CN201891793U - Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body - Google Patents
Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body Download PDFInfo
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- CN201891793U CN201891793U CN2010205653336U CN201020565333U CN201891793U CN 201891793 U CN201891793 U CN 201891793U CN 2010205653336 U CN2010205653336 U CN 2010205653336U CN 201020565333 U CN201020565333 U CN 201020565333U CN 201891793 U CN201891793 U CN 201891793U
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- inertial mass
- damper
- leading screw
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- spring
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Abstract
The utility model relates to an anti-resonance vibration isolation device for an inertial mass energy storage type helicopter body, which relates to the technical field of vibration and control of helicopters. The anti-resonance vibration isolation device comprises a spring, a damper and an inertial mass energy storage which are mounted between a main speed reducer and the helicopter body in parallel, cyclic low-frequency exciting force generated by a rotor wing is buffered by the spring, vibration energy of the cyclic low-frequency exciting force is consumed by the damper and absorbed by the inertial mass energy storage in an anti-resonance manner, and transmission of a load of the rotor wing to the helicopter body is reduced by means of combining buffering vibration isolation, damping vibration reduction and power vibration absorption. The anti-resonance vibration isolation device is safe and reliable, is light in weight, small in volume, low in cost, convenient in installation and easy in maintenance, and avoids the problem of additional horizontal vibration.
Description
Technical field
The utility model relates to helicopter vibration control technique field, the isolation mounting between a kind of concretely helicopter main reducing gear and the fuselage.
Background technique
The vibration problem of helicopter is very outstanding in the aeronautical engineering field.These vibration problems make that the helicopter dynamics environment is more abominable, have caused that occupant and driver's riding comfort are poor, the component fatiguability damages, and influence the function of airborne equipment, reduces the reliability of helicopter component and equipment, the increase use and maintenance cost.Wherein the excitation force that causes of rotor alternation pneumatic environment is the main factor of decision helicopter vibration level, and reducing the rotor dynamic load also is the main target of helicopter vibration isolation to the transmission of fuselage.The power of disturbing of rotor is big, and excited frequency is low, and excitation force and moment exist simultaneously, and traditional isolation mounting of being made up of spring and damper is difficult to reduce the level of vibration in the middle of the helicopter flight.
For solve in the lifting airscrew system excited frequency low with the quiet distortion of vibrating isolation system this principal contradiction greatly, U.S. Pat 3322379 discloses a kind of power anti-resonance vibration isolator (DAVI, Dynamic Anti-vibration Isolator), this vibration isolator comprises spring, damper and lever quality system, the two ends of spring and damper are articulated in main reducing gear and fuselage respectively, an end of lever is horizontally hinged in main reducing gear by hinge in the lever quality system, the other end and mass block rigidity link, fuselage is articulated in the middle end away from mass block of lever by hinge, size by adjustment (adjusting) lever arm of force length and mass block, make the anti-resonance peak under the lever quality system generation characteristic frequency, this characteristic frequency is exactly an antiresonance frequency, vibration isolator has very high vibration isolation efficiency near antiresonance frequency, can cut down periodically rotor excitation force effectively, thereby reach the purpose that excludes the fuselage low-frequency vibration.Yet this vibration isolator has used lever quality system, and mass block can significantly be swung with lever and take big quantity space, difficult arrangement in vibration processes; In addition, in the vertical vibration of vibration isolation fuselage, but bring the standard of fuselage vibration problem.
U.S. Pat 5052510 discloses a kind of active vibration isolation device, this vibration isolator has replaced the lever quality in the above-mentioned patent to be with break, solved the problem of difficult arrangement with the horizontal vibration of bringing, but this patent is an ACTIVE CONTROL, needs the energy of input big, the cost height, reliability is low, can cause system's instability, need complicated control strategy and components and parts, can not exclude vibration when control system breaks down at all.
