CN101508342A - Opposite spin coaxial twin-rotor helicopter main retarder - Google Patents

Opposite spin coaxial twin-rotor helicopter main retarder Download PDF

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Publication number
CN101508342A
CN101508342A CNA2008101090851A CN200810109085A CN101508342A CN 101508342 A CN101508342 A CN 101508342A CN A2008101090851 A CNA2008101090851 A CN A2008101090851A CN 200810109085 A CN200810109085 A CN 200810109085A CN 101508342 A CN101508342 A CN 101508342A
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CN
China
Prior art keywords
gear
rotor
internally toothed
wheel shaft
toothed annulus
Prior art date
Application number
CNA2008101090851A
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Chinese (zh)
Inventor
梅振兴
Original Assignee
梅振兴
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority to CN200720152442 priority Critical
Priority to CN200720152442.3 priority
Application filed by 梅振兴 filed Critical 梅振兴
Priority to CNA2008101090851A priority patent/CN101508342A/en
Publication of CN101508342A publication Critical patent/CN101508342A/en

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Abstract

The invention relates to a dual-rotor helicopter main speed reducer capable of generating running in mutually contrary directions on the same shaft, wherein a sun gear shaft drives a planet gear shaft to perform planet running in a fixed ring gear, including rotation and revolution. When the tooth number of an external rotor ring gear is more than that of the fixed ring gear, the main speed reducer performs speed-reducing running in a mode of tooth number difference, and the running direction is pathwise; and in a similar way, when the tooth number of an internal rotor ring gear is less than that of the fixed ring gear, the running direction is antidromic when the main speed reducer performs the speed-reducing running in the mode of the tooth number difference. The upper end and the lower end of a central upright post are provided with a suspension ring respectively, thus on a vertical plane, a plurality of airplanes can perform series operations to hoist military establishments such as various tanks, armored cars, and the like at the moment of truth of a war to cross lofty mountains and steep hills, great rivers, lakes and the sea so as to win the war.

