CN106314785B - A kind of coaxial dual-rotor helicopter - Google Patents
A kind of coaxial dual-rotor helicopter Download PDFInfo
- Publication number
- CN106314785B CN106314785B CN201610758288.8A CN201610758288A CN106314785B CN 106314785 B CN106314785 B CN 106314785B CN 201610758288 A CN201610758288 A CN 201610758288A CN 106314785 B CN106314785 B CN 106314785B
- Authority
- CN
- China
- Prior art keywords
- output shaft
- shaft
- fuselage
- auricle
- bevel gear
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 16
- 238000005192 partition Methods 0.000 claims description 13
- 210000005069 ears Anatomy 0.000 claims description 6
- 239000000725 suspension Substances 0.000 claims description 4
- 238000010276 construction Methods 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B64D27/40—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/04—Power-plant nacelles, fairings, or cowlings associated with fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The present invention relates to a kind of coaxial dual-rotor helicopters, mainly it is made of fuselage, power device and operating-controlling mechanism, bracket is connected and fixed by universal rotating shaft mechanism in fuselage, the input shaft that transmitter connects retarder with clutch is passed sequentially through on fixed bracket, retarder is two output shafts of coaxial arrangement, the top of interior output shaft connects upper propeller aircraft by the auricle of propeller hub, lower propeller aircraft is connected by the auricle of propeller hub at the top of outer output shaft, and interior output shaft is opposite with the direction of rotation of outer output shaft；In 6 °~15 ° angles between propeller hub auricle and rotation axis at the top of interior output shaft and outer output shaft, and upper and lower two propeller hubs auricle is oppositely oriented.The aircraft uses the trimmer with double freedom to assist the flight attitude of adjustment aircraft and fuselage is kept to stablize, and effectively reduces the complexity of rotor head, keeps airframe structure eased, reduce the resistance of aircraft, improves flight efficiency.
Description
Technical field
The present invention relates to a kind of coaxial dual-rotor helicopters, belong to one kind of aircraft.
Background technique
Coaxial rotor unmanned plane, with compact-sized, mobility is excellent, moves needed for high reliablity, specific lift
The advantages such as power is low, at present research work of the every country all in positive development to coaxial unmanned plane in the world.But coaxial nothing
It is man-machine that in flying quality and flight safety design aspect, there are certain difficult points.Such as rotor head structure is complicated, components are more,
The disadvantages of resistance is big, upper and lower rotor is easy to happen collision in mobile process.This patent is by grinding traditional coaxal helicopter
Study carefully, improves rotor header structure, airframe structure, torque adjustment mode of coaxial unmanned plane etc. and solve the above problem.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of coaxial dual-rotor helicopter, which is used with double
The trimmer of freedom degree is stablized come the flight attitude and holding fuselage for assisting adjustment aircraft, instead of traditional change propeller
Pitch control flight attitude, effectively reduce the complexity of rotor head, keep airframe structure eased, reduce winged
The resistance of row device improves flight efficiency.
In order to solve the above problem, the specific technical solution of the present invention is as follows: a kind of coaxial dual-rotor helicopter, mainly by machine
Body, power device and operating-controlling mechanism composition, are connected and fixed bracket by universal rotating shaft mechanism in fuselage, fix on bracket successively
The input shaft of retarder is connected with clutch by transmitter, retarder is two output shafts of coaxial arrangement, interior output shaft
Top connects upper propeller aircraft by the auricle of propeller hub, and the auricle for passing through propeller hub at the top of outer output shaft connects lower rotor spiral
Paddle, and interior output shaft is opposite with the direction of rotation of outer output shaft；Propeller hub auricle and rotary shaft at the top of interior output shaft and outer output shaft
It is in 6 °~15 ° angles between line, and upper and lower two propeller hubs auricle is oppositely oriented.
The fixation bracket is cross-shaped structure, is started respectively by engine support connection at fixed four angles of bracket
Machine, the output shaft of each engine pass through clutch respectively and connect with retarder.
