CN109665096A - A kind of shrouded propeller thrust coaxial double-rotor helicopter - Google Patents
A kind of shrouded propeller thrust coaxial double-rotor helicopter Download PDFInfo
- Publication number
- CN109665096A CN109665096A CN201811588465.8A CN201811588465A CN109665096A CN 109665096 A CN109665096 A CN 109665096A CN 201811588465 A CN201811588465 A CN 201811588465A CN 109665096 A CN109665096 A CN 109665096A
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- Prior art keywords
- rotor
- bevel gear
- wing
- shrouded propeller
- coaxial double
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- 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.)
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- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of shrouded propeller thrust coaxial double-rotor helicopters, belong to high-speed helicopter field, and the present invention is connected separately with port wing, starboard wing by the upper-end part of driving at left and right sides of fuselage；The port wing end is connected with left shrouded propeller, and the starboard wing end is connected with right shrouded propeller.Fuselage upper end is provided with rotor system, and the rotor system includes upper rotor wing rotation axis, the lower rotor rotary shaft, coaxial double-rotary wing that fuselage upper surface is set gradually upwards；It is fixedly installed lower bevel gear on the upper rotor wing rotation axis, is fixedly installed bevel gear in the lower rotor rotary shaft；Master bevel gear is provided between the lower bevel gear, upper bevel gear；In conjunction with coaxial double-rotary wing, the forward flight speed of coaxial double-rotor helicopter can be improved using shrouded propeller as thrust mechanism in the present invention, flies before realizing high speed.
Description
Technical field
The invention belongs to high-speed helicopter fields, are related to duct and coaxal helicopter technology, in particular to a kind of duct spiral shell
Revolve paddle thrust coaxial double-rotor helicopter.
Background technique
The advantages of duct, is that duct plays preferable protective effect to the blade tip of propeller, it is suppressed that the vortex of blade tip
With backflow phenomenon.Streamline passes through duct lip, sucks duct, and the air being inhaled into passes through paddle disk, increases rotor disk area, mentions
High pneumatic efficiency.Meanwhile duct outside pressure is greater than inside pressure, can generate certain power, and the force vector is into fan
Heart inclination, horizontal component are cancelled out each other due to symmetrical, and vertical component is additional duct lift.Shrouded propeller
Possess better pneumatic efficiency compared to traditional individually propeller.
Coaxial anti-paddle generally uses coaxial anti-paddle, is exactly that double-layer paddle shares a transmission shaft, but rotation direction is not on the contrary,
One-directional rotation deflection torque is only balanced, and first layer provides " precommpression " for the second layer, the second level just has bigger
" import/exhaust amount " and " current density ", although 2 times of effect is not achieved in lift, improvement is also apparent.
Although existing coaxial double-rotary wing can promote lift, still do not overcome using the helicopter of this configuration preceding at full speed
Lower disadvantage is spent, therefore, designing a kind of twin-rotor helicopter, to be able to solve existing coaxial double-rotor helicopter forward flight speed slow
The shortcomings that always those skilled in the art's technical problem to be solved.
Summary of the invention
For difficult point present in the current technology being previously mentioned in background technique, the present invention provides a kind of shrouded propeller and pushes away
Power coaxial double-rotor helicopter, to solve the slow disadvantage of existing coaxial double-rotor helicopter forward flight speed.The present invention is by duct spiral shell
It revolves paddle and is applied to coaxial double-rotor helicopter, greatly improve its forward flight speed, realize rapid flight.
The present invention is implemented as follows:
A kind of shrouded propeller thrust coaxial double-rotor helicopter, including fuselage, the upper-end part of driving at left and right sides of fuselage
It is connected separately with port wing, starboard wing；The port wing end is connected with left shrouded propeller, and the starboard wing end connects
It is connected to right shrouded propeller, can be controlled by controlling the revolving speed of left shrouded propeller, right shrouded propeller, two duct spiral shells
Paddle revolving speed is different can generate yawing for rotation, to realize yawing rotation.The present invention is using shrouded propeller as thrust machine
The forward flight speed of coaxial double-rotor helicopter can be improved in conjunction with coaxial double-rotary wing in structure, flies before realizing high speed.
Fuselage upper end is provided with rotor system, and the rotor system includes the upper rotation that fuselage upper surface is set gradually upwards
Wing rotary shaft, lower rotor rotary shaft, coaxial double-rotary wing；The coaxial double-rotary wing is lower rotor from bottom to top successively, upper rotation
The wing；It is fixedly installed lower bevel gear on the upper rotor wing rotation axis, is fixedly installed epicone in the lower rotor rotary shaft
Gear；The lower bevel gear is fixed on rotor wing rotation axis, drives upper rotor wing rotation by lower bevel gear, upper bevel gear is solid
It is scheduled in lower rotor rotary shaft, the rotation of the backspin wing is driven by epicone gear；It is arranged between the lower bevel gear, upper bevel gear
There is master bevel gear；The lower bevel gear, upper bevel gear engage rotation with master bevel gear, are acted on by the commutation of master bevel gear,
Lower bevel gear and upper bevel gear are oppositely oriented.
