CN103791029B - Transmission system of unmanned rotor wing helicopter - Google Patents

Transmission system of unmanned rotor wing helicopter Download PDF

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Publication number
CN103791029B
CN103791029B CN201410074420.4A CN201410074420A CN103791029B CN 103791029 B CN103791029 B CN 103791029B CN 201410074420 A CN201410074420 A CN 201410074420A CN 103791029 B CN103791029 B CN 103791029B
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China
Prior art keywords
gear
main shaft
concentric
driven
shaft
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CN201410074420.4A
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Chinese (zh)
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CN103791029A (en
Inventor
李建伟
赵泓波
赵曙光
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QINGDAO HONG BAICHUAN METAL PRECISION PRODUCTS Co Ltd
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QINGDAO HONG BAICHUAN METAL PRECISION PRODUCTS Co Ltd
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Priority to CN201410074420.4A priority Critical patent/CN103791029B/en
Publication of CN103791029A publication Critical patent/CN103791029A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/02—Toothed gearings for conveying rotary motion without gears having orbital motion
    • F16H1/20—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members
    • F16H1/203—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with non-parallel axes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/038—Gearboxes for accommodating bevel gears

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

The invention relates to a transmission system of an unmanned rotor wing helicopter. The transmission system comprises a drive shaft, a concentric drive gear, a driven shaft, a concentric driven gear, a concentric main shaft gear A and a concentric main shaft gear B. The concentric drive gear is fixedly arranged at the output end of the drive shaft, the concentric driven gear is fixedly arranged at the input end of the driven shaft, the concentric main shaft gear A penetrates through a main shaft and is fixedly connected with the main shaft, and the concentric main shaft gear B is located below the main shaft gear A, penetrates through the main shaft and is movably connected with the main shaft. The unmanned rotor wing helicopter comprises a rotor wing head and the main shaft fixedly connected with the rotor wing head. The main shaft gear A, the main shaft gear B, the drive gear and the driven gear are spiral beveled gears. The drive gear and the driven gear are symmetrically arranged in a concentric mode, the main shaft gear A is respectively meshed with the drive gear and the driven gear, and the main shaft gear B is respectively meshed with the drive gear and the driven gear. Mutual offset of force is achieved, gear abrasion is reduced, stability of the transmission system is improved, service life of the device is prolonged, and production cost is reduced.