The reducer structure is that four input shafts are axis in same level, and are in the umbrella tooth of cross distribution
Axis, bevel gear shaft is through bearing support in the shell of retarder, and the upper end of four bevel gear shafts is engaged with upper bevel gear jointly, lower end
It is engaged jointly with lower bevel gear；Interior output shaft and outer output shaft are arranged by coaxial bearing in shell output end, China and foreign countries' output
The bottom end of axis is connect by bolt with upper bevel gear, and the bottom end of interior output shaft is engaged by key with lower bevel gear.
The external fuselage is spheroidal radome fairing, and inside is support construction, is uniformly distributed in the outer surface of radome fairing
Several, each trimmer is along trimmer axis deflection.
The universal rotating shaft mechanism structure is, the ears piece of support arm upper end by swinging block in middle swinging block axis connection, in
The upper end ears piece of swinging block connects swinging block on universal shaft by upper swinging block shaft, is equipped with swing arm, swing arm on swinging block on universal shaft
Both ends be separately connected one end of connecting rod, the other end of connecting rod passes through the output axis connection of steering engine rocker arm and steering engine.
The fuselage interior is equipped with several frames and forms semicircular cavities structure, and upper partition is equipped in cavity under
Layer partition, universal rotating shaft mechanism is connected in upper partition, and fuel tank is arranged in lower partition.
The bottom of the frame is equipped with cargo hold suspension hook.
The bottom of the fuselage is equipped with undercarriage, and structure is that undercarriage principal arm circumference uniform distribution rises and falls in fuselage bottom
Frame principal arm connects footing plate by damper.
The coaxial dual-rotor helicopter uses the twin screw wing head driven using inside and outside output shaft, reduces air drag,
It is compact-sized simple, improve safety；Using fixed propeller hub, propeller collision is asked up and down when avoiding aircraft motor-driven
Topic.
It supports four engines to pass through clutch respectively using engine support to connect with retarder, it can be using four hairs
Any combination of motivation drives outer output shaft and interior output shaft, not only ensure that the general safety performance of aircraft, while real
Show that torque is big, high advantage of doing work to save fuel, while realizing power redundancy.
It is spheroidal radome fairing outside body and is provided with trimmer, the not qualitative of flight may be implemented, operate more flexible.
It partition is set on fuselage, realizes the separation in space, realizes different functional areas, suspension hook 26 is completed to lift.
The bottom of fuselage is equipped with undercarriage and rises and falls safer with shock-absorbing function.
Detailed description of the invention
Fig. 1 is the overall structure diagram of coaxial dual-rotor helicopter.
Fig. 2 is the structural schematic diagram of power device.
Fig. 3 is retarder schematic diagram of internal structure.
Fig. 4 is the structural schematic diagram of universal rotating shaft mechanism.
Fig. 5 is fuselage interior structural schematic diagram.
Fig. 6 is landing gear structure schematic diagram.
Specific embodiment
As shown in Figure 1, a kind of coaxial dual-rotor helicopter, is mainly made of fuselage, power device and operating-controlling mechanism, in machine
Bracket 7 is connected and fixed by universal rotating shaft mechanism in body, transmitter is passed sequentially through on fixed bracket 7 and connects retarder with clutch
3 input shaft, retarder 3 are two output shafts of coaxial arrangement, the auricle connection three that the top of interior output shaft 13 passes through propeller hub 1
On piece propeller aircraft 2 connects propeller aircraft 9 under three pieces, and interior output shaft by the auricle of propeller hub 1 at the top of outer output shaft 12
13 is opposite with the direction of rotation of outer output shaft 12；Interior output shaft 13 and outer 12 top propeller hub of output shaft, 1 auricle and rotation axis it
Between be in 6 °~15 ° angles, optimal angle is 10 ° of angles, and upper and lower two propeller hubs, 1 auricle is oppositely oriented.
As shown in Fig. 2, the fixation bracket 7 is cross-shaped structure, pass through engine respectively at fixed 7 four angles of bracket
Bracket 6 connects engine 5, and the output shaft of each engine 5 passes through clutch 4 respectively and connect with retarder 3.Four have been started together
Shi Zuowei power mechanism, powerful, while several engines can be turned off when moving horizontally, realize power redundancy, together
When can also be in some engine failure, remaining engine normally drives unmanned plane during flying, realizes the security performance of flight.
