CN204688405U - A kind of ultramicroscopic fuel oil depopulated helicopter - Google Patents

Abstract

The utility model proposes a kind of ultramicroscopic fuel oil depopulated helicopter, by to the screw propeller connection structure of helicopter, especially main rotor and tail rotor are innovated, carry out innovation to the engine power transferring structure of fuel oil depopulated helicopter to improve, introduce disengaging type Power output technology and deceleration differential-speed dynamic transferring structure, can according to engine speed dynamic conditioning transmitting ratio, stabilize the power transmission process of depopulated helicopter to greatest extent, turbo-charging structural development has been carried out to driving engine simultaneously, to ensure the power of depopulated helicopter, under the prerequisite improving engine output power, stabilize the transmission of power of driving engine and the rotation process of screw propeller, for the volume reducing fuel oil depopulated helicopter creates condition, thus the innovation realization ultramicroscopic fuel oil depopulated helicopter of fuselage length below 1 meter first, there is wide market practical prospect.

Description

A kind of ultramicroscopic fuel oil depopulated helicopter

Technical field

The utility model relates to small-sized depopulated helicopter technical field, particularly a kind of ultramicroscopic fuel oil depopulated helicopter.

Background technology

The most length of current fuel oil depopulated helicopter is on the market all more than one meter, and volume is excessive not portable, and discharge capacity is all at more than 5CC, excessive fuel consumption flight cost is high, screw propeller adopts traditional approach to connect, and during rotation, lethality is too large, and manipulator does not slightly note just having fatal danger! Existing depopulated helicopter is also had not adopt disengaging type Power output technology to driving engine, and the transmission of power poor-performing of driving engine, rational deceleration differential gear is not adopted to stablize transmission of power, make the flight stability of existing depopulated helicopter poor, obtaining high stability only has the volume by increasing helicopter to realize, this critical defect such as flight cost as previously mentioned can be caused on the contrary high, not portable, limits the application of depopulated helicopter.

Summary of the invention

The utility model is based on above-mentioned prior art problem, a kind of ultramicroscopic fuel oil depopulated helicopter is proposed, by to the screw propeller connection structure of helicopter, especially main rotor and tail rotor are innovated, carry out innovation to the engine power transferring structure of fuel oil depopulated helicopter to improve, introduce disengaging type Power output technology and deceleration differential-speed dynamic transferring structure, can according to engine speed dynamic conditioning transmitting ratio, stablize the power transmission process of depopulated helicopter to greatest extent, turbo-charging structural development has been carried out to driving engine simultaneously, to ensure the power of depopulated helicopter, under the prerequisite improving engine output power, stabilize the transmission of power of driving engine and the rotation process of screw propeller, for the volume reducing fuel oil depopulated helicopter creates condition, thus the innovation realization ultramicroscopic fuel oil depopulated helicopter of fuselage length below 1 meter first, there is wide market practical prospect.

It is as follows that the utility model solves the problems of the technologies described above taked technical scheme:

A kind of superminiature fuel oil depopulated helicopter, comprise main rotor system 1, dynamic clutch output system 2, tail rotor system 3, power-transmission system 4, empennage connecting rod 5, fuselage 6, rise and fall support 7 and blade 8, rise and fall described in the bottom connection of described fuselage 6 support 7, described dynamic clutch output system 2 and power-transmission system 4 are arranged in described fuselage 6, described power-transmission system 4 is connected to described dynamic clutch output system 2, described tail rotor system 3 and main rotor system 1 are connected to described power-transmission system 4, described main rotor system 1 is arranged at body upper, described tail rotor system 3 is connected to afterbody by empennage connecting rod 5, described main rotor system 1 and tail rotor system 3 are connected with blade 8,

Described main rotor system 1 comprises metal rotor head drg 10, left-handed wing holder 11, dextrorotation wing holder 12, rotor permanent center seat 13, connecting rod 14, cross plate 15, supporting disk 16 and main shaft 17, described rotor permanent center seat 13 comprises sleeve 132, be arranged at the transverse axis 131 in sleeve, be connected to the base 133 of sleeve bottom side, the through hole passed for main shaft 17 is offered in the middle part of described base 133, described left-handed wing holder 11 is the same with dextrorotation wing holder 12 structure, include permanent seat 121 and rocking arm 123, described rocking arm 123 self-retaining seat 121 sidewall is outwardly arranged, described permanent seat 121 offers the screw hole run through vertically, the outer end of described permanent seat offers clip slot 122, described clip slot 122 is for installing blade 8, the permanent seat of described left-handed wing holder 11 is fixedly connected on the left end of described transverse axis 131 by pad and check screw, and between transverse axis 131 and permanent seat, be provided with transverse axis packing ring 134 and transverse axis aluminium cover 135, the permanent seat of described dextrorotation wing holder 12 is fixedly connected on the right-hand member of described transverse axis 131 by pad and check screw, and between transverse axis 131 and permanent seat, be provided with transverse axis packing ring 134 and transverse axis aluminium cover 135, and the rocking arm on described left-handed wing holder 11 and the sub rocker arm other places on dextrorotation wing holder 12 are in the both sides of the sleeve 132 of rotor permanent center seat 13, described rocking arm is connected to described cross plate 15 by described connecting rod 14, described cross plate 15 is arranged on described supporting disk 16, the central authorities of described cross plate 15 are provided with cardan wheel 152, described cardan wheel 152 offers centre hole, described supporting disk 16 is connected to fuselage, is fixedly connected in base 133 through hole of described rotor permanent center seat 13 after described main shaft 17 passes the centre hole of described supporting disk 16 and cardan wheel, described metal rotor head drg 10 is arranged on the sleeve 132 of described rotor permanent center seat 13,

Described tail rotor system 3 comprises the left holder 31 of tail rotor, the right holder 32 of tail rotor, tail control group 33, tail rotor control assembly 34 and tail power-transmission system 35, the left holder 31 of described tail rotor comprises the first permanent seat 317, the middle part of described first permanent seat 317 offers connecting through hole, the left end of described first permanent seat 317 offers the first clip slot 311, described first clip slot 311 is for installing blade 8, the upside of described first permanent seat 317 is outwards integrally outstanding is formed with the first rocking arm 312, the central authorities of described first rocking arm 312 offer screw hole, the left and right sides of described first permanent seat 317 is outwardly formed with control fin, the right holder 32 of described tail rotor comprises the second permanent seat 325 and Connection Block 321, described Connection Block 321 radially offers tailing axle perforation, one end of described second permanent seat 325 connects described Connection Block 321, the other end of described second permanent seat 325 offers the second clip slot 322, described second clip slot 322 is for installing blade 8, the downside of described second permanent seat 325 is outwards integrally outstanding is formed with the second rocking arm 323, the central authorities of described second rocking arm 323 offer screw hole, the left and right sides of described second permanent seat 325 is outwardly formed with control fin, described Connection Block 321 offers threaded connection hole, pass the connecting through hole of the first permanent seat 317 by screw and be threadedly connected in the threaded connection hole on Connection Block 321 and left for described tail rotor holder 31 be fixedly connected on the right holder 32 of described tail rotor, and make described first rocking arm 312 and the second rocking arm 323 be in upper and lower both sides, described tail control group 33 comprises bearing seat aluminium liner 331, first tail control link head 332, second tail control link head, bearing block set 336, tailing axle sliding sleeve 337 and some screws, one end of described first tail control link head 332 is screwed the upper end being connected to bearing seat aluminium liner 331, the other end of described first tail control link head 332 is screwed the screw hole being connected to the first rocking arm 312, one end of described second tail control link head 332 is screwed the lower end being connected to bearing seat aluminium liner 331, the other end of described second tail control link head 332 is connected to the screw hole of the second rocking arm 323 by screw, the central authorities of described bearing seat aluminium liner 331 offer through hole, and described bearing block set 336 and tailing axle sliding sleeve 337 central authorities all offer axis hole, and described tailing axle sliding sleeve 337 is connected on described bearing seat aluminium liner 331 through after described bearing block set 336, described tail power-transmission system 35 comprises tail power transmission shaft, tailing axle 351, sleeve bearing 352, horizontal rotor gear 353 and longitudinal rotor gear 354, described tail power transmission shaft is connected to horizontal rotor gear 353 through after sleeve bearing 352, described longitudinal rotor gear 354 Vertical Meshing is on described horizontal rotor gear 353, one end of described tailing axle 351 is fixedly connected on described longitudinal rotor gear 354, the other end of described tailing axle 351 is successively through described tailing axle sliding sleeve 337, be fixedly connected on after the central through hole of bearing seat aluminium liner 331 Connection Block 321 of the right holder 32 of described tail rotor is offered tailing axle perforation in, described tail rotor control assembly 34 comprises I-shaped arm 341, regulation and control arm 342, Connection Block 343 and some screws 344, described regulation and control arm 342 is integrally connected to the bottom of I-shaped arm 341, described Connection Block 343 is connected between the upper lower branch arm of described I-shaped arm 341 side by screw 344, and the upper lower branch arm of described I-shaped arm 341 opposite side is connected to described bearing block set 336 by screw 344,

