CN213502874U - Wing folding structure of unmanned aerial vehicle - Google Patents
Wing folding structure of unmanned aerial vehicle Download PDFInfo
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- CN213502874U CN213502874U CN202022634192.5U CN202022634192U CN213502874U CN 213502874 U CN213502874 U CN 213502874U CN 202022634192 U CN202022634192 U CN 202022634192U CN 213502874 U CN213502874 U CN 213502874U
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Abstract
The application discloses unmanned aerial vehicle's wing beta structure, relate to the technical field of unmanned aerial vehicle wing, it is including setting firmly in the interior wing of fuselage, the one end that the interior wing deviates from the fuselage has outer wing through articulated shaft hinge, outer wing can overturn to the lower surface laminating with interior wing around the lower surface of articulated shaft towards interior wing, the state of the lower surface laminating of outer wing and interior wing is the fold condition of outer wing, the state that outer wing and interior wing are in same horizontal plane is the expansion state of outer wing, be provided with between outer wing and the interior wing and be used for spacing the locating part in fold condition with outer wing. This application has reduced the holistic area of wing and unmanned aerial vehicle, has increased the effect of the unmanned aerial vehicle's that can hold quantity in certain space.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicle wings, in particular to a wing folding structure of an unmanned aerial vehicle.
Background
An unmanned aircraft is an unmanned aircraft that is operated using a radio remote control device and self-contained program control means, or is operated autonomously, either completely or intermittently, by an on-board computer. With the continuous development of unmanned aerial vehicle technology, the application field of the unmanned aerial vehicle is more and more extensive, and in the military field, the unmanned aerial vehicle is widely applied to a plurality of military operations such as battlefield investigation, electronic countermeasure, post-war damage assessment, ground attack and the like, and is indispensable equipment for information-based warfare; in the civil field, the method is widely applied to the fields of aerial remote sensing, aerial surveying and mapping, forest fire prevention, coastline patrol and the like.
Unmanned aerial vehicle includes fuselage, fixed connection usually in the wing of fuselage both sides etc. and when unmanned aerial vehicle was in the quiescent condition of not flying, the wing that is located the fuselage both sides outwards extended and made the holistic area of unmanned aerial vehicle great, and the quantity of the unmanned aerial vehicle that can hold in certain space is less.
SUMMERY OF THE UTILITY MODEL
In order to reduce the holistic area of wing and unmanned aerial vehicle, increase the unmanned aerial vehicle's that can hold quantity in certain space, this application provides an unmanned aerial vehicle's wing beta structure.
The application provides a pair of unmanned aerial vehicle's wing beta structure adopts following technical scheme:
the utility model provides an unmanned aerial vehicle's wing beta structure, includes the interior wing that sets firmly in the fuselage, the one end that the interior wing deviates from the fuselage is articulated through the articulated shaft to have outer wing, outer wing can overturn to the lower surface laminating with interior wing around the lower surface of articulated shaft orientation interior wing, the state of the lower surface laminating of outer wing and interior wing is the fold condition of outer wing, the state that outer wing and interior wing are in same horizontal plane is the expansion state of outer wing, be provided with between outer wing and the interior wing and be used for limiting the locating part in fold condition with outer wing.
Through adopting above-mentioned technical scheme, when unmanned aerial vehicle was in the quiescent condition of placing on the rack, exert the effort to outer wing and make outer wing overturn downwards to with the lower surface laminating of interior wing, the locating part with the wing spacing in fold condition, realized accomodating of outer wing, reduced the holistic area of wing and unmanned aerial vehicle, increased the unmanned aerial vehicle's that can hold in certain space quantity.
Preferably, the limiting part comprises a foam limiting plate, a first limiting groove is formed in the foam limiting plate, and one side of the inner wing and one side of the outer wing are inserted into the first limiting groove.
By adopting the technical scheme, the limiting of the outer wing is realized, and the outer wing is kept in a folded state.
Preferably, the foam limiting plate is positioned on one side of the inner wing and one side of the outer wing close to the tail of the fuselage, an elastic resetting piece is arranged between the outer wing and the inner wing and used for driving the outer wing to turn towards the unfolding state, and a locking assembly used for automatically locking the outer wing and the inner wing in the unfolding state of the outer wing is arranged between the outer wing and the inner wing.
Through adopting above-mentioned technical scheme, when unmanned aerial vehicle launched forward under the effect of controller, interior wing breaks away from with outer wing and foam limiting plate, and outer wing overturns to the expansion state under the effect of elasticity piece that resets to through hasp subassembly and interior wing automatic locking, realized the automation of outer wing and bounce and locking.
