CN114537645A - Stable unmanned aerial vehicle telescopic wing structure - Google Patents
Stable unmanned aerial vehicle telescopic wing structure Download PDFInfo
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- CN114537645A CN114537645A CN202111663300.4A CN202111663300A CN114537645A CN 114537645 A CN114537645 A CN 114537645A CN 202111663300 A CN202111663300 A CN 202111663300A CN 114537645 A CN114537645 A CN 114537645A
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- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The application relates to the field of unmanned aerial vehicle wing extension, and particularly discloses a stable unmanned aerial vehicle extension wing structure, which comprises three wing sections which are sequentially sleeved, a first wing section connected with a machine body, a second wing section connected with the first wing section in a sliding manner, and a third wing section connected with the second wing section in a sliding manner, wherein an expansion structure is connected among the first wing section, the second wing section and the third wing section, the expansion structure comprises a pull rope, a driving structure used for pulling the pull rope and connected with the first wing section, and a plurality of pulleys, the two ends of the first wing section are respectively rotatably connected with the pulleys, the two ends of the second wing section are respectively rotatably connected with the pulleys, the pull rope bypasses the pulley at the end part of the first wing section close to the machine body from the driving structure position, and then sequentially bypasses the pulley at the end part of the first wing section far away from the machine body, the pulley at the end part of the second wing section close to the machine body, and the pulley at the end part of the second wing section far away from the machine body, and then connected to wing section three. The wing is more flexible than a large range, and the unmanned aerial vehicle can be launched in a smaller limited space.
Description
Technical Field
The application relates to the flexible field of unmanned aerial vehicle wing, especially a flexible wing structure of firm type unmanned aerial vehicle, this flexible wing system can change the aircraft wing span length, is applicable to a section of thick bamboo and penetrates unmanned aerial vehicle, patrols deformation unmanned aerial vehicle such as missile.
Background
The aerospace technology has been developed rapidly at the present stage, and in order to meet the flight efficiency of an aircraft and the space limitation of a launching device, a new requirement is provided for a deformed unmanned aerial vehicle so as to launch the unmanned aerial vehicle in a limited space, so that the unmanned aerial vehicle can be used in different environmental states and has the capability of multiple tasks. The demand of the unmanned aerial vehicle greatly promotes scholars in related fields at home and abroad to research the deformable aircraft, wherein the wing unfolding device is the key point of research.
Disclosure of Invention
In order to launch unmanned aerial vehicle in the finite space, this application discloses a flexible wing structure of firm type unmanned aerial vehicle.
The technical scheme is as follows:
the utility model provides a flexible wing structure of firm type unmanned aerial vehicle, including the three wing section that cup joints in proper order, be the wing section of being connected with the organism respectively, No. two wing sections with a wing section sliding connection, No. three wing sections with No. two wing section sliding connection, a wing section, be connected with the expanding structure between No. two wing sections and No. three wing sections, expanding structure includes the stay cord, be used for pulling the stay cord and connect in the drive structure of a wing section, and a plurality of pulley, the both ends of a wing section rotate respectively and connect the pulley, the both ends of No. two wing sections rotate respectively and connect the pulley, the stay cord begins to walk around the pulley that a wing section is close to the tip of organism from the drive structure position, then walk around the pulley that a wing section kept away from the tip of organism in proper order, No. two wing sections are close to the pulley of organism tip, No. two wing sections keep away from the pulley of organism tip, then be connected with No. three wing sections.
In the above-described telescopic wing structure, when the stay cord crosses over the end portion of the wing panel, the two pulleys are connected to the end portion of the wing panel across which the stay cord crosses.
In foretell flexible wing structure, No. two wing panel outsides are located to wing panel cover, No. three wing panel outsides are located to wing panel cover No. two, No. one the wing panel is close to the organism and connects first pulley and second pulley respectively with the tip of keeping away from the organism, No. two the wing panel is close to organism end connection third pulley, the end connection fourth pulley and the fifth pulley of organism are kept away from to wing panel No. two, the stay cord is walked around the second pulley from first pulley, then is walked around fourth pulley and fifth pulley from the outside of wing panel No. two, then with No. three the end connection that the wing panel is close to the organism.
