CN205801527U - The dynamic multi-rotor aerocraft of a kind of oil - Google Patents
The dynamic multi-rotor aerocraft of a kind of oil Download PDFInfo
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- CN205801527U CN205801527U CN201620476183.9U CN201620476183U CN205801527U CN 205801527 U CN205801527 U CN 205801527U CN 201620476183 U CN201620476183 U CN 201620476183U CN 205801527 U CN205801527 U CN 205801527U
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- engine
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- frame
- damper unit
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Abstract
The purpose of this utility model is to provide the dynamic multi-rotor aerocraft of a kind of oil, including engine, Airframe And Engine damper unit, described frame includes frame central plate, described frame central plate includes that upper spider central plate and lower bearing bracket central plate, described engine damper unit include the first engine Damping modules and the second engine Damping modules；Described first engine Damping modules, for being connected to engine below frame；Described second engine Damping modules, is arranged between described engine and described first engine Damping modules, for reducing the engine vibration conduction to the first engine Damping modules, it is possible to effectively solve the vibration problem of engine.After vibration damping is transformed, decrease vibration source engine by means such as suspending, flexibly connect to transmit to the vibration of rack construction, the transmission vibrated to rotor support arm is reduced by vibration damping hole, greatly reduce the amplitude of frame vibration, under engine height rotating speed, frequency of vibration declines, complete machine oscillation situation is effectively alleviated, it is possible to reach the demand of reliable operation.
Description
Technical field
This utility model belongs to technical field of aerospace, is specifically related to the dynamic multi-rotor aerocraft of a kind of oil.
Background technology
Small-sized aviation piston engine has been obtained for extensively applying in fixed-wing unmanned plane, and in recent years, many rotors are unmanned
Machine is fast-developing, uses the oil of small-sized aviation piston engine to move many rotor wing unmanned aerial vehicles and has load-carrying advantage big, long-endurance concurrently,
It is expected to be applied at agricultural, logistics, the numerous areas such as aerial survey of taking photo by plane.
Many rotors, compared with fixed-wing, have large number of rotating mechanism, vibration source and Vibration Condition more complicated, to engine
Vibrate more sensitive.Requirement for engine vibration damping also presents requirement different with fixed-wing because structure is different.In aviation
Piston engines is applied in the practice of many rotor wing unmanned aerial vehicles, and engine is as one of main vibration source of body, and vibrates for remaining
The energy source in source, under running power in difference, engine has different frequency of vibration, and body takes rigidly connected drawing
Hold up and easily causing the resonance of other vibration sources, the most then affect flight stability, heavy then destroy housing construction.Many rotors are moved for oil
For unmanned plane, it is necessary to cut off the vibration of engine, thus ensure the stable and reliable of unmanned plane structure.
Summary of the invention
The purpose of this utility model is to provide the dynamic multi-rotor aerocraft of a kind of oil, it is possible to the vibration effectively solving engine is asked
Topic.
The technical solution of the utility model is: the dynamic multi-rotor aerocraft of a kind of oil, including engine, Airframe And Engine vibration damping list
Unit, described frame includes that frame central plate, described frame central plate include upper spider central plate and lower bearing bracket central plate, its feature
It is:
Described engine damper unit includes the first engine Damping modules and the second engine Damping modules；
Described first engine Damping modules, for being connected to engine below frame；
Described second engine Damping modules, is arranged between described engine and described first engine Damping modules, is used for subtracting
Little engine vibration is to the conduction of the first engine Damping modules.
Further, described first engine Damping modules is arranged on below lower bearing bracket central plate, for by engine suspension even
It is connected to frame.
Further, this aircraft also includes gear drive and transmission damper unit, and wherein gear drive sets
Putting between upper spider central plate and lower bearing bracket central plate, described transmission damper unit flexibly connects the output machine in engine
Between structure and gear drive, for reducing the engine vibration conduction to gear drive.
Further, the output shaft of described engine is provided with clutch, and the output shaft of described clutch is provided with driving
Synchronous pulley, is provided with driven synchronous pulley in described first engine Damping modules, described driving synchronous pulley is by described biography
Dynamic damper unit is connected with driven synchronous pulley.
Further, described transmission damper unit is Timing Belt；Described driven synchronous pulley is connected with power output gear,
Described power output gear engages with being arranged on one of four master gears on spacing axle bed；Four master gears engage each other.
