CN209889099U - Unmanned aerial vehicle with reduce windage fuselage - Google Patents
Unmanned aerial vehicle with reduce windage fuselage Download PDFInfo
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- CN209889099U CN209889099U CN201920643758.5U CN201920643758U CN209889099U CN 209889099 U CN209889099 U CN 209889099U CN 201920643758 U CN201920643758 U CN 201920643758U CN 209889099 U CN209889099 U CN 209889099U
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- Prior art keywords
- aerial vehicle
- unmanned aerial
- support frame
- fuselage
- bolt
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- 238000013016 damping Methods 0.000 claims abstract description 20
- 230000035939 shock Effects 0.000 claims abstract description 8
- 239000012634 fragment Substances 0.000 claims abstract description 6
- 238000009434 installation Methods 0.000 claims description 2
- 239000000872 buffer Substances 0.000 abstract description 3
- 229920000122 acrylonitrile butadiene styrene Polymers 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000639 Spring steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of mechanical device, specifically be an unmanned aerial vehicle with reduce windage fuselage, including the unmanned aerial vehicle body, unmanned aerial vehicle body bottom is fixed with the support frame, the bottom corner that is close to the support frame all installs damping device, damping device includes the shock attenuation ball, the annular has been seted up to the top surface of shock attenuation ball, it has the spring to peg graft in the top of annular, the top of spring is connected with the cutting ferrule, the bottom center department of cutting ferrule is equipped with the projection, the inboard of side opening is pegged graft and is had the bolt, the other end of bolt is connected with the shell fragment, the square groove has been seted up to the one end of shell fragment, the other. The utility model discloses an installed damping device in the corner of support frame for when unmanned aerial vehicle stopped flying, its shock attenuation ball can touch ground earlier, transmits the impulsive force and buffers on the spring, causes the damage in avoiding the impulsive force to reach unmanned aerial vehicle's inner structure, makes the novice practice change the starting man.
Description
Technical Field
The utility model relates to the technical field of mechanical device, specifically be an unmanned aerial vehicle with reduce windage fuselage.
Background
The unmanned aerial vehicle is a self-powered remote control aircraft with wireless remote control function, can execute various tasks and can be used for multiple times. Unmanned aerial vehicle in the market is used for high altitude aerial photography mostly, the agricultural spouts medicine also or people's sports toy, wherein when as the sports toy, because its operation needs the training of professional personage, thereby when people just contact, the operation is unskilled is very usual thing, the direction of its speed is difficult to control, especially when stopping flying, the novice is when controlling unmanned aerial vehicle contact ground, the velocity of unavailability is too fast and not vertical whereabouts, lead to unmanned aerial vehicle collision ground damage, maintenance cost has been increased, inconvenient novice's a lot of exercise, increase psychological pressure for the novice. In view of this, we propose a drone with a fuselage that reduces the wind resistance.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle with reduce windage fuselage to solve the novice that proposes in the above-mentioned background art when practicing unmanned aerial vehicle, easily cause the problem of damage when stopping flying.
In order to achieve the above object, the utility model provides a following technical scheme:
an unmanned aerial vehicle with a wind resistance reducing body comprises an unmanned aerial vehicle body and propeller devices installed at the top corners of the unmanned aerial vehicle body, wherein support frames are symmetrically fixed at the bottom of the unmanned aerial vehicle body through bolts, through holes are formed in the bottoms of the support frames and close to the corners, damping devices are installed at the corners close to the bottoms of the support frames and comprise damping balls, annular grooves are formed in the top surfaces of the damping balls, springs are inserted into the upper portions of the annular grooves, clamping sleeves are connected to the upper portions of the springs and are in clamping fit with the support frames, side holes are formed in the two sides of each clamping sleeve, a convex column is arranged at the center of the bottom of each clamping sleeve and is in inserting fit with the inner sides of the springs, bolts are inserted into the inner sides of the side holes, a convex block is arranged at the bottom of one end of each bolt, a spring piece is, the square groove is matched with one end of the bolt in a clamping mode, the other end of the elastic piece is symmetrically provided with a disc, and the disc is hinged to the other end of the bolt.
Preferably, the unmanned aerial vehicle body is star structure and thick in the middle of the edge is thin.
Preferably, the support frame is concave and the bottom of the support frame is in a horizontal tubular shape.
Preferably, the through hole corresponds to the side hole.