In the above telescopic wing structure, No. two wing sections are sleeved outside the first wing section, No. three wing sections are sleeved outside the second wing section, the end part of the first wing section, which is close to the body, is connected with the first pulley, the end part of the first wing section, which is far away from the body, is connected with the second pulley and the third pulley, the end part of the second wing section, which is close to the body, is connected with the fourth pulley, the end part of the second wing section, which is far away from the body, is connected with the fifth pulley and the sixth pulley, the pull rope bypasses the second pulley and the third pulley from the first pulley, and then bypasses the fourth pulley, and bypasses the fifth pulley and the sixth pulley from the inner side of the second wing section, and then is connected with the end part of the third wing section, which is close to the body.
In foretell flexible wing structure, be provided with anti-disengaging structure between two wing sections that cup joint mutually, two wing sections that cup joint mutually are outside wing section and inside wing section respectively, and the holding tank has been seted up to outside wing section, and inside wing section is located the holding tank, and anti-disengaging structure includes first locking surface and second locking surface, and first locking surface is located the holding tank inner wall, and the second locking surface is located inside wing section outer wall, slides between outside wing section and the inside wing section and makes the wing expand when the limit, and first locking surface blocks the second locking surface.
In the above telescopic wing structure, along the moving direction of the inner wing section relative to the outer wing section when the wing is unfolded, the first locking surface gradually extends towards the direction close to the middle part of the inner wing section to form a wedge surface, and the second locking surface is a wedge surface matched with the wedge surface of the closing-in part.
In foretell flexible wing structure, be provided with the load-carrying structure between a wing section, No. two wing sections and No. three wing sections, the load-carrying structure includes a wing section roof beam, No. two wing section roof beams, No. three wing section roof beams that cup joint in proper order each other, and the end connection that the tip of a wing section roof beam and a wing section are close to the fuselage, and the end connection that another wing section was inserted to No. two wing sections is crossed to No. two wing section roof beams, and the end connection that the fuselage was kept away from to No. three wing section roof beams and No. three wing sections.
In the above retractable wing structure, the first wing section is sleeved outside the second wing section, and when the second wing section is sleeved outside the third wing section, the second wing section beam is sleeved outside the first wing section beam, and the third wing section beam is sleeved outside the second wing section beam.
In the above telescopic wing structure, the second wing section is sleeved outside the first wing section, and when the third wing section is sleeved outside the second wing section, the first wing section beam is sleeved outside the second wing section beam, and the second wing section beam is sleeved outside the third wing section beam.
In summary, the present application at least includes the following beneficial technical effects:
(1) the scheme of the telescopic wing provided by the invention adopts motor transmission to realize the contraction and expansion of the wing, and can meet the stability and reliability of the telescopic mechanism of the unmanned aerial vehicle;
(2) the wing is telescopic, so that the size of the wing in a launching state can be reduced, and the use requirements of unmanned aerial vehicles such as a barrel shooting and missile patrol can be met;
(3) the telescopic wing can increase the wing aspect ratio, improve the lift-drag ratio of the whole unmanned aerial vehicle, improve the endurance performance of the unmanned aerial vehicle and improve the multitasking capability of the unmanned aerial vehicle; .
Drawings
FIG. 1 is a schematic view of the deployment of an inner flexible wing according to an embodiment of the present application;
FIG. 2 is a schematic perspective view of the inner telescopic wing;
FIG. 3 is a schematic view of the retracted configuration of the inner flexible wing;
FIG. 4 is a schematic structural view of wing section number one;
FIG. 5 is a schematic view of the outer wing in the deployed configuration;
figure 6 is a cross-sectional view of the wing structure at the anti-separation structure position.
Description of reference numerals:
1. a wing joint; 2. a first wing panel; 21. a first pulley; 22. a motor; 23. a second pulley; 24. a first wing panel beam; 25. pulling a rope; 3. a wing panel II; 31. a third pulley; 32. a fourth pulley; 33. a fifth pulley; 34. a second wing panel beam; 35. a first locking surface; 4. a third wing panel; 41. a sixth pulley; 42. a second locking surface; 43. third wing panel roof beam.
