CN210822727U

CN210822727U - Unmanned aerial vehicle with detachable wings

Info

Publication number: CN210822727U
Application number: CN201921813285.5U
Authority: CN
Inventors: 张善文; 唐磊; 张曾; 许晓显
Original assignee: Suzhou Huarui Surveying And Mapping Co ltd
Current assignee: Suzhou Huarui Surveying And Mapping Co ltd
Priority date: 2019-10-25
Filing date: 2019-10-25
Publication date: 2020-06-23
Anticipated expiration: 2029-10-25

Abstract

The utility model discloses an unmanned aerial vehicle can be dismantled to wing relates to unmanned air vehicle technical field, aims at solving the problem that influences unmanned aerial vehicle's life easily among the prior art. The technical scheme is characterized in that a sliding groove into which the end part of a wing extends is arranged in the middle of a machine body, the sliding groove is arranged along the length direction of the machine body and extends to one end, close to a propeller, in the middle of the machine body, guide grooves are arranged on the upper side wall and the lower side wall of the sliding groove, and guide blocks which can extend into the guide grooves are arranged on the wing; the connecting rod is provided with a limiting groove for the hemispherical end part of the limiting rod to extend into, and an elastic part for applying acting force towards the limiting groove to the limiting rod is arranged in the limiting hole. In the connecting rod stretched into the connecting hole, the gag lever post stretched into the spacing inslot under the elastic force of elastic component, and the tip of wing was located the spout, had increased the area of contact of fuselage and wing, can improve the stability of wing to can effectively improve unmanned aerial vehicle's life.

Description

Unmanned aerial vehicle with detachable wings

Technical Field

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to an unmanned aerial vehicle can be dismantled to wing is related to.

Background

Topographic mapping refers to the operation of mapping a topographic map, i.e., the projection positions and elevations of features on the earth surface and terrains on a horizontal plane are measured, the measured features are reduced according to a certain proportion, symbols and marks are used for drawing a topographic map, the topographic map is basically mapped by adopting an aerial photogrammetry method, and aerial images are used for mapping mainly indoors. With the continuous development of science and technology, advanced digital aerial photogrammetry technology is widely applied in the geographic information surveying and mapping industry, and the terrain surveying and mapping industry in China also has great progress in the field of unmanned aerial vehicles.

An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. The unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology. But there are some problems with existing geo-mapped drones.

The main wing of unmanned aerial vehicle is formed by a plurality of part combinations, and the main wing of UAV reaches outside wing including the horn and the horn outside edge mount pad that are connected to unmanned aerial vehicle. The outer edges of the horn are square and circular grooves made of metal. The main wing is assembled by inserting the inboard edge of each outboard wing with a square insert and a round lead-in made of metal into the slots, respectively. A snap lock is provided on a surface of the insert to lock the insert into the hole in the underside of the horn.

However, the snap lock is arranged on the surface of the insert, is difficult to fasten during the actual insertion of the slot, and the insert and the insertion slot are the only joint point between the horn and the outer wing, so that the wing is not firmly installed, and the trailing edge outer wing which is jointed with the horn when the unmanned aerial vehicle flies tends to twist outwards, thereby affecting the service life of the unmanned aerial vehicle.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an unmanned aerial vehicle can be dismantled to wing, its effect that can effectively improve unmanned aerial vehicle life.

The above utility model discloses an above-mentioned utility model purpose can realize through following technical scheme: the unmanned aerial vehicle with the detachable wings comprises a body and wings arranged on two sides of the middle of the body, wherein a propeller is arranged at the tail end of the body, a sliding groove for the end part, close to the body, of the wings to extend into is arranged in the middle of the body, the sliding groove is arranged along the length direction of the body and extends to one end, close to the propeller, in the middle of the body, guide grooves are formed in the upper side wall and the lower side wall of the sliding groove, and guide blocks capable of extending into the guide grooves are arranged on the wings; the utility model discloses a spacing structure of aircraft wing, including spout, connecting hole, spacing hole, gag lever post, limiting rod, connecting rod, limiting groove, the diapire of spout is provided with the connecting hole, be provided with the connecting rod that can stretch into the connecting hole on the wing, be provided with spacing hole in the connecting hole, spacing downthehole gag lever post that is provided with, the one end that the gag lever post stretches out the gag lever post is hemispherical tip, be provided with on the connecting rod and supply the gag lever post to be the spacing groove that hemispherical tip stretches into, spacing downt.

