CN212243816U - Rotor shimmy structure of single-rotor-wing unmanned aerial vehicle without ailerons - Google Patents
Rotor shimmy structure of single-rotor-wing unmanned aerial vehicle without ailerons Download PDFInfo
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- CN212243816U CN212243816U CN202020236262.9U CN202020236262U CN212243816U CN 212243816 U CN212243816 U CN 212243816U CN 202020236262 U CN202020236262 U CN 202020236262U CN 212243816 U CN212243816 U CN 212243816U
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- rotor
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- shimmy
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- 238000013016 damping Methods 0.000 claims abstract description 36
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 21
- 239000010959 steel Substances 0.000 claims abstract description 21
- 230000000149 penetrating effect Effects 0.000 claims abstract description 8
- 229920002635 polyurethane Polymers 0.000 claims description 4
- 239000004814 polyurethane Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses a single-rotor wing unmanned aerial vehicle rotor wing shimmy structure, which belongs to the technical field of rotor wing shimmy structure, and comprises a propeller clamp and a blade, wherein a pinhole is formed in the left side of the upper end surface of the blade in a penetrating way, a U-shaped interface is formed in the middle part of the left side of the blade, a U-shaped opening is fixedly connected to the right side of the propeller clamp, a small hole and a large hole are formed in the upper end surface and the lower end surface of the U-shaped opening in a penetrating way from left to right, the upper end surface of the U-shaped opening is respectively provided with a screw matched with the small hole and a fixed pin matched with the pinhole from left to right, the upper end surface and the lower end surface of the U-shaped opening are respectively provided with a shouldered steel bushing matched with the large hole, and a damping block matched with the U-shaped interface is movably connected between the two small holes, and the structure has stronger stability, is convenient to assemble and disassemble, is convenient to use and maintain, is simple to manufacture, and reduces the use cost.
Description
Technical Field
The utility model relates to a rotor shimmy technical field, in particular to single rotor does not have aileron unmanned aerial vehicle rotor shimmy structure.
Background
The rotor part of helicopter is unmanned helicopter's core part, the stability of its function direct decision aircraft flight, its rotor shimmy design of current single rotor heavy load unmanned aerial vehicle adopts single fulcrum and dual fulcrum mode mostly, single fulcrum is only a hole of the fixed mode of paddle promptly and presss from both sides with the oar and be connected, its shimmy design is usually that the paddle root presss from both sides U type opening bottom at the paddle and increases elastomeric element, dual fulcrum is that the fixed mode of paddle has two holes to press from both sides with the oar and is connected, it shimmys the design and selects more to inlay like two small-size elastomeric element in the U type opening is pressed from both sides at the oar.
The existing single-pivot shimmy structure of the rotor shimmy structure of the unmanned aerial vehicle has the defects of low shimmy efficiency and quick damage of an elastic component if the elastic component is simply added and the elastic component is in line contact with the root of the blade in the motion process because the root of the blade and the elastic component move in an arc track in the shimmy motion process; the double-pivot pendulum vibration structure is embedded in the opening of the paddle clamp in the form of two small elastic parts, and because the thickness of the opening of the paddle clamp is limited, the embedded elastic parts have insufficient strength and can cause the frequency of damage to the elastic parts to be overhigh.
SUMMERY OF THE UTILITY MODEL
The utility model provides a single-rotor wing no-aileron unmanned aerial vehicle rotor wing shimmy structure, which aims to solve the problems that the current unmanned aerial vehicle rotor wing shimmy structure single-pivot shimmy structure is too simple, and the blade root and the elastic part move in a circular arc track in the shimmy motion process, if the elastic part is simply added, the elastic part is in line contact with the blade root in the motion process, thus leading to the defects of low shimmy efficiency and quick damage of the elastic part; the double-pivot pendulum vibration structure is embedded in the opening of the paddle clamp in the form of two small elastic parts, and because the thickness of the opening of the paddle clamp is limited, the embedded elastic part has insufficient strength, so that the problem of high frequency of damage is caused.