Description

The coaxial twin-rotor helicopter main retarder of opposite spin
Affiliated technical field
The present invention relates to a kind of new helicopter main reduction gear, especially the military helicopter of high maneuverability energy and main reduction gear heavy, the superduty helicopter.
Background technology
At present, known helicopter main reduction gear generally is planetary reduction gear and compound planetary retarder, and the single-stage speed ratio is little, and is single rotor.Along with the development of aero-engine technology, High Performance, high rotating speed, high-performance aero-engine constantly occur, and the retarder of Shi Yinging will increase progression with it.Like this, both increased the weight of aircraft itself, manufacturing cost, but also reduced machinery driving efficiency.Moreover because be single rotor rotation, fuselage will produce the moment with the rotor switched in opposite.So, make the aircraft can normal flight, just must give tail-rotor with about 12 percent power of gross horsepower, under transient state, the power of tail-rotor can reach 25% of gross horsepower, is used for producing a kind of moment and offsets, the moment that the balance rotor produces.Because this is a kind of dynamical equilibrium, when a few thing of aircraft (as MISSILE LAUNCHING), will produce some unsure states, strengthened the error (probability as guided missile shooting fall short increases) of work.
Summary of the invention
In order to overcome the unstable state of single-rotor helicopter in a few thing, reduce member, the weight of retarder, improve machinery driving efficiency and speed ratio, the invention provides the coaxial dual-rotor helicopter main reduction gear of the free planet contrarotation of a kind of tooth differential.It is being line of centers with the fuselage axis that the tail-rotor that matches with it is one, is 30 °-60 ° with angle on horizontal surface, at downward 15 °-30 ° movable two tail-rotors of vertical surface, its objective is the stability, alerting ability and the speed that strengthen aircraft.Particularly on perpendicular line, an airplane hangs an airplane, carries out the work compound of many airplanes, in order to handling heavy type, superduty object, as various tanks of handling and armored motor car afield.
The technical solution adopted for the present invention to solve the technical problems: the present invention is made of three parts.One, can be divided into the two sides road to power equably, and make the balance rocker arm body of upper and lower drive bevel gear producing balanced forces, this mechanism is by power input shaft, the bearing pin dish, and bearing pin, the balance rocking arm, flange, master and slave helical wheel and upper and lower finishing bevel gear cuter are formed.Power input shaft wherein, bearing pin dish, bearing pin are integrated members.Balance rocking arm and diesel engine spiracle structural similitude, only two ends are isometric.Active oblique gear is enclosed within on the power input shaft, with cooperating of axle be high-precision running-fit.Its mode of operation is: when power through input shaft, the bearing pin dish makes bearing pin rotation, thereby also drives the rotation of balance rocking arm.One end of balance rocking arm is to go up drive bevel gear and flange, and the other end of balance rocking arm is an active oblique gear, and driven helical wheel and active oblique gear engagement are rigidly connected by axle and following drive bevel gear again.And upper and lower drive bevel gear drives a two-sided driven wheel of differential simultaneously.In case because of manufacturing errors or other reason, make upper and lower drive bevel gear on two-sided finishing bevel gear cuter during unbalance stress, the balance rocking arm will change an angle very flexibly, makes upper and lower drive bevel gear at the stressed state that is in an equilibrium of two-sided driven wheel of differential.In addition, two-sided driven wheel of differential is the centre that is in upper and lower two drive bevel gear, that is to say, the axial motion of two-sided finishing bevel gear cuter suffers restraints.So, with the solar wheeling tooth wheel shaft that two-sided driven wheel of differential rigidity links, the axial motion of planetary gear wheel shaft equally also has been subjected to constraint, like this, has alleviated the bearing load of the sizable solar wheeling tooth wheel shaft of PV value.Though this mechanism has increased some parts, complex structure some, can make the member stress equilibrium, the retarder integral layout is reasonable, weight saving.
Two, free planet retarding stage, this level be by a two-sided driven wheel of differential, solar wheeling tooth wheel shaft, planetary gear wheel shaft, fixing internally toothed annulus, inside and outside rotor internally toothed annulus, upper and lower rolling ring, compositions such as inside and outside rotor shaft.For improving reliability, expendable weight reduces tooling cost, and main stressed member all is designed to the structure of whole one-tenth.Compensating-gear shaft among the present invention, it is exactly the integral structure that a tool is made up of five gears, the helical wheel on both sides is exactly a herringbone tooth structure of drawing back certain distance, upper and lower helical wheel engagement with the solar wheeling tooth wheel shaft, retrain the axial motion of planetary gear wheel shaft, there is master gear the centre, and is with fixedly internally toothed annulus engagement, constant in order to the mutual angle of fixing each planetary gear wheel shaft; Gear forward, with the internally toothed annulus engagement of outer rotor, its number of teeth is greater than master gear; Reverse gear, with interior rotor internally toothed annulus engagement, its number of teeth is less than master gear.There is the rolling annular groove on both sides outside helical gear, in order to lay rolling ring, retrain the radial motion of planetary gear wheel shaft.
Its type of drive is: when power makes two-sided dynamic bevel gear high speed revolution, drive the same high speed revolution of solar wheeling tooth wheel shaft, by upper and lower helical wheel, make the planetary gear wheel shaft fixedly do the planet running in the internally toothed annulus, around the sun, revolution is arranged as the earth, rotation is also arranged.When the number of teeth of outer rotor internally toothed annulus (just forward gear) during greater than the fixing internally toothed annulus number of teeth, master gear just, the rotating speed of outer rotor, with the form reduced power running of number of teeth difference, direction is identical with the revolution direction of planetary gear wheel shaft; When in like manner the number of teeth of the internally toothed annulus of interior rotor (reverse planetary gear just) was less than the fixing internally toothed annulus number of teeth, the rotating speed of interior rotor was equally also made decelerated movement with the form of number of teeth difference, and rotation direction is opposite with the revolution direction of planetary gear wheel shaft.Through the power of the low-speed big behind the big retarding ratio, under spline flange (constraint warp-wise moment) screw flange (constraint axial moment) synergy of inside and outside rotor shaft upper end, pass to inside and outside rotor, make low speed rotation, produce lift, aircraft is risen, flight.