Through adopting above-mentioned technical scheme, can place the wing in the spout through guide block and guide way, when the lateral wall that the screw was kept away from to guide block and guide way offseted, the connecting hole is corresponding with the connecting rod. At the moment, the force towards the direction of the fuselage is applied to the wing, the wing is abutted to the bottom wall of the sliding groove, the connecting rod stretches into the connecting hole, and the limiting rod stretches into the limiting groove under the elastic action force of the elastic part, so that the wing can be firmly fixed. The guide block of wing is located the guide way, can avoid the wing to break away from the fuselage from the both sides at fuselage middle part, and the tip of wing is located the spout, has increased the area of contact of fuselage and wing, under the prerequisite that increases wing stability, can effectively improve unmanned aerial vehicle's life.

The utility model discloses further set up to: the aircraft wing is characterized in that a clamping block is arranged at the end part, close to the aircraft body, of the aircraft wing, a clamping groove, extending into the clamping block, is formed in the bottom wall of the sliding groove, the clamping block is arranged in a convex shape, and the clamping groove is in a convex shape matched with the clamping block.

Through adopting above-mentioned technical scheme, the fixture block stretches into in the draw-in groove, can further improve the steadiness that increases the wing.

The utility model discloses further set up to: the aircraft wing is provided with the locating lever near the tip of fuselage, be provided with first elastic pin in the locating lever, the lateral wall of locating lever is worn out and is hemispherical tip to the one end of first elastic pin, be provided with the constant head tank that supplies the locating lever to stretch into on the diapire of spout, be provided with the spread groove that supplies first elastic pin to stretch into in the constant head tank.

Through adopting above-mentioned technical scheme, the locating lever stretches into in the constant head tank, and in first elastic pin stretched into the spread groove to can further the wing firmly fix, thereby further increase the steadiness of wing.

The utility model discloses further set up to: the lower terminal surface of wing and the one end of keeping away from the fuselage are provided with the fin, be provided with the buckle hole on the fin, the tip of wing is provided with the bayonet lock of inlaying the cooperation with the buckle hole card.

Through adopting above-mentioned technical scheme, the bayonet lock of wing and buckle hole inlay card cooperation, can be convenient for the installation and the dismantlement of fin.

The utility model discloses further set up to: the clamping hole comprises a long round hole and a positioning hole, the positioning hole is communicated with the long round hole, and the diameter of the positioning hole is larger than that of the long round hole; the bayonet lock comprises a pin rod and a fixing plate arranged at the end part of the pin rod, and the diameter of the fixing plate is smaller than that of the positioning hole and larger than that of the long round hole.

By adopting the technical scheme, the pin rod and the fixing plate are firstly stretched into the corresponding positioning holes, the fixing plate penetrates out of the positioning holes, and then the pin rod and the fixing plate are moved towards the long round holes. At the moment, the pin rod is positioned in the oblong hole, and the fixing plate is abutted against the end face of the tail wing. Thereby firmly fixing the empennage.

The utility model discloses further set up to: the tail wing is provided with a fixed slot on the end surface close to the wing, the fixed slot is in an arc shape, and the end part of the wing is provided with a second elastic pin stretching into the fixed slot.

By adopting the technical scheme, when the pin rod is positioned in the long round hole and the fixed plate is abutted against the end face of the tail wing, the second elastic pin extends into the fixed groove, so that the tail wing can be further fixed.

The utility model discloses further set up to: the wing comprises a fixed wing plate and a control wing plate, the fixed wing plate is connected with the body, the control wing plate is hinged to the fixed wing plate, and a driving piece for rotating the control wing plate is arranged in the fixed wing plate.

Through adopting above-mentioned technical scheme, through the rotation of control pterygoid lamina, the direction of control unmanned aerial vehicle flight can be convenient for, the rotation of control pterygoid lamina can be convenient for.

The utility model discloses further set up to: the output end of the driving piece is connected with a driving plate, the driving plate is located on the lower end face of the fixed wing plate, a driving rod is movably connected to the bottom face of the driving plate along the radial direction of the driving plate, and one end, far away from the driving plate, of the driving rod is movably connected with the control wing plate.

Through adopting above-mentioned technical scheme, driving piece drive plate rotates, and actuating lever and drive plate swing joint to can beat the radial movement of actuating lever along the drive plate, actuating lever and control pterygoid lamina swing joint, and control pterygoid lamina and fixed pterygoid lamina are articulated mutually, thereby can be convenient for control pterygoid lamina's rotation, thereby can be convenient for further be convenient for control pterygoid lamina's rotation.