The utility model is realized in such a way, a single rotor no aileron unmanned aerial vehicle rotor shimmy structure, including oar clamp and paddle, the oar clamp is located the left side of paddle, the pinhole has been run through to the left side of the up end of paddle, the U type interface has been seted up at the left side middle part of paddle, the right side fixedly connected with U type opening of oar clamp, the upper and lower both ends face of U type opening all runs through from left to right has been seted up aperture and macropore, the up end of U type opening is provided with respectively from left to right with aperture assorted screw and with pinhole assorted fixed pin, the lower terminal surface of U type opening has set gradually from left to right with screw assorted pentagon nut and with fixed pin assorted slotted nut, the upper and lower both ends of U type opening all are provided with shoulder steel bushing assorted with macropore, two shoulder steel bushing is located the below of fixed pin and above slotted nut respectively, and a damping block matched with the U-shaped interface is movably connected between the two small holes.
In order to make damping piece appearance and oar press from both sides root U type opening cooperation more reasonable, improve life, conduct the utility model discloses a single rotor does not have aileron unmanned aerial vehicle rotor and shimmys the structure preferred, the shape of damping piece is the cylinder form.
In order to have multiple hardness to the hardness of damping piece can be changed at any time according to the actual debugging state, as the utility model discloses a single rotor does not have aileron unmanned aerial vehicle rotor structure of shimmying is preferred, the material of damping piece is polyurethane, the hardness of damping piece can be changed according to the actual debugging state.
For the convenient device satisfies the required function of flight, conduct the utility model discloses a single rotor does not have aileron unmanned aerial vehicle rotor structure of shimmying is preferred, the part between oar clamp and paddle operates steadily each other.
In order to increase area of contact, reduce pressure, prevent not hard up, protection screw and pentagon nut, as the utility model discloses a single rotor does not have aileron unmanned aerial vehicle rotor shimmy structure is preferred, U type open-ended upper and lower both ends all are provided with gasket, two the gasket is located the below of screw and the top of pentagon nut respectively.
Compared with the prior art, the beneficial effects of the utility model are that:
1. when the paddle clamp and the paddle are installed, a damping block is placed between two small holes, the paddle is clamped into a U-shaped opening, the outer side of the damping block is matched with a U-shaped interface at the left end of the paddle, a screw is inserted into the small hole positioned above the damping block, the screw penetrates through a hole in the middle of the damping block and penetrates out of the small hole positioned below the damping block, a pentagonal nut is connected to one end of the small hole, which is penetrated out of the screw, namely the position is a pendulum vibration structure, shoulder steel sleeves are respectively placed into two large holes, a fixing pin is screwed into the shoulder steel sleeve positioned above the shoulder steel sleeve, the fixing pin penetrates through the large holes and the pin holes and penetrates out of the shoulder steel sleeve positioned below the shoulder steel sleeve, a slotted nut is installed at the lower end of the fixing pin penetrating out of the shoulder steel sleeve, the paddle clamp and the paddle are connected and fixed, the fixing pin is a cylindrical steel piece and is a main stressed component, after, the moving track of the root of the paddle and the paddle clamp in the relative motion is arc-shaped, so that the structure is a mechanical structure which is used for better integrating a rotor wing and a machine body and ensuring the flying posture of the airplane, and the structure has stronger stability, is convenient to assemble and disassemble, is convenient to use and maintain, is simple to manufacture and reduces the use cost;
2. the damping block is cylindrical, so that the damping block is more reasonable in shape and matched with the U-shaped opening at the root of the paddle clamp, and the service life is prolonged.
