CN105691607A - Single-direction shock absorption device for motor of multi-rotor aircraft - Google Patents
Single-direction shock absorption device for motor of multi-rotor aircraft Download PDFInfo
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- CN105691607A CN105691607A CN201510669852.4A CN201510669852A CN105691607A CN 105691607 A CN105691607 A CN 105691607A CN 201510669852 A CN201510669852 A CN 201510669852A CN 105691607 A CN105691607 A CN 105691607A
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- motor
- rotor aerocraft
- fixed
- damping device
- firm banking
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Abstract
The invention provides a single-direction shock absorption device for a motor of a multi-rotor aircraft. The single-direction shock absorption device comprises a fixed base, a suspension base and at least one connecting piece. The motor is fixed to the suspension base. One end of each connecting piece is fixed to the lower end of the suspension base, and the other end of each connecting piece is fixed to the fixed base. The fixed base is fixed to a body of the multi-rotor aircraft. The single-direction shock absorption device has the advantages that through design of the connecting pieces, the purposes of high rigidity in the direction of lifting power but low rigidity in other shock directions are achieved; and accordingly the lifting power is effectively utilized, shock is effectively isolated, the loading capacity and the cruising ability of the aircraft are improved, and the posture control effect and the loaded travelling effect of the aircraft are also improved.
Description
Technical field
The present invention relates to a kind of electric product damping device, particularly to a kind of unidirectional damping device of multi-rotor aerocraft motor。
Background technology
Along with the rise of automatic control technology, the application of multi-rotor aerocraft is more and more extensive。Multi-rotor aerocraft directly or indirectly drives rotor high-speed rotary then produces lift with motor, but simultaneously also due to the unequal reason of Mass Distribution and shake。If the coupling stiffness between multi-rotor aerocraft and motor is not enough, the utilization of motor lift will be affected, causing that gesture stability response is slow, but rigidity is crossed and can be caused again that by force vibrations directly affect attitude transducer and load, impact flight controls the operational effect with load equipment。
Summary of the invention
A kind of unidirectional damping device of multi-rotor aerocraft motor of the offer of the present invention, solves to improve lift in electric motor mounting structure design and utilizes and reduce the vibrations transmission contradiction for rigidity of structure demand, to overcome the defect of above-mentioned prior art。
The present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, including firm banking, suspension base and at least one connection sheet；Motor is fixed on suspension base；Connecting sheet one end and be fixed on the lower end of suspension base, the other end is fixed on firm banking；Firm banking is fixed on the fuselage of multi-rotor aerocraft。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that firm banking includes fixing body and extends chassis；Extend chassis in the side of fixing body。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that the quantity connecting sheet is more than 2。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that connecting sheet, firm banking and suspension base forms the tetragon closed。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that tetragon is rectangle。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that tetragon is trapezoidal。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that on firm banking fixed installation base or on horn。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that suspension base, connect between sheet and firm banking fixing adopt threaded, snap connection, any one or a few mode in bonding or welding。
Further, the present invention provides a kind of unidirectional damping device of multi-rotor aerocraft motor, it is also possible to have a feature in that the thickness connecting sheet is 0.01mm-20mm。
The beneficial effect of the invention
A kind of unidirectional damping device of multi-rotor aerocraft motor provided by the invention, can pass through to connect the design of sheet, realize lift direction high rigidity, other vibrations direction Low rigidity, thus realizing effectively utilizing of lift and effectively completely cutting off of vibrations, promote load capacity and the flying power of aircraft, promote aircraft manufacturing technology effect and load running effect simultaneously。
Accompanying drawing explanation