Described dynamic clutch output system 2 comprises clutch pack 20, described clutch pack 20 comprises the first transmission shaft 29, second driving shaft 21, first gear cluster 22, second gear cluster 23, get rid of block 24, elastic component 25, get rid of block 26, overload protection device 27 and reducing gear 28, described first gear cluster 22 is installed on the first transmission shaft 29, and comprise coaxial first gear 221 and the first miniature gears 222, described second gear cluster 23 is installed on described second driving shaft 21, and comprise coaxial second largest gear 231 and the second miniature gears 232, described first gear 221 engages with described second miniature gears 232, described first miniature gears 222 engages with described second largest gear 231, described reducing gear 28 to be installed on described first transmission shaft 29 and to be connected with a joggle with the power take-off shaft of engine unit 900, the side of described second miniature gears 232 is formed with cylindrical cavity along second driving shaft 21, be provided with in described cylindrical cavity and get rid of block 26, described get rid of block 26 is elasticly connected with by elastic component 25 described in get rid of block 24, when second driving shaft 21 slowly runs, described get rid of block 26 fit in described in get rid of on block 26 and rotate with second driving shaft 21, when the rotating speed of second driving shaft 21 is raised to a certain degree, described in get rid of block 26 and start to depart from and get rid of block 26 and support the inwall rubbed in described cylindrical cavity, described overload protection device 27 is arranged on described first transmission shaft 29,

Described power-transmission system 4 comprises sun wheel input shaft 41, fixed gear ring 43, satellite gear 42, planet wheel spindle 44, pinion carrier 45, input gear 47, upper rotor gear assembly 49, lower rotor gear assembly 48 and tail rotor output gear component 46, described sun wheel input shaft 41 is involute helical wheel shaft, the side of described pinion carrier 45 is provided with shoulder main shaft, the waist of shoulder main shaft is provided with spline, the opposite side of described pinion carrier 45 is connected with three planet wheel spindles 44, described fixed gear ring 43 has circular ring structure, and circle ring inner surface is provided with inner circular tooth, described inner circular tooth is involute helical, described satellite gear 42 corresponds to three planet wheel spindles 44 and includes three, structure is identical and be involute helical gear, by described sun wheel input shaft 41, fixed gear ring 43, satellite gear 42, planet wheel spindle 44 and pinion carrier 45 form 2K-H skewed tooth planetary gear train, described pinion carrier 45, fixed gear ring 43, sun wheel input shaft 41 is horizontally disposed with and central axes, the shoulder main shaft of pinion carrier 45 side is connected to input gear 47, three planet wheel spindles 44 of pinion carrier 45 opposite side are connected to three satellite gears 42 by bearing, the involute helical internal messing of described satellite gear 42 is on the inner circular tooth of fixed gear ring 43, the involute helical external toothing of described sun wheel input shaft 41 is on the involute helical of three satellite gears 42, described upper rotor gear assembly 49 comprises rotor toothed disc 491 and upper rotor gear wheel shaft 492, described upper rotor toothed disc 491 is disc structure and on neighboring, lower surface, is provided with screw conic tooth, described upper rotor gear wheel shaft 492 is connected to the central authorities of rotor toothed disc 491 and is provided with axially extending bore, described lower rotor gear assembly 48 comprises lower rotor toothed disc 481 and lower rotor gear wheel shaft 482, described lower rotor toothed disc 481 is disc structure and on neighboring, upper surface, is provided with screw conic tooth, described lower rotor gear wheel shaft 482 is connected to the central authorities of lower rotor toothed disc 481 and stretches into the axially extending bore of described upper rotor gear wheel shaft 492, described input gear 47 and tail rotor output gear component 46 are spiral conical tooth shaft, the screw conic tooth addendum flank of described input gear 47 is orthogonal to be engaged on the screw conic tooth of rotor toothed disc 491, on the orthogonal screw conic tooth being engaged in lower rotor toothed disc 481 of screw conic tooth dedendum flank of described input gear 47, on the orthogonal screw conic tooth being engaged in lower rotor toothed disc 481 of screw conic tooth dedendum flank of described tail rotor output gear component 46, described sun wheel input shaft 41 is connected to the second driving shaft 21 in power-transmission system 4, the main shaft 17 of described main rotor system 1 by spline joint in described lower rotor gear wheel shaft 482 or described upper rotor gear wheel shaft 492, described tail rotor output gear component 46 is connected with the tail power transmission shaft in tail rotor system 3,

Described engine unit 900 comprises engine body 910, air compressor 920, turbo-machine 930, waste gas bleeding device 940 and by passage 914, described air compressor 920 is connected to the air inlet pipe 912 of engine body 910, described turbo-machine 930 is connected to the freeing pipe 913 of engine body 910 and coaxial with air compressor 920, described by passage 914 be communicated with freeing pipe 913 and by passage 914 and freeing pipe 913 be communicated with the upstream and downstream that part lays respectively at turbo-machine 930, between the air inlet pipe 912 that described waste gas bleeding device 940 is connected to described engine body 910 and by passage 914, described waste gas bleeding device 940 comprises pressure sensor 941, ECU (Electrical Control Unit) 942, vacuum solenoid 943, vacuum pump 944, venting actuator 945 and aie escape valve 946, described pressure sensor 941 is arranged in engine body 910 air inlet pipe of described air compressor 920 downstream part, and be connected to described ECU (Electrical Control Unit) 942, described ECU (Electrical Control Unit) is connected to described vacuum solenoid 943, described vacuum solenoid 943 has a valve outlet port 947 and a valve import 948, the admission port of described vacuum pump 944 is connected with described valve outlet port 947, described venting actuator 945 comprises a control end 949 and an operating side 950, described control end 949 communicates with the valve import 948 of vacuum solenoid 943, described aie escape valve 946 is arranged on described by passage 914, and be connected with the operating side 950 of venting actuator 945.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, connecting rod 14 in wherein said main rotor system 1 comprises the body of rod 141, bearing 143, check screw 145 and aluminium cover 146, the top of the described body of rod 141 is provided with upper connecting base 144, the bottom of the described body of rod is provided with lower connecting base 142, the middle part of described upper connecting base 144 and lower connecting base 142 offers through hole, described rocking arm is provided with tapped bore, described check screw 145 is through bearing 143, upper connecting base 144 middle through-hole, aluminium overlaps 146 rear threads and is connected in the tapped bore of rocking arm, described cross plate 15 has circular ring, annulus central authorities are provided with described cardan wheel 152, described main shaft 17 slides through the centre hole that described cardan wheel 152 is offered, the periphery of described cross plate 15 is provided with connection lug, described connection lug is connected with movable bulb 151, the through hole that described movable bulb 151 is in described lower connecting base 142 is interior to be movably connected on described cross plate 15 by described connecting rod 14.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, elastic component 25 in wherein said dynamic clutch output system 2 comprises screw 251, spring 252 and the decorative pearl on top of an official cap 253, the described block 26 that gets rid of is provided with thread groove 261, described screw 251 is connected with thread groove 261, one end of described spring 252 is set in the end of described screw 251, the other end of described spring is connected to the described decorative pearl on top of an official cap 253, gets rid of block 24 described in the described decorative pearl on top of an official cap 253 is connected to.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, two backing pins 233 are provided with in the cylindrical cavity of wherein said second miniature gears 232, described second driving shaft 21 is arranged with unilateral bearing 211, and described unilateral bearing 211 is between described second largest gear 231 and the second miniature gears 232; Described overload protection device 27 is arranged at the front of described reducing gear 28.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, in wherein said power-transmission system 4, the annulus outer wall of described fixed gear ring 43 is provided with the shaft shoulder, circumferentially several keyways 431 uniform on the shaft shoulder, are fixedly connected on body shell by described keyway 431 by fixed gear ring 43; The central bore of described satellite gear 42 is provided with grid spacer 421, and described satellite gear 42 is located on planet wheel spindle 44 by the bearing carrier ring of grid spacer 421 both sides, and by lock screw axial restraint.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, the control end 949 of actuator 945 of exitting in wherein said engine unit 900 is a bellows-type actuator, and operating side 950 is a drive link.

Further according to superminiature fuel oil depopulated helicopter described in the utility model, the length of wherein said fuselage 6 is 760mm, highly for 225mm, width are 110mm, the entire length of fuel oil depopulated helicopter is within 1 meter.

At least following technique effect can be reached by the technical solution of the utility model:

1) the utility model carries out innovation improvement from many aspects to fuel oil depopulated helicopter integral structure, consider main rotor and tail rotor structure, engine power problem and transmission of power problem thereof, provided fuel oil depopulated helicopter is made to meet the condition of small size smooth operation, the innovation realization superminiature of fuselage length below 1 meter performance-oriented fuel oil depopulated helicopter, has wide market practical prospect first.