Preferably, the limiting member comprises a rigid limiting plate, the rigid limiting plate is fixedly arranged on the ground, a second limiting groove is formed in the rigid limiting plate, and one side of the inner wing and one side of the outer wing are inserted into the second limiting groove;
the rigid limiting plate is positioned on one side, close to the tail of the fuselage, of the inner wing and the outer wing, an elastic resetting piece is arranged between the outer wing and the inner wing and used for driving the outer wing to turn over towards the unfolding state, and a locking assembly used for automatically locking the outer wing and the inner wing in the unfolding state of the outer wing is arranged between the outer wing and the inner wing.
By adopting the technical scheme, when the unmanned aerial vehicle is launched forwards under the action of the controller, the inner wing and the outer wing are separated from the rigid limiting plate, the outer wing is overturned to an unfolded state under the action of the elastic resetting piece, and is automatically locked with the inner wing through the locking component, so that the outer wing is automatically bounced and locked.
Preferably, the two side walls of the second limiting groove are respectively and fixedly provided with a roll shaft, the axis of the roll shaft is arranged along the length direction of the wing, and the peripheral surface of the roll shaft is abutted against the two side walls of the inner wing and the two side walls of the outer wing which are opposite to each other.
Through adopting above-mentioned technical scheme, when having reduced unmanned aerial vehicle departure, the frictional force between rigidity limiting plate and interior wing and the outer wing.
Preferably, the elastic reset member comprises a torsion spring sleeved outside the hinge shaft.
By adopting the technical scheme, the torsion spring applies acting force to the outer wing to realize automatic reset of the outer wing.
Preferably, the locking assembly comprises a locking elastic sheet fixedly arranged on the upper surface of the inner wing, the locking elastic sheet is positioned on one side of the inner wing close to the outer wing and extends out of the outer side of the inner wing, a clamping groove is formed in the part of the locking elastic sheet extending out of the outer side of the inner wing, a clamping block corresponding to the clamping groove is fixedly arranged on the outer wing, and the clamping block can move along with the outer wing to be embedded into the clamping groove.
By adopting the technical scheme, when the outer wing overturns towards the unfolding state under the action of the torsion spring, the clamping block moves together with the outer wing to be embedded into the clamping groove, so that the outer wing is locked.
Preferably, when the outer wing is in the unfolded state, two opposite side walls of the outer wing and the inner wing are attached to each other.
Through adopting above-mentioned technical scheme, the setting of outer wing and the interior wing that can laminate each other has reduced the influence that the gap between outer wing and the interior wing produced the air current when unmanned aerial vehicle normally flies.
In summary, the present application includes at least one of the following beneficial technical effects:
1. when the unmanned aerial vehicle is placed on the placing rack in a static state, acting force is applied to the outer wings to enable the outer wings to be turned downwards to be attached to the lower surfaces of the inner wings, the wings are limited in a folded state by the limiting parts, the outer wings are stored, the overall occupied area of the wings and the unmanned aerial vehicle is reduced, and the number of the unmanned aerial vehicles capable of being contained in a certain space is increased;
2. the limiting piece is arranged to limit the outer wing, so that the outer wing is kept in a folded state;
3. when the unmanned aerial vehicle launches forward under the effect of controller, interior wing breaks away from with outer wing and foam limiting plate, and outer wing overturns to the expansion state under the effect of elasticity piece that resets to through automatic locking of hasp subassembly and interior wing, realized the automation of outer wing and bounce and locking.
Drawings
Fig. 1 is a schematic overall structure diagram in the first embodiment.
Fig. 2 is a schematic overall structure diagram of the outer wing in the expanded state in the first embodiment.
FIG. 3 is a schematic view of the outer wing in a folded state according to one embodiment.
Fig. 4 is a partially enlarged schematic view of a portion a in fig. 1.
Fig. 5 is a schematic diagram illustrating an overall structure of the limiting member structure according to the second embodiment.
Description of reference numerals: 1. an inner wing; 11. accommodating grooves; 2. hinging a shaft; 3. an outer wing; 31. reinforcing a steel plate; 4. a connecting assembly; 41. an inner sleeve; 42. an inner connection plate; 5. a connecting member; 51. an outer sleeve; 52. an outer connecting plate; 6. a torsion spring; 7. a latch assembly; 71. an inner connecting groove; 72. an outer connecting groove; 721. a bevel; 73. locking the elastic sheet; 731. a card slot; 74. a connecting screw; 741. a chute; 8. a foam limiting plate; 81. a first limit groove; 9. a rigid limit plate; 91. erecting a rod; 911. a square plate; 92. a second limit groove; 93. and (4) a roll shaft.