Fig. 1 is the structure chart of the unidirectional damping device of multi-rotor aerocraft motor of embodiment one。
Fig. 2 is the structure chart of the unidirectional damping device of multi-rotor aerocraft motor of embodiment two。
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention will be further described。
Embodiment one
Fig. 1 is the structure chart of the unidirectional damping device of multi-rotor aerocraft motor of embodiment one。
As it is shown in figure 1, the unidirectional damping device of multi-rotor aerocraft motor includes: firm banking 110, two connects sheet 120 and suspension base 130。
Firm banking 110 includes the fixing body 110-1 of rectangle and extends chassis 110-2。Fixing body 110-1 is hollow structure, the overall weight of alleviator。Fixing body 110-1 is fixed on the fuselage of multi-rotor aerocraft, it is possible to be fixed in the mounting seat of multi-rotor aerocraft electricity motor or with multi-rotor aerocraft horn integrator。Extending chassis 110-2 is flat structure, in the side of fixing body 110-1；And fixing body 110-1 and extend the bottom surface of chassis 110-2 in one plane。
Connecting sheet 120 one end and be fixed on the lower end of suspension base 110, the other end is fixed on the extension chassis 110-2 of firm banking。Two connect sheet 120 and are separately fixed at the two ends of suspension base 110。Connect sheet 120, the extension chassis 110-2 of firm banking and suspension base 130 and become four limits, form close trapezoidal。Connect the rustless steel that sheet 120 is thickness 0.05-0.1mm。
Motor 50 is fixed on suspension base 130。
Motor, suspension base, connect and bolt hole, installing hole, post or buckle can be adopted to be fixed between sheet and firm banking；Bonding or welding mode can certainly be adopted to fix。
Embodiment two
Fig. 2 is the structure chart of the unidirectional damping device of multi-rotor aerocraft motor of embodiment two。
As in figure 2 it is shown, the unidirectional damping device of multi-rotor aerocraft motor includes: firm banking 210, two connects sheet 220 and suspension base 230。
Firm banking 210 includes the fixing body 210-1 of rectangle and extends chassis 210-2。Fixing body 210-1 is hollow structure, the overall weight of alleviator。Fixing body 210-1 is fixed on the fuselage of multi-rotor aerocraft, it is possible to be fixed in the mounting seat of multi-rotor aerocraft electricity motor or with multi-rotor aerocraft horn integrator。Extending chassis 210-2 is flat structure, in the side of fixing body 210-1；And fixing body 210-1 and extend the bottom surface of chassis 210-2 in one plane。
Connecting sheet 220 one end and be fixed on the lower end of suspension base 210, the other end is fixed on the extension chassis 210-2 of firm banking。Two connect sheet 220 and are separately fixed at the two ends of suspension base 210。Connect sheet 220, the extension chassis 210-2 of firm banking and suspension base 230 and become four limits, form the rectangle closed。Connect the rustless steel that sheet is thickness 0.15-0.2mm。
Motor 50 is fixed on suspension base 230。
Suspension base, connect and bolt hole, installing hole, post or buckle can be adopted to be fixed between sheet and firm banking；Bonding or welding mode can certainly be adopted to fix。
Connect sheet and can need to arrange quantity according to design, minimum can arrange by monolithic, naturally it is also possible to greater number is set between firm banking and suspension base。Furthermore it is also possible to by changing the thickness connecting sheet, select within the scope of 0.01mm-20mm, thus controlling fluctuation size；The rigidity connecting sheet of unlike material is different, it is also possible to select as required。
In motor operation course, owing to rotor is eccentric with the Mass Distribution of rotor, radially vibrations and amplitude of fluctuation are bigger；Motor driving is generally adopted the output of pulse width modulation square wave and is controlled, and the fluctuating margin of its torque output is also bigger；Motor drive lift produced by rotor along motor output shaft to, the fluctuation of this lift is less。Therefore, the know-why of the present invention is through the quantity connecting sheet, position, direction, the appropriate design of material etc., improve the rigidity on lift direction, utilize lift produced by motor as much as possible, to strengthen load capacity and flying power, reduce the rigidity in a direction simultaneously, reduce the transmission of motor vibrations as much as possible, to avoid the negative effect to attitude sensing and load, make all to have in different directions between suspension base and firm banking suitable rigidity, thus solving the contradiction that said structure stiffness selects, can be widely used for multiple different motor configuration。