Drawings
Fig. 1 is a perspective view of a rotor shimmy structure of a single-rotor aileron-free unmanned aerial vehicle of the present invention;
fig. 2 is a perspective view of a rotor shimmy structure of the single-rotor aileron-free unmanned aerial vehicle of the present invention;
fig. 3 is a top view of the blade of the present invention;
in the figure: 1. a paddle clamp; 101. a U-shaped opening; 102. macropores; 103. a small hole; 2. a paddle; 201. a U-shaped interface; 202. a pin hole; 3. a damping block; 4. a fixing pin; 401. a shouldered steel sleeve; 402. a screw; 403. A pentagonal nut; 404. a gasket; 405. and (4) slotting the nut.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. In addition, in the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
Referring to fig. 1-3, the present invention provides a technical solution: a single-rotor aileron-free unmanned aerial vehicle rotor shimmy structure comprises a paddle clamp 1 and a blade 2, the paddle clamp 1 is positioned at the left side of the blade 2, the left side of the upper end surface of the blade 2 is provided with a pin hole 202 in a penetrating way, the middle part of the left side of the blade 2 is provided with a U-shaped interface 201, the right side of the paddle clamp 1 is fixedly connected with a U-shaped opening 101, the upper end surface and the lower end surface of the U-shaped opening 101 are respectively provided with a small hole 103 and a large hole 102 in a penetrating way from left to right, the upper end surface of the U-shaped opening 101 is respectively provided with a screw 402 matched with the small hole 103 and a fixed pin 4 matched with the pin hole 202 from left to right, the lower end surface of the U-shaped opening 101 is sequentially provided with a pentagonal nut 403 matched with the screw 402 and a slotted nut 405 matched with the fixed pin 4 from left to right, the upper end surface and the, a damping block 3 matched with the U-shaped interface 201 is movably connected between the two small holes 103.
In this embodiment: when the blade clamp 1 and the blade 2 are installed, the damping block 3 is placed between the two small holes 103, the blade 2 is clamped into the U-shaped opening 101, the outer side of the damping block 3 is matched with the U-shaped interface 201 at the left end of the blade 2, then the screws 402 are inserted into the small holes 103 positioned above, the screws 402 penetrate through the holes in the middle of the damping block 3 and penetrate out of the small holes 103 below, then the pentagonal nuts 403 are connected at the positions, where the screws 402 penetrate out of the small holes 103, namely, the pendulum vibration structure is formed, then the shouldered steel sleeves 401 are respectively placed into the two large holes 102, then the fixing pins 4 are screwed into the shouldered steel sleeves 401 from the upper part, the fixing pins 4 penetrate through the large holes 102 and the pin holes 202 and penetrate out of the shouldered steel sleeves 401 positioned below, then the slotted nuts 405 are installed at the lower ends of the fixing pins 4 penetrating out of the shouldered steel sleeves 401, so that the blade clamp 1 and the blade 2 are, after the installation, the pendulum is shaken mainly and is realized by damping piece 3, relies on another fixed pivot fixed pin 4, and the 2 roots of paddle press from both sides 1 with the oar and move the orbit in relative motion and be circular-arc to this structure is one kind and is used for letting rotor and organism better combine together, guarantees a mechanical structure of aircraft flight gesture, and this structure has stronger stability, and this structure is convenient in installing and removing, uses and maintains the convenience, and simple manufacture reduces use cost.
As a technical optimization scheme of the utility model, the shape of damping piece 3 is the cylinder form.
In this embodiment: the damping block 3 is cylindrical, so that the U-shaped opening 101 at the root part of the paddle clamp 1 is matched with the damping block 3 more reasonably, and the service life is prolonged.
As a technical optimization scheme of the utility model, damping piece 3's material is polyurethane, and damping piece 3's hardness can be changed according to the actual debugging state.
In this embodiment: the damping block 3 is made of polyurethane, so that the damping block 3 has various hardness, and the hardness of the damping block 3 can be replaced at any time according to an actual debugging state.
As a technical optimization scheme of the utility model, the part that the oar pressed from both sides 1 and paddle 2 is steady operation each other.
In this embodiment: the parts between the oar clamp 1 and the oar blade 2 are stable in operation, and the device further meets the functions required by flight.
As a technical optimization scheme of the utility model, the upper and lower both ends of U type opening 101 all are provided with gasket 404, and two gaskets 404 are located the below of screw 402 and the top of pentagonal nut 403 respectively.
In this embodiment: after the screw 402 is connected with the pentagonal nut 403, the two gaskets 404 are tightly attached to the upper end surface and the lower end surface of the U-shaped opening 101, so that the contact area is increased through the gaskets 404, the pressure is reduced, the looseness is prevented, and the screw 402 and the pentagonal nut 403 are protected.