Summary of the invention
The purpose of this utility model is: solve in the lifting airscrew system periodic excitation frequency low with the quiet distortion of vibrating isolation system can not too big this principal contradiction, reduce of the transmission of rotor dynamic load, solve lever quality system is brought in the power anti-resonance vibration isolator (DAVI) the horizontal vibration and the technical problem of difficult arrangement simultaneously to fuselage.
The utility model solves this technical problem the technological scheme that is adopted: spring, damper and the parallel connection of inertial mass accumulator vertically are installed between main reducing gear and the fuselage, the periodicity low frequency excitation force that rotor produces is cushioned by spring, consume its vibrational energy by damping, absorb its vibrational energy by the inertial mass accumulator in the anti-resonance mode, binding buffer vibration isolation, damping vibration attenuation and three kinds of modes of dynamic absorber reduce the transmission of rotor load to fuselage; Described inertial mass accumulator adopts ball screw inertial mass accumulator, to solve lever quality system is brought in the power anti-resonance vibration isolator (DAVI) the horizontal vibration and the technical problem of difficult arrangement.
Concrete scheme of the present utility model is to comprise spring, damper and inertial mass accumulator.
Spring is a spiral compression spring, damper is the cylinder type hydraulic damper, spring housing is outside the urceolus of damper, spring is fixedlyed connected with damper is coaxial, one end of spring is fixedlyed connected with the piston rod of damper, the other end is fixedlyed connected with the urceolus of damper, and damper rod is articulated in main reducing gear by hinge, and the damper urceolus is articulated in fuselage by hinge.
The inertial mass accumulator is a ball screw inertial mass accumulator, comprises hanger A, stroke chamber, nut, leading screw, bellows, leading screw supporting base, flywheel, flywheel chamber and hanger B.Leading screw comprises polished rod part and screw thread raceway part; Flywheel and the coaxial polished rod part that is fixed in leading screw of screw mandrel; In the leading screw supporting base bearing is installed, bearing outer ring cooperates with the endoporus of leading screw supporting base, bearing inner race partly cooperates with the polished rod of leading screw near raceway one side, and when rotating with respect to the leading screw supporting base with the assurance leading screw, the leading screw supporting base is axially remaining unchanged with the position that directly makes progress to leading screw; Nut is meshed with the screw thread raceway on the leading screw; The stroke chamber is the long tubular of an end opening one end sealing, and opening end is fixedly set on the cylindrical of nut, and coaxial with nut to guarantee the stroke chamber, closed end links to each other with the screw portion of hanger A; The flywheel chamber also is the long tubular of an end opening one end sealing, and opening end is fixedly set on the cylindrical of leading screw supporting base, and coaxial with the leading screw supporting base to guarantee the flywheel chamber, closed end links to each other with the screw portion of hanger B; Bellows is the organ-shaped dust-proof cover, and an end is set in the outdoor tube of stroke, and the other end is set in the outdoor tube of flywheel; The screw portion of hanger A and hanger B, respectively with stroke chamber and flywheel chamber closed end center hole on screw thread screw mutually, to guarantee that two hanger central points are on the leading screw axis.The inertial mass accumulator vertically is installed between fuselage and the main reducing gear, and hanger A and fuselage are hinged, and hanger B and main reducing gear are hinged.
Compare with power anti-resonance vibration isolator (DAVI), the utlity model has following advantage: 1, eliminated owing to the existence of mass lever system with the horizontal vibration problem; Occupation space was little when 2, the inertial mass accumulator was worked, and was easy to arrange; 3, safe and reliable, in light weight, volume is little, cost is low, easy accessibility, be easy to safeguard.
Description of drawings
Fig. 1 is an inertial mass energy-storage type helicopter anti-resonance vibration isolating device structural representation.
Fig. 2 is a ball screw inertial mass accumulator structure schematic representation.
Fig. 3 is a ball screw inertial mass accumulator outline drawing.
Fig. 4 is a ball screw inertial mass accumulator structure exploded view.
Among the figure, 1-main reducing gear 2-spring 3-damper 4-inertial mass accumulator 5-fuselage 6-hanger A 7-stroke chamber 8-nut 9-leading screw 10-bellows 11-leading screw supporting base 12-flywheel 13-flywheel chamber 14-hanger B.