To sum up, the utility model discloses a beneficial technological effect does:

1. the service life of the unmanned aerial vehicle can be effectively prolonged through the arrangement of the guide groove, the guide block, the limiting groove and the limiting rod;

2. the stability of the wing can be further improved through the arrangement of the clamping block, the clamping groove, the first elastic pin and the connecting groove;

3. through the arrangement of the long round holes, the positioning holes and the clamping pins, the mounting and the dismounting of the tail wing can be facilitated.

Drawings

Fig. 1 is a schematic view of an overall structure of a detachable wing unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of another detachable wing drone according to an embodiment of the present invention;

FIG. 3 is an enlarged view of portion A of FIG. 2;

FIG. 4 is an enlarged view of portion B of FIG. 2;

fig. 5 is a schematic structural diagram for showing a connection relationship between the fixing wing plate and the control wing plate according to an embodiment of the present invention;

fig. 6 is an enlarged view of a portion C in fig. 5.

In the figure, 1, a fuselage; 11. an airfoil; 12. a propeller; 13. a fixed wing plate; 14. a control flap; 2. a chute; 22. a guide block; 23. connecting holes; 231. a connecting rod; 24. a limiting hole; 25. a limiting rod; 26. a limiting groove; 27. a spring; 28. a groove; 29. a bump; 3. a clamping block; 31. a card slot; 32. positioning a rod; 33. a first elastic pin; 34. positioning a groove; 35. connecting grooves; 4. a tail wing; 41. a snap-in hole; 42. a long round hole; 43. positioning holes; 44. a bayonet lock; 45. a pin rod; 46. a fixing plate; 47. fixing grooves; 48. a second elastic pin; 5. a motor; 51. a drive bevel gear; 52. a driven bevel gear; 53. a driven lever; 54. a drive plate; 55. a drive rod.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

Referring to fig. 1 and 3, for the utility model discloses a unmanned aerial vehicle can be dismantled to wing, including fuselage 1 and install in the wing 11 of fuselage 1 middle part both sides, the tail end of fuselage 1 is provided with screw 12. The wing 11 comprises a fixed wing plate 13 and a control wing plate 14, the control wing plate 14 is positioned at one end of the fixed wing plate 13 close to the propeller 12, and the control wing plate 14 is hinged with the fixed wing plate 13. The middle part of fuselage 1 is provided with the spout 2 that supplies fuselage 1 to stretch into near the tip of fuselage 1, and spout 2 sets up and follows the one end that extends to fuselage 1 middle part and be close to screw 12 along the length direction of fuselage 1, all is provided with guide way (not shown in the figure) on two upper and lower lateral walls of spout 2, and the guide way sets up along the length direction of spout 2, is provided with the guide block 22 that can stretch into the guide way on the fixed pterygoid lamina 13.

Referring to fig. 2 and 3, a connecting hole 23 is formed in the bottom wall of the sliding chute 2, a connecting rod 231 that can be inserted into the connecting hole 23 is disposed on the fixing wing plate 13, the connecting rod 231 is disposed in a polygonal shape, and the connecting hole 23 is in a polygonal shape that is matched with the connecting rod 231. Be provided with spacing hole 24 on the lateral wall of connecting hole 23, be provided with gag lever post 25 in the spacing hole 24, the one end that gag lever post 25 stretched out spacing hole 24 is hemispherical tip, and is provided with the spacing groove 26 that supplies gag lever post 25 to be hemispherical tip and stretch into on the connecting rod, is provided with the elastic component in the spacing hole 24, and in this embodiment, the elastic component is spring 27, and the one end of spring 27 is connected with the diapire in spacing hole 24, and the other end of spring 27 is connected with gag lever post 25. And the inside wall of the limiting hole 24 is provided with a groove 28, and the outside wall of the limiting rod 25 is provided with a projection 29 extending into the groove 28 for preventing the limiting rod 25 from separating from the limiting hole 24.