Further, described frame central plate is provided with body damper unit with the connecting portion of rotor horn, draws for reduction
Hold up the conduction vibrated to rotor.
Further, described body damper unit is circular vibration damping hole, its can the stress distribution on uniform bore border, and
The diameter in hole is less than 0.7 times of described connecting portion width.
Further, described up/down frame central plate respectively arranges two vibration damping holes with the junction of each rotor horn, and
And connecting portion is provided with pipe clamp, it is used for connecting rotor horn.
Further, described frame central plate is provided with lightening hole, is used for alleviating fuselage weight, the shape bag of described lightening hole
Include circle, triangle and/or polygon.
Further, described lightening hole is crisscross arranged on body center's plate according to difformity.
Use the technical solution of the utility model, can effectively solve the vibration problem of engine.Wherein, the suspension peace of engine
Dress optimizes complete machine structure, beneficially vibration damping；Vibration absorber can filter engine dither；Between engine and drive system
Timing Belt flexibly connects, and has cut off vibration source；Frame central plate is provided with vibration damping hole at its connecting portion with rotor horn, reduces
Vibrate the propagation to horn.
Accompanying drawing explanation
Fig. 1 is this utility model complete machine structure schematic diagram；
Fig. 2 is that engine of the present utility model assembles structural representation with drive mechanism；
Fig. 3 is center machine shelf structure schematic diagram of the present utility model.
Detailed description of the invention
Small-sized aeronautical engine is based on piston engines, and piston engines is one of primary oscillation source of small-sized aerial craft, and it shakes
Dynamic main cause is cylinder knock, power output shaft rotary part dynamic equilibrium problems.Wherein, asymmetric the shaking of cylinder knock generation
Dynamic is inevitable, can calculate the frequency of cylinder knock from engine speed, and the vibration that can obtain detonation generation is a class
Amplitude is less, and frequency is delivered to being rigidly connected of Flight Vehicle Structure along engine in the vibration source of the KHz order of magnitude, this vibration
Housing construction, under certain frequency, causes resonance, aircraft body structure is caused irreversible destruction.And rotary part
Dynamic equilibrium problems, can be improved by the machining accuracy and material homogeneity that improve rotary part.
For the feature of engine vibration, the method slowed down in conjunction with vibration, we use change structural focus and damping vibration attenuation
Two ways realizes the vibration damping for engine.By engine installation site and mode are changed by the connection of housing construction upper rigid
Connect for housing construction damping suspended below, on the one hand by centre of gravity adjustment, change the mode of oscillation of body；On the one hand rubber is used
Rubber cushion partition engine is rigidly connected with frame, utilizes rubber blanket flexible member attribute, slowing down vibration amplitude, cuts down Vibration propagation
Path.
For drive system vibration damping, by using belt to connect between engine outfan and drive system input, keep away
Exempt from vibration and be delivered to drive system each several part by rigidly connected drive mechanism by engine.
For the conduct vibrations path of frame to rotor, circular vibration damping hole is set at cantilever beam and frame junction, reduces
Cantilever beam-frame junction rigidity, reduces cantilever beam-frame junction power transmission area.
1-3 illustrates detailed description of the invention of the present utility model below in conjunction with the accompanying drawings.
Embodiment one:
As illustrated in the accompanying drawings from 1 to 3, the dynamic many rotor wing unmanned aerial vehicles of a kind of oil, it includes frame, with electric starter 3 and exhaustor 2
Engine 1, engine damper unit.Described frame include frame central plate, described frame central plate include upper spider central plate and
Lower bearing bracket central plate (as shown in Figure 3).Described engine damper unit includes the first engine Damping modules 6 and the second engine vibration damping mould
Block 4.
First engine Damping modules 6 usually installing rack, installing frame or mounting rail structure, installing rack can be circle, three
Dihedral or polygonized structure, installing frame uses closed type structure, mounting rail can use concave or convex structure.
First engine Damping modules 6 is fixed on the lower section of lower bearing bracket central plate, for being connected above engine from engine, makes
Whole engine 1 is suspended on below frame, and the advantage of suspension mounting means is that the gravity utilizing engine 1 self is to realize engine
With flexibly connecting of engine mount 6.