As shown in figure 3,3 structure of retarder is, four input shafts are axis in same level, and are in cross
The bevel gear shaft 31 of distribution, for bevel gear shaft 31 through bearing support in the shell 30 of retarder 3, the upper end of four bevel gear shafts 31 is common
It is engaged with upper bevel gear 32, lower end is engaged with lower bevel gear 33 jointly；Interior output shaft 13 passes through coaxial bearing with outer output shaft 12
Setting is connect by bolt 34 with upper bevel gear 32 in 30 output end of shell, the bottom end of China and foreign countries' output shaft 12, interior output shaft 13
Bottom end engaged with lower bevel gear 33 by key 35.Since lower bevel gear 33 is engaged with bevel gear shaft 31 jointly with upper bevel gear 32,
To realize the opposite direction of interior output shaft 13 and outer output shaft 12.
The external fuselage is spheroidal radome fairing, and inside is support construction, is uniformly distributed in the outer surface of radome fairing
Several, each trimmer is along trimmer axis deflection.
As shown in figure 4, the universal rotating shaft mechanism structure is, the ears piece of 18 upper end of support arm passes through middle swinging block axis 17
The upper end ears piece of swinging block 16 in connection, middle swinging block 16 connects swinging block 14 on universal shaft by upper swinging block shaft 15, in universal shaft
Upper swinging block 14 is equipped with swing arm 19, and the both ends of swing arm 19 are separately connected one end of connecting rod 20, and the other end of connecting rod 20 passes through steering engine
The output axis connection of rocker arm 21 and steering engine 22.
As shown in figure 5, the fuselage interior, which is equipped with several frames 23, forms semicircular cavities structure, it is equipped in cavity
Upper partition 24 and lower partition 25, universal rotating shaft mechanism is connected in upper partition 24, and fuel tank is arranged in lower partition 25.
The bottom of the frame 23 is equipped with cargo hold suspension hook 26.
As shown in fig. 6, the bottom of the fuselage is equipped with undercarriage, structure is that 27 circumference uniform distribution of undercarriage principal arm exists
Fuselage bottom, undercarriage principal arm 27 connect footing plate 29 by damper 28.
In conclusion the advantages of coaxial dual-rotor helicopter of the invention, is:
A) the fixed propeller hub of use, upper and lower propeller collision problem when avoiding aircraft motor-driven；
B) simpler propeller wing head reduces air drag, compact-sized simple, improves safety；
C) double freedom trimmer, manoeuvrable are used；
D) high foot formula undercarriage, lifting more safe ready.
Claims (7)
1. a kind of coaxial dual-rotor helicopter, it is characterised in that: be mainly made of fuselage, power device and operating-controlling mechanism, in machine
It is connected and fixed bracket (7) by universal rotating shaft mechanism in body, passes sequentially through engine in fixation bracket (7) and connected with clutch and subtract
The input shaft of fast device (3), retarder (3) have outer output shaft (12) and (13) two output shafts of interior output shaft, and outer output shaft
(12) and interior output shaft (13) coaxial arrangement, the top of interior output shaft (13) connect upper rotor spiral by the auricle of propeller hub (1)
Paddle (2) is connected lower propeller aircraft (9) by the auricle of propeller hub (1) at the top of outer output shaft (12), and interior output shaft (13) and outer
The direction of rotation of output shaft (12) is opposite；Propeller hub (1) auricle and rotation axis at the top of interior output shaft (13) and outer output shaft (12)
Between be in 6 °~15 ° angles, and upper and lower two propeller hub (1) auricle is oppositely oriented；Wherein universal rotating shaft mechanism structure are as follows: support arm
(18) the ears piece of upper end is by swinging block (16) in the connection of middle swinging block axis (17), and the upper end ears piece of middle swinging block (16) is by above shaking
Block shaft (15) connects swinging block (14) on universal shaft, is equipped with swing arm (19) on swinging block (14) on universal shaft, and the two of swing arm (19)
End is separately connected one end of connecting rod (20), and the other end of connecting rod (20) is connected by the output shaft of steering engine rocker arm (21) and steering engine (22)
It connects.