Description

The drive system of unmanned rotary wing helicopter
Technical field
The invention belongs to the art drive systems field of aircraft, specifically, being related to one kind, to be applied to unmanned rotary wing straight The drive system of the machine of liter.
Background technology
The drive system of existing unmanned rotary wing helicopter is to enter action edge transmission by the way of ratchet transmission, its knot Structure is fairly simple.The driving force of unmanned rotary wing lifting airscrew is larger, simultaneously gear engagement when also can produce larger torsion and Stress, the time one is long, the situation of the even tired broken teeth of gear shifting quadrant texturing, abrasion easily, substantially reduces unmanned rotary wing and go straight up to The service life of machine, even results in the generation of security incident.
Content of the invention
For solving above-mentioned technical problem, the present invention proposes a kind of gear that eliminates and engages torsion and stress, reduces gear grinding Damage, reduce gear tooth breakage risk, be applied to the drive system of unmanned rotary wing helicopter.
The technical scheme is that a kind of drive system of unmanned rotary wing helicopter, described unmanned rotary wing helicopter bag Include the rotor head main shaft affixed with rotor head.Described drive system includes driving shaft, is fixedly installed on the same of driving shaft outfan Heart driving gear, driven shaft, be fixedly installed on the concentric driven gear of driven shaft input, through on described main shaft and with Concentric mainshaft gear a that main shaft is fixedly connected and be located at below described mainshaft gear a, through on described main shaft and with master The concentric mainshaft gear b that axle is flexibly connected.Described mainshaft gear a, mainshaft gear b, driving gear and driven gear are spiral Bevel gear.Described driving gear and driven gear centrosymmetric setting, described mainshaft gear a respectively with described driving gear and from Moving gear engages, and described mainshaft gear b is engaged with described driving gear and driven gear respectively.Described driving gear, main shaft tooth Take turns a, driven gear, engaging becomes symmetrical closed-system to mainshaft gear b two-by-two, ratchet in prior art is driven by this structure When the torsion that bears of gear and stress dispersed to driving gear and driven gear, realize cancelling out each other of power, decrease Gear wear, increased the stability of drive system.
Described mainshaft gear b is connected with described main shaft by bearing.
Described mainshaft gear a, mainshaft gear b, driving gear and driven gear outer cladding setting lock case.
It is respectively equipped with dividing plate, dividing plate is the positioner of mast, effect is to main shaft above and below described lock case It is fixed and support.
The beneficial effects of the present invention is: solve the torsion that when ratchet is driven in prior art, gear bears and answer The technical problem of the gear wear that power Relatively centralized leads to, the present invention is by dispersed to this part torsion and stress to driving gear On driven gear, realize cancelling out each other of power, decrease gear wear, increased the stability of drive system, extend dress The service life put, reduces production cost.
Brief description
Fig. 1 is the structural representation of the present invention.
Wherein, 1, rotor head；2nd, main shaft；3rd, mainshaft gear a；4th, driving gear；5th, driving shaft；6th, lock case；7th, main shaft tooth Wheel b；8th, driven shaft；9th, driven gear；10th, bearing.
Specific embodiment
Illustrate the present invention below in conjunction with drawings and Examples.
As shown in Figure 1: the present invention is the drive system being applied to unmanned rotary wing helicopter, unmanned rotary wing helicopter includes revolving Wing head 1 main shaft 2 affixed with rotor head 1, drive system includes driving shaft 5, is fixedly installed on the concentric of driving shaft 5 outfan Driving gear 4, driven shaft 8, be fixedly installed on the concentric driven gear 9 of driven shaft 8 input, through on main shaft 2 and with master The concentric mainshaft gear a3 that axle 2 is fixedly connected, below mainshaft gear a3, through on main shaft 2 and with main shaft 2 activity even The concentric mainshaft gear b7 connecing, mainshaft gear a3, mainshaft gear b7, driving gear 4 and driven gear 9 are spiral bevel gear； Driving gear 4 and the setting of driven gear 9 centrosymmetric, mainshaft gear a3 is engaged with driving gear 4 and driven gear 9 respectively, main Shaft gear b7 is engaged with driving gear 4 and driven gear 9 respectively.Driving gear 4, mainshaft gear a3, driven gear 9, main shaft tooth Engaging becomes symmetrical closed-system to wheel b7 two-by-two, this structure by prior art during ratchet transmission the torsion that bears of gear and Stress dispersed to driving gear 4 and driven gear 9, realize cancelling out each other of power, decrease gear wear, increased biography The stability of dynamic system.
Mainshaft gear b7 is connected with main shaft 2 by bearing 10.
Mainshaft gear a3, mainshaft gear b7, driving gear 4 and driven gear 9 outer cladding setting lock case 6.
It is respectively equipped with dividing plate 11 above and below lock case 6.Dividing plate is the positioner of mast 2, and effect is to main shaft 2 It is fixed and support.
The work process of the present invention is as follows:
During the operation in the air of unmanned rotary wing helicopter, the electromotor of driving shaft 5 provides power, driving shaft 5 high-speed rotation, master Moving gear 4 is engaged rotation with mainshaft gear a3 and mainshaft gear b7 respectively, drives driven gear 9 to rotate simultaneously.As shown in figure 1, Assume that driving shaft rotates along shown by arrow direction, drive driving gear 4 rotating Vortex simultaneously, mainshaft gear a3 revolves from left to right Turn, drive rotor head 1 rotating Vortex, drive driven gear 9 to rotate in the opposite direction by 5 turns with driving shaft simultaneously.