Referring to fig. 2 and 3, the end portion, close to the body 1, of the fixing wing plate 13 is provided with a clamping block 3, a clamping groove 31 for the clamping block 3 to extend into is formed in the bottom wall of the sliding groove 2, the clamping block 3 is in a convex shape, the clamping groove 31 is in a convex shape matched with the clamping block 3, the clamping block 3 is made of plastic materials, and the clamping block 3 has certain elasticity and can be firmly fixed with the clamping groove 31 by extending the clamping block 3 into the clamping groove 31. The end portion of the fixing wing plate 13 close to the body 1 is provided with a positioning rod 32, a first elastic pin 33 is arranged in the positioning rod 32, one end of the first elastic pin 33 penetrates out of the outer side wall of the positioning rod 32 and is hemispherical, a positioning groove 34 for the positioning rod 32 to extend into is arranged on the bottom wall of the sliding groove 2, in the embodiment, the positioning rod 32 is arranged in a polygonal mode, and the positioning groove 34 is a polygon matched with the positioning rod 32. And the inner wall of the positioning groove 34 is provided with a connecting groove 35 for the first elastic pin 33 to extend into, and the connecting groove 35 is arc-shaped.

Referring to fig. 2 and 4, a tail fin 4 is disposed at a lower end of the fixed wing plate 13 and at an end far from the fuselage 1, and a fastening hole 41 is disposed on an end surface of the tail fin 4 close to the fixed wing plate 13, in this embodiment, the fastening hole 41 includes an oblong hole 42 and a positioning hole 43 which are communicated with each other, and a diameter of the positioning hole 43 is larger than a diameter of the oblong hole 42. The end of the fixing wing plate 13 is provided with a bayonet 44 extending into the fastening hole 41, the bayonet 44 comprises a pin rod 45 and a fixing plate 46, one end of the pin rod 45 is connected with the fixing wing plate 13, one end of the pin rod 45 far away from the fixing wing plate 13 is connected with the fixing plate 46, and the diameter of the fixing plate 46 is smaller than that of the positioning hole 43 and larger than that of the oblong hole 42. And the end surface of the tail wing 4 close to the fixed wing plate 13 is provided with a fixing groove 47, the fixing groove 47 is arranged in an arc shape, and the end part of the fixed wing plate 13 is provided with a second elastic pin 48 extending into the fixing groove 47. The pin rod 45 and the fixing plate 46 are firstly extended into the corresponding positioning holes 43, the fixing plate 46 is made to penetrate out of the positioning holes 43, and then the pin rod 45 and the fixing plate 46 are moved towards the oblong hole 42. At this time, the pin rod 45 is positioned in the oblong hole 42, and the fixing plate 46 abuts against the end surface of the tail fin 4. Thereby firmly fixing the rear wing 4. When the pin rod 45 is positioned in the oblong hole 42 and the fixing plate 46 abuts against the end surface of the rear wing 4, the second elastic pin 48 extends into the fixing groove 47, thereby further fixing the rear wing 4.

Referring to fig. 5 and 6, a driving member for controlling the rotation of the wing plate 14 is disposed in the fixed wing plate 13, in this embodiment, the driving member is a motor 5, an output end of the motor 5 is connected with a driving bevel gear 51, the driving bevel gear 51 is engaged with a driven bevel gear 52, the driven bevel gear 52 is connected with a driven rod 53, one end of the driven rod 53 penetrates through the fixed wing plate 13 and is connected with a driving plate 54, the driving plate 54 is located on a lower end surface of the fixed wing plate 13, a driving rod 55 is movably connected to one side of a bottom surface of the driving plate 54, which is far away from a center of a circle, along a radial direction of the side. The starter motor 5, motor 5 can drive initiative bevel gear 51 and driven bevel gear 52 and rotate to can change the transmission direction, driven bevel gear 52 can drive driven lever 53 and rotate, make drive plate 54 rotate, thereby can drive actuating lever 55 along drive plate 54's radial movement, and actuating lever 55 and control pterygoid lamina 14 swing joint, thereby can drive control pterygoid lamina 14 and rotate, thereby can control unmanned aerial vehicle's flight direction.

The implementation principle of the embodiment is as follows:

the wing 11 can be placed in the chute 2 through the guide block 22 and the guide groove on the fixed wing plate 13, and the connecting hole 23 corresponds to the connecting rod when the guide block 22 abuts against the side wall of the guide groove 2 far away from the propeller 12. At this time, a force toward the fuselage 1 is applied to the wing 11, the wing 11 abuts against the bottom wall of the sliding groove 2, the connecting rod extends into the connecting hole 23, and the limiting rod 25 extends into the limiting groove 26 under the elastic action force of the elastic part, so that the wing 11 can be firmly fixed. The guide block 22 of wing 11 is located the guide way, can avoid wing 11 to break away from fuselage 1 from the both sides at fuselage 1 middle part, and the tip of wing 11 is located spout 2, has increased the area of contact of fuselage 1 with wing 11, under the prerequisite that increases wing 11 stability, can effectively improve unmanned aerial vehicle's life.

