JP2013173417A - Variable wing structure - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a variable wing structure which is suitable for application to a thin wing since no complicated link mechanism is required, and which can alter and maintain a wing shape without causing weight increase even under a condition that aerodynamic load applied to a wing is large.SOLUTION: A variable wing structure 1 for varying a wing shape includes: a plurality of split wings 2 freely turnably coupled to each other to make the relative angle of each other variable; an oil chamber 3 formed in one of two adjacent split wings 2 and having hydraulic fluid thereinside; a partition member 5 projected to the other of the two adjacent split wings 2 to partition the inside of the oil chamber 3 into two hydraulic fluid chambers 4 and turning inside the oil chamber 3 in response to a change of relative angle; and an oil supply/discharge means for adjusting oil pressure applied to the partition member 5 in each hydraulic fluid chamber 4 by supplying and discharging hydraulic fluid to two hydraulic fluid chambers 4 and changing the relative angle by turning the partition member 5.

Description

  The present invention relates to a variable wing structure that changes the shape of a wing used in an aircraft or the like.

  In recent years, research and development of so-called morphing wings that smoothly deform the wing shape has been promoted for the purpose of improving aerodynamic characteristics as a wing structure used in an aircraft or the like. As this type of variable wing structure, there is known a structure in which a link mechanism or the like is housed in the wing and the wing shape is changed by operating the link mechanism or the like (Patent Documents 1 to 4). .

JP 2011-178292 A JP 2011-178291 A JP 2011-178290 A US2010 / 0019096

  By the way, in a variable wing structure using a link mechanism, since it is necessary to accommodate a complicated link mechanism inside the wing, a certain wing thickness is required as the accommodation space, and a wing having a thin wing thickness (for example, It is difficult to apply to high-speed blades.

  In a variable wing structure using a link mechanism, each link of the link mechanism is rotated by an actuator such as an electric motor to change the wing shape, and the angle of each link is fixed at that position to change the wing shape. I try to keep it. For this reason, as the aerodynamic load applied to the wing increases, the load applied to the link mechanism also increases. Therefore, it is necessary to increase the rigidity of the link mechanism in order to deform the shape of the wing and maintain the shape under conditions where the aerodynamic load applied to the wing is large (for example, during high-speed flight or sudden turning) Incurs weight increase.

  The object of the present invention, which was created in view of the above circumstances, is suitable for thin blades without requiring a complicated link mechanism, and does not cause an increase in weight even under a large aerodynamic load applied to the blades. An object of the present invention is to provide a variable wing structure capable of changing the shape of a wing and maintaining the wing in that state.

  The present invention created to achieve the above object is a variable wing structure that changes the wing shape, and a plurality of divided wing pieces that are rotatably connected so that their relative angles are variable, and An oil chamber formed in one of two adjacent divided blade pieces and filled with hydraulic oil, and protruded on the other of the two adjacent divided blade pieces, and partitioning the oil chamber into two hydraulic oil chambers The hydraulic oil applied to the partition member by the hydraulic oil in each hydraulic oil chamber is adjusted by supplying and discharging the hydraulic oil to and from the partition member that rotates in the oil chamber according to the change in the relative angle. The variable wing structure includes oil supply / discharge means for rotating the partition member to change the relative angle.

  In the variable blade structure according to the present invention, the oil chamber has an opening facing the other of the divided blade pieces, the tip of the partition member is inserted into the oil chamber through the opening, and the root of the partition member blocks the opening. It may be.

  In the variable blade structure according to the present invention, a rotating shaft and a bearing for rotatably connecting adjacent divided blade pieces are disposed at the base of the partition member, and the opposing surface is opposed to the tip of the partition member of the oil chamber. However, you may form in the arc shape centering on the rotating shaft.

  In the variable wing structure according to the present invention, a tip hydraulic seal may be provided at the tip of the partition member in sliding contact with the opposing surface of the oil chamber as the relative angle changes.