Preferably, the plug is inserted into the through hole.
Preferably, the spring plate is arc-shaped, and the length of the square groove is larger than the diameter of the bolt.
Preferably, the elastic sheet is clamped on the top side of the support frame.
Compared with the prior art, the beneficial effects of the utility model are that:
this unmanned aerial vehicle with reduce windage fuselage has installed damping device through the corner at the support frame for when unmanned aerial vehicle stopped flying, its shock attenuation ball can touch ground earlier, transmits the impulsive force and buffers on the spring, avoids the impulsive force to lead to the fact the damage in unmanned aerial vehicle's inner structure, makes the beginner practice change the shang shou.
Drawings
Fig. 1 is a schematic view of the overall assembly structure of the present invention;
fig. 2 is a schematic structural view of the unmanned aerial vehicle body of the present invention;
fig. 3 is a side view of the unmanned aerial vehicle body of the present invention;
FIG. 4 is a schematic structural view of the damping device of the present invention;
fig. 5 is an exploded view of the shock absorbing device of the present invention.
In the figure: 1. an unmanned aerial vehicle body; 10. a camera system; 2. a propeller device; 3. a support frame; 30. a through hole; 4. a damping device; 40. a shock absorbing ball; 400. a ring groove; 41. a spring; 42. a card sleeve; 420. a side hole; 421. a convex column; 43. a bolt; 430. a bump; 44. a spring plate; 440. square groove, 441, disc.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be considered as limiting the present invention, and in the description of the present invention, "a plurality" means two or more unless there is an explicit specific limitation.
Example 1
The utility model provides an unmanned aerial vehicle with reduce windage fuselage, for making the unmanned aerial vehicle fuselage reduce the windage, the inventor has improved unmanned aerial vehicle body 1, as an preferred embodiment, as shown in fig. 2 and 3, including the screw device 2 of unmanned aerial vehicle body 1 and apex angle department installation, the bottom of unmanned aerial vehicle body 1 is fixed with support frame 3 through the bolt symmetry, and support frame 3's bottom just is close to the corner and has all seted up through-hole 30.
In this embodiment, the shell of unmanned aerial vehicle body 1 adopts ABS to make, and its is hard and the surface is smooth, durable.
Specifically, unmanned aerial vehicle body 1 is star structure and thick in the middle of the edge is thin for wind is along the fuselage and is slided away, reduces the windage, makes its flight stabilize the power consumption and reduces.
Furthermore, the support frame 3 is in a concave shape, the bottom of the support frame is in a horizontal tubular shape, and the support frame is high in support strength and stable in placement.
In addition, the through hole 30 corresponds to the position of the side hole 420, and the axis is horizontal, so that the damper 4 is assembled horizontally.
Example 2
As a second embodiment of the present invention, in order to avoid collision damage caused by stopping flying of the unmanned aerial vehicle, the inventor sets a damping device 4, as shown in fig. 1, 4 and 5, the damping device 4 is installed near the bottom corner of the support frame 3, the damping device 4 includes a damping ball 40, a ring groove 400 is opened on the top surface of the damping ball 40, a spring 41 is inserted above the ring groove 400, a sleeve 42 is connected above the spring 41, the sleeve 42 is engaged with the support frame 3, side holes 420 are opened on both sides of the sleeve 42, a convex column 421 is disposed at the center of the bottom of the sleeve 42, the convex column 421 is engaged with the inner side of the spring 41, a bolt 43 is inserted inside the side hole 420, a projection 430 is disposed at the bottom of one end of the bolt 43, the other end of the bolt 43 is connected with a spring 44, a square groove 440 is disposed at one end of the bolt 44, the square groove 440 is engaged with, the other end of the elastic sheet 44 is symmetrically provided with a disc 441, and the disc 441 is hinged with the other end of the bolt 43.
In this embodiment, the damping ball 40 and the clip 42 are made of ABS plastic, which has hard strength and wear resistance, and the plug 43 and the elastic piece 44 are made of spring steel, which has hard strength and good elasticity.
Specifically, the plug 43 is inserted into the through hole 30, and the plug 43 penetrates through the ferrule 42 and the support 3, so that the two are connected into a whole.