2), disengaging type Power output technology described in the utility model not only can extensively be extended to depopulated helicopter field, and other power technology fields multiple can be applicable to simultaneously, the unmanned plane turbo-charging structure that the utility model is initiated significantly can promote the power of existing unmanned plane, has stronger popularizing value.

3), the utility model overcomes difficult, dangerous large, the shortcoming such as flight cost is high of the ubiquitous heaviness of existing fuel oil helicopter, manipulation, and it can realize common cruising flight, also can carry out the flight of stunt fancy, light, small and exquisite, flexibly, cruise duration is grown and could change mutually by oily electricity! Become the fuel oil helicopter that the whole world is minimum, fill up the technological gap of less than 1 meter small size fuel oil depopulated helicopter.

Accompanying drawing explanation

Accompanying drawing 1 is the integral structure schematic diagram of fuel oil depopulated helicopter described in the utility model;

Accompanying drawing 2 (a) is the integral assembling structure schematic diagram of the main rotor system in fuel oil depopulated helicopter described in the utility model;

Accompanying drawing 2 (b) is the mounting structure schematic diagram in main rotor system accompanying drawing 2 (a) Suo Shi between left and right rotor holder and rotor permanent center seat;

Accompanying drawing 2 (c) is the mounting structure schematic diagram in main rotor system accompanying drawing 2 (a) Suo Shi between rotor permanent center seat and cross plate;

Accompanying drawing 3 (a) is the fractionation structural representation of tail rotor system in fuel oil depopulated helicopter described in the utility model;

Accompanying drawing 3 (b) is the package assembly schematic diagram of tail rotor system accompanying drawing 3 (a) Suo Shi;

Accompanying drawing 4 (a) is the integral installation structural representation of fuel oil depopulated helicopter medium power clutch output system described in the utility model;

Accompanying drawing 4 (b) is the integral structure schematic diagram of clutch pack in dynamic clutch output system accompanying drawing 4 (a) Suo Shi;

Accompanying drawing 4 (c) is the fractionation structural representation of clutch pack accompanying drawing 4 (b) Suo Shi;

Accompanying drawing 4 (d) is in for getting rid of block in described clutch pack the structural representation thrown away and close in two kinds of situations;

Accompanying drawing 5 (a) is the integral structure schematic diagram of fuel oil depopulated helicopter medium power transmission system described in the utility model;

Accompanying drawing 5 (b) is the cross section structure schematic diagram of power-transmission system accompanying drawing 5 (a) Suo Shi;

Accompanying drawing 6 is the turbo-charging structural representation in the engine unit of fuel oil depopulated helicopter described in the utility model;

In figure, the implication of each Reference numeral is as follows:

1-main rotor system, 2-dynamic clutch output system, 3-tail rotor system, 4-power-transmission system, 5-empennage connecting rod, 6-fuselage, 7-rises and falls support, 8-blade;

10-metal rotor head drg, the left-handed wing holder of 11-, 12-dextrorotation wing holder, 13-rotor permanent center seat, 14-connecting rod, 15-cross plate, 16-supporting disk, 17-main shaft; 121-permanent seat, 122-clip slot, 123-rocking arm, 124-pad, 125-check screw; 131-transverse axis, 132-sleeve, 133-base, 134-transverse axis packing ring, 135-transverse axis aluminium cover; The 141-body of rod, 142-lower connecting base, 143-bearing, 144-upper connecting base, 145-check screw, 146-aluminium cover; The movable bulb of 151-, 152-cardan wheel; 161-fixed link, 162-connects lug;

20-clutch pack, 21-second driving shaft, 22-first gear cluster, the first gear of 221-, 222-first miniature gears, 23-second gear cluster, the second largest gear of 231-, 232-second miniature gears, 233-backing pin, 24-gets rid of block, 25-elastic component, 251-screw, 252-spring, the 253-decorative pearl on top of an official cap, 26-gets rid of block, 261-thread groove, 27-overload protection device, 28-reducing gear, 29-first transmission shaft, 900-engine unit;

The left holder of 31-tail rotor, 312-rocking arm, 311-clip slot, 313-bearing, 314-pad, 315-screw, 316-bearing, 317-permanent seat; The right holder of 32-tail rotor, 321-Connection Block, 322-clip slot, 324-antidiarrheal screw, 325-permanent seat; 33-tail control group, 331-bearing seat aluminium liner, 332-tail control link head, 333-top of connecting rod copper sheathing, 334-Philip's head screw, 335-bearing, 336-bearing block set, 337-tailing axle sliding sleeve; 34-tail rotor control assembly, 341-I-shaped arm, 342-regulates and controls arm, 343-Connection Block, 344-screw, 345-bearing; 35-tail power-transmission system, 351-tailing axle, 352-sleeve bearing, the horizontal rotor gear of 353-, the longitudinal rotor gear of 354-;

41-sun wheel input shaft, 42-satellite gear, 421-grid spacer, 43-fixed gear ring, 431-keyway, 44-planet wheel spindle, 45-pinion carrier, 46-tail rotor output gear component, 47-input gear, 471-sleeve, rotor gear assembly under 48-, rotor toothed disc under 481-, rotor gear wheel shaft under 482-, the upper rotor gear assembly of 49-, the upper rotor toothed disc of 491-, the upper rotor gear wheel shaft of 492-;

910-engine body, 912-air inlet pipe, 913-freeing pipe, 914-by passage, 920-air compressor, 930-turbo-machine, 940-waste gas bleeding device, 941-pressure sensor, 942-ECU (Electrical Control Unit), 943-vacuum solenoid, 947-valve outlet port, the import of 948-valve, 944-vacuum pump, 945-exits actuator, 949-control end, 950-operating side, 946-aie escape valve.

Detailed description of the invention

Below in conjunction with accompanying drawing, the technical solution of the utility model is described in detail, to enable those skilled in the art's understanding the utility model clearly, but does not therefore limit protection domain of the present utility model.

Superminiature fuel oil depopulated helicopter integral structure described in the utility model as shown in Figure 1, comprise main rotor system 1, dynamic clutch output system 2, tail rotor system 3, power-transmission system 4, empennage connecting rod 5, fuselage 6, rise and fall support 7 and blade 8, the bottom of described fuselage 6 connects the support 7 that rises and falls, described dynamic clutch output system 2 and power-transmission system 4 are arranged in described fuselage 6, and dynamic clutch output system 2 is as the power unit of whole fuel oil depopulated helicopter, be kinetic energy by the chemical energy of fuel oil, for the flight of helicopter provides Power output, described power-transmission system 4 is connected to described dynamic clutch output system 2, power distribution for dynamic clutch output system 2 being provided passes to tail rotor system 3 and main rotor system 1, namely described power-transmission system 4 is connected to described tail rotor system 3 and main rotor system 1, for it transmits running power, concrete described tail rotor system 3 is arranged at tail and is connected to power-transmission system 4 by empennage connecting rod 5, power drive shaft is provided with in empennage connecting rod 5, described main rotor system 1 is arranged at body upper and is connected to the power transmission shaft of described power-transmission system 4, described main rotor system 1 and tail rotor system 3 are connected with blade.During described fuel oil depopulated helicopter work, by dynamic clutch output system 2 chemical energy of fuel oil be kinetic energy and be provided to power-transmission system 4, by power-transmission system 4, rotational power is passed to main rotor system 1 and tail rotor system 3, thus drive the blade in main rotor system 1 and tail rotor system 3 to rotate, act as helicopter by aerodynamic friction and flying power is provided, make depopulated helicopter can free flight.The utility model is by the above-mentioned main rotor system 1 included by helicopter, dynamic clutch output system 2, tail rotor system 3, power-transmission system 4, engine unit carries out innovation simultaneously to be improved, common formation innovation point of the present utility model, the main rotor system 1 of described helicopter and tail rotor system 3 is made to have stabilized rotation drive ability, simultaneously under the prerequisite improving dynamic clutch output system 2 outputting power, by the power transmission ratio of innovative impetus transmission system 4, greatly stabilize the power distribution of helicopter, provided fuel oil depopulated helicopter is made to meet the condition of small size smooth operation, the innovation realization ultramicroscopic fuel oil depopulated helicopter of fuselage length below 1 meter first, below respectively to the main rotor system 1 that the utility model is created, dynamic clutch output system 2, tail rotor system 3, the concrete innovation structure of power-transmission system 4 and engine unit is described in detail.