Detailed Description
The present application is described in further detail below with reference to figures 1-5.
The embodiment of the application discloses unmanned aerial vehicle's wing beta structure.
Example one
Referring to fig. 1, the aircraft comprises an inner wing 1 fixedly connected to an aircraft body, wherein one end of the inner wing 1, which faces away from the aircraft body, is hinged to an outer wing 3 through a hinge shaft 2, the hinge shaft 2 is arranged along the length direction of the joint of the outer wing 3 and the inner wing 1, and the hinge shaft 2 is located outside two opposite side walls of the outer wing 3 and the inner wing 1.
Referring to fig. 2 and 3, a state in which the outer wing 3 and the inner wing 1 are on the same horizontal plane is a deployed state of the outer wing 3, and when the outer wing 3 is in the deployed state, the hinge shaft 2 is located below the outer wing 3 and the inner wing 1. The outer wing 3 can be turned downwards around the hinge shaft 2 to be attached to the lower surface of the inner wing 1, and at the moment, the outer wing 3 is in a folded state.
With reference to fig. 1 and 4, the hinge shaft 2 is provided with two groups of connection assemblies 4 for connecting with the inner wing 1, and the connection assemblies 4 are spaced in the axial direction of the hinge shaft 2. The connecting assembly 4 comprises two inner sleeves 41 which are arranged along the axial direction of the hinge shaft 2 at intervals, and the inner sleeves 41 are coaxially sleeved on the outer side of the hinge shaft 2 and are fixedly connected with the hinge shaft 2. An inner connecting plate 42 extends radially outwards along the outer peripheral surface of the inner sleeve 41, a containing groove 11 is formed in the side wall, facing the outer wing 3, of the inner wing 1, the containing groove 11 extends downwards to the lower surface penetrating through the inner wing 1, the inner connecting plate 42 is fixed on the inner wall, facing the outer wing 3, of the containing groove 11 in a pressing mode through screws, and the thickness of the inner connecting plate 42 is smaller than the depth of the containing groove 11.
In order to enhance the connection strength between the outer wing 3 and the inner wing 1, a reinforcing steel plate 31 which is matched with the side wall of the outer wing 3 facing the inner wing 1 in shape is fixed on the side wall in a gluing mode. The articulated shaft 2 is provided with connecting pieces 5 for being connected with the outer wings 3, the connecting pieces 5 correspond to the connecting components 4 one by one, and the connecting pieces 5 are positioned between two inner connecting plates 42 in the connecting components 4 corresponding to the connecting pieces 5. The connecting piece 5 comprises an outer sleeve 51 coaxially sleeved outside the hinge shaft 2 and rotatably connected with the hinge shaft 2, an outer connecting plate 52 extends outwards along the radial direction of the outer sleeve 51 on the peripheral surface, the thickness of the outer connecting plate 52 is the same as that of the inner connecting plate 42, and the outer connecting plate 52 is fixed on the side wall of the connecting steel plate, which is back to the outer wing 3, in a pressing manner by using screws. When the outer wing 3 is in the unfolded state, the outer connecting plate 52 is located in the accommodating groove 11, and two opposite side walls of the outer wing 3 and the inner wing 1 are attached to each other.
The articulated shaft 2 is sleeved with an elastic reset piece for driving the outer wing 3 to overturn from a folded state to an unfolded state, the elastic reset piece comprises a torsion spring 6 coaxially sleeved on the outer side of the articulated shaft 2, and the torsion spring 6 is used for applying an acting force for overturning the outer wing 3 to the unfolded state of the outer wing so as to enable the outer wing 3 to overturn to the unfolded state around the articulated shaft 2.
A locking assembly 7 is arranged between the two opposite sides of the outer wing 3 and the inner wing 1, the locking assembly 7 comprises an inner connecting groove 71 and an outer connecting groove 72, the inner connecting groove 71 is formed in one side, close to the outer wing 3, of the upper surface of the inner wing 1, the outer connecting groove 72 is formed in one side, close to the inner wing 1, of the upper surface of the outer wing 3, the outer connecting groove 72 corresponds to the inner connecting groove 71, the outer connecting groove 72 extends outwards to penetrate through the reinforcing steel plate 31, and when the outer wing 3 is in a spreading state, the outer connecting groove 72 is communicated with the inner connecting groove 71. A locking spring plate 73 is fixedly pressed in the inner connecting groove 71 by using a screw, one side of the locking spring plate 73 extends outwards to the outer side of the inner wing 1, and a clamping groove 731 is formed in one end, extending out of the inner wing 1, of the locking spring plate 73. The engaging groove 731 is a circular groove, and the engaging groove 731 penetrates the upper and lower surfaces of the locking spring 73. A latch corresponding to the latch groove 731 is disposed in the external connection groove 72, and the latch is configured as a connection screw 74 screwed into the external connection groove 72. In order to facilitate the worker to screw the connection screw 74 into the inner connection groove 71, an inclined groove 741 is formed on an end surface of the head of the connection screw 74 facing away from the rod portion of the connection screw 74. The outer wing 3 is turned to the unfolded state in the state of the torsion spring 6, and the head of the connection screw 74 is inserted into the locking groove 731, so that the outer wing 3 is locked in the unfolded state.
