CN205801506U - The center frame of multi-rotor aerocraft - Google Patents
The center frame of multi-rotor aerocraft Download PDFInfo
- Publication number
- CN205801506U CN205801506U CN201620476182.4U CN201620476182U CN205801506U CN 205801506 U CN205801506 U CN 205801506U CN 201620476182 U CN201620476182 U CN 201620476182U CN 205801506 U CN205801506 U CN 205801506U
- Authority
- CN
- China
- Prior art keywords
- frame
- engine
- vibration
- central plate
- center
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Vibration Prevention Devices (AREA)
Abstract
In aviation piston engine is applied to the practice of many rotor wing unmanned aerial vehicles, engine is as one of main vibration source of body, and be the energy source of remaining vibration source, under running power in difference, engine has different frequency of vibration, take rigidly connected engine easily causing the resonance of other vibration sources with body, the most then affect flight stability, heavy then destroy housing construction.For oil moves many rotor wing unmanned aerial vehicles, it is necessary to cut off the vibration of engine, thus ensure the stable and reliable of unmanned plane structure.The utility model discloses the center frame of a kind of multi-rotor aerocraft, including the upper and lower two blocks frame central plates be arrangeding in parallel, wherein, described frame central plate is provided with vibration damping hole at the position being connected with rotor support arm, and described vibration damping hole shape is circular, reduce cantilever beam frame junction rigidity, reduce cantilever beam frame junction power transmission area, thus realize the purpose of vibration damping.
Description
Technical field
This utility model belongs to technical field of aerospace, is specifically related to a kind of oil and moves the center frame of multi-rotor aerocraft.
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 rotation
Rotation mechanism, vibration source and Vibration Condition are more complicated, more sensitive to engine vibration.Requirement for engine vibration damping is also different because of structure
And present requirement different with fixed-wing.In aviation piston engine is applied to the practice of many rotor wing unmanned aerial vehicles, engine is made
For one of vibration source that body is main, and being the energy source of remaining vibration source, under running power in difference, engine has not
With frequency of vibration, and body take rigidly connected engine easily cause other vibration sources resonance, the most then affect flight
Stable, heavy then destroy housing construction.For oil moves many rotor wing unmanned aerial vehicles, it is necessary to cut off the vibration of engine, thus ensure nothing
Stablizing and reliable of man-machine structure.
Summary of the invention
The purpose of this utility model is to provide the center frame of a kind of multi-rotor aerocraft, it is possible to effectively solve shaking of engine
Dynamic problem.
The technical solution of the utility model is: the center frame of a kind of multi-rotor aerocraft, parallel sets including upper and lower two pieces
The frame central plate put, described frame central plate is square, and square corner stretches out, and forms the connection with rotor support arm
Portion, described vibration damping hole is arranged on this connecting portion, is provided with pipe between up/down frame central plate and the connecting portion of rotor support arm
Folder, is used for connecting rotor support arm.Wherein, described frame central plate is provided with vibration damping hole at the position being connected with rotor support arm, and
Described vibration damping hole shape is circular.
Rotor support arm is owing to being cantilever beam, and the impact of vibrated problem is the most prominent.Use technical side of the present utility model
Case, reduces the propagation vibrated to rotor support arm, is the means of a kind of effective solution engine vibration problem.
Further, the lower section of described lower bearing bracket central plate arranges engine mount, and its lower end is provided with and is connected with engine
Damping block, has installation clutch and the space of synchronous belt drive mechanism in described engine mount.
Use the technical solution of the utility model, can effectively solve the vibration problem of engine.Wherein, frame central plate exists
It is provided with vibration damping hole with the connecting portion of rotor support arm, reduces the propagation vibrated to horn；The suspension installation of engine optimizes whole
Machine structure, beneficially vibration damping；Damping block can filter engine dither.
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.
The relative position relation of engine 1 and frame and internal drive system thereof, as shown in accompanying drawing 1, accompanying drawing 2, opens with electricity
The engine 1 of dynamic device 3 and exhaustor 2 is connected with engine mount 6, and the two junction is provided with damping block 4 for slowing down
Engine 1 vibrates the conduction to rack construction.Engine mount 6 is fixed on below frame central plate, it is characterized in that, makes whole
The mounting means of engine 1 power plant module is suspension, suspension mounting means utilize the gravity of engine 1 self to realize engine and
Flexibly connecting of engine mount 6.
Engine 1 output shaft is mounted with clutch 5, and clutch 5 output shaft is provided with driving synchronous pulley 81,
It is characterized in that, drive synchronous pulley 81 by Timing Belt 7 and the driven synchronous pulley being arranged on belt wheel installing rack 9
82 connect, and are for primary transmission system, utilize Timing Belt 7 to realize engine 1 clutch end and input with drive train power
Flexibly connecting of end, plays the effect of slowing down vibration conduction equally.
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, is for secondary driving system, it is characterized in that, 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.