Embodiment
The utility model is described in further detail below in conjunction with drawings and Examples.
The utility model comprises spring 2, damper 3 and inertial mass accumulator 4, spring 2 is a spiral compression spring, damper 3 is the cylinder type hydraulic damper, and inertial mass accumulator 4 is a ball screw inertial mass accumulator, and the three vertically is installed in parallel between main reducing gear 1 and fuselage 5.
Below in conjunction with accompanying drawing the utility model specific implementation process is described further.
As shown in Figure 1, in the course of the work, the periodicity low frequency excitation force that rotor produces is cushioned by spring 2, consume its vibrational energy by damper 3, absorb its vibrational energy by inertial mass accumulator 4 in the anti-resonance mode, binding buffer vibration isolation, damping vibration attenuation and three kinds of modes of dynamic absorber reduce the transmission of rotor load to fuselage.
Shown in Fig. 2 and 4, inertial mass accumulator 4 is the input endpoint with hanger A6 and hanger B14 in the course of the work, when waiting big reverse power
fWhen being applied on two end points, hanger A6 does straight line motion with respect to hanger B14, by nut 8 and leading screw 9 straight line motion is transformed rotatablely moving of leading screw 9, and then drive flywheel 12 and rotate, thereby make inertial mass accumulator 4 show the attribute of mass elements.
The kinetic equations of inertial mass accumulator is
f=
Ba, wherein
f,
aWith
bExpression is applied to the power on the two-end-point, the relative acceleration and the inertial mass coefficient of two-end-point respectively, and the inertial mass coefficient can be calculated by the pitch of leading screw 9 and the rotary inertia of flywheel 12.If the pitch of leading screw 9
P, the rotary inertia of flywheel 12
ICan derive following relation by Newton's second law:
According to following formula, the pitch of change leading screw and the rotary inertia of flywheel just can obtain having the ball screw inertial mass accumulator of suitable inertial mass coefficient.
Shown in Fig. 2 and 3, the center of hanger A6 and hanger B14 is all on the axis of leading screw 9, they do linear relative movement along this knot, and this axis also direction with the fuselage vertical vibration is consistent, therefore in the vertical vibration of vibration isolation fuselage, the utility model eliminated since the existence that mass lever is with the horizontal vibration problem.In addition, clearly the inertial mass accumulator also has occupation space little, the advantage that is easy to arrange.
The utility model does not need complicated controller, control strategy and electronic parts and components, does not need the energy input, and is safe and reliable, in light weight, volume is little, cost is low, easy accessibility, be easy to safeguard.
Claims (4)
1. inertial mass energy-storage type helicopter anti-resonance vibration isolating device, it is characterized in that, comprise spring (2), damper (3) and inertial mass accumulator (4), described spring (2) is a spiral compression spring, described damper (3) is the cylinder type hydraulic damper, described inertial mass accumulator (4) is a ball screw inertial mass accumulator, and spring (2), damper (3) and inertial mass accumulator (4) three vertically are installed in parallel between main reducing gear (1) and fuselage (5).
2. inertial mass energy-storage type helicopter anti-resonance vibration isolating device according to claim 1, it is characterized in that, described spring (2) is enclosed within outside the urceolus of damper (3), described spring (2) and coaxial the fixedlying connected of damper (3), one end of described spring (2) is fixedlyed connected with the piston rod of damper (3), the other end of described spring (2) is fixedlyed connected with the urceolus of damper (3), the piston rod of described damper (3) is articulated in main reducing gear (1) by hinge, and the urceolus of damper (3) is articulated in fuselage (5) by hinge.
3. inertial mass energy-storage type helicopter anti-resonance vibration isolating device according to claim 1, it is characterized in that, described inertial mass accumulator (4) vertically is installed between fuselage (5) and the main reducing gear (1), the hanger A(6 of fuselage (5) and inertial mass accumulator (4)) hinged, the hanger B(14 of main reducing gear (1) and inertial mass accumulator (4)) hinged.