Further, the tail portion of the fuselage is provided with H-type empennage, and H-type empennage provides yaw and pitching power for helicopter
Square.
Further, the lower end of the fuselage is provided with undercarriage, and the undercarriage is tricycle landing gear.
Further, the lower rotor, upper rotor size are consistent.
Further, the lower rotor lower end is provided with lower inclinator, and the upper rotor lower end is provided with inclinator；
The lower inclinator, upper inclinator control respectively lower rotor, upper rotor always away from variation.
Further, the left shrouded propeller and right shrouded propeller and horizontal plane.Left shrouded propeller and the right side
Shrouded propeller can generate thrust horizontally forward, therefore helicopter can possess higher forward flight speed.
The beneficial effect of the present invention and the prior art is:
1) shrouded propeller is applied to coaxial double-rotor helicopter by the present invention, greatly improves its forward flight speed, is realized
Rapid flight；In addition, left shrouded propeller of the invention and right shrouded propeller and horizontal plane, pushing away horizontally forward is generated
Power, when flying before helicopter, the forward thrust component for not only having rotor to generate, more there are also left shrouded propeller and right ducts
The forward thrust that propeller generates, therefore helicopter can possess higher forward flight speed；
2) present invention can realize the quick yawing rotation of helicopter by control shrouded propeller, specifically pass through control
The revolving speed of two shrouded propellers is controlled to control, two shrouded propeller revolving speeds are different to generate yawing, thus
Realize yawing rotation.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of shrouded propeller thrust coaxial double-rotor helicopter of the present invention；
Fig. 2 is the rotor system schematic diagram of shrouded propeller thrust coaxial double-rotor helicopter of the present invention；
In figure, 1-H type tail, the left shrouded propeller of 2-, 3- port wing, 4- undercarriage, 5- fuselage, 6- starboard wing, the right side 7-
Shrouded propeller, rotor under 8-, the upper rotor of 9-, 10- master bevel gear, bevel gear under 11-, the upper rotor wing rotation axis of 12-, 13- epicone
Gear, rotor rotary shaft under 14-, inclinator under 15-, the upper inclinator of 16-.
Specific embodiment
It is clear to keep the purpose of the present invention, technical solution and effect clearer, example is exemplified below to the present invention into one
Step is described in detail.It should be understood that specific implementation described herein is not intended to limit the present invention only to explain the present invention.
As shown in FIG. 1, FIG. 1 is the structural schematic diagram of shrouded propeller thrust coaxial double-rotor helicopter of the present invention,
Helicopter of the invention includes H-type empennage 1, left shrouded propeller 2, port wing 3, undercarriage 4, fuselage 5, starboard wing
6, right shrouded propeller 7, lower rotor 8, upper rotor 9.Left shrouded propeller 2 therein is connect with port wing 3, port wing 3 and machine
Body 5 connects, and right shrouded propeller 7 is connect with starboard wing 6, and starboard wing 6 is connect with fuselage 5.Undercarriage 4 is that first three point type rises and falls
Frame.
As shown in Fig. 2, Fig. 2 is the rotor system schematic diagram of shrouded propeller thrust coaxial double-rotor helicopter of the present invention；
The rotor system includes the upper rotor wing rotation axis 12, lower rotor rotary shaft 14, coaxial that 5 upper surface of fuselage is set gradually upwards
DCB Specimen；The coaxial double-rotary wing is lower rotor 8, upper rotor 9 from bottom to top successively.
It is fixedly installed lower bevel gear 11 on upper rotor wing rotation axis 12, is fixedly installed in the lower rotor rotary shaft 14
Upper bevel gear 13；The lower bevel gear 11 is fixed on rotor wing rotation axis 12, drives upper rotor 9 to revolve by lower bevel gear 11
Turn, upper bevel gear 13 is fixed in lower rotor rotary shaft 14, drives lower rotor 8 to rotate by upper bevel gear 13；The lower cone
Master bevel gear 10 is provided between gear 11, upper bevel gear 13；Lower bevel gear 11, upper bevel gear 13 and the master bevel gear 10
Engagement rotation is acted on by the commutation of master bevel gear 10, and lower bevel gear 11 and upper bevel gear 13 are oppositely oriented.The rotor system
System further includes the lower inclinator 15 of lower 8 lower end of rotor setting and the upper inclinator 16 of 9 lower end of upper rotor setting, lower inclinator
15, upper inclinator 16 control respectively lower rotor 8 and upper rotor 9 always away from variation.
Concrete operating principle of the present invention are as follows:
Left shrouded propeller 2 and right shrouded propeller 7 and horizontal plane, generate thrust horizontally forward, before helicopter
When flying, the forward thrust component for not only having rotor to generate, more there are also left shrouded propellers 2 and right shrouded propeller 7 to produce
Raw forward thrust, therefore helicopter can possess higher forward flight speed.