Further, shell fragment 44 is circular-arc, and the length of square groove 440 is greater than the diameter of bolt 43, through the top of pressing shell fragment 44 for square groove 440 card goes into bolt 43 one end and is spacing by lug 430, makes cutting ferrule 42 wholly stabilize on support frame 3, when opening, presses the shell fragment 44 top once more, makes square groove 440 break away from lug 430, and the reuse hand is stirred outward, makes it break away from bolt 43, alright unblock restriction.
In addition, the elastic sheet 44 is clamped on the top side of the support frame 3, and the radius of the spring 44 is larger than that of the support frame 3, so that the elastic sheet 44 has enough space to deform.
When the unmanned aerial vehicle with the fuselage for reducing wind resistance is used, the bottom end of a spring 41 is inserted into an annular groove 400 of a damping ball 40, the top end of the spring 41 is sleeved outside a convex column 421 of a clamping sleeve 42, the damping ball 40 is pressed, the clamping sleeve 42 is clamped on a support frame 3 through the spring 41 to absorb buffer pressure, a side hole 420 of the clamping sleeve is aligned with a through hole 30, the clamping sleeve 43 passes through a bolt 43 and is hinged with a spring sheet 44 through a bolt, the top end of the spring sheet 44 is pressed at the moment, a square groove 440 is clamped into one end of the bolt 43 and limited by a lug 430, the clamping sleeve 42 is integrally and stably fixed on the support frame 3, when the unmanned aerial vehicle is opened, the top end of the spring sheet 44 is pressed again, the square groove 440 is separated from the lug 430 and is stirred outwards by hands, the bolt 43 can be unlocked and limited, when the unmanned aerial vehicle is controlled to stop flying, the damping ball 40 firstly contacts the ground, avoid causing the damage to unmanned aerial vehicle's important inner structure, also provide the guarantee for novice exercise.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides an unmanned aerial vehicle with reduce windage fuselage, includes screw device (2) of unmanned aerial vehicle body (1) and apex angle department installation, the bottom of unmanned aerial vehicle body (1) is fixed with support frame (3), its characterized in that through the bolt symmetry: the bottom of support frame (3) just is close to the corner and all has seted up through-hole (30), is close to the bottom corner of support frame (3) all installs damping device (4), damping device (4) include shock attenuation ball (40), annular (400) have been seted up to the top surface of shock attenuation ball (40), it has spring (41) to peg graft in the top of annular (400), the top of spring (41) is connected with cutting ferrule (42), cutting ferrule (42) with support frame (3) joint cooperation, side opening (420) have all been seted up to the both sides of cutting ferrule (42), the bottom center department of cutting ferrule (42) is equipped with projection (421), projection (421) with the inboard grafting cooperation of spring (41), the inboard grafting of side opening (420) has bolt (43), the one end bottom of bolt (43) is equipped with lug (430), the other end of bolt (43) is connected with shell fragment (44), a square groove (440) is formed in one end of the elastic sheet (44), the square groove (440) is matched with one end of the bolt (43) in a clamping mode, discs (441) are symmetrically arranged at the other end of the elastic sheet (44), and the discs (441) are hinged to the other end of the bolt (43).
2. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: unmanned aerial vehicle body (1) is star structure and edge thin middle thick.
3. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: the support frame (3) is in a concave shape, and the bottom of the support frame is in a horizontal tubular shape.
4. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: the through hole (30) corresponds to the position of the side hole (420).
5. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: the plug pin (43) is inserted into the through hole (30).
6. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: the elastic sheet (44) is arc-shaped, and the length of the square groove (440) is larger than the diameter of the plug pin (43).
7. The drone with fuselage of reduced wind resistance according to claim 1, characterized in that: the elastic sheet (44) is clamped on the top side of the support frame (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920643758.5U CN209889099U (en) | 2019-05-04 | 2019-05-04 | Unmanned aerial vehicle with reduce windage fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920643758.5U CN209889099U (en) | 2019-05-04 | 2019-05-04 | Unmanned aerial vehicle with reduce windage fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209889099U true CN209889099U (en) | 2020-01-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920643758.5U Expired - Fee Related CN209889099U (en) | 2019-05-04 | 2019-05-04 | Unmanned aerial vehicle with reduce windage fuselage |
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| CN (1) | CN209889099U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | A foldable landing gear inspection drone |
-
2019
- 2019-05-04 CN CN201920643758.5U patent/CN209889099U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | A foldable landing gear inspection drone |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200103 Termination date: 20210504 |