Second engine Damping modules 4 is arranged between engine 1 and the first engine damping module 6, is used for slowing down engine 1 and shakes
The conduction of trend rack construction.
Second engine Damping modules 4 usually flexible member or damping element, including damping block, damping material, rubber ring,
Rubber blanket etc..
Second engine Damping modules 4 can arrange multiple, and its structure can be as shown in Figure 2 additional around central shaft
Elastomeric material is constituted.
Embodiment two:
On the basis of embodiment one, the present embodiment is further directed to drive system and has carried out Vibration Absorption Designing.Concrete scheme
As follows:
Engine 1 output shaft is mounted with clutch 5, and clutch 5 output shaft is provided with driving synchronous pulley 81,
Drive synchronous pulley 81 by transmission damper unit 7 with the driven synchronous pulley 82 being arranged on belt wheel installing rack 9 even
Connecing, this structure constitutes the primary transmission system of multi-rotor aerocraft.
Engine 1 power is via primary transmission systems communicate to driven synchronous pulley 82, and driven synchronous pulley 82 is with dynamic
Power output gear 10 connects, power output gear 10 with in four master gears 12 being arranged on spacing axle bed 11
One engagement, four master gears 12 engage each other, and spacing axle bed 11 is the main support structure of drive system, and it processes essence
Close degree requires higher, it is ensured that master gear 12 engages in order, and said structure constitutes secondary driving system.Power exports
The gear ratio of gear 10 and master gear 12 determines the speed reducing ratio of drive system, for ensureing that transmission effect can meet design need
Asking, speed reducing ratio should be between 1.5-3.5.
Transmission damper unit 7 is set in said structure further, it is achieved engine 1 clutch end and drive system
Flexibly connecting of power intake, plays the effect of slowing down vibration conduction.
Wherein transmission damper unit 7 is arranged between driving synchronous pulley 81 and driven synchronous pulley 82, it is achieved drive
Flexibly connecting of synchronous pulley 81 and driven synchronous pulley 82.
Transmission damper unit 7 can use Timing Belt structure to realize flexibly connecting.Timing Belt can use elastomeric material system
Become.
Transmission damper unit 7 can also use the drive mechanism such as elastic chain, resislient gear to realize.
Embodiment three
On the basis of embodiment before, the present embodiment is provided with body damper unit further on body, is used for subtracting
Little engine vibration is to the conduction of rotor.Concrete scheme is as follows:
As it is shown on figure 3, the connecting portion at horn 15 and frame central plate 14 is provided with body damper unit 13, this is
Vibration damping key Design in rack construction.
Body damper unit can be designed as circular vibration damping pore structure.On the one hand play the effect of loss of weight, on the one hand cut down
Vibration to the conducting path of horn 15, slows down the vibration of horn from frame central plate 14.
Circular vibration damping pore structure can also the borderline stress distribution of uniform bore.Preferably, the diameter of circular port is less than
0.7 times of frame central plate 14 terminal end width (namely connecting portion).
Preferentially, two vibration damping holes 13 are respectively set in upper and lower frame central plate 14 and horn 15 junction, so,
On four horn about 15 frame central plates 14,16 vibration damping holes 13 are set altogether.
Body damper unit 13 is in addition to being arranged to circular vibration damping pore structure, it is also possible to be set to rib shapes, projection shape
Shape, groove shapes etc., its effect is all to cut down vibration from frame central plate 14 to the conducting path of horn 15.
In addition, on frame central plate, it is also possible to multiple lightening hole is set further, plays and alleviate fuselage weight
Effect.Lightening hole can be the structures such as circle, triangle, rectangle, polygon.And can be crisscross arranged according to difformity
On body center's plate.
After vibration damping is transformed, decrease vibration source engine 1 shaking to rack construction by means such as suspending, flexibly connect
Dynamic transmission, is reduced the transmission vibrated to rotor support arm, greatly reduces the amplitude of frame vibration, at engine 1 by vibration damping hole
Under high rotating speed, frequency of vibration declines, and complete machine oscillation situation is effectively alleviated, it is possible to reach the demand of reliable operation.
Embodiment described above is only preferred implementation of the present utility model, not enters scope of the present utility model
Row limits, and on the premise of without departing from this utility model design spirit, those of ordinary skill in the art are to skill of the present utility model
Various deformation that art scheme is made and improvement, all should fall in the protection domain that claims of the present utility model determine.