2. coaxial dual-rotor helicopter as described in claim 1, it is characterised in that: the fixation bracket (7) is cross
Structure passes through engine support (6) connection engine (5) at fixed (7) four angles of bracket respectively, each engine (5) it is defeated
Shaft passes through clutch (4) respectively and connect with retarder (3).
3. coaxial dual-rotor helicopter as claimed in claim 2, it is characterised in that: described retarder (3) structure are as follows: four
Input shaft is axis in same level, and is in the bevel gear shaft (31) of cross distribution, and bevel gear shaft (31) is existed by bearing support
In the shell (30) of retarder (3), the upper end of four bevel gear shafts (31) is engaged with upper bevel gear (32) jointly, and lower end is jointly under
Bevel gear (33) engagement；Interior output shaft (13) and outer output shaft (12) are arranged by coaxial bearing in shell (30) output end,
The bottom end of China and foreign countries' output shaft (12) is connect by bolt (34) with upper bevel gear (32), and the bottom end of interior output shaft (13) passes through key
(35) it is engaged with lower bevel gear (33).
4. coaxial dual-rotor helicopter as described in claim 1, it is characterised in that: the external fuselage is spheroidal rectification
Cover, inside are support construction, are uniformly distributed several trimmers (8) in the outer surface of radome fairing, each trimmer is along adjustment
Piece axis deflection.
5. coaxial dual-rotor helicopter as described in claim 1, it is characterised in that: the fuselage interior is equipped with several frames
(23) the semicircular cavities structure formed is equipped with upper partition (24) and lower partition (25), upper partition (24) in cavity
Fuel tank is arranged in the upper universal rotating shaft mechanism of connection, lower partition (25).
6. coaxial dual-rotor helicopter as claimed in claim 5, it is characterised in that: the bottom of the frame (23) is equipped with cargo hold
Suspension hook (26).
7. coaxial dual-rotor helicopter as described in claim 1, it is characterised in that: the bottom of the fuselage is equipped with and rises and falls
Frame, structure are as follows: undercarriage principal arm (27) is uniformly distributed along the circumference in fuselage bottom, and undercarriage principal arm (27) is connected by damper (28)
Connection pad sole (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610758288.8A CN106314785B (en) | 2016-08-30 | 2016-08-30 | A kind of coaxial dual-rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610758288.8A CN106314785B (en) | 2016-08-30 | 2016-08-30 | A kind of coaxial dual-rotor helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106314785A CN106314785A (en) | 2017-01-11 |
| CN106314785B true CN106314785B (en) | 2019-01-01 |
Family
ID=57788634
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610758288.8A Active CN106314785B (en) | 2016-08-30 | 2016-08-30 | A kind of coaxial dual-rotor helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106314785B (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107117300B (en) * | 2017-04-26 | 2019-04-16 | 哈尔滨工业大学 | Unmanned vehicle based on coaxial more rotor pose adjustments |
| CN107117302A (en) * | 2017-05-27 | 2017-09-01 | 济宁市圣泽低温设备制造有限公司 | A kind of disjunctor is double to drive coaxal helicopter power set |
| TWI627103B (en) * | 2017-06-03 | 2018-06-21 | Feng Chia University | Coaxial double-rotor turbine drive unmanned vehicle mechanism system |
| CN107588957B (en) * | 2017-08-30 | 2019-09-27 | 长光卫星技术有限公司 | A kind of electronic unmanned plane dynamical system multi-function test stand |
| CN107580087A (en) * | 2017-09-05 | 2018-01-12 | 广东欧珀移动通信有限公司 | Image capture device, image-pickup method and device |