Detailed Description
The present application is described in further detail below with reference to the following figures and specific examples:
example 1
Referring to fig. 1-4, a stable unmanned aerial vehicle telescopic wing structure comprises three wing sections which are sequentially sleeved, namely a first wing section 2 connected with a machine body, a second wing section 3 connected with the first wing section 2 in a sliding manner, a third wing section 4 connected with the second wing section 3 in a sliding manner, an expansion structure is connected among the first wing section 2, the second wing section 3 and the third wing section 4, an anti-drop structure is arranged between the two sleeved wing sections, and a force bearing structure is arranged among the first wing section 2, the second wing section 3 and the third wing section 4,
referring to fig. 1 and 3, the unfolding structure includes stay cord 25, be used for pulling stay cord 25 and connect in the drive structure of wing section 2 No. one, and a plurality of pulley, the both ends of wing section 2 rotate respectively and connect the pulley, the both ends of wing section 3 rotate respectively and connect the pulley, stay cord 25 starts to walk around the pulley that wing section 2 is close to the tip of organism from the drive structure position, then walk around the pulley that wing section 2 keeps away from the tip of organism in proper order, No. two the pulley that wing section 3 is close to the organism tip, No. two the pulley that wing section 3 keeps away from the organism tip, then be connected with No. three wing sections 4. When the pull rope 25 crosses the end of the panel, the two pulleys are connected to the end of the panel across which the pull rope 25 crosses. The driving structure comprises an accommodating wheel rotationally connected with the first wing section 2 and a motor 22 driving the accommodating wheel to rotate. The storage wheel rotates to drive the pull rope 25 to be wound around the circumferential direction of the storage wheel gradually, so that the pull rope 25 is pulled.
In this embodiment, form interior flexible wing between the three wing panel, No. 2 wing panels locate the 3 outsides of No. two wing panels, No. 3 wing panels locate the 4 outsides of No. three wing panels, No. 2 wing panels are close to the organism and the tip of keeping away from the organism is connected first pulley 21 and second pulley 23 respectively, No. two wing panels 3 are close to organism end connection third pulley 31, No. two end connection fourth pulley 32 and the fifth pulley 33 of keeping away from the organism of wing panels 3, No. three end connection sixth pulley 41 that the wing panels 4 are close to the organism, stay cord 25 is from first pulley 21 around second pulley 23, then from the outside of No. two wing panels 3 around fourth pulley 32 and fifth pulley 33, then be connected with the sixth pulley 41 that No. three wing panels 4 are connected. The motor 22 is driven, the pull rope 25 is pulled, and the second wing section 3 and the third wing section 4 are unfolded under the action of a plurality of pulleys.
Referring to fig. 6 and 2, two wing sections that cup joint are outside wing section and inside wing section respectively, the holding tank has been seted up to outside wing section, inside wing section is located the holding tank, anti-disengaging structure includes first locking surface 35 and second locking surface 42, first locking surface 35 is located the holding tank inner wall, second locking surface 42 is located inside wing section outer wall, slide between outside wing section and the inside wing section and make the wing expand when the limit, first locking surface 35 blocks second locking surface 42. Along the moving direction of the inner wing panel relative to the outer wing panel when the wing is unfolded, the first locking surface 35 gradually extends towards the direction close to the middle of the inner wing panel to form a wedge surface, and the second locking surface 42 is a wedge surface matched with the wedge surface of the closing-in part.
Referring to fig. 1, the force bearing structure comprises a first wing section beam 24, a second wing section beam 34 and a third wing section beam 43 which are sequentially sleeved with one another, the end portion of the first wing section beam 24 is connected with the end portion, close to the fuselage, of the first wing section 2, the second wing section beam 34 is connected with the end portion, inserted into the other wing section, of the second wing section 3, and the third wing section beam 43 is connected with the end portion, far away from the fuselage, of the third wing section 4. The cross section of the first, second and third wing beams 24, 34, 43 may be any shape, such as rectangular, circular, oval, etc., and in this embodiment, the cross section of the first, second and third wing beams 24, 34, 43 is rectangular.