4. according to claim 1,2 or 3 described inertial mass energy-storage type helicopter anti-resonance vibration isolating devices, it is characterized in that, described inertial mass accumulator (4) comprises hanger A(6), stroke chamber (7), nut (8), leading screw (9), bellows (10), leading screw supporting base (11), flywheel (12), flywheel chamber (13) and hanger B(14); Described leading screw (9) comprises polished rod part and screw thread raceway part; Described flywheel (12) and the coaxial polished rod part that is fixed in leading screw (9) of screw mandrel (9); In the described leading screw supporting base (11) bearing is installed, bearing outer ring cooperates with the endoporus of leading screw supporting base (11), and bearing inner race partly cooperates with the polished rod of leading screw (9) near raceway one side; Screw thread raceway on the same leading screw of described nut (8) (9) is meshed; Described stroke chamber (7) is the long tubular of an end opening one end sealing, and the opening end of described stroke chamber (7) is fixedly set on the cylindrical of nut (8), the closed end of described stroke chamber (7) and hanger A(6) screw portion link to each other; Described flywheel chamber (13) is the long tubular of an end opening one end sealing, and the opening end of described flywheel chamber (13) is fixedly set on the cylindrical of leading screw supporting base (11), the closed end of described flywheel chamber (13) and hanger B(14) screw portion link to each other; Described bellows (10) is the organ-shaped dust-proof cover, and an end of described bellows (10) is set in stroke chamber (7) urceolus, and the other end of described bellows (10) is set in flywheel chamber (13) urceolus; Described hanger A(6) and hanger B(14) screw portion, respectively with stroke chamber (7) and flywheel chamber (13) closed end center hole on screw thread screw mutually.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205653336U CN201891793U (en) | 2010-10-19 | 2010-10-19 | Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205653336U CN201891793U (en) | 2010-10-19 | 2010-10-19 | Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body |
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| CN2010205653336U Expired - Fee Related CN201891793U (en) | 2010-10-19 | 2010-10-19 | Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body |
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Cited By (14)
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| WO2013071667A1 (en) * | 2011-11-15 | 2013-05-23 | 江苏大学 | Passive ceiling and floor damping and vibration isolation system |
| CN103953612A (en) * | 2014-05-22 | 2014-07-30 | 沈阳东北电力调节技术有限公司 | Dust cover for piston rod of oil cylinder in hydraulic loading system of vertical mill |
| CN105232244A (en) * | 2015-09-21 | 2016-01-13 | 中国人民解放军军事医学科学院卫生装备研究所 | Novel stretcher table for use in ambulance |
| CN105782342A (en) * | 2016-04-27 | 2016-07-20 | 江苏科技大学 | Ball screw type inerter with adjustable inerter value |
| CN107399427A (en) * | 2016-05-19 | 2017-11-28 | 波音公司 | Container and method are used in rotation for damped actuator |
| CN107654566A (en) * | 2017-08-07 | 2018-02-02 | 上海交通大学 | The liquid bullet formula isolation mounting of Parameter adjustable |
| CN109765022A (en) * | 2019-01-16 | 2019-05-17 | 南京航空航天大学 | A kind of Helicopter Main Reducer vibrating isolation system experimental rig |
| CN110259881A (en) * | 2019-06-17 | 2019-09-20 | 石家庄铁道大学 | A kind of dynamic vibration absorber |
| CN110608258A (en) * | 2019-09-23 | 2019-12-24 | 中北大学 | Helicopter main-reduction and semi-driving hydraulic vibration isolator |