Claims (4)

1. a kind of drive system of unmanned rotary wing helicopter, described unmanned rotary wing helicopter includes rotor head (1) and rotor head (1) affixed main shaft (2) it is characterised in that: described drive system includes driving shaft (5), be fixedly installed on driving shaft (5) output The concentric driving gear (4) at end, driven shaft (8), it is fixedly installed on the concentric driven gear (9) of driven shaft (8) input, run through The concentric mainshaft gear a (3) being fixedly connected on main shaft (2) and with main shaft (2), and be located at below mainshaft gear a (3), pass through It is through at the concentric mainshaft gear b (7) that main shaft (2) is upper and is flexibly connected with main shaft (2)；Described mainshaft gear a (3), mainshaft gear B (7), driving gear (4) and driven gear (9) are spiral bevel gear；Driving gear (4) and driven gear (9) centrosymmetric Setting, mainshaft gear a (3) engaged with driving gear (4) and driven gear (9) respectively, mainshaft gear b (7) respectively with driving tooth Wheel (4) and driven gear (9) engagement.
2. the drive system of unmanned rotary wing helicopter according to claim 1 is it is characterised in that institute mainshaft gear b (7) leads to Cross bearing (10) to be connected with main shaft (2).
3. unmanned rotary wing helicopter according to claim 1 drive system it is characterised in that institute mainshaft gear a (3), Mainshaft gear b (7), driving gear (4) and driven gear (9) outer cladding setting lock case (6).
4. the drive system of unmanned rotary wing helicopter according to claim 3 is it is characterised in that above described lock case (6) Be respectively arranged below with dividing plate (11).
CN201410074420.4A 2014-03-03 2014-03-03 Transmission system of unmanned rotor wing helicopter Active CN103791029B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410074420.4A CN103791029B (en) 2014-03-03 2014-03-03 Transmission system of unmanned rotor wing helicopter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410074420.4A CN103791029B (en) 2014-03-03 2014-03-03 Transmission system of unmanned rotor wing helicopter

Publications (2)

Publication Number Publication Date
CN103791029A CN103791029A (en) 2014-05-14
CN103791029B true CN103791029B (en) 2017-01-18

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104787323A (en) * 2015-04-01 2015-07-22 天峋创新（北京）科技有限公司 Unmanned helicopter transmission mechanism with combination of synchronous belt and wet type speed reducer
CN106812924A (en) * 2017-02-21 2017-06-09 陈洁 A kind of transmission case for inside small size lathe
CN107380412A (en) * 2017-05-27 2017-11-24 天津曙光天成科技有限公司 A kind of twin-engined depopulated helicopter deceleration transmission systems and depopulated helicopter

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2546207A1 (en) * 2006-05-08 2007-11-08 Guangming Minc He Flying vehicle
CN201148211Y (en) * 2007-10-12 2008-11-12 刘世英 Helicopter main shaft oscillation transmission mechanism
CN201209648Y (en) * 2008-06-13 2009-03-18 河北理工大学 Transmission mechanism of aeromodelling helicopter
CN203743312U (en) * 2014-03-03 2014-07-30 青岛宏百川金属精密制品有限公司 Transmission system for unmanned rotor wing helicopter

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090057481A1 (en) * 2007-08-29 2009-03-05 Charles Lin Dual-Power Transmission Device for a Twin-Rotor Helicopter

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2546207A1 (en) * 2006-05-08 2007-11-08 Guangming Minc He Flying vehicle
CN201148211Y (en) * 2007-10-12 2008-11-12 刘世英 Helicopter main shaft oscillation transmission mechanism
CN201209648Y (en) * 2008-06-13 2009-03-18 河北理工大学 Transmission mechanism of aeromodelling helicopter
CN203743312U (en) * 2014-03-03 2014-07-30 青岛宏百川金属精密制品有限公司 Transmission system for unmanned rotor wing helicopter

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