  The variable blade structure according to the present invention may be provided with a root hydraulic seal that seals between the root of the partition member and the chamber wall of the hydraulic oil chamber.

  In the variable wing structure according to the present invention, the root hydraulic seal is made of a flexible plate, one end of which is fixed to the base of the partition member, the middle is bent, and the other end is the chamber of the oil chamber. It may be fixed to the wall.

  According to the variable blade structure according to the present invention, a plurality of divided blade pieces are rotatably connected so that the relative angle between them is variable, and the other chamber is formed in one of the adjacent divided blade pieces. By inserting a partition member protruding from the split blade piece, the chamber is partitioned into two hydraulic fluid chambers by the partition member, and the hydraulic fluid is supplied to and discharged from each hydraulic fluid chamber, so that the hydraulic fluid in each hydraulic fluid chamber is partitioned. The relative pressure between the divided blade pieces can be changed by adjusting the hydraulic pressure applied to the member and rotating the partition member in the oil chamber.

  Thus, since the oil pressure is directly applied to the oil chamber and the partition member provided in the divided blade pieces and the relative angle between the divided blade pieces is changed to deform the blade shape, the relative angle between the divided blade pieces is changed. A complicated link mechanism that is conventionally required for the change is not necessary. Therefore, a space for accommodating the link mechanism is not required, and the present invention can be applied to a blade having a thin blade thickness.

  Further, since the hydraulic pressure is directly applied to the oil chamber and the partition member provided in the split piece to deform the blade shape, the hydraulic pressure in the hydraulic oil chamber can be increased to counter the aerodynamic load applied to the blade. Therefore, even under a condition where the aerodynamic load applied to the wing is large, the shape of the wing can be changed and maintained in that state without causing an increase in weight.

It is a perspective view which shows the external appearance of the variable wing | blade structure which concerns on 1st Embodiment of this invention. It is a schematic sectional drawing of the variable wing | blade structure which concerns on 1st Embodiment. (A) is the elements on larger scale of FIG. 2, (b) is a side view which shows the side end surface of a division | segmentation blade piece. It is explanatory drawing which shows the oil supply / discharge means of the variable blade structure which concerns on 1st Embodiment. It is a schematic sectional drawing which shows the operating state of the variable wing | blade structure which concerns on 1st Embodiment. It is the elements on larger scale of the variable wing | blade structure which concerns on 1st Embodiment, (a) shows a straight state (refer FIG. 2), (b) shows a bending state (refer FIG. 5). It is sectional drawing of the variable wing | blade structure which concerns on 2nd Embodiment of this invention. It is sectional drawing which bent the variable wing | blade structure which concerns on 2nd Embodiment. It is sectional drawing of the variable wing | blade structure which concerns on 3rd Embodiment of this invention. It is sectional drawing which bent the variable wing | blade structure which concerns on 3rd Embodiment.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for facilitating understanding of the invention, and do not limit the present invention unless otherwise specified. In the present specification and drawings, elements having substantially the same function and configuration are denoted by the same reference numerals, and redundant description is omitted, and elements not directly related to the present invention are not illustrated. To do.

(Variable wing structure 1: first embodiment)
FIG. 1 shows the appearance of the variable blade structure 1 according to the first embodiment of the present invention, and FIG. 2 shows a schematic cross-sectional view of the variable blade structure 1. A variable wing structure 1 according to the present embodiment is applied to a trailing edge of a main wing of an aircraft, and a plurality of divided wing pieces 2 that are rotatably connected so that their relative angles are variable, and two adjacent wing pieces 2 An oil chamber 3 formed on one of the divided blade pieces 2, and a partition member 5 that projects from the other of the two adjacent divided blade pieces 2 and partitions the oil chamber 3 into two hydraulic oil chambers 4. Yes.