In this embodiment, the second wing beam 34 is sleeved outside the first wing beam 24, and the third wing beam 43 is sleeved outside the second wing beam 34. At this time, the first wing section 2, the second wing section 3 and the third wing section 4 are main bearing structures relative to the first wing section beam 24, the second wing section beam 34 and the third wing section beam 43.
Example 2
The difference from example 1 is noted in that:
referring to fig. 5, in this embodiment, an outer telescopic wing is formed between three wing sections, a second wing section 3 is sleeved outside a first wing section 2, a third wing section 4 is sleeved outside the second wing section 3, the end of the first wing section 2 close to the airframe is connected with a first pulley 21, the end of the first wing section 2 far away from the airframe is connected with a second pulley 23 and a third pulley 31, the end of the second wing section 3 close to the airframe is connected with a fourth pulley 32, the end of the second wing section 3 far away from the airframe is connected with a fifth pulley 33 and a sixth pulley 41, a pull rope 25 is wound around the second pulley 23 and the third pulley 31 from the first pulley 21, then around the fourth pulley 32, and is wound around the fifth pulley 33 and the sixth pulley 41 from the inner side of the second wing section 3, and then is connected with the end of the third wing section 4 close to the airframe.
The first wing section beam 24 is sleeved outside the second wing section beam 34, and the second wing section beam 34 is sleeved outside the third wing section beam 43. At this time, the first wing beam 24, the second wing beam 34 and the third wing beam 43 are main bearing structures relative to the first wing 2, the second wing 3 and the third wing 4.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (9)
1. The utility model provides a flexible wing structure of firm type unmanned aerial vehicle which characterized in that: the wing comprises three wing sections which are sequentially sleeved, wherein the first wing section (2) is connected with a machine body, the second wing section (3) is connected with the first wing section (2) in a sliding manner, the third wing section (4) is connected with the second wing section (3) in a sliding manner, an unfolding structure is connected between the first wing section (2), the second wing section (3) and the third wing section (4), the unfolding structure comprises a pull rope (25), a driving structure and a plurality of pulleys, the driving structure is used for pulling the pull rope (25) and is connected to the first wing section (2), the connecting pulleys are respectively rotated at two ends of the second wing section (3), the pull rope (25) bypasses the pulley at the end part, close to the machine body, of the first wing section (2) from the driving structure position, then the pulley at the end part, far away from the machine body, the pulley at the end part, close to the machine body, the pulley at the second wing section (3), the pulley at the end part, the end part of the machine body of the second wing section, The second wing panel (3) is far away from the pulley at the end part of the machine body and then is connected with the third wing panel (4).
2. The telescopic wing structure of a stable unmanned aerial vehicle of claim 1, wherein: when the pull rope (25) stretches across the end part of the wing panel, the end part of the wing panel across which the pull rope (25) stretches is connected with two pulleys.
3. A robust unmanned aerial vehicle telescopic wing structure according to any one of claims 1-2, wherein: no. two wing panel (3) outsides are located to a wing panel (2) cover, No. three wing panel (4) outsides are located to No. two wing panel (3) covers, No. two wing panel (2) are close to the organism and the tip of keeping away from the organism is connected first pulley (21) and second pulley (23) respectively, No. two wing panel (3) are close to organism end connection third pulley (31), No. two wing panel (3) keep away from the end connection fourth pulley (32) and fifth pulley (33) of organism, stay cord (25) are from first pulley (21) around second pulley (23), then from the outside of No. two wing panel (3) around fourth pulley (32) and fifth pulley (33), then with No. three wing panel (4) be close to the end connection of organism.
4. A robust unmanned aerial vehicle telescopic wing structure according to any one of claims 1-2, wherein: no. two wing panel (3) cover is located No. one wing panel (2) outside, No. three wing panel (4) cover is located No. two wing panel (3) outsides, end connection first pulley (21) that a wing panel (2) is close to the organism, end connection second pulley (23) and third pulley (31) that organism was kept away from to a wing panel (2), No. two wing panel (3) are close to the end connection fourth pulley (32) of organism, end connection fifth pulley (33) and sixth pulley (41) that organism was kept away from to No. two wing panel (3), stay cord (25) are walked around second pulley (23) and third pulley (31) from first pulley (21), then are walked around fourth pulley (32), and are walked around fifth pulley (33) and sixth pulley (41) from the inboard of No. two wing panel (3), then with the end connection that No. three wing panel (4) are close to the organism.