Accompanying drawing 2 (a)-2 (c) specifically provides the composition structure of main rotor system 1, as shown in the figure, described main rotor system 1 comprises metal rotor head drg 10, left-handed wing holder 11, dextrorotation wing holder 12, rotor permanent center seat 13, connecting rod 14, cross plate 15, supporting disk 16 and main shaft 17, described left-handed wing holder 11 and dextrorotation wing holder 12 are fixedly connected on the two ends, left and right of described rotor permanent center seat 13, and described left-handed wing holder 11 and dextrorotation wing holder 12 are fixedly connected with blade 8.Described main shaft 17 is fixedly connected on described rotor permanent center seat 13, and rotor permanent center seat 13 can be driven to rotate, described metal rotor head drg 10 is arranged on described rotor permanent center seat 13, for carrying out control for brake to the rotation of the main shaft 17 being connected to rotor permanent center seat 13, described left-handed wing holder 11 and dextrorotation wing holder 12 are connected to described cross plate 15 by described connecting rod 14, the centre of described cross plate 15 is provided with cardan wheel 152, the centre hole of cardan wheel 152 and main shaft 17 sliding block joint, described cross plate 15 is fixedly installed on described supporting disk 16, the periphery of described supporting disk is connected to fuselage by lug and connecting rod, described main shaft 17 is fixedly connected on described rotor permanent center seat 13 through after described supporting disk 16 and cross plate 15.Concrete, described rotor permanent center seat 13 comprises columniform sleeve 132, the transverse axis 131 be arranged in described sleeve 132, be fixedly connected on the base 133 of described sleeve bottom side, offers the through hole passed for main shaft 17 in the middle part of described base 133.Described left-handed wing holder 11 is the same with the structure of dextrorotation wing holder 12, include permanent seat 121 and be integrally connected to the rocking arm 123 on permanent seat 121, the sidewall of described rocking arm 123 self-retaining seat 121 is outwardly arranged, the central authorities of described permanent seat 121 offer screw hole, the outer end of permanent seat offers clip slot 122, and described clip slot 122 is for installing blade 8.Described permanent seat 121 is fixedly connected on described transverse axis 131 by pad 124 and check screw 125, and between described transverse axis 131 and permanent seat 121, be provided with transverse axis packing ring 134 and transverse axis aluminium cover 135, described transverse axis packing ring 134 and transverse axis aluminium cover 135 are sheathed on described transverse axis 131, after the screw hole of described permanent seat 121 central authorities is stretched in the front end of described transverse axis, by check screw 125, permanent seat 121 is connected on transverse axis, described permanent seat 121 is built with three bearings, two common deep groove ball bearings and a surface bearing, by the cooperation of three bearings, limit the motion of left and right rotor holder two axis, make it relative to transverse axis rotational motion only.Described left-handed wing holder 11 and dextrorotation wing holder 12 mode that is fixedly connected with on described rotor permanent center seat 13 is symmetrical consistent.And described left-handed wing holder 11 and dextrorotation wing holder 12 are when being fixedly connected on described rotor permanent center seat 13, sub rocker arm other places on rocking arm on left-handed wing holder 11 and dextrorotation wing holder 12 are in the both sides of the sleeve 132 of rotor permanent center seat 13, rocking arm corresponding to every side includes the connecting rod 14 described in two, every root connecting rod 14 is connected on a rocking arm, described connecting rod 14 comprises the body of rod 141, bearing 143, check screw 145 and aluminium cover 146, the top of the body of rod 141 is provided with upper connecting base 144, the bottom of the body of rod is provided with lower connecting base 142, the middle part of described upper connecting base 144 and lower connecting base 142 all offers through hole, described rocking arm is provided with tapped bore, every root connecting rod 14 is screwed and is connected on a rocking arm, concrete described check screw 145 is through bearing 143, upper connecting base 144 middle through-hole, aluminium overlaps 146 rear threads and is connected in the tapped bore of described rocking arm, described bearing 143 comprises two, be arranged between described check screw 145 and upper connecting base 144 middle through-hole inwall and between described check screw 145 and swing arm threaded hole inwall respectively, ensure that described connecting rod 14 can carry out free rotation after being connected to described rocking arm.Described cross plate cross plate 15 has circular ring, annulus central authorities are provided with cardan wheel 152, described cardan wheel 152 offers centre hole, described main shaft through described centre hole and with its sliding block joint, the periphery of described cross plate 15 is provided with connection lug, described connection lug is connected with movable bulb 151, and described movable bulb 151 is in the through hole on described connecting rod 14 lower connecting base 142, thus described connecting rod 14 is movably connected on described cross plate 15 by movable bulb 151.Described cross plate 15 is fixedly installed on described supporting disk 16, and the periphery of described supporting disk is connected to fuselage by connecting lug.Described main shaft 17 is connected to rotor permanent center seat 13 through after described supporting disk and cross plate, and described main shaft 17 can carry out swinging and sliding up and down in the cardan wheel 152 of cross plate, like this by changing the angle of cross plate, left and right rotor holder can be driven to change different angles, obtain the lift in different size, zones of different face, thus control aircraft obtains different flight paths.

Accompanying drawing 3 (a)-3 (b) specifically provides the composition structure of tail rotor system 3, as shown in the figure, described tail rotor system 3 comprises the left holder of tail rotor 31, the right holder 32 of tail rotor, tail control group 33, tail rotor control assembly 34 and tail power-transmission system 35.The left holder 31 of described tail rotor comprise permanent seat 317, bearing 313,316, pad 314 and screw 315, the middle part of described permanent seat 317 offers connecting through hole, the threaded one end of described permanent seat 317 is connected to the right holder 32 of tail rotor, the other end of described permanent seat 317 offers clip slot 311, sandwiched blade in described clip slot 311, the upside one of described permanent seat 317 is outstanding is formed with rocking arm 312, described rocking arm 312 central authorities offer screw hole, and the left and right sides of described permanent seat 317 is outwardly formed with control fin.The right holder 32 of described tail rotor comprises permanent seat 325, Connection Block 321 and antidiarrheal screw 324, one end of described permanent seat 325 connects described Connection Block 321, the other end of described permanent seat 325 offers clip slot 322, sandwiched blade 8 in described clip slot 322, the downside one of described permanent seat 325 is outstanding is formed with rocking arm 323, described rocking arm 323 central authorities offer screw hole, the left and right sides of described permanent seat 325 is outwardly formed with control fin, the central authorities of described Connection Block 321 and permanent seat 325 offer runs through connecting bore, together with the left holder of described tail rotor 31 is bolted to connection with the right holder 32 of tail rotor, concrete screw 315 passes pad 314 successively from one end of the left holder 31 of tail rotor, centre hole rear thread through permanent seat 317 in the clip slot of the left holder of tail rotor 31 after bearing 313 is connected to the Connection Block 321 of the right holder 32 of tail rotor, and bearing 316 is provided with between the left holder of tail rotor 31 and the right holder 32 of tail rotor, and described bearing 313 is between screw 315 and tail rotor left holder 31 inwall, ensure that its rocking arm is in upper and lower sides during the linking together of the left holder of described tail rotor 31 and the right holder 32 of tail rotor, namely the rocking arm of the left holder 31 of tail rotor is positioned at upside, the rocking arm of the right holder 32 of tail rotor is positioned at downside, described Connection Block 321 radially offers tailing axle perforation.Described tail control group 33 comprises bearing seat aluminium liner 331, tail control link head 332, top of connecting rod copper sheathing 333, Philip's head screw 334, bearing 335, bearing block set 336 and tailing axle sliding sleeve 337, described tail control group 33 is connected on the rocking arm on the left holder of described tail rotor 31 and the right holder 32 of tail rotor, corresponding to two rocking arms, comprise two described tail control link heads 332, the two ends of described tail control link head 332 all offer screw, one end of one of them tail control link head 332 is fixedly connected on the upper end of bearing seat aluminium liner 331 by top of connecting rod copper sheathing 333 and Philip's head screw 334, the other end of described tail control link head 332 is connected to by Philip's head screw 334 on the rocking arm 312 of the left holder 31 of described tail rotor, one end of another tail control link head 332 is fixedly connected on the lower end of bearing seat aluminium liner 331 by top of connecting rod copper sheathing 333 and Philip's head screw 334, the other end of described tail control link head 332 is connected to by Philip's head screw 334 on the rocking arm 323 of the right holder 32 of described tail rotor, such bearing seat aluminium liner 331 is connected on the rocking arm on the left holder of tail rotor 31 and the right holder 32 of tail rotor by tail control link head 332.Offer through hole in the central authorities of described bearing seat aluminium liner 331, described bearing block set 336 and tailing axle sliding sleeve 337 central authorities all offer axis hole, and described bearing block set 336 is close to bearing seat aluminium liner 331 and is arranged.Described tailing axle sliding sleeve 337 is locked on bearing seat aluminium liner 331 through thread cw after described bearing 335 and bearing block set 336, namely described bearing 335 is between bearing block set 336 inwall and tailing axle sliding sleeve 337 outer wall, is fixedly connected in the tailing axle perforation that the Connection Block 321 of the right holder 32 of described tail rotor is offered after the tailing axle 351 in described tail power-transmission system 35 passes the central through hole of described tailing axle sliding sleeve 337 and bearing seat aluminium liner 331.Described tail power-transmission system 35 comprises tail power transmission shaft, tailing axle 351, sleeve bearing 352, horizontal rotor gear 353 and longitudinal rotor gear 354, wherein tail power transmission shaft is connected to horizontal rotor gear 353 through after sleeve bearing 352, on the engagement that described longitudinal rotor gear 354 is vertical and described horizontal rotor gear 353, one end of described tailing axle 351 is fixedly connected on described longitudinal rotor gear 354, the other end of described tailing axle 351 is successively through tailing axle sliding sleeve 337, bearing 335, bearing block set 336, bearing 335, be fixedly connected on after the central through hole of bearing seat aluminium liner 331 Connection Block 321 of the right holder 32 of described tail rotor is offered tailing axle perforation in, dynamical axis from power-transmission system is connected to described tail power transmission shaft, and its rotary power is passed to tail power transmission shaft, horizontal rotor gear 353 is driven to rotate by tail power transmission shaft, and then drive longitudinal rotor gear 354 to rotate by gears meshing effect, by longitudinal rotor gear 354, rotary power is passed to tailing axle 351, the left holder of tail rotor 31 and the right holder 32 of tail rotor is driven to rotate by tailing axle 351.Described tail rotor control assembly 34 comprises I-shaped arm 341, regulation and control arm 342, Connection Block 343, some screws 344 and bearing 345; Described regulation and control arm 342 is integrally connected to the bottom of I-shaped arm 341, and it is vertical with face, I-shaped arm 341 place, described Connection Block 343 to be connected between the upper lower branch arm of described I-shaped arm 341 side and the low control fin being connected to the left holder 31 of described tail rotor by screw 344 and bearing 345, the upper lower branch arm of described I-shaped arm 341 opposite side is connected to described bearing block set 336 by screw 344 and bearing 345, and described regulation and control arm 342 is for carrying out weave control.Whole tail rotor system 3 fits together as shown in accompanying drawing 3 (b), transmission of power from power-transmission system rotates to driving the left holder of tail rotor 31 and the right holder 32 of tail rotor after tailing axle, and then drive the blade be installed on the holder of tail rotor left and right to rotate, the pull bar that moves through of tail servomechanism is delivered on the regulation and control arm 342 of tail rotor control assembly simultaneously, tail rotor control assembly and tail control group are rotatedly connected, and then swung by the weave control tail rotor left and right holder of tail rotor control assembly, tail servo action is delivered on tail rotor holder, blade pendulum angle fixing on tail rotor holder is changed with this.Due to connection 2 points symmetrically of tail rotor control assembly and tail control group centre bearer block set, improve force-bearing situation, do not have and singly push away such single load bearing, increase the resistance of copper sheathing, easily the defect of wearing and tearing copper sheathing.

Accompanying drawing 4 (a)-4 (d) specifically provides the composition structure of dynamic clutch output system 2, as shown in the figure, described dynamic clutch output system 2 is as the power take-off unit of whole fuel oil depopulated helicopter, for the flight of helicopter provides Power output, concrete described dynamic clutch output system 2 comprises clutch pack 20, the power take-off shaft of described engine unit 900 is connected to described clutch pack 20, described clutch pack 20 comprises the first transmission shaft 29, second driving shaft 21, first gear cluster 22, second gear cluster 23, get rid of block 24, elastic component 25, get rid of block 26, overload protection device 27 and reducing gear 28, first gear cluster 22 is installed on the first transmission shaft 29, and comprise first gear 221 and the first miniature gears 222, this two gear is coaxial, described second gear cluster 23 is installed on described second driving shaft 21, second gear cluster 23 comprises second largest gear 231 and the second miniature gears 232, and first gear 221 engages with the second miniature gears 232, first miniature gears 222 engages with second largest gear 231, described first transmission shaft 29 is also provided with reducing gear 28, described reducing gear 28 is coaxial with described first gear cluster 22, and described reducing gear 28 is connected with the power take-off shaft gears meshing of engine unit 900, for transmission of power that engine unit is exported to clutch pack 2, like this when the power take-off shaft of engine unit rotates, its rotational power is passed to the first transmission shaft by reducing gear 28, the first gear cluster 22 on it is driven to rotate, the gears meshing effect that rotates through of the first gear cluster 22 passes to the second gear cluster 23, thus drive second driving shaft 21 to rotate by the second gear cluster 23, reach the object exported by second driving shaft transmission by the outputting power of engine unit.Further also to be provided with in the housing of clutch pack 2 on a second driving shaft 21 of fitting when slowly running and when high speed rotating, friction second miniature gears 232 can be supported in one end, the other end connects second driving shaft 21 gets rid of block 24.Particularly, first gear 221 can be set as 21 teeth, first miniature gears 222 is 18 teeth, second largest gear 231 is 40 teeth, second miniature gears 232 is 37 teeth, when helicopter just starts, the rotating speed that engine unit exports is slower, get rid of between block 24 with the second miniature gears 232 and do not contact, now clutch pack 2 obtains rotating speed by the first miniature gears 222 with the engaged transmission of second largest gear 231, transmitting ratio I=40/18=2.2 between the two, provide high torsion, at this moment the rotating speed of second driving shaft 21 is also slower, and the output speed of engine pack reach certain in, get rid of block 24 to start to have an effect, it supports friction second miniature gears 232, when friction moment is greater than resistance torque, second driving shaft 21 obtains rotating speed by the engaged transmission of first gear 221 and the second miniature gears 232, transmitting ratio I=37/21=1.76 between the two, transmission is smaller, now second driving shaft 21 obtains higher rotating speed.By two groups of engaging gears, simultaneously under the effect of getting rid of block 24, transmitting ratio is changed, two kinds of different rotating speeds so both can be produced, and when transmitting ratio diminishes, higher transmission speed can be obtained, stabilize the outputting power of the engine unit of helicopter greatly.The described block that gets rid of is connected on described second driving shaft 21 by elastic component 25 elasticity, concrete is provided with an elastic component 25 on second driving shaft 21, described elastic component 25 comprises screw 251, spring 252 and the decorative pearl on top of an official cap 253, simultaneously on second driving shaft 21 sheathed one get rid of block 26, be provided with thread groove 261 getting rid of on block 26, screw 251 is connected with the thread groove 261 getting rid of block 26, described spring 252 one end is set in the end of clamp screw 251, the other end with get rid of block 24 and be connected, in order to the connection facilitating spring 252 further and get rid of between block 24, and can also get rid of between block 24 and be provided with a decorative pearl on top of an official cap 253 at spring 252, this decorative pearl on top of an official cap 253 part is positioned at gets rid of block 24, another part is positioned at spring 252, getting rid of on block 26 of second driving shaft 21 is connected to by getting rid of block elasticity like this by elastic component 25.The side of described second miniature gears 232 is formed with cylindrical cavity along second driving shaft 21, the described block 26 that gets rid of is installed in the cylindrical cavity of described second miniature gears 232, described get rid of block be connected to by elastic component 25 elasticity described in get rid of on block 26, when second driving shaft 21 slowly runs, get rid of block 26 to be positioned at by the elastic shrinkage effect of elastic component 25 and to get rid of on block 26 and rotate with second driving shaft 21, and when the rotating speed of second driving shaft 21 is raised to certain speed time, the centnifugal force getting rid of block 24 rotated with second driving shaft 21 is greater than the pulling force of elastic component 25, get rid of block 24 one end like this to start to depart from getting rid of block 26 and supporting friction with the cylindrical cavity inwall of the second miniature gears 232 of second driving shaft 21, the transmitting ratio between engine unit and clutch pack 2 is made to change (as mentioned above), and then stabilized speed transmission under helicopter rotation speed change faster situation.Further, in the cylindrical cavity of the second miniature gears 232, be provided with two backing pins 233, can prevent when high speed rotating, get rid of the cylindrical cavity inwall excessive slip of block 24 along the second miniature gears 232, larger friction moment is provided.On second driving shaft 21, be also arranged with a unilateral bearing 211, usually this unilateral bearing 211 is between second largest gear 231 and the second miniature gears 232, effectively can prevent the reversion of second driving shaft 21 simultaneously, plays the gear-driven effect of protection.Described first transmission shaft is also provided with overload protection device 27; specifically described overload protection device 27 is set in the front of reducing gear 28; for when reducing gear 28 is rotated too fast; ensure that the first gear cluster 22 can not rotate too fast with reducing gear 28, thus play the overload protective function of engine output power axle.