When the locking elastic piece 73 is inserted into the outer connecting groove 72, the end of the locking elastic piece 73 opposite to the end of the inner connecting groove 71 is easily worn at the position of the outer connecting groove 72 on the reinforced steel plate 31, and in order to reduce this, the position of the outer connecting groove 72 on the reinforced steel plate 31 is set to be the inclined surface 721.
A limiting part is arranged between the outer wing 3 and the inner wing 1, and the limiting part comprises a foam limiting plate 8 which is positioned on one side of the outer wing 3 and the inner wing 1 close to the tail of the airplane body. The foam limiting plate 8 is provided with a first limiting groove 81 towards one side of the inner wing 1 and one side of the outer wing 3, the inner wing 1 and one side of the outer wing 3 are inserted into the first limiting groove 81, the outer wing 3 is limited in a folded state, and the outer wing 3 is prevented from overturning under the action of the torsion spring 6.
The implementation principle of the wing folding structure of the unmanned aerial vehicle in the embodiment of the application is as follows:
when the unmanned aerial vehicle is placed on the placing rack in a static state, acting force is applied to the outer wing 3 to enable the outer wing 3 to be downwards turned to be attached to the lower surface of the inner wing 1, the foam limiting plate 8 is connected to enable the inner wing 1 and the outer wing 3 to be inserted into the limiting groove, the outer wing 3 is limited in a folded state, the outer wing 3 is prevented from being turned over under the action of the torsion spring 6, the outer wing 3 is stored, the integral occupied area of the wings and the unmanned aerial vehicle is reduced, and the number of the unmanned aerial vehicles capable of being contained in a certain space is increased;
when the unmanned aerial vehicle launches forward under the effect of controller, interior wing 1 breaks away from with outer wing 3 and foam limiting plate 8, and outer wing 3 overturns to the expansion state under the effect of torsional spring 6, and the head of screw is embedded in draw-in groove 731, locks outer wing 3 in the expansion state, has realized the automatic bounce and the locking of outer wing 3.
Example two
Referring to fig. 5, an unmanned aerial vehicle's wing beta structure, with embodiment 1 difference lie in that, the locating part includes rigidity limiting plate 9, and welded fastening has pole setting 91 on the bottom terminal surface of rigidity limiting plate 9, and pole setting 91 bottom welded fastening has square slab 911, and square slab 911 compresses tightly through the bolt and connects on the ground.
The rigid limiting plate 9 is positioned on one side of the inner wing 1 and the outer wing 3 close to the tail of the fuselage, and a second limiting groove 92 is formed in one side of the rigid limiting plate 9 facing the inner wing 1 and the outer wing 3. The upper and lower side walls of the second limiting groove 92 are fixedly connected with a roll shaft 93, the roll shaft 93 located on the upper side wall of the second limiting groove 92 is axially arranged along the extending direction of the inner wing 1, and the roll shaft 93 located on the lower side wall of the second limiting groove 92 is axially arranged along the extending direction of the outer wing 3. One side of the inner wing 1 and one side of the outer wing 3 are inserted into the second limiting groove 92, and the two surfaces of the inner wing 1 and the outer wing 3, which are opposite to each other, are respectively abutted against the outer peripheral surface of the roll shaft 93. The arrangement of the roll shaft 93 reduces the friction force between the rigid limiting plate 9 and the inner wing 1 and the outer wing 3 when the unmanned aerial vehicle flies out.
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 (7)
1. The utility model provides an unmanned aerial vehicle's wing beta structure, includes inner wing (1) that sets firmly in the fuselage, its characterized in that: one end of the inner wing (1) deviating from the fuselage is hinged with an outer wing (3) through a hinged shaft (2), the outer wing (3) can be turned to be attached to the lower surface of the inner wing (1) around the hinged shaft (2) towards the lower surface of the inner wing (1), the state of the outer wing (3) attached to the lower surface of the inner wing (1) is a folded state of the outer wing (3), the state of the outer wing (3) and the inner wing (1) on the same horizontal plane is an unfolded state of the outer wing (3), and a limiting part used for limiting the outer wing (3) to be in the folded state is arranged between the outer wing (3) and the inner wing (1);
the locating part includes foam limiting plate (8), first spacing groove (81) have been seted up on foam limiting plate (8), one side of interior wing (1) and outer wing (3) is inserted in first spacing groove (81).