(Split blade 2)
As shown in FIGS. 1 and 2, the adjacent divided blade pieces 2 are rotatably connected by a rotation shaft (hinge pin) 6 and its bearing so that the relative angle to each other is variable. . Each pivot shaft 6 is provided with a steering angle sensor (angle sensor) 7 for detecting a relative angle between the adjacent divided blade pieces 2.

  As shown in FIG. 3A, an outer plate (skin plate) 8 forming a blade surface is attached to each divided blade piece 2. The adjacent one (left side in the figure) split blade piece 2 is formed with a recess 9 into which the other (right side in the figure) split blade piece is inserted. In the outer plate 8, at least a portion 8 a from the end of the divided blade piece 2 to the tip inserted into the recess 9 is made of a flexible material (spring steel or the like).

(Oil chamber 3)
As shown in FIG. 2, an oil chamber 3 is formed in one of the divided blade pieces 2 adjacent to each other. The oil chamber 3 has an opening 3a facing the other adjacent divided blade piece 2, and is filled with hydraulic oil. The oil chamber 3 is formed along the blade span direction, and one divided blade piece 2 is disposed one or a plurality at intervals in the blade span direction.

(Partition member 5)
As shown in FIG. 3 (a), the other adjacent (the right side in the figure) split wing piece 2 has a position facing the opening 3a of the oil chamber 3 of the one (left side in the figure) split wing piece 2. A partition member 5 is projected. The partition member 5 is formed in a tapered cross-section so that the tip is inserted into the oil chamber 3 through the opening 3a and the root closes the opening 3a. At the base of the partition member 5, a rotation shaft 6 and its bearing for rotatably connecting the adjacent divided blade pieces 2 are disposed. The surface (opposite surface) 3 b of the oil chamber 3 that is opposed to the tip of the partition member 5 is formed in an arc shape around the rotation shaft 6. The partition member 5 partitions the oil chamber 3 into two hydraulic oil chambers 4 and rotates in the oil chamber 3 as the relative angle between the adjacent divided blade pieces 2 changes around the rotation shaft 6. .

(Tip hydraulic seal 10)
As shown in FIG. 3A, the front end of the partition member 5 is provided with a front end hydraulic seal 10 that contacts the facing surface 3 b of the oil chamber 3. The tip hydraulic seal 10 is in sliding contact with the facing surface 3 b of the oil chamber 3 when the partition member 5 rotates in the oil chamber 3 with a change in the relative angle between the divided blade pieces 2. The tip hydraulic seal 10 is formed from an elastic material such as rubber along the blade span direction, and hydraulic fluid passes from one hydraulic fluid chamber 4 between the partition member 5 and the opposing surface 3b, and the other hydraulic fluid. The leakage to the chamber 4 is suppressed. It should be noted that the tip hydraulic seal 10 may be arranged in two or more stages at intervals in the rotation direction instead of one stage.

(Root hydraulic seal 11)
As shown in FIG. 3A, a root hydraulic seal 11 is provided between the root of the partition member 5 and the chamber wall (opening 3a) of the oil chamber 3 to seal between them. The base hydraulic seal 11 is made of a flexible plate (for example, a rubber plate), one end of which is fixed to the base of the partition member 5 (adhesion, welding, bolting, etc.), and the middle is bent, The other end is fixed to the chamber wall (opening 3a) of the oil chamber 3. The root hydraulic seal 11 prevents the hydraulic oil in the hydraulic oil chamber 4 from leaking outside between the partition member 5 and the opening 3a.

(Side hydraulic seals 12, 13)
FIG. 3B is a side view showing the side end face of the divided blade piece 2 in the blade span direction. As shown in FIG. 3 (b), a first side hydraulic seal 12 is provided on the side end surface of the partition member 5 from the tip to the base along the blade cord direction, and at the base of the side end surface of the partition member 5. Is provided with a second side hydraulic seal (O-ring or the like) 13 formed in a ring shape so as to surround the rotation shaft 6. These first and second side surface hydraulic seals 12 and 13 are covered by a side wall portion (not shown) of the oil chamber 3 or by a side wall plate 14 (see FIG. 1) attached to the end face of the divided blade piece 2. The sealing state is maintained.