They are three years old, center stand column, any type of retarder before the present invention does not all have the term and the notion of center stand column, have only the present invention that this term and structure are just arranged, the outer peripheral face of this center stand column has position of bearings, with supporting solar wheeling tooth wheel shaft, running with interior rotor shaft, and the lift that interior rotor produces is also directly acted on the column by bearing, and outer rotor produce lift also most of by casing pass to column in a word the motive power (applied external force when comprising many airplanes work compound) on the autogyro all concentrate on the center stand column, so fuselage is stressed not quite from heavy and light, simplicity of design; Secondly, the centre of center stand column is empty, and this space has not only alleviated the weight of column itself, makes rational in infrastructure, still lubricating oil pump output lubricating oil storage, the desirable place of buffering, general here bullet is not worn, and the space is big, oil storage is many, afield, when major-minor oil pump situation in bad order, can make that aircraft safety is counter to navigate.Moreover, outstanding feature is: the upper/lower terminal of center stand column links to each other with the suspension hook seat with screw thread, except carry out usual single frame do out of trade, if any heavy type or extra-duty goods, just can carry out many work compounds, the lifting rope hook of top aircraft is hooked in the hook seat of following aircraft, like this, top aircraft hang following aircraft, hang following aircraft again ... like this, one is hung one, just can the heavy or extra-duty goods of handling.Special at the crucial moment of war, remove the military tank of handling on the battlefield, armored motor car allows them cross that lofty mountains and steep hills, great river Hu Hai, reach the triumph of war.
Description of drawings.
Because the present invention's gear simple in structure only just can get across with a section-drawing all to be gauge member, Figure of description 1 is a section-drawing, among the figure: 1, hook seat; 2, interior rotor shaft screw flange; 3, interior rotor male splines flange; 4, outer rotor male splines flange; 5, outer rotor shaft screw flange; 6, interior rotor shaft; 7, outer rotor shaft; 8, go up rolling ring; 9, solar wheeling tooth wheel shaft; (901, helical wheel on the sun wheel; 902, helical wheel under the sun wheel; ) 10, upper shell; 11, interior rotor internally toothed annulus, its number of teeth is less than the fixing internally toothed annulus number of teeth; 12, outer rotor internally toothed annulus, its number of teeth is greater than the fixing internally toothed annulus number of teeth; 13, fixing internally toothed annulus; 14, following rolling ring; 15, lower house; 16, two-sided driven wheel of differential; 17, oil inlet screw; 18, fuel feed hole; 19, following suspension hook seat; 20, following drive bevel gear; 21, balance rocker arm body housing; 22, go up drive bevel gear; 23, flange links to each other with last drive bevel gear axle with spline; 24, driven helical wheel links to each other with following drive bevel gear axle with spline; 25, bearing pin dish; (251, power input shaft; 252, bearing pin; ) 26, active oblique gear, be enclosed within on the power input shaft, with the cooperation of axle as the plunger and barrel assembly in the high-pressure oil pump in the diesel engine, be accurate running-fit; 27, balance rocking arm, its shape is similar to the valve rocker in the diesel engine, with cooperating of bearing pin also be accurate running-fit; 28, rolling annular groove back-up ring; 29, circlip for shaft; 30, planetary gear wheel shaft; (301, following helical wheel, with the declivity gear mesh of solar wheeling tooth wheel shaft; 302, master gear is with fixedly internally toothed annulus engagement; 303, forward its number of teeth of gear meshes greater than the accurate gear number of teeth and outer rotor internally toothed annulus; 304, its number of teeth of reverse gear is less than the benchmark number of teeth, with interior rotor internally toothed annulus engagement; 305, go up helical wheel, constitute the herringbone tooth structure, with the last helical wheel engagement of solar wheeling tooth wheel shaft with following helical wheel; ) 31 all dotted lines all are lubricating oil output apertures; 32, outer rotor sealing member; 33, interior rotor sealing member.
Setting-up procedure of the present invention is: at first be that 5 compensating-gear shafts are bundled on the solar wheeling tooth wheel shaft with cord, then just outer rotor internally toothed annulus, interior rotor internally toothed annulus, fixing internally toothed annulus, be contained on the position separately, (annotate to want, when first outer rotor internally toothed annulus of dress, note the mutual angle of 5 compensating-gear shafts) complete planet gear transmission system just assembles have been finished.Besides interior rotor shaft is assemblied on the center stand column, planet gear transmission system is assemblied on the center stand column,, tighten, and lock with steel wire or epoxy resin with the predetermincd tension of torque-indicating wrench by standard interior rotor shaft and interior rotor internally toothed annulus bolt.(aspect the lower casing installation lubricating system is being arranged, accessory drive system and cooling of the oil fan etc. before not finishing second embodiment, all are outer adding systems, do not do any explanation in the present invention in the installation of lower house besides.) fixing internally toothed annulus is placed on the lower house, and good with bolt.Two-sided driven wheel of differential is placed in the lower house, many group balance rocker arm bodies from outer toward insertion successively, two-sided driven wheel of differential to be placed between two drive bevel gear, and be engaged with.With bolt the balance rocker arm body is fixed one by one, and make the moving commentaries on classics of two-sided driven wheel of differential, then with hand rotational power input shaft, pass through auxiliary hole, tightly fixing with bolt two-sided driven wheel of differential and solar wheeling tooth wheel shaft, (this auxiliary hole is not on hatching, so do not draw among the figure).Outer rotor shaft bolt up outside on the internally toothed annulus of rotor, its fastening method is identical with interior rotor besides.Be exactly upper shell, fixedly internally toothed annulus and lower house bolt are last, are exactly outer rotor sealing member, and interior rotor sealing member is placed on position separately, loads onto screw flange, the spline flange of inside and outside rotor shaft in order, and thrust bearing cap is compressed.Nimbly and freely whether such retarder just installs substantially, then, with hand turning effort input shaft, makes inside and outside rotor shaft running one, two commentaries on classics, to see.Here need to illustrate be: 1, used bearing, only fixed again after second embodiment.The present bearing of usefulness, the bearing of using in the time of can not be as work is not so be described.2, rotor shaft can not be rotated.Can only rotate and to rotate by input shaft.
Second embodiment, 1, the retarder that installs is placed on the test run stand, drive with HM Hydraulic Motor, break-in some hrs under various rotating speeds during this period, goes to measure flow rate of lubricating oil, and pressure and temperature write down the best lubrication parameter when non-loaded.2, the good retarder of break-in, be placed on open-air one overhead on 50 meters the steel towers, fix, and rotor, driving engine is also set up, engine on, make rotor be operated in 1/4th, 1/2nd, 3/4ths and the full-power state under, the running some hrs is in order to check the contact patch and the crackle of gear tooth.3, stick sheetlike temperature indicator in the place of rotating.Equipment such as thermometric TV or infrared camera are then used in the casing outside, remove to write down the temperature traverse temperature traverse of casing and the hot-fluid route of casing.4, the pressure-strain sheet is sticked in the place of stress concentration, under normal and improper situation, remove the some hrs that turns round, in order to measure the distribution of stress of various movement parts.5, with retarder and the glass wool thermal insulation of lubricating oil oil circuit, measure the water-in and water-out water temperature of radiator, flow, calculate the friction loss power of tested retarder, thereby determine the power of fan, the heat interchanging area of oil radiator, the efficient of retarder etc.
This retarder is through the test of top hundreds of hour, and oil system, and various bearings are determined to install and just removed to load onto fuselage, tail-rotor, aloft carries out taking a flight test after at least 50 hours the mooring experiment.