Claims (10)
1. oil moves a multi-rotor aerocraft, and including engine, Airframe And Engine damper unit, described frame includes frame central
Plate, described frame central plate includes upper spider central plate and lower bearing bracket central plate, it is characterised in that:
Described engine damper unit includes the first engine Damping modules and the second engine Damping modules；
Described first engine Damping modules, for being connected to engine below frame；
Described second engine Damping modules, is arranged between described engine and described first engine Damping modules, draws for reduction
Hold up the conduction vibrated to the first engine Damping modules.
2. multi-rotor aerocraft as claimed in claim 1, it is characterised in that:
Described first engine Damping modules is arranged on below lower bearing bracket central plate, for engine suspension is connected to frame；
Described second engine Damping modules is flexible member.
3. multi-rotor aerocraft as claimed in claim 1, it is characterised in that:
This aircraft also includes gear drive and transmission damper unit；
Wherein gear drive is arranged between upper spider central plate and lower bearing bracket central plate；
Described transmission damper unit flexibly connects between the power take-off mechanism and gear drive of engine, draws for reduction
Hold up the conduction vibrated to gear drive.
4. multi-rotor aerocraft as claimed in claim 3, it is characterised in that:
The output shaft of described engine is provided with clutch, and the output shaft of described clutch is provided with driving synchronous pulley；
It is provided with driven synchronous pulley in described first engine Damping modules；
Described driving synchronous pulley is connected with driven synchronous pulley by described transmission damper unit.
5. multi-rotor aerocraft as claimed in claim 4, it is characterised in that:
Described transmission damper unit is Timing Belt；
Described driven synchronous pulley is connected with power output gear；
Described power output gear engages with being arranged on one of four master gears on spacing axle bed；Four master gears engage each other.
6. the multi-rotor aerocraft as described in any one of claim 1-5, it is characterised in that:
Described frame central plate is provided with body damper unit with the connecting portion of rotor horn, for reducing engine vibration to rotor
Conduction.
7. multi-rotor aerocraft as claimed in claim 6, it is characterised in that:
Described body damper unit is circular vibration damping hole, and it can the stress distribution on uniform bore border
The diameter in described circular vibration hole is less than 0.7 times of described connecting portion width.
8. multi-rotor aerocraft as claimed in claim 7, it is characterised in that:
Described up/down frame central plate respectively arranges two vibration damping holes with the junction of each rotor horn；
Described connecting portion is provided with pipe clamp, is used for connecting rotor horn.
9. the multi-rotor aerocraft as described in any one of claim 1-5, it is characterised in that:
Described frame central plate is provided with lightening hole, is used for alleviating fuselage weight；
The shape of described lightening hole includes circle or polygon.
10. multi-rotor aerocraft as claimed in claim 9, it is characterised in that: described lightening hole sets according to difformity is staggered
Put on body center's plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476183.9U CN205801527U (en) | 2016-05-24 | 2016-05-24 | The dynamic multi-rotor aerocraft of a kind of oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476183.9U CN205801527U (en) | 2016-05-24 | 2016-05-24 | The dynamic multi-rotor aerocraft of a kind of oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205801527U true CN205801527U (en) | 2016-12-14 |
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ID=57500632
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620476183.9U Active CN205801527U (en) | 2016-05-24 | 2016-05-24 | The dynamic multi-rotor aerocraft of a kind of oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205801527U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
| CN106864758A (en) * | 2017-03-02 | 2017-06-20 | 西安天问智能科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle engine damping of oil |
-
2016
- 2016-05-24 CN CN201620476183.9U patent/CN205801527U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
| CN106864758A (en) * | 2017-03-02 | 2017-06-20 | 西安天问智能科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle engine damping of oil |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180601 Address after: 100080 2106-030, 9 North Fourth Ring Road, Haidian District, Beijing. Co-patentee after: BEIJING GUOZHICHUANGTOU TECHNOLOGY CO., LTD. Patentee after: The fast online Science and Technology Ltd. in Beijing three Address before: 100191 Beijing Haidian District Haidian Avenue 3 1 1 10 story 1001-52 Co-patentee before: BEIJING GUOZHICHUANGTOU TECHNOLOGY CO., LTD. Patentee before: BEIJING HAOHENG JOURNEY AVIATION TECHNOLOGY CO., LTD. |