  The first side hydraulic seal 12 has one end connected to the tip hydraulic seal 10 and the other end connected to the second side hydraulic seal 13. The second side hydraulic seal 13 is connected to the root hydraulic seal 11. The first side hydraulic seal 12 is configured such that the hydraulic oil is between one hydraulic oil chamber 4 and the side end surface of the partition member 5 and the side wall portion of the oil chamber 3, or the side end surface of the partition member 5 and the side wall plate of the divided blade piece 2. 14 (see FIG. 1) to prevent leakage to the other hydraulic oil chamber 4. The second side hydraulic seal 13 is configured such that the hydraulic oil in the hydraulic oil chamber 4 is between the side end surface of the partition member 5 and the side wall portion of the oil chamber 3, or the side end surface of the partition member 5 and the side wall plate 14 of the divided blade piece 2. To prevent leakage to the outside through.

(Oil supply / discharge means 15)
As shown in FIG. 4, the variable blade structure 1 according to the present embodiment includes oil supply / discharge means 15 that supplies and discharges hydraulic oil to and from each hydraulic oil chamber 4. The oil supply / discharge means 15 adjusts the hydraulic pressure applied to the partition member 5 by the hydraulic oil in each hydraulic oil chamber 4 by supplying and discharging the hydraulic oil to each hydraulic oil chamber 4. By adjusting the hydraulic pressure applied to the partition member 5, the partition member 5 can be rotated to change the relative angle between the adjacent divided blade pieces 2.

  The oil supply / discharge means 15 is provided separately for each oil chamber 3 for changing the relative angle between adjacent divided blade pieces 2 (three systems for each of three oil chambers 3 in FIG. 4), The reservoir 16 in which the hydraulic oil is stored, the hydraulic pump 17 that pumps the hydraulic oil in the reservoir 16 toward the hydraulic oil chamber 4, and the supply destination of the hydraulic oil pumped from the hydraulic pump 17 is the upper side in FIG. A servo valve 18 having a function of switching between the oil chamber 4 and the lower hydraulic oil chamber 4 and a function of blocking is provided.

  The servo valve 18 has a switching mechanism for a cross 18a, a shut 18b, and a parallel 18c. When the servo valve is set to parallel 18 c, the hydraulic oil pumped from the hydraulic pump 17 is supplied to the lower hydraulic oil chamber 4, and the hydraulic oil in the upper hydraulic oil chamber 4 is returned to the reservoir 16. When the servo valve 18 is set to the cross 18 a, the hydraulic oil pumped from the hydraulic pump 17 is supplied to the upper hydraulic oil chamber 4, and the hydraulic oil in the lower hydraulic oil chamber 4 is returned to the reservoir 16. When the servo valve 18 is set to the shut 18b, the supply and discharge of the hydraulic oil to and from the upper and lower hydraulic oil chambers 4 are blocked.

(Action / Effect)
In the variable blade structure 1 according to the present embodiment, the blade shape is deformed downward as shown in FIG. 5 by making the servo valve 18 of the oil supply / discharge means 15 shown in FIG. 4 a cross 18a. At this time, the wing shape is deformed from FIG. 6A (the wing shape represents a straight state) to FIG. 6B (the wing shape represents a downward state), and the upper outer plate 8 is deformed. The end portion 8a is pulled out from the recess 9 while being bent, and the end portion 8a of the lower outer plate is inserted into the recess 9 while being bent. When the servo valve 18 is set to the parallel 18c, the blade shape is deformed upward. By making the servo valves 18 appropriately cross 18a and parallel 18c, the blade shape can be meandered. Then, by setting each servo valve 18 to the shut 18b, the hydraulic pressure in each hydraulic oil chamber 4 is locked, and the blade shape can be held in a deformed shape at that time.