Claims (5)

1, can be divided into two-way to power equably, and make upper and lower drive bevel gear, the balance rocker arm body of producing balanced forces, it is characterized in that: when power makes bearing pin when rotation on the bearing pin dish, just drive balance rocking arm rotation flexibly, an end of balance rocking arm is a flange, last drive bevel gear, the other end is an active oblique gear, and driven helical wheel reaches drive bevel gear down.
2, by two-sided driven wheel of differential, center stand column, the solar wheeling tooth wheel shaft, the planetary gear wheel shaft, fixing internally toothed annulus, inside and outside rotor internally toothed annulus, the free planet retarding stage that inside and outside rotor shaft and upper and lower rolling ring are formed, it is characterized in that: when power rotates two-sided driven wheel of differential, drive the rotation of solar wheeling tooth wheel shaft, drive the planetary gear wheel shaft again and fixedly making planet motion in the internally toothed annulus, making inside and outside rotor internally toothed annulus is benchmark with fixing internally toothed annulus, form with number of teeth difference is made decelerated movement, with opposite each other direction rotation.
3, the one-piece construction formed by five gears of planetary gear wheel shaft, it is characterized in that: upper and lower helical wheel is a double helical gear structure of drawing back certain distance, the upper and lower helical wheel engagement with the solar wheeling tooth wheel shaft retrains its axial motion; Middle master gear, with fixedly internally toothed annulus engagement, it is constant to fix the mutual angle of each planetary gear wheel shaft; Gear forward, its number of teeth are greater than the master gear number of teeth, with outer rotor inner gear ring engagement; Reverse gear, its number of teeth are less than the master gear number of teeth, with interior rotor internally toothed annulus engagement.
4, simple shape, but the center stand column of multiple effect is arranged, it is characterized in that: the position of bearings of outer peripheral face is to bear and support the solar wheeling tooth wheel shaft, the running of interior rotor shaft and the motive power that produces therefrom; Volume inside is a buffering, stores the lubricating oil of lubricating oil pump output; Upper/lower terminal links to each other with the suspension hook seat with screw, hangs an airplane in order to an airplane, carries out many airplanes work compound.
5, bear commutation, and the two-sided driven wheel of differential of the axial motion of car and constraint solar wheeling tooth wheel shaft, it is characterized in that:, have drive bevel gear engagement up and down in middle and many groups the integral structure of the synthetic two-sided finishing bevel gear cuter of two single face bevel gear set.
CNA2008101090851A 2007-05-31 2008-05-23 Opposite spin coaxial twin-rotor helicopter main retarder CN101508342A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN200720152442 2007-05-31
CN200720152442.3 2007-05-31
CNA2008101090851A CN101508342A (en) 2007-05-31 2008-05-23 Opposite spin coaxial twin-rotor helicopter main retarder

