CN101249887A - An aileron rotating retractable flapping wing device - Google Patents

Abstract

The present invention is an aileron rotating retractable flapping wing device, specifically comprising: aileron rotating retractable flapping wing and corresponding driving device, wherein the wing is divided into two parts, the main wing and the aileron along the span direction , the leading edge frame of the main wing and the leading edge frame of the aileron are connected by a hinge, and the two can take the hinge as the axis and rotate relatively in the plane of the wing, so that the aileron surface can be received under the main wing surface; the driving device includes the main wing The driving device and the aileron driving device are driven and connected by the drive shaft; the main wing driving device is located in the nose part and consists of two sets of symmetrical crank-rocker mechanisms, which drive the left and right wings respectively; the aileron The driving device is located in the middle and rear of the wing in the chord direction. The invention adopts the bevel gear pair to realize the transformation of the rotating shaft, so that a single power can drive multi-degree-of-freedom movements, which is equivalent to saving a driving shaft and a corresponding motor, and greatly reducing the weight.

Description

An aileron rotating retractable flapping wing device

1. Technical field

The invention relates to an aileron rotating and retractable flapping wing device, in particular to a flapping wing airfoil and a driving device thereof which rely on the aileron rotating and retracting to change the wing area and increase lift, and belongs to the technical field of flapping wing aircraft.

2. Background technology

Flapping-wing flight can take off in situ or in a small field, and lift, hover and propel are realized only by flapping wings. It has strong air maneuverability, high flight aerodynamic efficiency and low energy consumption. Therefore, the research on flapping-wing aircraft has great prospects and value. . However, flapping wing research is still immature in all aspects and needs to be developed.

A single-degree-of-freedom flapping simple wing produces little lift and poor flight effects. To increase lift and improve load capacity, it is necessary to achieve multi-degree-of-freedom flapping wings similar to birds or insects or flapping wings with variable effective area of the wings. However, this often results in a complex driving device and excessive structural weight, which is not worth the candle. The existing mechanical flapping wing device does not have a good solution for this contradiction.

3. Contents of the invention

The object of the present invention is to provide an aileron rotating retractable flapping wing device to solve the contradictions in the prior art, which can produce relatively complex motion and large lift without causing excessive weight.

The present invention is an aileron rotating and retractable flapping wing device, which specifically includes: aileron rotating and retractable flapping wing wings and corresponding drive devices, wherein

(1) flapping wing

According to the direction of the wingspan, the wing is divided into two parts, the main wing and the aileron. The part close to the wing root and with a larger area is the main wing, and the part of the wing spanning to the outer edge is the aileron. The main support and movement tasks of the wing are undertaken by its leading edge skeleton, and the specific airfoil and the secondary skeleton of the airfoil can be selected according to actual needs. The leading edge frame of the main wing and the leading edge frame of the aileron are connected by a hinge, and the two can rotate relative to each other in the plane of the wing with the hinge as the axis, so that the aileron surface can be received under the main wing surface.

Wherein, the root of the leading edge frame of the main wing is respectively fixed on a frame plate through a rotating shaft.

(2) Drive device

The drive device of the present invention comprises a main wing drive device and an aileron drive device, and the two drive devices are driven and connected by a drive shaft (ie a drive shaft);

The main wing driving device is located at the nose part and consists of two sets of symmetrical crank-rocker mechanisms to drive the left and right wings respectively. The crank-rocker mechanism on each side consists of a large spur gear with an eccentric hole and a connecting rod. The center of the large cylindrical gear is fixed on the frame plate through a rotating shaft; one end of the connecting rod is hinged with the eccentric hole of the large cylindrical gear, and the other end is hinged with the leading edge frame of the main wing closer to the root.

The drive shaft is parallel to the axis of symmetry of the fuselage, located at the lower part of the fuselage, and in the plane of symmetry of the fuselage; the transmission from the drive shaft to the main wing drive device uses a commonly used secondary gear, and one of the large cylindrical gears is used as a secondary gear The low-speed gear in the middle can be used; wherein, the transmission from the drive shaft to the main wing drive device can also be selected with multi-stage gears.

The aileron driving device is located at the middle rear of the wing in the chord direction and is divided into three parts:

One is a bevel gear pair consisting of a driving bevel gear and a driven bevel gear. The driving bevel gear is driven by the driving shaft, and the axis is horizontal; the axis of the driven bevel gear is vertical. Among them, this part can also increase the cylindrical gear pair according to the needs of the reduction ratio.

The second is a slider crank mechanism, including an eccentric wheel, a connecting rod, a slide block and a slide block guide rail. The eccentric wheel is located above the driven bevel gear and rotates coaxially with it; one end of the connecting rod is hinged on the eccentric hole of the eccentric wheel, and the other end is connected with the slide block. The slider guide rail is located in the vertical symmetry plane of the fuselage. In this way, the rotation of the eccentric wheel drives the slider to reciprocate along the track. Wherein, the slider is formed by fitting the first component and the second component. The first component is a square block base with a thin cylindrical rod protruding from the center of the upper part, and the base is embedded in the slider guide rail; the lower part of the second component is a cylindrical sleeve, which is tightly matched with the thin cylindrical rod of the first component. The upper part is a long block structure with a ring at the left and right ends, which is used to install the left and right spherical hinges, and the rings are sleeved on the arms of the spherical hinges. Its specific shape depends on the spherical hinge used, and it cooperates with common spherical hinges. Wherein, the connecting rod has a ring at one end connected with the slider, which is sleeved outside the cylindrical sleeve of the slider.

The third is two symmetrical hinge mechanisms, which are used to directly realize the rotation and retraction of the left and right ailerons. The hinge mechanism on each side consists of a slider, a connecting rod and the leading edge frame of the aileron on that side. One end of the connecting rod is hinged on the slider, and the other end is hinged on a point in the middle of the aileron leading edge frame. In this way, when the slide block moves forward and backward, it will pull the aileron leading edge skeleton to rotate around its hinge point with the main wing leading edge skeleton. Wherein, the hinged connection between one end of the connecting rod and the slider is a spherical hinge connection, so that the connecting rod can not only move with the slider but also rotate relative to the slider, so that the aileron and its connecting rod can flutter with the main wing. It is a two-degree-of-freedom movement that can rotate and retract relative to the main wing.

The present invention is an aileron rotating retractable wing flapping device. Its advantages and effects are: the wing airfoil proposed by the present invention transfers the change of the wing area during flight to the outer edge, and the plane of the wing is always a whole. It not only realizes the variable wing area but also avoids this uncertainty; the bevel gear pair is used in the driving device to realize the transformation of the rotating shaft, so that a single power can drive multi-degree-of-freedom motion, which is equivalent to saving a driving shaft and Corresponding to the motor, the weight is greatly reduced. Therefore, a kind of aileron rotation and retractable flapping wing device of the present invention not only realizes the improvement of lift to a large extent, but also avoids excessive weight of the mechanism.

4. Description of drawings:

Figure 1 shows a schematic diagram of two driving devices driven by one driving shaft

Figure 2 shows the schematic diagram of the main wing and its driving device

Figure 3 shows a schematic diagram of the aileron and its driving device

Fig. 4 shows the skeleton schematic diagram of flapping wing device structure of the present invention

Fig. 5 shows the structural representation of slider in the present invention

Fig. 6 is a schematic structural view of component 1 of the slider in the present invention

The specific labels in the figure are as follows:

A. Drive shaft (drive shaft) B. Transmission shaft

1. Driving bevel gear 2. Driven bevel gear 3. Small cylindrical gear

3', the low-speed gear in the first-level cylindrical gear pair 4, the high-speed gear in the second-level cylindrical gear pair

4', 5, large cylindrical gear 6, 9, 12, connecting rod 7, main wing leading edge skeleton

8. Eccentric wheel 10. Slider 11. Slider guide rail

13. Aileron leading edge frame 14. Shelf plate 101. Base

102. Cylindrical thin rod 103. Cylindrical sleeve

5. Specific implementation methods:

Below in conjunction with accompanying drawing, technical scheme of the present invention is further described as follows:

Please refer to Fig. 1 to Fig. 4, an aileron rotating retractable flapping wing device according to the present invention, which specifically includes: aileron rotating retractable flapping wing wing and corresponding driving device, wherein

(1) flapping wing

According to the direction of the wingspan, the wing is divided into two parts, the main wing and the aileron. The part close to the wing root and with a larger area is the main wing, and the part of the wing spanning to the outer edge is the aileron. The main support and movement tasks of the wing are undertaken by its leading edge skeleton, and the specific airfoil and the secondary skeleton of the airfoil can be selected according to actual needs. The main wing leading edge frame 7 and the aileron leading edge frame 13 are connected by a hinge, and the two can take the hinge as an axis to relatively rotate in the wing plane, so that the aileron surface can be received under the main wing surface.

Wherein, the root of the leading edge frame 7 of the main wing is respectively fixed on a frame plate 14 through a rotating shaft.

During a flapping cycle:

When the wings are flapping down, the ailerons are partially rotated → fully extended → partially retracted;

When the wings are flapping up, the ailerons are partially retracted → fully retracted → partially rotated out.

The wing area that produces resistance when the wing flutters up like this is always smaller than the wing area that produces lift when fluttering down, thereby can significantly increase the average lift.

(2) Drive device

The drive device of the present invention comprises a main wing drive device and an aileron drive device, and the two drive devices are driven and connected by a drive shaft (ie a drive shaft);

The main wing driving device is located at the nose part and consists of two sets of symmetrical crank-rocker mechanisms to drive the left and right wings respectively. The crank-rocker mechanism on each side includes a large spur gear 4', 5 with an eccentric hole and a connecting rod 6. The centers of the large cylindrical gears 4', 5 are fixed on the frame plate 14 through the rotating shaft; Hinge near the root end. When the large gear rotates like this, the eccentric hole that plays the role of the crank just drives the wing leading edge skeleton as the rocker to swing back and forth around its root to realize the flapping action. The left and right symmetrical two large gears are meshed to realize the synchronous flapping of the two wings.

The drive shaft A is parallel to the axis of symmetry of the fuselage, located at the lower part of the fuselage, and the drive shaft A is located in the plane of symmetry of the fuselage. The transmission from the drive shaft to the main wing drive device uses a commonly used secondary gear, and one of the large cylindrical gears It can be used as a low-speed gear in the secondary gear; wherein, the transmission from the drive shaft to the main wing drive device can also be a multi-stage gear.

The aileron driving device is located at the middle rear of the wing in the chord direction and is divided into three parts:

One is a bevel gear pair, which is composed of a driving bevel gear 1 and a driven bevel gear 2. The driving bevel gear is driven by the driving shaft, and the axis is horizontal; the axis of the driven bevel gear is vertical. Among them, this part can also increase the cylindrical gear pair according to the needs of the reduction ratio.

The second is a slider crank mechanism, including an eccentric wheel 8, a connecting rod 9, a slide block 10 and a slide block guide rail 11. The eccentric wheel is located above the driven bevel gear and rotates coaxially with it; one end of the connecting rod 9 is hinged on the eccentric hole of the eccentric wheel 8 , and the other end is hinged on the slider 10 . The slider guide rail 11 is located in the vertical symmetrical plane of the fuselage. In this way, the rotation of the eccentric wheel drives the slider to reciprocate along the track. Wherein, the slider 10 is formed by fitting the first component and the second component. Component 1 is a square block base 101 with a cylindrical thin rod 102 protruding from the center of the top, wherein the base 101 is embedded in the slider guide rail 11; the lower part of component 2 is a cylindrical sleeve 103, which is consistent with the cylindrical thin The rod is a tight fit, and the upper part is a long block structure with a ring at the left and right ends, which is used to install the left and right spherical hinges, and the rings are sleeved on the arms of the spherical hinges. Its specific shape depends on the spherical hinge used, and it cooperates with common spherical hinges. Wherein, the connecting rod 9 has a ring at one end connected with the slider, which is sleeved outside the cylindrical sleeve 103 of the slider.

The third is two symmetrical hinge mechanisms, which are used to directly realize the rotation and retraction of the left and right ailerons. The hinge mechanism of each side is made up of slide block 10, connecting rod 12 and this side aileron leading edge skeleton 13. One end of the connecting rod 12 is hinged on the slider 10, and the other end is hinged on a point in the middle section of the aileron leading edge frame 13. In this way, when the slide block moves forward and backward, it will pull the aileron leading edge frame 13 to rotate around its hinge point with the main wing leading edge frame. Wherein, the hinged connection between one end of the connecting rod and the slider is a spherical hinge connection, so that the connecting rod can not only move with the slider but also rotate relative to the slider, so that the aileron and its connecting rod can flutter with the main wing. It is a two-degree-of-freedom movement that can rotate and retract relative to the main wing.

Utilize above-mentioned structure composition, the two-degree-of-freedom motion realization process of wing of the present invention is as follows:

First, the rotation is input by the driving shaft A.

In the main wing drive device, the two-stage gear transmission 3-3', 4-4' transmits the rotation to the large cylindrical gear 4' and 5, and the large cylindrical gear 4' and 5 form a gear pair with a transmission ratio of 1. The two gears There is an eccentric hole on each side, and the two holes are symmetrical. The distance from the eccentric hole to the center of the large cylindrical gear is equivalent to the crank, which forms a double-crank rocker mechanism with the connecting rod 6 and the main wing front edge frame 7. When the driving shaft A rotates, the main wing will realize flapping move. Large cylindrical gear 4 ' and 5 rotate one cycle, just realize that main wing lifts up and down flutters one cycle.

In the aileron drive device, the horizontal rotation of the driving shaft A is transformed into the vertical rotation of the transmission shaft through the transmission of the driving bevel gear 1 and the driven bevel gear 2. The eccentric wheel 8 rotates coaxially with the driven bevel gear 2, and an eccentric hole is opened on the eccentric wheel 8, and the crank slider mechanism is composed of the eccentric hole, the connecting rod 9 and the slider 10, and the slider 10 is driven along the slider guide rail 11. In reciprocating motion, the slider 10 forms a slider mechanism with the connecting rod 12 and the aileron leading edge frame 13 to drive the aileron to rotate relative to the main wing. One revolution of the eccentric wheel 8 just realizes one cycle of outward rotation and retraction of the aileron.

The present invention adopts the bevel gear pair to realize the conversion of the rotating shaft, so that a single power can drive multi-degree-of-freedom motion, which is equivalent to saving a driving shaft and a corresponding motor, and greatly reducing the weight.

Claims (4)

1, a kind of Aileron rotary retractable flapping wing device specifically comprises: Aileron rotary retractable flapping wing wing and corresponding driving device is characterized in that:

(1) flapping wing wing

Be divided into main wing, aileron two parts by wing along spanwise, close wing root, the part that area is bigger are main wing, and the wing exhibition is an aileron to peripheral edge portion; Main wing leading edge skeleton (7), aileron leading edge skeleton (13) link to each other by hinge, and both can be axle with the hinge, rotation relatively in wingpiston, make aileron surface can receive under the main plane;

Wherein, the root of main wing leading edge skeleton (13) is fixed on the frame plate (14) by rotating shaft respectively;

(2) actuating device

Comprise main wing actuating device and aileron actuating device, drive connection by imput shaft (A) between two actuating devices; Described main wing actuating device is positioned at head section, is made up of the quadric linkage of two cover symmetries, drives left and right both wings respectively; The quadric linkage of each side includes the big column gear (4 '), (5) and the connecting rod (6) that have eccentric orfice; Described big column gear (4 '), (5) center are fixed on the frame plate (14) by rotating shaft; The eccentric orfice of described connecting rod (6) one ends and big column gear (4 '), (5) is hinged, and the other end and main wing leading edge skeleton (13) are hinged near root end;

Described imput shaft (A) is parallel to the fuselage axis of symmetry line, is positioned at underbelly, and in the fuselage symmetrical plane;

Described aileron actuating device, be positioned at airfoil chord to postmedian, be divided into three parts:

One is a bevel-gear pair, is made up of a drive bevel gear (1), a driven wheel of differential (2); Described drive bevel gear (1) is driven by imput shaft (A), axis horizontal; Described driven wheel of differential (2) axis is vertical;

It two is a slider-crank mechanism, comprises an eccentric wheel (8), a connecting rod (9), a slide block (10) and a slide block guide rail (11); Described eccentric wheel (8) is positioned at the top of driven wheel of differential (2), coaxial rotation with it; One end of connecting rod (9) is articulated on the eccentric orfice of eccentric wheel (8), and the other end links to each other with slide block (10); Slide block guide rail (11) is positioned at the vertical symmetrical plane of fuselage;

It three is the linkage of two symmetries, is used for directly realizing the rotation folding and unfolding of left and right aileron; The linkage of every side is made up of slide block (10), connecting rod (12) and this side aileron leading edge skeleton (13); One end of connecting rod (12) is articulated on the slide block (10), and the other end is articulated in a bit of aileron leading edge skeleton (13) stage casing.

2, a kind of Aileron rotary retractable flapping wing device according to claim 1, it is characterized in that: described slide block (10) is to be formed by assembly one and assembly two two parts phase fits: assembly one is a square block base (101), the thin bar of center projection one cylinder (102) above it, wherein base (101) is embedded among the slide block guide rail (11); The bottom of assembly two is a cylindrical sleeves (103), with the thin bar of cylinder of assembly one be flush fit, top is that left and right end respectively is the long block structure of a ring, two spherical linkages about being used for installing, described ring set is on the arm of ball pivot.

3, a kind of Aileron rotary retractable flapping wing device according to claim 1 is characterized in that: described connecting rod (9), its end that links to each other with slide block has an annular, is placed in outside the cylindrical sleeves (103) of described slide block.

4, a kind of Aileron rotary retractable flapping wing device according to claim 1 is characterized in that: described connecting rod (12) one ends are to adopt spherical linkage to be connected with the articulated manner of slide block (10).

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