  Each servo valve 18 is controlled by a control unit (not shown). The control unit sets a target angle of each rotating shaft 6 according to a desired blade shape to be deformed, and an output value (detection angle) of a rudder angle sensor 7 (see FIG. 1) disposed on each rotating shaft 6. Based on the above, each servo valve 18 is feedback-controlled so that the deviation between the detected angle and the target angle converges to zero. Thereby, a wing | blade shape can be correctly changed into a desired shape. Moreover, the nominal rudder angle of a wing | blade can be formed by balancing the hydraulic pressure of the upper and lower hydraulic oil chambers 4 in the same hydraulic system. The control unit holds and fixes the blade shape by changing the shape of the blade to a desired shape and then setting each servo valve 18 to the shut 18b.

  As described above, according to the variable blade structure 1 according to the present embodiment, the plurality of divided blade pieces 2 are rotatably connected by the rotation shaft 6 so that the relative angles of the divided blade pieces 2 are variable, and adjacent to each other. A partition member 5 projecting from the other split blade piece 2 is inserted into the oil chamber 3 formed on one of the split blade pieces 2, and the inside of the oil chamber 3 is partitioned into two hydraulic oil chambers 4 by the partition member 5, By supplying and discharging the hydraulic oil to and from each hydraulic oil chamber 4, the hydraulic pressure applied to the partition member 5 by the hydraulic oil in each hydraulic oil chamber 4 is adjusted, and the partition member 5 is rotated and divided in the oil chamber 3. The relative angle between the wing pieces 2 is changed.

  Thus, since the oil pressure 3 is directly applied to the oil chamber 3 and the partition member 5 provided in the divided blade piece 2 and the relative angle between the divided blade pieces 2 is changed, the blade shape is deformed. In order to change the relative angle between them, a complicated link mechanism that has been conventionally required is not required. Therefore, a space for accommodating the link mechanism is not required, and the present invention can be applied to a blade having a thin blade thickness (for example, a high-speed blade).

  In addition, since the hydraulic pressure is directly applied to the oil chamber 3 and the partition member 5 provided in the divided blade piece 2 to deform the blade shape, the hydraulic pressure in the hydraulic oil chamber 4 is increased, so that the blade can be easily Can counteract aerodynamic loads applied to Therefore, the shape of the wing can be changed and maintained without causing an increase in weight even under use conditions where the aerodynamic load applied to the wing is large (for example, during high-speed flight or sudden turning).

  Further, the moment (hinge moment) for changing the relative angle between the adjacent divided blade pieces 2 is obtained by the hydraulic pressure applied to the partition member 5 in the oil chamber 3. The longer the length to the tip, the larger the length. Therefore, the hinge moment can be earned without increasing the blade thickness by elongating the partition member 5 in the blade cord direction and correspondingly deepening the oil chamber 3 in the blade cord direction. Therefore, the variable blade structure 1 is suitable for a blade having a thin blade thickness.

  Further, since the oil chamber 3 is formed inside the divided blade piece 2, the invention according to Japanese Patent Application No. 2011-41685 filed earlier by the present applicant (a part of the oil chamber is formed by a flexible outer plate). Compared with the one to be partitioned), the seal configuration can be simplified and the possibility of leakage of hydraulic oil can be reduced.

  Moreover, since the some division | segmentation blade piece 2 is connected, even if one connection part (rotating shaft 6) is damaged and failed, it has the redundancy that a wing | blade shape can be deform | transformed by the remaining connection part. Further, as shown in FIG. 4, since three oil supply / discharge means 15 are provided for each of the three oil chambers 3, even if some of the oil supply / discharge means 15 are damaged / failed, the remaining oil Redundancy that the blade shape can be deformed by the supply / discharge means 15 is provided.

(Second Embodiment)
7 and 8 show a variable blade structure 1a according to a second embodiment of the present invention. In the variable wing structure 1a according to the second embodiment, two oil chambers 3 on the root side (the leading edge side of the wing) are formed by an inner skin (inner plate) 19 and a girder 20, and the tip side (the trailing edge side of the wing) ) Except that the one oil chamber 3 is formed by the outer plate 8 and the girder 20. Therefore, the same components as those in the first embodiment are denoted by the same reference numerals and description thereof is omitted. The effect of 2nd Embodiment is the same as that of 1st Embodiment.

(Third embodiment)
9 and 10 show a variable wing structure 1b according to a third embodiment of the present invention. In the variable wing structure 1 b according to the third embodiment, the partition member 5 is disposed on the trailing edge side of the blade with respect to the rotation shaft 6. This is different from the first and second embodiments arranged on the edge side, and the other configurations are substantially the same as those of the first and second embodiments. Therefore, the same components as those in the first embodiment are denoted by the same reference numerals and description thereof is omitted. The third embodiment is also different in that the oil chamber 3 is formed by the outer plate 8 and the girder 20, but the basic function and effect are the same as those of the first embodiment.

  The preferred embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the above-described embodiments, and various modifications within the scope of the claims. Needless to say, examples and modifications also belong to the technical scope of the present invention.

  For example, the variable wing structure according to the present invention is not limited to the one applied to the trailing edge side of the main wing of an aircraft, but includes at least one of the leading edge side of the main wing, the trailing edge side and the leading edge side of the horizontal tail, the trailing edge side and the front of the vertical tail. You may apply to at least one of the edge side. Moreover, you may apply to the front-end | tip of the span direction of a wing | blade.

  The present invention can be used for a variable wing structure that changes the shape of a wing of an aircraft or the like.

DESCRIPTION OF SYMBOLS 1 Variable blade structure 2 Split blade piece 3 Oil chamber 3a Opening 3b Opposite surface 4 Hydraulic oil chamber 5 Partition member 6 Rotating shaft 10 Tip hydraulic seal 11 Root hydraulic seal 15 Oil supply / discharge means

Claims (6)

A variable wing structure that changes the wing shape,
A plurality of split wing pieces that are rotatably coupled so that their relative angles are variable;
An oil chamber formed in one of two adjacent divided blade pieces and filled with hydraulic oil therein;
A partition member that protrudes from the other of the two adjacent divided blade pieces, partitions the oil chamber into two hydraulic oil chambers, and rotates the oil chamber as the relative angle changes;
Oil that supplies and discharges hydraulic oil to and from the two hydraulic oil chambers, adjusts the hydraulic pressure applied to the partition member by the hydraulic oil in each hydraulic oil chamber, and rotates the partition member to change the relative angle. A variable wing structure comprising a supply / discharge means. The oil chamber has an opening facing the other of the divided blade pieces;
The tip of the partition member is inserted into the oil chamber through the opening,
The variable wing structure according to claim 1, wherein a base of the partition member closes the opening. At the base of the partition member, a rotating shaft and a bearing that rotatably connect adjacent divided blade pieces are disposed,
3. The variable wing structure according to claim 1, wherein a facing surface of the oil chamber facing the tip of the partition member is formed in an arc shape centering on the rotation shaft.   The variable according to any one of claims 1 to 3, wherein a tip hydraulic seal is provided at a tip of the partition member so as to be in sliding contact with a facing surface of the oil chamber as the relative angle changes. Wing structure.   The variable blade structure according to any one of claims 1 to 4, further comprising a root hydraulic seal that seals between a root of the partition member and a chamber wall of the hydraulic oil chamber.   The base hydraulic seal is made of a flexible plate, one end of which is fixed to the base of the partition member, the middle is bent, and the other end is fixed to the chamber wall of the oil chamber. The variable wing structure according to claim 5.

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