Claims (9)
1. the unidirectional damping device of multi-rotor aerocraft motor, it is characterised in that: include firm banking, suspension base and at least one connection sheet；
Wherein, motor is fixed on described suspension base；
Described connection sheet one end is fixed on the lower end of described suspension base, and the other end is fixed on described firm banking；
Described firm banking is fixed on the fuselage of multi-rotor aerocraft。
2. the unidirectional damping device of multi-rotor aerocraft motor as claimed in claim 1, it is characterised in that:
Wherein, described firm banking includes fixing body and extends chassis；Described extension chassis is in the side of described fixing body。
3. the unidirectional damping device of multi-rotor aerocraft motor as claimed in claim 1, it is characterised in that:
Wherein, the quantity of described connection sheet is more than 2。
4. the unidirectional damping device of multi-rotor aerocraft motor as claimed in claim 1, it is characterised in that:
Wherein, described connection sheet, described firm banking and described suspension base form the tetragon closed。
5. the unidirectional damping device of multi-rotor aerocraft motor as claimed in claim 4, it is characterised in that:
Wherein, described tetragon is rectangle。
6. the unidirectional damping device of multi-rotor aerocraft motor as claimed in claim 4, it is characterised in that:
Wherein, described tetragon is trapezoidal。
7. the unidirectional damping device of multi-rotor aerocraft motor as described in any one in claim 1 to 6, it is characterised in that:
Wherein, on described firm banking fixed installation base or on horn。
8. such as the unidirectional damping device of any one multi-rotor aerocraft motor in claim 1 to 6, it is characterised in that:
Wherein, described suspension base, between described connection sheet and described firm banking fixing adopt threaded, snap connection, any one or a few mode in bonding or welding。
9. such as the unidirectional damping device of any one multi-rotor aerocraft motor in claim 1 to 6, it is characterised in that:
Wherein, the thickness of described connection sheet is 0.01mm-20mm。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510669852.4A CN105691607A (en) | 2015-10-13 | 2015-10-13 | Single-direction shock absorption device for motor of multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510669852.4A CN105691607A (en) | 2015-10-13 | 2015-10-13 | Single-direction shock absorption device for motor of multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105691607A true CN105691607A (en) | 2016-06-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510669852.4A Pending CN105691607A (en) | 2015-10-13 | 2015-10-13 | Single-direction shock absorption device for motor of multi-rotor aircraft |
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| Country | Link |
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| CN (1) | CN105691607A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691622A (en) * | 2015-10-13 | 2016-06-22 | 中科新松有限公司 | Suspension shock absorption device for motor of multi-rotor aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6065718A (en) * | 1998-03-23 | 2000-05-23 | Piasecki; Michael W. | Universal VTOL power and rotor system module |
| US6098921A (en) * | 1999-05-06 | 2000-08-08 | Piasecki Aircraft Corp. | Rotary wing aircraft supplementary power drive system |
| CN102267569A (en) * | 2011-05-10 | 2011-12-07 | 北京航空航天大学 | Suspended engine connecting device for small-size unmanned helicopter |
| CN203996885U (en) * | 2014-06-03 | 2014-12-10 | 王雪阳 | Combustion engine powered multirotor helicopter |
| CN104925250A (en) * | 2015-07-04 | 2015-09-23 | 苏州科锐恒机械科技有限公司 | Multi-rotor craft |
-
2015
- 2015-10-13 CN CN201510669852.4A patent/CN105691607A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6065718A (en) * | 1998-03-23 | 2000-05-23 | Piasecki; Michael W. | Universal VTOL power and rotor system module |
| US6098921A (en) * | 1999-05-06 | 2000-08-08 | Piasecki Aircraft Corp. | Rotary wing aircraft supplementary power drive system |
| CN102267569A (en) * | 2011-05-10 | 2011-12-07 | 北京航空航天大学 | Suspended engine connecting device for small-size unmanned helicopter |
| CN203996885U (en) * | 2014-06-03 | 2014-12-10 | 王雪阳 | Combustion engine powered multirotor helicopter |
| CN104925250A (en) * | 2015-07-04 | 2015-09-23 | 苏州科锐恒机械科技有限公司 | Multi-rotor craft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691622A (en) * | 2015-10-13 | 2016-06-22 | 中科新松有限公司 | Suspension shock absorption device for motor of multi-rotor aircraft |
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Application publication date: 20160622 |
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