| RU2725826C2 (en) * | 2018-12-25 | 2020-07-06 | Закрытое акционерное общество Научно-исследовательский центр "Резонанс" | Device for damping mechanical vibrations of elements of antenna systems made in form of cantilever beam |
| CN111486189A (en) * | 2020-04-16 | 2020-08-04 | 北京空间飞行器总体设计部 | Reusable small celestial body surface attachment buffer mechanism |
| CN112855824A (en) * | 2021-03-11 | 2021-05-28 | 中国北方车辆研究所 | Inertial volume type vibration isolation device aiming at simple harmonic displacement excitation and design method |
| CN113738813A (en) * | 2021-11-03 | 2021-12-03 | 杭州斯诺康技术有限公司 | Spring buffer type new energy automobile damping device |
| CN113955130A (en) * | 2021-11-19 | 2022-01-21 | 中国直升机设计研究所 | Double-frequency adjustable vibration isolation device for helicopter main reducer |
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2010
- 2010-10-19 CN CN2010205653336U patent/CN201891793U/en not_active Expired - Fee Related
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| US9074652B2 (en) | 2011-11-15 | 2015-07-07 | Jiangsu University | Passive skyhook and groundhook damping vibration isolation system |
| WO2013071667A1 (en) * | 2011-11-15 | 2013-05-23 | 江苏大学 | Passive ceiling and floor damping and vibration isolation system |
| CN103953612A (en) * | 2014-05-22 | 2014-07-30 | 沈阳东北电力调节技术有限公司 | Dust cover for piston rod of oil cylinder in hydraulic loading system of vertical mill |
| CN105232244A (en) * | 2015-09-21 | 2016-01-13 | 中国人民解放军军事医学科学院卫生装备研究所 | Novel stretcher table for use in ambulance |
| CN105782342A (en) * | 2016-04-27 | 2016-07-20 | 江苏科技大学 | Ball screw type inerter with adjustable inerter value |
| CN107399427A (en) * | 2016-05-19 | 2017-11-28 | 波音公司 | Container and method are used in rotation for damped actuator |
| CN107654566A (en) * | 2017-08-07 | 2018-02-02 | 上海交通大学 | The liquid bullet formula isolation mounting of Parameter adjustable |
| CN107654566B (en) * | 2017-08-07 | 2019-10-08 | 上海交通大学 | The liquid bullet formula isolation mounting of Parameter adjustable |
| RU2725826C2 (en) * | 2018-12-25 | 2020-07-06 | Закрытое акционерное общество Научно-исследовательский центр "Резонанс" | Device for damping mechanical vibrations of elements of antenna systems made in form of cantilever beam |
| CN109765022A (en) * | 2019-01-16 | 2019-05-17 | 南京航空航天大学 | A kind of Helicopter Main Reducer vibrating isolation system experimental rig |
| CN109765022B (en) * | 2019-01-16 | 2024-04-16 | 南京航空航天大学 | Helicopter main reducer vibration isolation system test device |
| CN110259881A (en) * | 2019-06-17 | 2019-09-20 | 石家庄铁道大学 | A kind of dynamic vibration absorber |
| CN110608258A (en) * | 2019-09-23 | 2019-12-24 | 中北大学 | Helicopter main-reduction and semi-driving hydraulic vibration isolator |
| CN111486189A (en) * | 2020-04-16 | 2020-08-04 | 北京空间飞行器总体设计部 | Reusable small celestial body surface attachment buffer mechanism |
| CN111486189B (en) * | 2020-04-16 | 2021-07-13 | 北京空间飞行器总体设计部 | Reusable small celestial body surface attachment buffer mechanism |
| CN112855824A (en) * | 2021-03-11 | 2021-05-28 | 中国北方车辆研究所 | Inertial volume type vibration isolation device aiming at simple harmonic displacement excitation and design method |
| CN113738813A (en) * | 2021-11-03 | 2021-12-03 | 杭州斯诺康技术有限公司 | Spring buffer type new energy automobile damping device |
| CN113955130A (en) * | 2021-11-19 | 2022-01-21 | 中国直升机设计研究所 | Double-frequency adjustable vibration isolation device for helicopter main reducer |
| CN113955130B (en) * | 2021-11-19 | 2023-10-27 | 中国直升机设计研究所 | Dual-frenquency adjustable helicopter main reducer vibration isolator |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110706 Termination date: 20141019 |
|
| EXPY | Termination of patent right or utility model |