Vibration damping hole 13 is the vibration damping key Design in rack construction, and its position is positioned at rotor support arm 15 and frame central
The junction of plate 14, on the one hand plays the effect of loss of weight, on the one hand cuts down vibration from frame central plate 14 to rotor support arm
The conducting path of 15, slows down the vibration of horn, it is characterised in that use circular port to carry out the borderline stress distribution of uniform bore, directly
Footpath is less than 0.7 times of frame central plate 14 terminal end width, upper and lower frame central plate 14 and rotor support arm 15 junction
Two vibration dampings are respectively set and subtract 13, four rotor support arm about 15 frame central plates 14 arrange 16 vibration damping holes 13 altogether
.In addition, frame central plate is additionally provided with lightening hole, and the shape of described lightening hole includes circle, triangle and/or polygon
Shape.Described lightening hole is crisscross arranged according to difformity.After vibration damping is transformed, decreased by means such as suspending, flexibly connect
Vibration source engine 1 transmits to the vibration of rack construction, is reduced the transmission vibrated to rotor support arm by vibration damping hole, significantly subtracts
The little amplitude of frame vibration, under the high rotating speed of engine 1, 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 (9)
1. a center frame for multi-rotor aerocraft, including the upper spider central plate be arrangeding in parallel and lower bearing bracket central plate, its
Being characterised by, described frame central plate is provided with vibration damping hole at the position being connected with rotor support arm, and described vibration damping hole shape is
Circular.
2. center as claimed in claim 1 frame, it is characterised in that described frame central plate is additionally provided with lightening hole.
3. center as claimed in claim 2 frame, it is characterised in that the shape of described lightening hole includes circle or polygon.
4. center as claimed in claim 3 frame, it is characterised in that described lightening hole is crisscross arranged according to difformity.
5. the center frame as described in any one of claim 1-4, it is characterised in that described frame central plate is square, square
Corner stretch out, formed and the connecting portion of rotor support arm, described vibration damping hole is arranged on this connecting portion.
6. center as claimed in claim 5 frame, it is characterised in that described vibration damping bore dia is less than described connecting portion width
0.7 times, up/down frame central plate and each rotor support arm junction respectively arrange two vibration damping holes.
7. center as claimed in claim 5 frame, it is characterised in that up/down frame central plate and the connecting portion of rotor support arm
Between be provided with pipe clamp, be used for connecting rotor support arm.
8. the center frame as described in any one of claim 1-4, it is characterised in that the lower section of described lower bearing bracket central plate is arranged
Engine mount, its lower end is provided with the damping block being connected with engine.
9. center as claimed in claim 8 frame, it is characterised in that have in described engine mount installation clutch and with
The space of step tape handler.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476182.4U CN205801506U (en) | 2016-05-24 | 2016-05-24 | The center frame of multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476182.4U CN205801506U (en) | 2016-05-24 | 2016-05-24 | The center frame of multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205801506U true CN205801506U (en) | 2016-12-14 |
Family
ID=57500143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620476182.4U Active CN205801506U (en) | 2016-05-24 | 2016-05-24 | The center frame of multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205801506U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112326122A (en) * | 2020-09-25 | 2021-02-05 | 中国航空工业集团公司上海航空测控技术研究所 | Coaxial forward and reverse rotation dual-rotor balance adjustment method |
-
2016
- 2016-05-24 CN CN201620476182.4U patent/CN205801506U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112326122A (en) * | 2020-09-25 | 2021-02-05 | 中国航空工业集团公司上海航空测控技术研究所 | Coaxial forward and reverse rotation dual-rotor balance adjustment method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10364865B2 (en) | Circular force generator (CFG) devices, systems, and methods having indirectly driven imbalanced rotors | |
| CN105882984A (en) | Oil-drive multi-rotor aircraft | |
| CN102102733B (en) | Vibration damping mechanism and aircraft | |
| CN101871499B (en) | Piezoelectric liquid inertia vibration eliminator | |
| CN105243172B (en) | A kind of Engine Mounting System optimization method considering dynamic rate and dynamic antivibration | |
| CN103917447A (en) | A system and method for reducing the transmission of vibration from a first vibrating body to a second body | |
| CN207072248U (en) | A kind of robot chassis | |
| CN203758713U (en) | Vibration testing stand and amplitude adding mechanism thereof | |
| CN205801527U (en) | The dynamic multi-rotor aerocraft of a kind of oil | |
| CN105276076B (en) | A kind of novel high-precision hybrid vibration isolation device | |
| CN205801506U (en) | The center frame of multi-rotor aerocraft | |
| CN105547628A (en) | Vibration reaction force active balancing device for vibration-acceleration test device | |
| Newland | Developments in the Design of Centrifugal Pendulum Vibration Absorbers. | |
| WO2007001371A3 (en) | Vibration isolation engine mount system and method for ducted fan aircraft | |
| JP2014521035A5 (en) | ||
| KR101089557B1 (en) | Vibration exciter for vibration compensation | |
| CN110884682A (en) | Ground test system for actively controlling multidirectional vibration reduction efficiency by helicopter vibration | |
| CN203753399U (en) | Vertically take-off and landing unmanned aerial vehicle | |
| EP3712062B1 (en) | Vibration attenuation system for electric and hybrid electric vehicles | |
| GB1471956A (en) | Rotorcraft and a suspension device for the main rotor thereof | |
| CN108357685B (en) | Power system and unmanned helicopter | |
| CN103969051A (en) | Diesel testbed of modular structure | |
| CA2496755A1 (en) | Torsionally de-coupled engine mount system | |
| CN111946770A (en) | Combined type vibration damper and unmanned aerial vehicle | |
| CN207799370U (en) | A kind of armed helicopter boiler-plate vibrating device |
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: 20180528 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. |