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CNA2008101090851A CN101508342A (en) 2007-05-31 2008-05-23 Opposite spin coaxial twin-rotor helicopter main retarder

Related Child Applications (1)

Application Number Title Priority Date Filing Date
CN201110023000XA Division CN102141129A (en) 2008-05-23 2008-05-23 First-stage balance rocker arm mechanism for double-rotor main speed reducer

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CN101508342A true CN101508342A (en) 2009-08-19

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102107735A (en) * 2011-01-20 2011-06-29 陈志新 Airplane crash retarder
CN102184308A (en) * 2011-05-31 2011-09-14 中国航空动力机械研究所 Design method of test simulated transmission-torque changeover panel
CN102886637A (en) * 2012-10-24 2013-01-23 哈尔滨东安发动机(集团)有限公司 Overhauling method for foreign speed reducer of helicopter
CN103968003A (en) * 2014-05-20 2014-08-06 西北工业大学 Torque shunting transmission mechanism for helicopter main reducing gear
CN103979108A (en) * 2014-05-29 2014-08-13 合肥工业大学 Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle
CN110422325A (en) * 2019-06-27 2019-11-08 四川航天中天动力装备有限责任公司 A kind of coaxial double-rotary wing unmanned plane power system architecture
CN111706642A (en) * 2020-05-27 2020-09-25 南京航空航天大学 Coaxial dual-rotor helicopter transmission device with bevel gear shunt

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102107735A (en) * 2011-01-20 2011-06-29 陈志新 Airplane crash retarder
CN102107735B (en) * 2011-01-20 2012-12-05 陈志新 Airplane crash retarder
CN102184308A (en) * 2011-05-31 2011-09-14 中国航空动力机械研究所 Design method of test simulated transmission-torque changeover panel
CN102886637A (en) * 2012-10-24 2013-01-23 哈尔滨东安发动机(集团)有限公司 Overhauling method for foreign speed reducer of helicopter
CN102886637B (en) * 2012-10-24 2017-05-10 哈尔滨东安发动机(集团)有限公司 Overhauling method for foreign speed reducer of helicopter
CN103968003A (en) * 2014-05-20 2014-08-06 西北工业大学 Torque shunting transmission mechanism for helicopter main reducing gear
CN103979108A (en) * 2014-05-29 2014-08-13 合肥工业大学 Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle
CN103979108B (en) * 2014-05-29 2015-12-30 合肥工业大学 A kind of coaxial double-rotary wing high-speed helicopter main reduction gear of tensile force of belt oar
CN110422325A (en) * 2019-06-27 2019-11-08 四川航天中天动力装备有限责任公司 A kind of coaxial double-rotary wing unmanned plane power system architecture
CN110422325B (en) * 2019-06-27 2021-02-09 四川航天中天动力装备有限责任公司 Coaxial double-rotor unmanned aerial vehicle power system structure
CN111706642A (en) * 2020-05-27 2020-09-25 南京航空航天大学 Coaxial dual-rotor helicopter transmission device with bevel gear shunt

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Application publication date: 20090819