, the rear control blade 22r attached to the rear support member 20r is driven in the cord direction (X-axis direction) of the blade 14.

  The control device 30 performs positioning control of at least one of the front control blade 22f and the rear control blade 22r with respect to the cord direction (X-axis direction) of the blade 14 to generate the front control blade 22f and the rear control blade 22r. The dynamic pressure torque (Xf × Lf + Xr × Lr) can be adjusted by changing the moment arm lengths Xf and Xr of the front control blade lift Lf and the rear control blade lift Lr (see FIGS. 4 to 7). Then, the dynamic pressure torque generated when the wing 14 is twisted can be adjusted to improve the flutter limit and widen the flight speed region.

  In the embodiment shown in FIG. 18, the front control blade 22f and the rear control blade 22r extend from the blade tip of the blade 14 toward the fuselage, but the front control blade 22f and the rear control blade are shown. It is also possible to use a configuration in which at least one of 22r extends outward from the blade tip of blade 14.

  Further, the control device 30 performs control to independently drive the front control blade 22f and the rear control blade 22r in the cord direction (X-axis direction) of the blade 14 as shown in FIG. Can be stored in the front storage section 40f, and the rear control blade 22r can be stored in the rear storage section 40r. As shown in FIG. 19, by storing the front control wing 22f in the front storage section 40f and storing the rear control wing 22r in the rear storage section 40r, only in a desired flight condition where flutter is generated, At least one of the front control blade 22f and the rear control blade 22r can be extended to the use state.

(Embodiment in which at least one of the front control blade 22f and the rear control blade 22r is driven to rotate around the cord axis)
18 and 19, the embodiment in which at least one of the front control blade 22f and the rear control blade 22r is driven in the cord direction (X-axis direction) of the blade 14 has been described. On the other hand, in FIGS. 20 and 21, the front control blade 22f and the rear control blade 22r are independently rotated around the cord axis of the blade 14 (around the X axis shown in FIG. 20). Will be described. FIG. 20 is a plan view of a flutter control device for explaining an embodiment in which the front control blade 22f and the rear control blade 22r are driven to rotate around the code axis of the blade. FIG. 21 is a front view of the flutter control device shown in FIG. 20 observed from the front. In addition, about the site | part which has the same function as the site | part shown in FIG.17 and FIG.18, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  Referring to FIGS. 20 and 21, a front control blade 22f is attached to the front support member 20f. A rear control blade 22r is attached to the rear support member 20r. The front support member 20f is supported by a front rotation guide portion (radial bearing RB) so as to be rotatable around the cord axis of the blade 14 (around the X axis shown in FIGS. 20 and 21). The rear support member 20r is supported by a rear rotation guide portion (radial bearing RB) so as to be rotatable around the cord axis of the blade 14 (around the X axis shown in FIGS. 20 and 21). The forward rotation drive unit (motor M) can rotationally drive the front control blade 22f about the code axis (X axis) of the blade 14 by rotating the front support member 20f. The backward rotation drive unit (motor M) can rotationally drive the rear control blade 22r around the code axis (X axis) of the blade 14 by rotationally driving the rear support member 20r.

  Referring to FIG. 20, the stator of motor M (forward rotation drive unit and rear rotation drive unit) is fixed to the blade tip of blade 14, and the rotor of motor M rotates the spur gear PG and the rotor of encoder E. Let The encoder E measures a rotation angle of the rotor of the motor M (corresponding to an angle around the code axis (around the X axis) of the front control blade 22f and the rear control blade 22r) and controls the control device 30 (for example, information from a computer or the like). A signal corresponding to the measured value is output to the processing device. The control device 30 controls the rotation and stop of the motor M. The spur gears PG attached to the rotors of the front turning drive unit and the rear turning drive unit (motor M) mesh with the spur gears PG attached to the front support member 20f and the rear support member 20r, respectively. Yes.