| CN107745808A (en) * | 2017-11-15 | 2018-03-02 | 孙林青 | A kind of compound helicopter |
| CN107757904A (en) * | 2017-11-17 | 2018-03-06 | 北京航景创新科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle of displacement four of oil |
| CN108116672A (en) * | 2017-12-19 | 2018-06-05 | 重庆大学 | A kind of DCB Specimen Electrostatic Absorption unmanned plane |
| CN110040246B (en) * | 2018-01-15 | 2022-05-24 | 江尚峰 | Single-shaft double-rotor unmanned aerial vehicle device, system with same and remote control method |
| CN108045576A (en) * | 2018-01-15 | 2018-05-18 | 缪顺文 | Deformable bionical rotor flapping wing fixed-wing one aircraft |
| CN108357685B (en) * | 2018-02-08 | 2022-11-08 | 天津凤凰智能科技有限公司 | Power system and unmanned helicopter |
| CN108791857B (en) * | 2018-06-27 | 2024-01-19 | 盛利元 | Coaxial full-rigid double-rotor helicopter |
| CN113306713B (en) * | 2021-06-29 | 2022-06-14 | 哈尔滨工业大学 | Coaxial dual-rotor unmanned aerial vehicle based on parallelogram control rotor shaft |
| CN113335513A (en) * | 2021-06-30 | 2021-09-03 | 史智勇 | Vector coaxial double-rotor helicopter |
| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340279A (en) * | 1992-06-22 | 1994-08-23 | United Technologies Corporation | Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors |
| CN100503365C (en) * | 2003-12-30 | 2009-06-24 | 何主能 | Coaxial unmanned crane vertical lifting machine |
| JP5027631B2 (en) * | 2007-12-03 | 2012-09-19 | エンジニアリングシステム株式会社 | Fixed-pitch coaxial double inversion helicopter |
| CN101870361A (en) * | 2010-06-19 | 2010-10-27 | 张奎 | Direct-type double-shaft counter-rotating turbine engine |
-
2016
- 2016-08-30 CN CN201610758288.8A patent/CN106314785B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106314785A (en) | 2017-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106314785B (en) | A kind of coaxial dual-rotor helicopter | |
| CN107140198B (en) | Nacelle structure of double coaxial tilting rotor unmanned aerial vehicle | |
| CN108557070A (en) | A kind of small-sized coaxial dual-rotor helicopter | |
| CN206984348U (en) | Electronic double coaxial tiltrotor aircrafts | |
| CN102490897B (en) | Multi-driving embedded rotor manned helicopter | |
| CN104859838A (en) | Oil-driving multi-rotor unmanned flying platform | |
| CN106864746A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three | |
| CN102085912A (en) | Dishing magnetic suspension ring-wing aircraft | |
| CN103057702B (en) | Jet-propelled type helicopter with rotating wings | |
| CN107662702B (en) | Hybrid power double-coaxial same-side reverse tilting rotor aircraft | |
| CN107672793A (en) | Rotor driver, aircraft and its flight control method | |
| CN111332462A (en) | Portable small-sized cylinder type coaxial reverse-propeller three-blade rotor type unmanned aerial vehicle | |
| CN102069905B (en) | Oblique wing helicopter | |
| CN203094441U (en) | Improved four-rotor aircraft | |
| CN111003166A (en) | Tandem electric double-rotor helicopter and control system thereof | |
| CN206826927U (en) | Mixed layout unmanned plane | |
| RU146302U1 (en) | SPEED COMBINED HELICOPTER | |
| CN207374648U (en) | The double coaxial homonymy reversion tiltrotor aircrafts of hybrid power | |
| CN109466751A (en) | A kind of helicopter | |
| CN108569396A (en) | Combined type blended wing-body high-speed helicopter | |
| CN108298072A (en) | A kind of rotor system of titling coaxial bispin wing aircraft | |
| CN104229132B (en) | Coaxial anti-paddle spherical aircraft transmission system | |
| CN205499349U (en) | Electronic unmanned helicopter of compound thrust | |
| CN208248494U (en) | A kind of rotor system of titling coaxial bispin wing aircraft | |
| CN209938948U (en) | Coaxial rotor unmanned aerial vehicle of folded cascade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |