CN208630871U - A kind of unmanned helicopter drive mechanism damping - Google Patents
A kind of unmanned helicopter drive mechanism damping Download PDFInfo
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- CN208630871U CN208630871U CN201821138337.9U CN201821138337U CN208630871U CN 208630871 U CN208630871 U CN 208630871U CN 201821138337 U CN201821138337 U CN 201821138337U CN 208630871 U CN208630871 U CN 208630871U
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- damper
- shock absorber
- mounting bracket
- unmanned helicopter
- drive mechanism
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Abstract
The utility model discloses a kind of unmanned helicopter drive mechanism dampings, including multiple dampers and mounting bracket of shock absorber, first mounting bracket of shock absorber, second mounting bracket of shock absorber and third mounting bracket of shock absorber use tricycle layout mode, front three-point layout type is to arrange first mounting bracket of shock absorber in the front end of unmanned helicopter gear-box longitudinal axis, there are the second mounting bracket of shock absorber and third mounting bracket of shock absorber gear box back is symmetrically placed along longitudinal direction, first damper, second damper and third damper is corresponding is horizontally installed to the first mounting bracket of shock absorber, in second mounting bracket of shock absorber and third mounting bracket of shock absorber；Damper connection frame is installed on helicopter fuselage, damper connection frame is connected by bolt and nut with damper, damper connection frame is the adapter that three end faces are U-shaped, the bottom end of U-shaped adapter is connected with fuselage, the through-hole consistent with shock absorber lining sets of holes is offered at left and right sides of U-shaped adapter, the utility model structure is simple, easy for installation.
Description
Technical field
The utility model relates to unmanned plane accessory technical field, particularly relate to a kind of unmanned helicopter transmission knot
Structure damping.
Background technique
Helicopter relies on the advantages that its maneuverability, low-latitude flying, original place landing, in military affairs, geology, electric power and fire-fighting etc.
Various fields have obtained extremely wide application, and especially as the continuous progress of scientific and technological level, unmanned technology is deeply answered in recent years
For helicopter field, unmanned helicopter has not only consolidated the application field of helicopter, and border inspection, forest fire protection,
The application in the fields such as electromagnetic interference has new breakthrough.
Unmanned helicopter still needs the technological difficulties in face of conventional helicopters, especially helicopter vibration problem, a side
Face will affect complete machine flight quality, the stability of airborne equipment work be influenced, as helicopter vibration problem will affect bulb on machine
Use and imaging effect, on the other hand can also on acceleration machine components damage, not only reduce the service life of complete machine, also
The maintenance cost of unmanned helicopter can be greatly increased.As an airflight individual cell, unmanned helicopter is in operational process
In with the presence of the dynamic components such as rotor and drive mechanism vibration source, and vibrate without transmitting other than normal direction complete machine, can only be in inner bulk
System's transmitting；Simultaneously in order to which the low vibration for pursuing helicopter is horizontal and flight stability, and require to hinder retainer by seismic isolation technology
The vibration of part is transmitted to complete machine, is that the one of current helicopter vibration control is big especially for the isolation of helicopter low-frequency vibration
Difficult point.
Unmanned helicopter with constant weight (>=100kg), generally uses gear-driven form, and input terminal is to start
Machine, output end are rotor structure, so the vibration frequency of drive mechanism not only includes rotation and the meshing frequency between each gear,
The also rotational frequency of the output speed-frequency comprising engine and rotor structure, frequency domain is wide, vibrational energy is big, so
The damping for carrying out helicopter drive mechanism has the significance of reality.
Utility model content
Technical problem to be solved in the utility model is, the shortcomings that for the above prior art, proposes that a kind of nobody is straight
Machine drive mechanism damping is risen, the damping layout structure is simple, easy for installation.
In order to solve the above-mentioned technical problem, the technical solution of the utility model is achieved in the following ways: Yi Zhongwu
People's helicopter drive mechanism damping, including multiple dampers and mounting bracket of shock absorber, multiple dampers include the
One damper, the second damper and third damper, mounting bracket of shock absorber subtract including the first mounting bracket of shock absorber, second
Shake device mounting bracket and third mounting bracket of shock absorber, the first mounting bracket of shock absorber, the second mounting bracket of shock absorber and
Third mounting bracket of shock absorber uses tricycle layout mode, and front three-point layout type is longitudinal in unmanned helicopter gear-box
First mounting bracket of shock absorber is arranged in the front end of axis, has the second damper peace gear box back is symmetrically placed along longitudinal direction
Fill bracket and third mounting bracket of shock absorber, the first damper, the second damper and the corresponding water of third damper
Safety is loaded in the first mounting bracket of shock absorber, the second mounting bracket of shock absorber and third mounting bracket of shock absorber；Helicopter
Damper connection frame is installed, damper connection frame is connected by bolt and nut with damper, and damper connects on fuselage
Connecing frame is the adapter that three end faces are U-shaped, and the bottom end of U-shaped adapter is connected with fuselage, is opened at left and right sides of U-shaped adapter
Equipped with the through-hole consistent with shock absorber lining sets of holes.
The technical solution that the utility model further limits is:
Unmanned helicopter drive mechanism damping above-mentioned, the first damper, the second damper and third damping
Device be as metal external bushing, metal inner lining set and rubber it is cementing made of damper.
Unmanned helicopter drive mechanism damping above-mentioned, the first mounting bracket of shock absorber and gear-box one at
Type, the bottom end of three mounting bracket of shock absorber are equipped with the through-hole for capableing of horizontal axis mounting shock absorber, the internal diameter of through-hole with subtract
The outer diameter for shaking device is consistent.
Unmanned helicopter drive mechanism damping above-mentioned, symmetrically placed the second damping along longitudinal direction of gear box back
The fore-and-aft distance of device and third damper is 240-260mm, the second damper and third damper of longitudinally asymmetric placement
Lateral distance be 150-170mm.
Unmanned helicopter drive mechanism damping above-mentioned, damper are axially to be horizontally installed in horizontal plane,
Wherein the first damper shaft of front end installation point to horizontally-parallel, the second damper of rear end and the axial direction of third damper
It is parallel with longitudinal direction.
The beneficial effects of the utility model are: by the technical solution of the utility model, by cementing by metal and rubber
Made of rational deployment and damper and fuselage of the damper in drive mechanism connection configuration, on the one hand can effectively subtract
The small low-frequency vibration because of rotor and drive mechanism rotation generation is transmitted to fuselage, reduces complete machine oscillation magnitude；It on the other hand can
The stability of complete machine flight is effectively improved, the stabilization of bulb picture such as may be implemented by damping layout；Meanwhile passing through raising
Complete machine fatigue resistance can reduce maintenance cost, improve usage economy, and technical solution used by this is practical simply has
It imitates, is easy to accomplish, having important practical significance.
Detailed description of the invention
Fig. 1, Fig. 2 are the utility model structure diagram；
Wherein: the first damper of 1-, the second damper of 2-, 3- third damper, the first mounting bracket of shock absorber of 4-, 5-
Two mounting bracket of shock absorber, 6- third mounting bracket of shock absorber, 7- gear-box.
Specific embodiment
The utility model is described in further detail below:
Embodiment 1
A kind of unmanned helicopter drive mechanism damping provided in this embodiment, including multiple dampers and damping
Device mounting bracket, multiple dampers include the first damper 1, the second damper 2 and third damper 3, damper installation branch
Frame includes the first mounting bracket of shock absorber 4, the second mounting bracket of shock absorber 5 and third mounting bracket of shock absorber 6, the first damping
Device mounting bracket 4, the second mounting bracket of shock absorber 5 and third mounting bracket of shock absorber 6 use tricycle layout mode, preceding
3 layout type are to arrange first mounting bracket of shock absorber 4 in the front end of 7 longitudinal axis of unmanned helicopter gear-box,
7 rear end of gear-box is symmetrically placed along longitudinal direction the second mounting bracket of shock absorber 5 and third mounting bracket of shock absorber 6, and first subtracts
Shake device 1, the second damper 2 and third damper 3 is corresponding is horizontally installed to the first mounting bracket of shock absorber 4, second
In mounting bracket of shock absorber 5 and third mounting bracket of shock absorber 6；Damper connection frame, damping are installed on helicopter fuselage
Device connection frame is connected by bolt and nut with damper, and damper connection frame is the adapter that three end faces are U-shaped, U
The bottom end of shape adapter is connected with fuselage, offers at left and right sides of U-shaped adapter consistent with shock absorber lining sets of holes
Through-hole；First damper 1, the second damper 2 and third damper 3 are for by metal external bushing, metal inner lining set and rubber
Damper made of glue is cementing；First mounting bracket of shock absorber 4 is integrally formed with gear-box 7, three mounting bracket of shock absorber
Bottom end is equipped with the through-hole for capableing of horizontal axis mounting shock absorber, and the internal diameter of through-hole and the outer diameter of damper are consistent；After gear-box 7
The fore-and-aft distance for holding symmetrically placed along longitudinal direction the second damper 2 and third damper 3 is 240mm, longitudinally asymmetric placement
The lateral distance of second damper 2 and third damper 3 is 150mm；Damper is axially to be horizontally installed in horizontal plane,
Wherein the first damper 1 of front end installation point it is axial with it is horizontally-parallel, the second damper 2 of rear end and third damper 3
It is axial parallel with longitudinal direction.