  The control device 30 independently controls the front linear motion drive unit (motor M) and the rear linear motion drive unit (motor M), thereby independently controlling the front support member 20f and the rear support material 20r. It can be rotated around the axis (around the X axis shown in FIGS. 20 and 21). When the control device 30 outputs a command to rotate the rotor of the motor M that drives the front support member 20f, the motor M rotates in the received direction, and the spur gear PG of the motor M rotates around the X axis. The spur gear PG of the front support member 20f rotates (reversely rotates) around the X axis. Then, the front control blade 22f attached to the front support member 20f is rotationally driven around the cord axis (X axis) of the blade 14 (see angle θ shown in FIG. 21).

  Similarly, when the control device 30 outputs a command to rotate the rotor of the motor M that drives the rear support member 20r, the motor M rotates in the received direction, and the spur gear PG of the motor M rotates around the X axis. The spur gear PG of the rear support member 20r rotates around the X axis (reverse rotation). Then, the rear control blade 22r attached to the rear support member 20r is rotationally driven around the cord axis (X axis) of the blade 14 (see angle θ shown in FIG. 21).

  The control device 30 controls the rotational positioning of at least one of the front control blade 22f and the rear control blade 22r around the code axis (X axis) of the blade 14 to thereby control the front control blade 22f and the rear control blade. The projected area with respect to the horizontal plane 22r (the XY plane shown in FIG. 20) can be changed. Then, by changing the front control blade lift Lf and the rear control blade lift Lr (see FIGS. 5 and 7), the dynamic pressure torque (Xf × Lf + Xr × Lr) based on the front control blade lift Lf and the rear control blade lift Lr is obtained. It can be adjusted (see FIGS. 4 to 7). Then, the dynamic pressure torque generated when the wing 14 is twisted can be adjusted to improve the flutter limit and widen the flight speed region.

  In the embodiment shown in FIG. 20, the front control blade 22f and the rear control blade 22r extend from the blade tip of the blade 14 toward the fuselage, but the front control blade 22f and the rear control blade 22r. A configuration in which at least one of the control blades 22r is extended outward from the blade end portion of the blade 14 can also be used.

(Generation of flutter and countermeasures)
In general, the wing structure is designed so that no flutter occurs. However, if the occurrence of flutter is found by the result of specification change, structural analysis, flight test, etc., (1) Set operational restrictions such as flight speed, altitude and weight, (2) Improve and strengthen the structure. (3) It is common to take measures such as adding weights. However, setting operational restrictions for aircraft involves a reduction in aircraft performance. Further, structural modification and weight addition are not preferable because they cause an increase in weight and a decrease in performance of the aircraft. In general, structural modifications to change the vibration characteristics of blades often require large-scale modifications, resulting in high costs such as design changes and the addition of environmental tests. May decrease.

  As described above, when the generation of flutter is suppressed by adding a flutter control device having the front control blade 22f and the rear control blade 22r to the blade tip of the blade 14, the repaired portion is the blade tip. Therefore, the increase in weight due to refurbishment is small. Accordingly, it is possible to suppress a decrease in performance of the aircraft.

  Further, the front control blade area Sf of the front control blade 22f and the rear control blade area Sr of the rear control blade 22r, and the moment arm lengths Xf and Xr of the front control blade lift Lf and the rear control blade lift Lr described above are the occurrence of flutter. It can be set as appropriate according to the situation (see FIGS. 4 to 7).

  The flutter control device according to the present invention has been described above with reference to the embodiment, but the flutter control device according to the present invention is not limited to the above embodiment. Various modifications can be made to the above embodiment. It is possible to combine the matters described in the above embodiment with the matters described in the other embodiments.

10. Aircraft 12 ... Fuselage 14 ... Wings 16 ... Horizontal tail 18 ... Vertical tail 20f ... Front support 20r ... Back support 22f ... Front control wing 22r. .. Rear control wing 24 ... Multi-leaf mounting material 30 ... Control device 32f ... Front vibration meter 32r ... Back vibration meter 34 ... Relative speedometer 40f ... Front storage 40r ... Back storage part CPf ... Front control blade wind pressure center CPr ... Back control blade wind pressure center DP ... Dynamic pressure E ... Encoder EL ... Lead edge ET ... Rear edge LG ... Linear Guide Lf ... Forward control blade lift Lw ... Blade lift Lr ... Back control blade lift M ... Motor MRC ... Twist center MC ... Virtual structure center PG ... Spur gear Sf .. .Front control blade area Sr ... Rear control blade area WG ... Worm gear

Claims (18)

A flutter control device having a front control wing disposed at a wing end of a wing that moves in a fluid and receives relative wind, and a rear control wing disposed at the wing end,
The wind pressure center of the front control blade is disposed in front of the front edge of the blade tip,
A flutter control device in which the wind pressure center of the rear control blade is disposed behind the rear edge of the blade tip. The flutter control device according to claim 1, wherein a direction of lift generated by the front control blade and a direction of lift generated by the rear control blade are the same direction. The front control wing is disposed in front of the front edge of the wing tip,
The flutter control device according to claim 1, wherein the rear control blade is disposed behind a rear edge of the blade tip. The wing has a bending vibration mode leading to the flutter and a torsional vibration mode leading to the flutter,
In the case where the frequency of the torsional vibration mode increases as the dynamic pressure acting on the wing increases,
The direction of the torque to which the torsional deformation caused by the torsional vibration mode is to be restored;
The front control blade and the rear control blade are arranged so that the direction of the dynamic pressure torque around the torsion center of the torsional vibration mode is reversed by the lift generated at the wind pressure center of the front control blade and the rear control blade. The flutter control device according to any one of claims 1 to 3. The wing has a bending vibration mode leading to the flutter and a torsional vibration mode leading to the flutter,
In the case where the frequency of the torsional vibration mode decreases as the dynamic pressure acting on the blades increases,
The direction of the torque to which the torsional deformation caused by the torsional vibration mode is to be restored;
The front control blade and the rear control blade are arranged so that the direction of the dynamic pressure torque around the torsion center of the torsional vibration mode is the same due to the lift generated at the wind pressure center of the front control blade and the rear control blade. The flutter control device according to any one of claims 1 to 3. A front support member disposed at the wing tip and supporting the front control wing;
The flutter control device according to claim 1, further comprising: a rear support member disposed at the blade tip portion and supporting the rear control blade. The flutter control device according to any one of claims 1 to 6, wherein at least one of the front control blade and the rear control blade extends from the blade tip toward the outside of the blade. The flutter control device according to any one of claims 1 to 6, wherein at least one of the front control blade and the rear control blade extends from the blade tip toward the fuselage. The flutter control device according to any one of claims 1 to 8, wherein a planar shape of at least one of the front control blade and the rear control blade is a receding blade shape. The flutter control device according to any one of claims 1 to 8, wherein a planar shape of at least one of the front control blade and the rear control blade is a delta blade shape. The flutter control device according to any one of claims 1 to 10, wherein at least one of the front control blade and the rear control blade includes a plurality of control blades. The flutter control device according to claim 11, wherein the plurality of control blades are arranged in parallel to a cord direction and a span direction of the blade. The plurality of control blades are parallel to a cord direction of the blade, and an angle formed by one of the plurality of control blades and the span direction is an angle between the other one of the plurality of control blades and the span. The flutter control device according to claim 11, wherein the flutter control device is different from an angle formed with a direction. A front linear motion guide portion that guides the front support member so as to be movable in the cord direction of the blade tip;
The flutter control device according to claim 6, further comprising: a front linear motion drive unit that drives the front support member in a cord direction of the blade tip. A rear linear motion guide that guides the rear support member so as to be movable in the cord direction of the blade tip;
The flutter control device according to claim 6, further comprising: a rear linear drive unit that drives the rear support member in a cord direction of the blade tip. At least one of the front linear motion drive unit and the rear linear motion drive unit is formed with at least one of the front control blade and the rear control blade on the front edge or the rear edge of the blade tip. The flutter control device according to claim 14 or 15, wherein a drive for storing in at least one of the front storage unit and the rear storage unit is performed. A front rotation guide portion that supports the front support member so as to be rotatable around a cord axis of the wing tip;
The flutter control device according to claim 6, further comprising: a front rotation drive unit that drives the front support member to rotate about a cord axis of the blade tip. A rear rotation guide part that supports the rear support member so as to be rotatable around a cord axis of the blade tip; and
The flutter control device according to claim 6, further comprising: a rear rotation drive unit configured to rotate the rear support member about a cord axis of the blade tip.

Images