The working principle is as follows: when the blade clamp 1 and the blade 2 are installed, the damping block 3 is placed between the two small holes 103, the blade 2 is clamped into the U-shaped opening 101, the outer side of the damping block 3 is matched with the U-shaped interface 201 at the left end of the blade 2, then the screws 402 are inserted into the small holes 103 positioned above, the screws 402 penetrate through the holes in the middle of the damping block 3 and penetrate out of the small holes 103 below, then the pentagonal nuts 403 are connected at the positions, where the screws 402 penetrate out of the small holes 103, namely, the pendulum vibration structure is formed, then the shouldered steel sleeves 401 are respectively placed into the two large holes 102, then the fixing pins 4 are screwed into the shouldered steel sleeves 401 from the upper part, the fixing pins 4 penetrate through the large holes 102 and the pin holes 202 and penetrate out of the shouldered steel sleeves 401 positioned below, then the slotted nuts 405 are installed at the lower ends of the fixing pins 4 penetrating out of the shouldered steel sleeves 401, so that the blade clamp 1 and the blade 2 are, after installation, shimmy is mainly realized by damping piece 3, relies on another fixed pivot fixed pin 4, and the orbit that moves is circular-arc in relative motion between paddle 2 root and oar clamp 1.
The above description is only exemplary of the present invention and should not be construed as limiting the present invention, and any modifications, equivalents and improvements made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (5)
1. The utility model provides a single rotor does not have aileron unmanned aerial vehicle rotor shimmy structure, includes oar clamp (1) and paddle (2), the oar presss from both sides (1) and is located the left side of paddle (2), pinhole (202) have been seted up in the upper end left side of paddle (2) through, U type interface (201), its characterized in that have been seted up at the left side middle part of paddle (2): the right side of the paddle clamp (1) is fixedly connected with a U-shaped opening (101), the upper end surface and the lower end surface of the U-shaped opening (101) are both provided with a small hole (103) and a large hole (102) in a penetrating way from left to right, the upper end surface of the U-shaped opening (101) is respectively provided with a screw (402) matched with the small hole (103) and a fixing pin (4) matched with the pin hole (202) from left to right, the lower end surface of the U-shaped opening (101) is sequentially provided with a pentagonal nut (403) matched with the screw (402) and a slotted nut (405) matched with the fixing pin (4) from left to right, the upper end and the lower end of the U-shaped opening (101) are respectively provided with a shouldered steel sleeve (401) matched with the large hole (102), the shouldered steel sleeves (401) are respectively positioned below the fixing pin (4) and above the slotted nut (405), and a damping block (3) matched with the U-shaped connector (201) is movably connected between the small holes (103).
2. The rotor shimmy structure of a single-rotor aileron-less drone of claim 1 wherein: the damping block (3) is cylindrical.
3. The rotor shimmy structure of a single-rotor aileron-less drone of claim 2 wherein: the damping block (3) is made of polyurethane, and the hardness of the damping block (3) can be replaced according to an actual debugging state.
4. The rotor shimmy structure of a single-rotor aileron-less drone of claim 1 wherein: the parts between the paddle clamp (1) and the paddle (2) are stable in operation.
5. The rotor shimmy structure of a single-rotor aileron-less drone of claim 1 wherein: the upper end and the lower end of the U-shaped opening (101) are provided with gaskets (404), and the two gaskets (404) are respectively positioned below the screw (402) and above the pentagonal nut (403).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020236262.9U CN212243816U (en) | 2020-02-29 | 2020-02-29 | Rotor shimmy structure of single-rotor-wing unmanned aerial vehicle without ailerons |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020236262.9U CN212243816U (en) | 2020-02-29 | 2020-02-29 | Rotor shimmy structure of single-rotor-wing unmanned aerial vehicle without ailerons |
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| Publication Number | Publication Date |
|---|---|
| CN212243816U true CN212243816U (en) | 2020-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020236262.9U Expired - Fee Related CN212243816U (en) | 2020-02-29 | 2020-02-29 | Rotor shimmy structure of single-rotor-wing unmanned aerial vehicle without ailerons |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123533A (en) * | 2022-09-01 | 2022-09-30 | 北京赛沃摩申科技有限公司 | Mixed rotor configuration coaxial unmanned aerial vehicle |
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2020
- 2020-02-29 CN CN202020236262.9U patent/CN212243816U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123533A (en) * | 2022-09-01 | 2022-09-30 | 北京赛沃摩申科技有限公司 | Mixed rotor configuration coaxial unmanned aerial vehicle |
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Granted publication date: 20201229 |