By described dynamic clutch output system 2, the dynamical stability that engine unit exports is passed to its second driving shaft 21, described second driving shaft 21 is connected to power-transmission system 4 further.As shown in accompanying drawing 5 (a)-5 (b), described power-transmission system 4 passes to tail rotor system 3 and main rotor system 1 for power distribution dynamic clutch output system 2 provided, and concrete described power-transmission system 4 comprises sun wheel input shaft 41, fixed gear ring 43, satellite gear 42, planet wheel spindle 44, pinion carrier 45, input gear 47, upper rotor gear assembly 49, lower rotor gear assembly 48 and tail rotor output gear component 46.Described sun wheel input shaft 41 is involute helical wheel shaft, and one end of described pinion carrier 45 is provided with main shaft, and described main shaft is shoulder axle, and the waist of main shaft is provided with spline, and the other end of described pinion carrier 45 is connected to three planet wheel spindles 44.Described fixed gear ring 43 entirety has circular ring structure, and circle ring inner surface is provided with inner circular tooth, described inner circular tooth is involute helical, annulus outer wall is provided with the shaft shoulder, circumferentially several keyways 431 uniform on the shaft shoulder, described satellite gear 42 corresponds to three planet wheel spindles 44 and includes three, and structure is identical and be involute helical gear, and satellite gear 42 central bore is provided with grid spacer 421.By described sun wheel input shaft 41, fixed gear ring 43, satellite gear 42, planet wheel spindle 44 and pinion carrier 45 be composition 2K-H skewed tooth planetary gear train jointly, concrete described pinion carrier 45, fixed gear ring 43, sun wheel input shaft 41 3 modular level ground is arranged, and the central axes of three components, fixed gear ring 43 is fixedly connected on body shell by the keyway 431 on the shaft shoulder, pinion carrier 45 is positioned at the left side of fixed gear ring 43, and the main shaft of pinion carrier 45 side is connected to input gear 47, the opposite side of pinion carrier 45 is fixedly connected on three planet wheel spindles 44, and three planet wheel spindles 44 stretch within fixed gear ring 43.Three satellite gears 42 are located on planet wheel spindle 44 respectively by the bearing carrier ring at respective Internal hole positioning dividing plate 421 two ends, and by lock screw axial restraint.The involute helical internal messing of three satellite gears 42 is on the inner circular tooth of fixed gear ring 43.Sun wheel input shaft 41 is positioned at the right side of fixed gear ring 43, and the involute helical of sun wheel input shaft 41 stretches in fixed gear ring 43, and external toothing is on the involute helical of three satellite gears 42.Described input gear 47 is connected on the main shaft of pinion carrier 45 by splined hole key, and passes through inner ring and sleeve 471 axial restraint of tapered roller bearing.Described upper rotor gear assembly 49, lower rotor gear assembly 48 are axle and the coaxial conjugant coiling tooth, and the head of axle is equipped with spline, to realize output shaft torque transmission.Described upper rotor gear assembly 49 comprises rotor toothed disc 491 and upper rotor gear wheel shaft 492, described upper rotor toothed disc 491 is disc structure and on neighboring, lower surface, is provided with screw conic tooth, the center of upper rotor toothed disc 491 is provided with axis hole, and the axle center of upper rotor gear wheel shaft 492 is provided with through hole and is communicated with the axis hole of upper rotor toothed disc 491; Described lower rotor gear assembly 48 comprises lower rotor toothed disc 481 and lower rotor gear wheel shaft 482, described lower rotor gear wheel shaft 482 is provided with shoulder, lower rotor toothed disc 481 is disc structure and on neighboring, upper surface, is provided with screw conic tooth, and lower rotor gear wheel shaft 482 is integrally connected to the center of lower rotor toothed disc 481.Described lower rotor gear assembly 48 is nested with upper rotor gear assembly 49 to combine, the lower rotor gear wheel shaft 482 of concrete described lower rotor gear assembly 48 is through the axis hole of upper rotor toothed disc 491 and the axle central through hole of upper rotor gear wheel shaft 492, and stretch out in outside rotor gear wheel shaft 492, and bearing is provided with between upper rotor gear wheel shaft 492 and lower rotor gear wheel shaft 482, the screw conic tooth of described lower rotor toothed disc 481 and upper rotor toothed disc 491 is just right, and the periphery, end of described lower rotor gear wheel shaft 482 and upper rotor gear wheel shaft 492 is provided with spline.Described input gear 47 is spiral bevel, and centre hole is splined hole, is connected with the main spindle multiple spline of pinion carrier 45.Described tail rotor output gear component 46 is spiral conical tooth shaft, and one end head is provided with spline, and to realize output shaft torque transmission, the front and back ends of its screw conic tooth is equipped with bearing neck.Described lower rotor gear assembly 48, upper rotor gear assembly 49 liang of components to lower and on be arranged on the left side of described 2K-H skewed tooth planetary gear train vertically, and the dead in line of two components.The addendum flank of the screw conic tooth of described input gear 47 is orthogonal to be engaged on the screw conic tooth of rotor toothed disc 491, on the orthogonal screw conic tooth being engaged in lower rotor toothed disc 481 of the dedendum flank of the screw conic tooth of described input gear 47.Described tail rotor output gear component 46 on even keel is arranged on the left side of lower rotor gear assembly 48, on the orthogonal screw conic tooth being engaged in lower rotor toothed disc 481 of the dedendum flank of the screw conic tooth of described tail rotor output gear component 46, the addendum flank of the screw conic tooth of described tail rotor output gear component 46 can be selected to arrange with the screw conic space of teeth of upper rotor toothed disc 491, or engagement orthogonal with it simultaneously, this depends on the requirement of tail rotor Power output.Such sun wheel input shaft 41 transmits input torque by 2K-H skewed tooth planetary gear train, drives input gear 47 to rotate and realizes the upper rotor gear assembly 49 of screw conic tooth differential gear train, the lower output torque of rotor gear assembly 48 contrarotation and the output torque of tail rotor output gear component 46.When described power-transmission system 4 is connected in described dynamic clutch output system 2, sun wheel input shaft 41 is connected to the second driving shaft 21 in power-transmission system 4, at second driving shaft 21, the rotational power of driving engine is passed to sun wheel input shaft 41, the gears meshing that rotates through of sun wheel input shaft 41 conducts to three satellite gears rotations, the rotation of satellite gear drives pinion carrier 45 to rotate, pinion carrier 45 by spline by the transmission of power of planet circular system to input gear 47, the two ends up and down of input gear 47 are engaged with rotor gear assembly 49 and lower rotor gear assembly 48 respectively, and lower rotor gear assembly 48 is nested is arranged in rotor gear assembly 49, thus the rotating through rotor gear assembly 49 and lower rotor gear assembly 48 and can realize contrarotation DCB Specimen and export of input gear 47, the main shaft 17 of described main rotor system 1 is connected to described lower rotor gear wheel shaft 482 or upper rotor gear wheel shaft 492 by spline is selectable, thus make main shaft can carry out selection switching between forward and contrarotation, to need according to the flight of helicopter to select rotor to turn to.Described tail rotor output gear component 46 obtains rotational power by engaging with lower rotor gear assembly 48 screw conic tooth simultaneously, and described tail rotor output gear component 46 and the tail power transmission shaft in tail rotor system 3 are by spline joint, thus the tail rotor system 3 that the power provided by driving engine is provided to according to the mode perpendicular with main rotor system 1.Further preferred the utility model lower rotor gear assembly 48 is nested be arranged in rotor gear assembly 49 time, the upper end of two rotor shaft is all castellated shafts, for Power output, in upper rotor gear assembly 49, the lower end of upper end, lower rotor gear assembly 48 is back-to-back is simultaneously provided with heavy cone coro bearng, and deep groove ball bearing is installed therebetween, realize the axial and circumferential location of DCB Specimen axle; In planetary gear train, sun wheel input shaft 41 is all involute helicals with satellite gear 42, fixed gear ring 43, and modulus is identical; Input gear 47 is all that screw conic tooth engages with upper rotor gear assembly 49, lower rotor gear assembly 48, tail rotor output gear component 46, and modulus is identical; Sun wheel input shaft 41, planet wheel spindle 44, lower rotor gear assembly 48, upper rotor gear assembly 49, tail rotor output gear component 46 are all hollow shafts, and object is the weight alleviating total.This power-transmission system of use of the utility model innovation is by high for spiral bevel transmission efficiency, vibration noise is low, the feature that load-carrying capacity is high and planet circular system compact conformation, transmitting ratio is large, carry uniform advantage to combine, high-speed helicopter main reduction gear high-mechanic can be met better, high pass efficiency, the performance characteristics such as low-vibration noise and compact conformation, the constructional feature of the large grade of transmitting ratio, the high-speed flight of high-speed helicopter and the requirement of powerful lifting power can be met, take off distance can be shortened again, unit design advantages of simple, installation and maintenance are convenient, vibration noise is low, load-carrying capacity is high.Spiral bevel system can solve the vertically arranged problem of geared rotor system well simultaneously, meets tail rotor system and the vertically arranged requirement of main rotor system power transmission shaft.