2. The wing folding structure of unmanned aerial vehicle of claim 1, characterized in that: foam limiting plate (8) are located one side that interior wing (1) and outer wing (3) are close to the fuselage afterbody, be provided with the elasticity piece that resets between outer wing (3) and interior wing (1), the elasticity piece that resets is used for driving outer wing (3) and overturns to the expansion state, be provided with between outer wing (3) and interior wing (1) and be used for the two automatic locking in hasp subassembly (7) of the expansion state of outer wing (3).
3. The wing folding structure of unmanned aerial vehicle of claim 1, characterized in that: the limiting piece comprises a rigid limiting plate (9), the rigid limiting plate (9) is fixedly arranged on the ground, a second limiting groove (92) is formed in the rigid limiting plate (9), and one sides of the inner wing (1) and the outer wing (3) are inserted into the second limiting groove (92);
rigidity limiting plate (9) are located one side that interior wing (1) and outer wing (3) are close to the fuselage afterbody, be provided with the elasticity piece that resets between outer wing (3) and interior wing (1), the elasticity piece that resets is used for driving outer wing (3) and overturns to the expansion state, be provided with between outer wing (3) and interior wing (1) and be used for the two automatic locking in hasp subassembly (7) of the expansion state of outer wing (3).
4. The wing folding structure of unmanned aerial vehicle of claim 3, characterized in that: the two side walls of the second limiting groove (92) are respectively and fixedly provided with a roller shaft (93), the axis of the roller shaft (93) is arranged along the length direction of the wing, and the peripheral surface of the roller shaft (93) is abutted against the two side walls of the inner wing (1) and the outer wing (3) which are opposite to each other.
5. A wing-folding structure of unmanned aerial vehicle according to claim 2 or 3, characterized in that: the elastic reset piece comprises a torsion spring (6) sleeved on the outer side of the hinged shaft (2).
6. A wing-folding structure of unmanned aerial vehicle according to claim 2 or 3, characterized in that: the locking assembly (7) comprises a locking elastic sheet (73) fixedly arranged on the upper surface of the inner wing (1), the locking elastic sheet (73) is positioned on one side, close to the outer wing (3), of the inner wing (1) and extends out of the inner wing (1), a clamping groove (731) is formed in the part, extending out of the outer side of the inner wing (1), of the locking elastic sheet (73), a clamping block corresponding to the clamping groove (731) is fixedly arranged on the outer wing (3), and the clamping block can move along with the outer wing (3) to be embedded into the clamping groove (731).
7. The wing folding structure of unmanned aerial vehicle of claim 1, characterized in that: when the outer wing (3) is in an unfolded state, two opposite side walls of the outer wing (3) and the inner wing (1) are mutually attached.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022634192.5U CN213502874U (en) | 2020-11-13 | 2020-11-13 | Wing folding structure of unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022634192.5U CN213502874U (en) | 2020-11-13 | 2020-11-13 | Wing folding structure of unmanned aerial vehicle |
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| CN213502874U true CN213502874U (en) | 2021-06-22 |
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| CN202022634192.5U Active CN213502874U (en) | 2020-11-13 | 2020-11-13 | Wing folding structure of unmanned aerial vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113665793A (en) * | 2021-08-12 | 2021-11-19 | 广东空天科技研究院 | Thin folding wing and spring driving mechanism thereof |
| CN115158377A (en) * | 2022-08-23 | 2022-10-11 | 中南大学 | High-speed train crosswind resisting method and turnable wing |
| CN117141710A (en) * | 2023-10-30 | 2023-12-01 | 西安现代控制技术研究所 | Hypersonic folding airfoil surface gap air flow partition structure |
-
2020
- 2020-11-13 CN CN202022634192.5U patent/CN213502874U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113665793A (en) * | 2021-08-12 | 2021-11-19 | 广东空天科技研究院 | Thin folding wing and spring driving mechanism thereof |
| CN115158377A (en) * | 2022-08-23 | 2022-10-11 | 中南大学 | High-speed train crosswind resisting method and turnable wing |
| CN115158377B (en) * | 2022-08-23 | 2023-11-28 | 中南大学 | Method for resisting crosswind of high-speed train and reversible wing |
| CN117141710A (en) * | 2023-10-30 | 2023-12-01 | 西安现代控制技术研究所 | Hypersonic folding airfoil surface gap air flow partition structure |
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