CN109533278B - Wing rib structure capable of realizing uniform telescopic deformation - Google Patents
Wing rib structure capable of realizing uniform telescopic deformation Download PDFInfo
- Publication number
- CN109533278B CN109533278B CN201811473820.7A CN201811473820A CN109533278B CN 109533278 B CN109533278 B CN 109533278B CN 201811473820 A CN201811473820 A CN 201811473820A CN 109533278 B CN109533278 B CN 109533278B
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- China
- Prior art keywords
- sliding
- rib
- pressurizing
- slideway
- wing rib
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- 238000005253 cladding Methods 0.000 claims 1
- 239000000835 fiber Substances 0.000 description 12
- 229920001971 elastomer Polymers 0.000 description 7
- 239000000806 elastomer Substances 0.000 description 6
- 239000012783 reinforcing fiber Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000001050 lubricating effect Effects 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229920000126 latex Polymers 0.000 description 1
- 239000004816 latex Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/30—Wings comprising inflatable structural components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
- Bearings For Parts Moving Linearly (AREA)
Abstract
The invention provides a rib structure capable of realizing uniform expansion and deformation, which comprises a rib front end fixed with a left slideway, a rib rear end fixed with a right slideway and a flexible skin covering between the rib front end and the rib rear end, wherein the left slideway and the right slideway are provided with clamping grooves matched with each other. A plurality of sliding blocks sliding along the sliding ways are uniformly arranged on the left sliding way and the right sliding way respectively, and the upper end and the lower end of each sliding block are respectively connected with a pressurizing type telescopic device. The two ends of the pressurizing type telescopic device are respectively connected with the left slideway and the right slideway through fixing pieces, the vertical direction of the pressurizing type telescopic device is provided with out-of-plane supporting rigidity for the flexible skin through the sliding blocks, and the horizontal direction of the pressurizing type telescopic device is provided with the distance between the sliding blocks through telescopic adjustment. The invention realizes larger deformation of the chord direction in the rib structure plane, and the deformation is uniform, the chord direction deformation amount can reach 50% -80%, and the rib structure plane has enough out-of-plane supporting rigidity.
Description
Technical Field
The invention relates to the field of aircraft structural design, in particular to a wing rib structure capable of realizing uniform telescopic deformation.
Background
In the flying process of the variant aircraft, the shape of the structure can be correspondingly changed according to different mission missions and flying conditions, and the flying mission can be executed with optimal aerodynamic performance in the whole flying envelope. Wings are the primary components that provide aerodynamic forces to maneuver aircraft, so research for variant aircraft has focused mainly on changes in wing configuration, including camber, thickness, span, sweep, area, etc., with the most critical being how the structure is implemented.
In the prior art, many researches on structural technologies of camber change, sweep change, span change and thickness change are reported, but few technical researches on changing the wing area through the chord direction deformation of the wing are reported.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a rib structure capable of realizing uniform expansion and deformation of the chord direction, realizing larger deformation of the chord direction in the plane of the rib structure, having uniform deformation, enabling the chord direction deformation to reach 50% -80%, and having enough out-of-plane supporting rigidity.
The invention comprises a rib front end and a rib rear end which are coated with a flexible skin, wherein a pressurizing type expansion device, a left slideway, a sliding block and a right slideway which are connected with a pressurizing valve are arranged between the rib front end and the rib rear end, one end of the left slideway is fixedly connected with the rib front end, one end of the right slideway is fixedly connected with the rib rear end, clamping grooves which are matched with each other are arranged on the left slideway and the right slideway, and when the chord direction distance between front and rear beams is changed, the left slideway and the right slideway only can slide relatively along the chord direction; a plurality of sliding blocks sliding along the sliding ways are uniformly arranged on the left sliding way and the right sliding way respectively, and the upper end and the lower end of each sliding block are respectively connected with a pressurizing type telescopic device; the two ends of the pressurizing type telescopic device are respectively connected with the left slideway and the right slideway through fixing pieces, the vertical direction of the pressurizing type telescopic device is provided with out-of-plane supporting rigidity for the flexible skin through the sliding blocks, and the horizontal direction of the pressurizing type telescopic device is provided with the distance between the sliding blocks through telescopic adjustment.
The sliding block is composed of a supporting rod, a sliding sleeve and a semicircular shell, wherein the sliding sleeve is sleeved on the left slideway and the right slideway, the middle part of the sliding sleeve is provided with a bulge, and the sliding sleeve slides on the left slideway, the right slideway and the matching part of the left slideway and the right slideway through the bulge; one end of the supporting rod is fixed on the sliding sleeve, the other end of the supporting rod is fixedly connected with the semicircular shell, and the pressurizing type telescopic device is nested in the semicircular shell.
In order to enable the driving force of the pressurizing type telescopic device to be effectively transmitted to the sliding block without relative sliding, the semicircular shell is provided with a clamp similar to the semicircular shell in structure, the flexible skin is fixed with the edge strip of the clamp, and the semicircular shell and the clamp are combined into a hollow ring to tightly lock the pressurizing type telescopic device. In order to compensate for the height difference between the flexible skin and the clamp, a gasket is arranged between the flexible skin and the edge strip of the clamp.
A gasket is arranged between the flexible skin and the edge strip of the clamp. The rib front end and the rib rear end are fixedly connected with concave fixing pieces, the pressurizing valve is connected with the corresponding concave fixing pieces, the pressurizing valve is provided with a connecting joint, the pressurizing joint is positioned at the rib front end, and the pressure relief joint is positioned at the rib rear end.
Providing sufficient torsion resistance for the rib, the left slide and the right slide are in closed cross-sectional configuration.
Further improved, the pressurizing type expansion device comprises an inner pressurizing elastomer and a reinforcing fiber net, wherein the inner pressurizing elastomer is a hollow cylindrical elastomer, and the reinforcing fiber net is wound outside the elastic shell in a form of a woven net. The reinforced fiber net has several pairs of fiber, each pair of fiber includes two fiber bundles wound symmetrically clockwise and anticlockwise, and the fiber is polymer or metal wire with great elastic modulus. The axial included angle between the fiber and the pressurizing type expansion device is 60-90 degrees, and the larger the angle is, the stronger the axial elongation capability is.
The invention has the beneficial effects that:
(1) The aircraft adopting the wing rib can realize uniform expansion deformation of the aircraft wing in the chord direction in the flight process, and change the area of the wing, thereby changing the lift force and the resistance on the wing and improving the aerodynamic appearance of the aircraft.
(2) The novel wing rib has a simple structure, is easy to realize, and does not increase weight too much while improving aerodynamic characteristics of the wing.
Drawings
Fig. 1 is a schematic view of a rib structure when not deformed by extension.
Fig. 2 shows a schematic view of the rib structure during the telescopic deformation.
Fig. 3 is a schematic diagram of the left and right slide assembly front and rear cross-section.
Fig. 4 is a schematic top view of the slideway slide after assembly.
FIG. 5 is a schematic cross-sectional view of the slider assembled with the slideway.
Fig. 6 is a schematic diagram of a connection device.
Description of the embodiments
The invention is further described below with reference to the accompanying drawings.
Under the condition of realizing the basic function of the wing rib, the wing rib can change in length along the chord direction, so that the wing area is changed. The wing rib mainly comprises a wing rib front end 1, a pressurizing valve 2, a pressurizing type telescopic device 3, a left slideway 4, a sliding block 5, a clamp 6, a right slideway 7 and a wing rib rear end 8, wherein the structure of the wing rib when not in telescopic deformation is shown in the attached figure 1, and the structure after telescopic deformation is shown in the attached figure 2.
One end of the left slideway 4 is fixedly connected with the front end 1 of the wing rib fixed on the front girder web, and one end of the right slideway 7 is fixedly connected with the rear end 8 of the wing rib connected on the rear girder web. When the chord direction distance between the front beam and the back beam changes, the left slide rail and the right slide rail relatively slide, the pressurizing type telescopic device 3 pressurizes and adjusts the length of the wing rib, the sliding blocks 5 are uniformly arranged on the slide rail to support the pressurizing type telescopic device 3, out-of-plane supporting rigidity is provided for the flexible skin, and along with the extension of the pressurizing type telescopic device 3, the distance between the sliding blocks 5 is also uniformly changed.
The left slideway 4 and the right slideway 7 are respectively provided with a clamping groove, after assembly, the left slideway 4 and the right slideway 7 can only slide relatively along the chord direction, and the sectional shapes before assembly and after assembly are shown in the figure 3. The left runner 4 and the right runner 7 are each of a closed cross-sectional configuration providing sufficient torsion resistance to the rib.
The slide block 5 consists of a support rod, a sliding sleeve and a semicircular shell. The sliding sleeve is sleeved on the left slide way 4 and the right slide way 7, the middle part of the sliding sleeve is provided with a bulge, so that the sliding sleeve can slide on the left slide way 4, the right slide way 7 and the matched part of the left slide way 4 and the right slide way 7, the top view of the sliding sleeve after the sliding sleeve is matched is shown in the figure 4, and the section of the sliding sleeve is shown in the figure 5. One end of the supporting rod is fixed on the sliding sleeve, and the other end is fixedly connected with the semicircular shell. The pressurizing type telescopic device 3 is connected with the pressurizing valve 2 and then is respectively connected with the front end and the rear end of the wing rib through fixing pieces, as shown in figure 6.
The structure of the pressurizing type stretching device 3 mainly comprises an inner pressurizing elastomer and a reinforcing fiber net. Wherein the internal pressurizing elastomer is hollow cylindrical elastomer, and the material can be superelastic material such as rubber, latex, etc. Wherein the fiber is wound outside the elastic shell in the form of a woven mesh, and when the inside of the elastic body is pressurized, the reinforced fiber mesh limits the radial deformation of the elastic body and has stronger deformation capacity in the axial direction. The reinforcing fiber web has a plurality of pairs, each pair comprising two bundles of fibers symmetrically wound in clockwise and counterclockwise directions, respectively. The material of the fiber should be a polymer or a metal wire with a large elastic modulus. According to experience, the axial included angle between the fiber and the pressurizing type telescopic device 3 can be a value within 60-90 degrees, the larger the angle is, the stronger the axial elongation capability is, and the specific numerical value of the angle is determined according to actual conditions.
The specific assembly implementation method of the invention is as follows:
(1) The left slideway 4 and the right slideway 7 are assembled according to the figure 3, the roughness of the sliding contact surface is required to be high, and lubricating oil is used for lubricating so as to reduce the sliding friction force as much as possible.
(2) The slide block 5 is formed by a support rod, a sliding sleeve and a semicircular shell and is formed by integral machining. The height of the struts on each slide is adjusted according to the position of the slide 5 on the slide and the size of the actual airfoil. The angle of the semi-circular shell with the chord direction depends on the angle of the corresponding airfoil with the chord direction.
(3) The sliding block 5 is assembled with the slideway according to fig. 5, the roughness of the sliding contact surface is required to be high, and lubricating oil is used for lubricating, so that the sliding friction force is reduced as much as possible.
(4) The left slideway 4 and the right slideway 7 are respectively fixed on the front end 1 and the rear end 8 of the wing rib. The rib front end 1 and the rib rear end 8 are respectively connected with the wing front beam and the wing rear beam.
(5) The two ends of the pressurizing type expansion device 3 are respectively connected with a pressurizing valve 2, concave fixing pieces are fixedly connected on the front end 1 of the wing rib and the rear end 8 of the wing rib, and the pressurizing valves 2 are connected with the corresponding concave fixing pieces, as shown in figure 6. The pressurizing valve 2 is provided with a connecting joint, wherein the pressurizing joint is positioned at the front end 1 of the wing rib, and the pressure relief joint is positioned at the rear end 8 of the wing rib. The specific position of the pressurizing (discharging) joint and the specific form of the pressurizing valve 2 can be changed correspondingly according to the actual situation.
(6) The pressurizing type telescopic device 3 is placed on the semicircular shell, so that the driving force of the pressurizing type telescopic device 3 can be effectively transmitted to the sliding block without relative sliding. The clamp 6 with the structure similar to that of the semicircular shell is arranged on the semicircular shell for placing the pressurizing type telescopic device 3, and the clamp and the semicircular shell are fixed, so that the pressurizing type telescopic device 3 is locked, and driving force can be effectively transmitted to the sliding block.
(7) The spanwise fibers of the flexible skin are fixed with the pressurizing type telescoping device 3. At the position of the semicircular shell and the clamping hoop 6 locking the pressurizing type telescopic device 3, the flexible skin is fixed with the edge strip of the clamping hoop 6. To compensate for the height difference, a spacer is provided between the flexible skin and the rim of the clip 6.
(8) Among the front and rear beams connected to the rib, the rear beam should be a movable beam, and a slideway and a driver are provided at the root so that it can be displaced in the chord direction.
The actual extension distance of the wing rib has a large relationship with the deformation and output performance of the pressurizing type telescopic device 3, the friction factor between sliding rails, the actual bearing of the wing rib, the movable distance of the root of the rear beam and the performance of a driver.
In practical application, the deformation condition of the pressurizing type expansion device 3 can be measured through a displacement sensor to control the pressurizing and depressurizing of the pressurizing type expansion device 3 by the air pressure source. The form of the partial structure is adjusted and the pressurizing type telescopic device 3 is designed according to the actual needed deformability and bearing condition.
The present invention has been described in terms of the preferred embodiments thereof, and it should be understood by those skilled in the art that various modifications can be made without departing from the principles of the invention, and such modifications should also be considered as being within the scope of the invention.
Claims (4)
1. The utility model provides a rib structure that can realize even flexible deformation, includes rib front end (1) and rib rear end (8) that the cladding has flexible covering, its characterized in that: the novel wing rib comprises a wing rib front end (1) and a wing rib rear end (8), wherein a pressurizing type telescopic device (3), a left slide way (4), a sliding block (5) and a right slide way (7) which are connected with a pressurizing valve (2) are arranged between the wing rib front end (1) and the wing rib rear end (8), one end of the left slide way (4) is fixedly connected with the wing rib front end (1), one end of the right slide way (7) is fixedly connected with the wing rib rear end (8), clamping grooves which are matched with each other are formed in the left slide way (4) and the right slide way (7), and when the chord direction distance between front and rear beams is changed, the left slide way (4) and the right slide way (7) only can slide relatively along the chord direction; a plurality of sliding blocks (5) sliding along the sliding ways are uniformly arranged on the left sliding way (4) and the right sliding way (7) respectively, and the upper end and the lower end of each sliding block (5) are connected with a pressurizing type telescopic device (3) respectively; two ends of the pressurizing type expansion device (3) are respectively connected with the left slideway (4) and the right slideway (7) through fixing pieces, the pressurizing type expansion device (3) provides out-of-plane supporting rigidity for the flexible skin through the sliding blocks (5) in the vertical direction, and the interval between the sliding blocks (5) is adjusted through the expansion of the pressurizing type expansion device (3) in the horizontal direction; the sliding block (5) consists of a supporting rod, a sliding sleeve and a semicircular shell, wherein the sliding sleeve is sleeved on the left sliding way (4) and the right sliding way (7), the middle part of the sliding sleeve is provided with a bulge, and the sliding sleeve slides on the left sliding way (4), the right sliding way (7) and the matching part of the left sliding way (4) and the right sliding way (7) through the bulge; one end of the supporting rod is fixed on the sliding sleeve, the other end of the supporting rod is fixedly connected with the semicircular shell, and the pressurizing type telescopic device (3) is nested in the semicircular shell; the semicircular shell is provided with a clamp (6) similar to the semicircular shell in structure, the flexible skin is fixed with a rim of the clamp (6), and the semicircular shell and the clamp (6) are combined into a hollow ring to tightly lock the pressurizing type telescopic device (3).
2. The rib structure capable of achieving uniform telescopic deformation according to claim 1, wherein: a gasket is arranged between the flexible skin and the edge strip of the clamp (6).
3. The rib structure capable of achieving uniform telescopic deformation according to claim 1, wherein: concave fixing pieces are fixedly connected to the front end (1) and the rear end (8) of the wing rib, the pressurizing valve (2) is connected with the corresponding concave fixing pieces, a connecting joint is arranged on the pressurizing valve (2), the pressurizing joint is positioned at the front end (1) of the wing rib, and the pressure relief joint is positioned at the rear end (8) of the wing rib.
4. The rib structure capable of achieving uniform telescopic deformation according to claim 1, wherein: the left slideway (4) and the right slideway (7) are of closed cross-section configuration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811473820.7A CN109533278B (en) | 2018-12-04 | 2018-12-04 | Wing rib structure capable of realizing uniform telescopic deformation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811473820.7A CN109533278B (en) | 2018-12-04 | 2018-12-04 | Wing rib structure capable of realizing uniform telescopic deformation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109533278A CN109533278A (en) | 2019-03-29 |
| CN109533278B true CN109533278B (en) | 2024-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811473820.7A Active CN109533278B (en) | 2018-12-04 | 2018-12-04 | Wing rib structure capable of realizing uniform telescopic deformation |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112098041B (en) * | 2020-08-18 | 2021-08-06 | 南京航空航天大学 | Rigidity adjusting device of wing low-speed flutter wind tunnel test model |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009190574A (en) * | 2008-02-14 | 2009-08-27 | Honda Motor Co Ltd | Wing structure for aircraft |
| WO2013027388A1 (en) * | 2011-08-23 | 2013-02-28 | 三菱航空機株式会社 | Slat, wing of aircraft, moving blade of aircraft, and aircraft |
| EP2639152A2 (en) * | 2012-03-14 | 2013-09-18 | The Boeing Company | Attachment of aircraft ribs to spars having variable geometry |
| CN106741845A (en) * | 2017-02-10 | 2017-05-31 | 哈尔滨工业大学 | A kind of empty amphibious aircraft wing distressed structure of water |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN107628228A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing continuously bent structure |
| CN108622369A (en) * | 2018-05-09 | 2018-10-09 | 南京航空航天大学 | Morphing aircraft wing structure |
-
2018
- 2018-12-04 CN CN201811473820.7A patent/CN109533278B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009190574A (en) * | 2008-02-14 | 2009-08-27 | Honda Motor Co Ltd | Wing structure for aircraft |
| WO2013027388A1 (en) * | 2011-08-23 | 2013-02-28 | 三菱航空機株式会社 | Slat, wing of aircraft, moving blade of aircraft, and aircraft |
| EP2639152A2 (en) * | 2012-03-14 | 2013-09-18 | The Boeing Company | Attachment of aircraft ribs to spars having variable geometry |
| CN106741845A (en) * | 2017-02-10 | 2017-05-31 | 哈尔滨工业大学 | A kind of empty amphibious aircraft wing distressed structure of water |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN107628228A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing continuously bent structure |
| CN108622369A (en) * | 2018-05-09 | 2018-10-09 | 南京航空航天大学 | Morphing aircraft wing structure |
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| Publication number | Publication date |
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| CN109533278A (en) | 2019-03-29 |
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