5. The telescopic wing structure of a stable unmanned aerial vehicle of claim 1, wherein: be provided with anti-disengaging structure between two wing sections that cup joint mutually, two wing sections that cup joint mutually are outside wing section and inside wing section respectively, the holding tank has been seted up to outside wing section, inside wing section is located the holding tank, anti-disengaging structure includes first locking surface (35) and second locking surface (42), first locking surface (35) are located the holding tank inner wall, second locking surface (42) are located inside wing section outer wall, slide between outside wing section and the inside wing section and make the wing expand when the limit, first locking surface (35) block second locking surface (42).
6. A robust unmanned aerial vehicle telescopic wing structure according to claim 5, characterized in that: along the moving direction of the inner wing panel relative to the outer wing panel when the wing is unfolded, the first locking surface (35) gradually extends towards the direction close to the middle part of the inner wing panel to form a wedge surface, and the second locking surface (42) is a wedge surface matched with the wedge surface of the closing-in part.
7. The telescopic wing structure of a stable unmanned aerial vehicle of claim 1, wherein: be provided with the load-bearing structure between a wing panel (2), No. two wing panels (3) and No. three wing panels (4), the load-bearing structure is including a wing panel roof beam (24), No. two wing panel roof beams (34), No. three wing panel (43) roof beams that cup joint in proper order each other, the end connection that the tip and a wing panel (2) of a wing panel roof beam (24) are close to the fuselage, the end connection that No. two wing panel roof beams (34) and No. two wing panels (3) inserted another wing panel, the end connection that the fuselage was kept away from with No. three wing panel (4) to No. three wing panel (43) roof beams.
8. The telescopic wing structure of a robust unmanned aerial vehicle according to claim 7, wherein: no. two wing panel (3) outsides are located to a wing panel (2) cover, and when No. three wing panel (4) outsides are located to No. two wing panel (3) covers, No. one wing panel roof beam (24) outside is located to No. two wing panel roof beams (34) covers, and No. two wing panel roof beams (34) outside is located to No. three wing panel (43) roof beam covers.
9. The telescopic wing structure of a robust unmanned aerial vehicle according to claim 7, wherein: no. two wing sections (3) are located No. one wing section (2) outside in the cover, and when No. two wing sections (3) outside is located in No. three wing section (4) cover, No. two wing section roof beams (34) outside is located in the cover of No. one wing section roof beam (24), No. three wing section (43) roof beams outside is located in the cover of No. two wing section roof beams (34).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111663300.4A CN114537645A (en) | 2021-12-31 | 2021-12-31 | Stable unmanned aerial vehicle telescopic wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111663300.4A CN114537645A (en) | 2021-12-31 | 2021-12-31 | Stable unmanned aerial vehicle telescopic wing structure |
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| CN114537645A true CN114537645A (en) | 2022-05-27 |
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| CN202111663300.4A Pending CN114537645A (en) | 2021-12-31 | 2021-12-31 | Stable unmanned aerial vehicle telescopic wing structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374156A (en) * | 2023-06-05 | 2023-07-04 | 西安羚控电子科技有限公司 | Wing telescoping mechanism, wing and wing telescoping method |
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| CN111114752A (en) * | 2020-01-07 | 2020-05-08 | 北京航空航天大学 | Deformable wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090206193A1 (en) * | 2006-06-09 | 2009-08-20 | File David J | Ballistically deployed telescoping aircraft wing |
| CN107905944A (en) * | 2012-10-17 | 2018-04-13 | 李洪泽 | Adjust the telescopic wing of the Universal Windmill of paddle length |
| US9139284B1 (en) * | 2013-10-16 | 2015-09-22 | Sanjay Dhall | Telescopic wing with rotating structural spar |
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| CN116374156A (en) * | 2023-06-05 | 2023-07-04 | 西安羚控电子科技有限公司 | Wing telescoping mechanism, wing and wing telescoping method |
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