The embodiment of this specific implementation mode is the preferred embodiment of the present invention, not limit according to this the utility model discloses a protection scope, so: all equivalent changes made according to the structure, shape and principle of the utility model are covered within the protection scope of the utility model.

Claims

1. The utility model provides an unmanned aerial vehicle can be dismantled to wing, includes fuselage (1) and installs in wing (11) of fuselage (1) middle part both sides, the tail end of fuselage (1) is provided with screw (12), its characterized in that: the aircraft is characterized in that a sliding chute (2) into which the end part of the wing (11) close to the aircraft body (1) extends is arranged in the middle of the aircraft body (1), the sliding chute (2) is arranged along the length direction of the aircraft body (1) and extends to one end of the middle of the aircraft body (1) close to the propeller (12), guide grooves are arranged on the upper side wall and the lower side wall of the sliding chute (2), and guide blocks (22) which can extend into the guide grooves are arranged on the wing (11); be provided with connecting hole (23) on the diapire of spout (2), be provided with connecting rod (231) that can stretch into connecting hole (23) on wing (11), be provided with spacing hole (24) in connecting hole (23), be provided with gag lever post (25) in spacing hole (24), the one end that gag lever post (25) stretched out gag lever post (25) is hemispherical, be provided with spacing groove (26) that supply gag lever post (25) to be hemispherical tip and stretch into on connecting rod (231), be provided with in spacing hole (24) and be used for applying the elastic component of the effort towards spacing groove (26) to gag lever post (25).

2. The detachable-wing unmanned aerial vehicle of claim 1, wherein: be provided with fixture block (3) on the tip that wing (11) are close to fuselage (1), be provided with draw-in groove (31) that stretch into with fixture block (3) on the diapire of spout (2), fixture block (3) are the convex setting, draw-in groove (31) are the convex with fixture block (3) looks adaptation.

3. The detachable-wing unmanned aerial vehicle of claim 1, wherein: the aircraft wing locating device is characterized in that a locating rod (32) is arranged at the end part, close to the aircraft body (1), of the wing (11), a first elastic pin (33) is arranged in the locating rod (32), one end of the first elastic pin (33) penetrates out of the outer side wall of the locating rod (32) and is hemispherical, a locating groove (34) for the locating rod (32) to stretch into is arranged on the bottom wall of the sliding groove (2), and a connecting groove (35) for the first elastic pin (33) to stretch into is arranged in the locating groove (34).

4. The detachable-wing unmanned aerial vehicle of claim 1, wherein: the lower terminal surface of wing (11) and the one end of keeping away from fuselage (1) are provided with fin (4), be provided with buckle hole (41) on fin (4), the tip of wing (11) is provided with bayonet lock (44) with buckle hole (41) inlay card complex.

5. The detachable-wing unmanned aerial vehicle of claim 4, wherein: the clamping hole (41) comprises a long round hole (42) and a positioning hole (43), the positioning hole (43) is communicated with the long round hole (42), and the diameter of the positioning hole (43) is larger than that of the long round hole (42); the bayonet lock (44) comprises a pin rod (45) and a fixing plate (46) arranged at the end part of the pin rod (45), and the diameter of the fixing plate (46) is smaller than that of the positioning hole (43) and larger than that of the long round hole (42).

6. The detachable-wing unmanned aerial vehicle of claim 4, wherein: the tail wing is characterized in that a fixing groove (47) is formed in the end face, close to the wing (11), of the tail wing (4), the fixing groove (47) is arranged in an arc shape, and a second elastic pin (48) stretching into the fixing groove (47) is arranged at the end portion of the wing (11).

7. The detachable-wing unmanned aerial vehicle of claim 1, wherein: wing (11) are including fixed pterygoid lamina (13) and control pterygoid lamina (14), fixed pterygoid lamina (13) are connected with fuselage (1), control pterygoid lamina (14) are articulated mutually with fixed pterygoid lamina (13), be provided with in the fixed pterygoid lamina (13) and supply control pterygoid lamina (14) pivoted driving piece.

8. The detachable-wing drone of claim 7, wherein: the output end of the driving piece is connected with a driving plate (54), the driving plate (54) is located on the lower end face of the fixed wing plate (13), a driving rod (55) is movably connected to the bottom face of the driving plate (54) along the radial direction of the driving rod, and one end, far away from the driving plate (54), of the driving rod (55) is movably connected with the control wing plate (14).