In this way, by the technical solution of the utility model, by as metal and rubber it is cementing made of damper be driven
The connection configuration of rational deployment and damper and fuselage in structure, on the one hand can effectively reduce because of rotor and drive mechanism
It rotates the low-frequency vibration generated to transmit to fuselage, reduces complete machine oscillation magnitude；On the other hand complete machine flight can be effectively improved
The stabilization of bulb picture such as may be implemented in stability by damping layout；Meanwhile by improving complete machine fatigue resistance, energy
Maintenance cost is enough reduced, usage economy is improved, technical solution used by this is practical is simple and effective, easy to accomplish, has weight
The realistic meaning wanted.
Above embodiments are only to illustrate the technical idea of the utility model, and the protection model of the utility model cannot be limited with this
Enclose, it is all according to the utility model proposes technical idea, any changes made on the basis of the technical scheme each falls within this reality
Within the scope of novel protected.
Claims (5)
1. a kind of unmanned helicopter drive mechanism damping, including multiple dampers and mounting bracket of shock absorber, special
Sign is: the multiple damper includes the first damper (1), the second damper (2) and third damper (3), described to subtract
Shaking device mounting bracket includes the first mounting bracket of shock absorber (4), the second mounting bracket of shock absorber (5) and the installation of third damper
Bracket (6), first mounting bracket of shock absorber (4), the second mounting bracket of shock absorber (5) and third mounting bracket of shock absorber
(6) tricycle layout mode is used, the front three-point layout type is before unmanned helicopter gear-box (7) longitudinal axis
End arrangement one the first mounting bracket of shock absorber (4), gear-box (7) rear end along longitudinal direction it is symmetrically placed have the second damper installation
Bracket (5) and third mounting bracket of shock absorber (6), first damper (1), the second damper (2) and third damping
Device (3) is corresponding to be horizontally installed to the first mounting bracket of shock absorber (4), the second mounting bracket of shock absorber (5) and third
In mounting bracket of shock absorber (6)；Damper connection frame is installed, the damper connection frame passes through spiral shell on the helicopter fuselage
Bolt and nut are connected with damper, and the damper connection frame is the adapter that three end faces are U-shaped, the U-shaped switching
The bottom end of part is connected with fuselage, and consistent with shock absorber lining sets of holes lead to is offered at left and right sides of the U-shaped adapter
Hole.
2. unmanned helicopter drive mechanism damping according to claim 1, it is characterised in that: described first subtracts
It is cementing by metal external bushing, metal inner lining set and rubber for shaking device (1), the second damper (2) and third damper (3)
Made of damper.
3. unmanned helicopter drive mechanism damping according to claim 1, it is characterised in that: described first subtracts
It shakes device mounting bracket (4) and gear-box (7) to be integrally formed, the bottom end of three mounting bracket of shock absorber is equipped with can be horizontal
The through-hole of axially mounted damper, the internal diameter of through-hole and the outer diameter of damper are consistent.
4. unmanned helicopter drive mechanism damping according to claim 1, it is characterised in that: the gear-box
(7) fore-and-aft distance of rear end symmetrically placed the second damper (2) and third damper (3) along longitudinal direction is 240-260mm, institute
The lateral distance of the second damper (2) and third damper (3) of stating longitudinally asymmetric placement is 150-170mm.
5. unmanned helicopter drive mechanism damping according to claim 1, it is characterised in that: the damper
Be it is axial be horizontally installed in horizontal plane, wherein the first damper (1) of front end installation point it is axial with it is horizontally-parallel, rear end
The axial direction of second damper (2) and third damper (3) is parallel with longitudinal direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821138337.9U CN208630871U (en) | 2018-07-18 | 2018-07-18 | A kind of unmanned helicopter drive mechanism damping |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821138337.9U CN208630871U (en) | 2018-07-18 | 2018-07-18 | A kind of unmanned helicopter drive mechanism damping |
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| Publication Number | Publication Date |
|---|---|
| CN208630871U true CN208630871U (en) | 2019-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821138337.9U Active CN208630871U (en) | 2018-07-18 | 2018-07-18 | A kind of unmanned helicopter drive mechanism damping |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
-
2018
- 2018-07-18 CN CN201821138337.9U patent/CN208630871U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
| CN110844090B (en) * | 2019-10-11 | 2022-11-22 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
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