Finally the structure of the engine unit applied in helicopter described in the utility model is described, turbo-charging structure is introduced in the helicopter engine of the utility model innovation, by reference to the accompanying drawings shown in 6, described engine unit 900 comprises engine body 910, air compressor 920, turbo-machine 930, waste gas bleeding device 940 and by passage 914, described air compressor 920 is connected to the air inlet pipe 912 of engine body 910, and described turbo-machine 930 is connected to the freeing pipe 913 of engine body 910 and coaxial with air compressor 920.Described by passage 914 is communicated with freeing pipe 913 and in parallel and turbo-machine 930 both sides, and concrete by passage 914 is communicated with freeing pipe 913 the upstream and downstream that part lays respectively at turbo-machine 930.Between the air inlet pipe 912 that described waste gas bleeding device 940 is connected to described engine body 910 and by passage 914, concrete described waste gas bleeding device 940 comprises a pressure sensor 941, ECU (Electrical Control Unit) 942, vacuum solenoid 943, vacuum pump 944, venting actuator 945 and an aie escape valve 946.Described pressure sensor 941 is connected in engine body 910 air inlet pipe of described air compressor 920 downstream part, and be connected to described ECU (Electrical Control Unit) 942, described ECU (Electrical Control Unit) 942 can receive the signal that sensor 941 of calming the anger is monitored, described ECU (Electrical Control Unit) is connected to described vacuum solenoid 943, described vacuum solenoid 943 can receive the output signal of ECU (Electrical Control Unit) 942, and described vacuum solenoid 943 has a valve outlet port 947 and a valve import 948.The admission port of described vacuum pump 944 is connected with the valve outlet port 947 of vacuum solenoid 943.Described venting actuator 945 comprises a control end 949 and an operating side 950, and described control end 949 communicates with the valve import 948 of vacuum solenoid 943.Described aie escape valve 946 is arranged on by passage 914, and is connected with the operating side 950 of venting actuator 945, and is operated by operating side 950.The control end 949 of described venting actuator 945 is a bellows-type actuator, and operating side 950 is a drive link.In this turbocharger of motor of the present utility model, ECU (Electrical Control Unit) 942 can according to the size of the intake pressure received from pressure sensor 941, export control signal, control the work of vacuum solenoid 943, regulate the aperture of aie escape valve 946 by venting actuator 945.Such as, when engine operation process, the Boost-Pressure-Desired value that ECU (Electrical Control Unit) 942 can be obtained by engine calibration under the pressure that records of comparison pressure sensor 941 and this operating condition, when institute's measuring pressure is higher, aie escape valve 946 aperture can be increased, otherwise then reduce aie escape valve 946 aperture, realize regulating driving engine increase and decrease pressure.

The utility model passes through the main rotor system included by helicopter, dynamic clutch output system, tail rotor system, power conveying system unify engine unit carry out simultaneously innovation improve, the main rotor system of described helicopter and tail rotor system is made to have stabilized rotation drive ability, while raising engine unit outputting power, the outputting power of driving engine under different rotating speeds is stabilized by the dynamic clutch output system adjustment transmitting ratio of original creation, and exported by the transmission achieving orthogonal rotary power that innovative impetus transmission system is stable, thus by engine power stable delivery to main rotor system and tail rotor system, greatly stabilize the power distribution of helicopter, thered is provided fuel oil depopulated helicopter is made to meet the condition of small size smooth operation, the innovation realization ultramicroscopic fuel oil depopulated helicopter of fuselage length below 1 meter first, can reach through overtesting fuel oil depopulated helicopter provided by the utility model minimum size: fuselage length 760mm, height 225mm, width 110mm.

Below be only that preferred implementation of the present utility model is described; the technical solution of the utility model is not limited to this; the any known distortion that those skilled in the art do on the basis that major technique of the present utility model is conceived all belongs to the claimed technology category of the utility model, and the concrete protection domain of the utility model is as the criterion with the record of claims.

Claims (7)

1. a superminiature fuel oil depopulated helicopter, it is characterized in that, comprise main rotor system (1), dynamic clutch output system (2), tail rotor system (3), power-transmission system (4), empennage connecting rod (5), fuselage (6), rise and fall support (7) and blade (8), rise and fall described in the bottom connection of described fuselage (6) support (7), described dynamic clutch output system (2) and power-transmission system (4) are arranged in described fuselage (6), described power-transmission system (4) is connected to described dynamic clutch output system (2), described tail rotor system (3) and main rotor system (1) are connected to described power-transmission system (4), described main rotor system (1) is arranged at body upper, described tail rotor system (3) is connected to afterbody by empennage connecting rod (5), described main rotor system (1) and tail rotor system (3) are connected with blade (8),

Described main rotor system (1) comprises metal rotor head drg (10), left-handed wing holder (11), dextrorotation wing holder (12), rotor permanent center seat (13), connecting rod (14), cross plate (15), supporting disk (16) and main shaft (17), described rotor permanent center seat (13) comprises sleeve (132), be arranged at the transverse axis (131) in sleeve, be connected to the base (133) of sleeve bottom side, described base (133) middle part offers the through hole passed for main shaft (17), described left-handed wing holder (11) is the same with dextrorotation wing holder (12) structure, include permanent seat (121) and rocking arm (123), described rocking arm (123) self-retaining seat (121) sidewall is outwardly arranged, described permanent seat (121) offers the screw hole run through vertically, the outer end of described permanent seat offers clip slot (122), described clip slot (122) is for installing blade (8), the permanent seat of described left-handed wing holder (11) is fixedly connected on the left end of described transverse axis (131) by pad and check screw, and between transverse axis (131) and permanent seat, be provided with transverse axis packing ring (134) and transverse axis aluminium cover (135), the permanent seat of described dextrorotation wing holder (12) is fixedly connected on the right-hand member of described transverse axis (131) by pad and check screw, and between transverse axis (131) and permanent seat, be provided with transverse axis packing ring (134) and transverse axis aluminium cover (135), and the rocking arm on described left-handed wing holder (11) and the sub rocker arm other places on dextrorotation wing holder (12) are in the both sides of the sleeve (132) of rotor permanent center seat (13), described rocking arm is connected to described cross plate (15) by described connecting rod (14), described cross plate (15) is arranged on described supporting disk (16), the central authorities of described cross plate (15) are provided with cardan wheel (152), (152) offer centre hole to described cardan wheel, described supporting disk (16) is connected to fuselage, and described main shaft (17) is through being fixedly connected in the through hole of described rotor permanent center seat (13) base (133) after the centre hole of described supporting disk (16) and cardan wheel, described metal rotor head drg (10) is arranged on the sleeve (132) of described rotor permanent center seat (13),

Described tail rotor system (3) comprises the left holder of tail rotor (31), the right holder of tail rotor (32), tail control group (33), tail rotor control assembly (34) and tail power-transmission system (35), the left holder of described tail rotor (31) comprises the first permanent seat (317), the middle part of described first permanent seat (317) offers connecting through hole, the left end of described first permanent seat (317) offers the first clip slot (311), described first clip slot (311) is for installing blade (8), the upside of described first permanent seat (317) is outwards integrally outstanding is formed with the first rocking arm (312), the central authorities of described first rocking arm (312) offer screw hole, the left and right sides of described first permanent seat (317) is outwardly formed with control fin, the right holder of described tail rotor (32) comprises the second permanent seat (325) and Connection Block (321), described Connection Block (321) radially offers tailing axle perforation, one end of described second permanent seat (325) connects described Connection Block (321), the other end of described second permanent seat (325) offers the second clip slot (322), described second clip slot (322) is for installing blade (8), the downside of described second permanent seat (325) is outwards integrally outstanding is formed with the second rocking arm (323), the central authorities of described second rocking arm (323) offer screw hole, the left and right sides of described second permanent seat (325) is outwardly formed with control fin, (321) offer threaded connection hole to described Connection Block, pass the connecting through hole of the first permanent seat (317) by screw and be threadedly connected in the threaded connection hole on Connection Block (321) and left for described tail rotor holder (31) is fixedly connected on the right holder of described tail rotor (32), and make described first rocking arm (312) and the second rocking arm (323) be in upper and lower both sides, described tail control group (33) comprises bearing seat aluminium liner (331), first tail control link head (332), second tail control link head, bearing block set (336), tailing axle sliding sleeve (337) and some screws, one end of described first tail control link head (332) is screwed the upper end being connected to bearing seat aluminium liner (331), the other end of described first tail control link head (332) is screwed the screw hole being connected to the first rocking arm (312), one end of described second tail control link head (332) is screwed the lower end being connected to bearing seat aluminium liner (331), the other end of described second tail control link head (332) is connected to the screw hole of the second rocking arm (323) by screw, the central authorities of described bearing seat aluminium liner (331) offer through hole, described bearing block set (336) and tailing axle sliding sleeve (337) central authorities all offer axis hole, and described tailing axle sliding sleeve (337) is through being connected on described bearing seat aluminium liner (331) after described bearing block set (336), described tail power-transmission system (35) comprises tail power transmission shaft, tailing axle (351), sleeve bearing (352), horizontal rotor gear (353) and longitudinal rotor gear (354), described tail power transmission shaft is connected to horizontal rotor gear (353) through after sleeve bearing (352), described longitudinal rotor gear (354) Vertical Meshing is on described horizontal rotor gear (353), one end of described tailing axle (351) is fixedly connected on described longitudinal rotor gear (354), the other end of described tailing axle (351) is successively through being fixedly connected in the tailing axle that the Connection Block (321) of the right holder of described tail rotor (32) is offered bores a hole after the central through hole of described tailing axle sliding sleeve (337) and bearing seat aluminium liner (331), described tail rotor control assembly (34) comprises I-shaped arm (341), regulation and control arm (342), Connection Block (343) and some screws (344), described regulation and control arm (342) is integrally connected to the bottom of I-shaped arm (341), described Connection Block (343) is connected between the upper lower branch arm of described I-shaped arm (341) side by screw (344), and the upper lower branch arm of described I-shaped arm (341) opposite side is connected to described bearing block set (336) by screw (344),

Described dynamic clutch output system (2) comprises clutch pack (20), described clutch pack (20) comprises the first transmission shaft (29), second driving shaft (21), first gear cluster (22), second gear cluster (23), get rid of block (24), elastic component (25), get rid of block (26), overload protection device (27) and reducing gear (28), described first gear cluster (22) is installed on the first transmission shaft (29), and comprise coaxial first gear (221) and the first miniature gears (222), described second gear cluster (23) is installed on described second driving shaft (21), and comprise coaxial second largest gear (231) and the second miniature gears (232), described first gear (221) is engaged with described second miniature gears (232), described first miniature gears (222) is engaged with described second largest gear (231), described reducing gear (28) is installed on described first transmission shaft (29) and goes up and be connected with a joggle with the power take-off shaft of engine unit (900), the side of described second miniature gears (232) is formed with cylindrical cavity along second driving shaft (21), be provided with in described cylindrical cavity and get rid of block (26), described get rid of block (26) is elasticly connected with by elastic component (25) described in get rid of block (24), when second driving shaft (21) slowly runs, described get rid of block (26) fit in described in get rid of block (26) upper and rotate with second driving shaft (21), when the rotating speed of second driving shaft (21) is raised to a certain degree, the described block (26) that gets rid of starts disengaging and gets rid of block (26) and support the inwall rubbed in described cylindrical cavity, described overload protection device (27) is arranged on described first transmission shaft (29),

Described power-transmission system (4) comprises sun wheel input shaft (41), fixed gear ring (43), satellite gear (42), planet wheel spindle (44), pinion carrier (45), input gear (47), upper rotor gear assembly (49), lower rotor gear assembly (48) and tail rotor output gear component (46), described sun wheel input shaft (41) is involute helical wheel shaft, the side of described pinion carrier (45) is provided with shoulder main shaft, the waist of shoulder main shaft is provided with spline, the opposite side of described pinion carrier (45) is connected with three planet wheel spindles (44), described fixed gear ring (43) has circular ring structure, and circle ring inner surface is provided with inner circular tooth, described inner circular tooth is involute helical, described satellite gear (42) includes three corresponding to three planet wheel spindles (44), structure is identical and be involute helical gear, by described sun wheel input shaft (41), fixed gear ring (43), satellite gear (42), planet wheel spindle (44) and pinion carrier (45) composition 2K-H skewed tooth planetary gear train, described pinion carrier (45), fixed gear ring (43), sun wheel input shaft (41) is horizontally disposed with and central axes, the shoulder main shaft of pinion carrier (45) side is connected to input gear (47), three planet wheel spindles (44) of pinion carrier (45) opposite side are connected to three satellite gears (42) by bearing, the involute helical internal messing of described satellite gear (42) is on the inner circular tooth of fixed gear ring (43), the involute helical external toothing of described sun wheel input shaft (41) is on the involute helical of three satellite gears (42), described upper rotor gear assembly (49) comprises rotor toothed disc (491) and upper rotor gear wheel shaft (492), described upper rotor toothed disc (491) is for disc structure and be provided with screw conic tooth on neighboring, lower surface, described upper rotor gear wheel shaft (492) is connected to the central authorities of rotor toothed disc (491) and is provided with axially extending bore, described lower rotor gear assembly (48) comprises lower rotor toothed disc (481) and lower rotor gear wheel shaft (482), described lower rotor toothed disc (481) is for disc structure and be provided with screw conic tooth on neighboring, upper surface, described lower rotor gear wheel shaft (482) is connected to the central authorities of lower rotor toothed disc (481) and stretches into the axially extending bore of described upper rotor gear wheel shaft (492), described input gear (47) and tail rotor output gear component (46) are spiral conical tooth shaft, on the orthogonal screw conic tooth being engaged in rotor toothed disc (491) of screw conic tooth addendum flank of described input gear (47), on the orthogonal screw conic tooth being engaged in lower rotor toothed disc (481) of the screw conic tooth dedendum flank of described input gear (47), on the orthogonal screw conic tooth being engaged in lower rotor toothed disc (481) of the screw conic tooth dedendum flank of described tail rotor output gear component (46), described sun wheel input shaft (41) is connected to the second driving shaft (21) in power-transmission system (4), the main shaft (17) of described main rotor system (1) by spline joint in described lower rotor gear wheel shaft (482) or described upper rotor gear wheel shaft (492), described tail rotor output gear component (46) is connected with the tail power transmission shaft in tail rotor system (3),

Described engine unit (900) comprises engine body (910), air compressor (920), turbo-machine (930), waste gas bleeding device (940) and by passage (914), described air compressor (920) is connected to the air inlet pipe (912) of engine body (910), described turbo-machine (930) is connected to the freeing pipe (913) of engine body (910) and coaxial with air compressor (920), described by passage (914) be communicated with freeing pipe (913) and by passage (914) and freeing pipe (913) be communicated with the upstream and downstream that part lays respectively at turbo-machine (930), described waste gas bleeding device (940) is connected between the air inlet pipe (912) of described engine body (910) and by passage (914), described waste gas bleeding device (940) comprises pressure sensor (941), ECU (Electrical Control Unit) (942), vacuum solenoid (943), vacuum pump (944), venting actuator (945) and aie escape valve (946), described pressure sensor (941) is arranged in engine body (910) air inlet pipe of described air compressor (920) downstream part, and be connected to described ECU (Electrical Control Unit) (942), described ECU (Electrical Control Unit) is connected to described vacuum solenoid (943), described vacuum solenoid (943) has a valve outlet port (947) and a valve import (948), the admission port of described vacuum pump (944) is connected with described valve outlet port (947), described venting actuator (945) comprises a control end (949) and an operating side (950), described control end (949) communicates with the valve import (948) of vacuum solenoid (943), described aie escape valve (946) is arranged on described by passage (914), and be connected with the operating side (950) of venting actuator (945).

2. superminiature fuel oil depopulated helicopter according to claim 1, it is characterized in that, connecting rod (14) in described main rotor system (1) comprises the body of rod (141), bearing (143), check screw (145) and aluminium cover (146), the top of the described body of rod (141) is provided with upper connecting base (144), the bottom of the described body of rod is provided with lower connecting base (142), the middle part of described upper connecting base (144) and lower connecting base (142) offers through hole, the rocking arm of described left-handed wing holder (11) and dextrorotation wing holder (12) is provided with tapped bore, described check screw (145) is through bearing (143), upper connecting base (144) middle through-hole, aluminium cover (146) rear thread is connected in the tapped bore of rocking arm, described cross plate (15) has circular ring, annulus central authorities are provided with described cardan wheel (152), described main shaft (17) slides through the centre hole that described cardan wheel (152) is offered, the periphery of described cross plate (15) is provided with connection lug, described connection lug is connected with movable bulb (151), the through hole that described movable bulb (151) is in described lower connecting base (142) is interior to be movably connected on described cross plate (15) by described connecting rod (14).

3. superminiature fuel oil depopulated helicopter according to claim 1 and 2, it is characterized in that, elastic component (25) in described dynamic clutch output system (2) comprises screw (251), spring (252) and the decorative pearl on top of an official cap (253), the described block (26) that gets rid of is provided with thread groove (261), described screw (251) and thread groove (261) are connected, one end of described spring (252) is set in the end of described screw (251), the other end of described spring is connected to the described decorative pearl on top of an official cap (253), block (24) is got rid of described in the described decorative pearl on top of an official cap (253) is connected to.

4. superminiature fuel oil depopulated helicopter according to claim 3, it is characterized in that, two backing pins (233) are provided with in the cylindrical cavity of described second miniature gears (232), described second driving shaft (21) is arranged with unilateral bearing (211), described unilateral bearing (211) is between described second largest gear (231) and the second miniature gears (232); Described overload protection device (27) is arranged at the front of described reducing gear (28).

5. the superminiature fuel oil depopulated helicopter according to claim 1,2 or 4, it is characterized in that, in described power-transmission system (4), the annulus outer wall of described fixed gear ring (43) is provided with the shaft shoulder, circumferentially uniform several keyways (431) on the shaft shoulder, are fixedly connected on body shell by described keyway (431) by fixed gear ring (43); The central bore of described satellite gear (42) is provided with grid spacer (421), and described satellite gear (42) is located on planet wheel spindle (44) by the bearing carrier ring of grid spacer (421) both sides, and by lock screw axial restraint.

6. superminiature fuel oil depopulated helicopter according to claim 1, is characterized in that, in described engine unit (900), the control end (949) of venting actuator (945) is a bellows-type actuator, and operating side (950) are a drive link.

7. superminiature fuel oil depopulated helicopter according to claim 1, is characterized in that, the length of described fuselage (6) is 760mm, highly for 225mm, width are 110mm, the entire length of fuel oil depopulated helicopter is within 1 meter.