Port wing 3 and starboard wing 6 not only act as the effect of connection shrouded propeller, when flying before helicopter, can generate
A certain size lift, to promote the flying quality of helicopter.
It is tested, is obtained by performance of the simulation calculation to shrouded propeller thrust coaxial double-rotor helicopter of the present invention
Such as the performance parameter of following table one；
The major parameter of one shrouded propeller thrust coaxial double-rotor helicopter of table
| Length × width × height | 4.1×2.2×1.5m |
| Rotor diameter | 4.1m |
| Airscrew diameter | 0.9m |
| Max level speed | 420km/h |
| Maximum take-off weight | 320kg |
| Water surface takeoff distance | 320m |
| Voyage | 1000km |
| Endurance | 4h |
Note: machine width 2.2m is propeller center distance；Obtain from above-mentioned emulation data: shrouded propeller of the invention pushes away
Power coaxial double-rotor helicopter max level speed reaches 420km/h, and the emulation is statistics indicate that helicopter of the invention can be gathered around
There is very high forward flight speed.
There are many concrete application approach of the present invention, the above is only a preferred embodiment of the present invention, it is noted that for
For those skilled in the art, without departing from the principle of the present invention, it can also make several improvements, this
A little improve also should be regarded as protection scope of the present invention.
Claims (6)
1. a kind of shrouded propeller thrust coaxial double-rotor helicopter, including fuselage (5), which is characterized in that the fuselage (5)
The upper-end part of driving of the left and right sides is connected separately with port wing (3), starboard wing (6)；Described port wing (3) end is connected with left culvert
Road propeller (2), the starboard wing (6) end are connected with right shrouded propeller (7)；Described fuselage (5) upper end is provided with
Rotor system, the rotor system include upper rotor wing rotation axis (12), the lower rotor that fuselage (5) upper surface is set gradually upwards
Rotary shaft (14), coaxial double-rotary wing；The coaxial double-rotary wing is lower rotor (8), upper rotor (9) from bottom to top successively；Institute
It is fixedly installed lower bevel gear (11) on the upper rotor wing rotation axis (12) stated, is fixedly installed on the lower rotor rotary shaft (14)
There are upper bevel gear (13)；The lower bevel gear (11) is fixed on rotor wing rotation axis (12), passes through lower bevel gear (11) band
Dynamic upper rotor (9) rotation, upper bevel gear (13) are fixed on lower rotor rotary shaft (14), drive backspin by upper bevel gear (13)
The wing (8) rotation；Master bevel gear (10) are provided between the lower bevel gear (11), upper bevel gear (13)；The lower cone tooth
Wheel (11), upper bevel gear (13) engage rotation with master bevel gear (10), are acted on by the commutation of master bevel gear (10), lower bevel gear
(11) and upper bevel gear (13) is oppositely oriented.
2. a kind of shrouded propeller thrust coaxial double-rotor helicopter according to claim 1, which is characterized in that described
The tail portion of fuselage (5) is provided with H-type empennage (1).
3. a kind of shrouded propeller thrust coaxial double-rotor helicopter according to claim 1, which is characterized in that described
The lower end of fuselage (5) is provided with undercarriage (4), and the undercarriage (4) is tricycle landing gear.
4. a kind of shrouded propeller thrust coaxial double-rotor helicopter according to claim 1, which is characterized in that described
Lower rotor (8), upper rotor (9) size are consistent.
5. a kind of shrouded propeller thrust coaxial double-rotor helicopter according to claim 4, which is characterized in that described
Lower rotor (8) lower end is provided with lower inclinator (15), and described upper rotor (9) lower end is provided with inclinator (16)；Described
Lower inclinator (15), upper inclinator (16) control respectively lower rotor (8), upper rotor (9) always away from variation.
6. a kind of shrouded propeller thrust coaxial double-rotor helicopter according to claim 1, which is characterized in that described
Left shrouded propeller (2) and right shrouded propeller (7) and horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811588465.8A CN109665096A (en) | 2018-12-25 | 2018-12-25 | A kind of shrouded propeller thrust coaxial double-rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811588465.8A CN109665096A (en) | 2018-12-25 | 2018-12-25 | A kind of shrouded propeller thrust coaxial double-rotor helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109665096A true CN109665096A (en) | 2019-04-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811588465.8A Pending CN109665096A (en) | 2018-12-25 | 2018-12-25 | A kind of shrouded propeller thrust coaxial double-rotor helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN109665096A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111003154A (en) * | 2019-12-28 | 2020-04-14 | 长安大学 | Propeller |
| CN111169630A (en) * | 2020-02-20 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Vector coaxial double-propeller unmanned aerial vehicle |
| CN113401341A (en) * | 2021-08-05 | 2021-09-17 | 北京航空航天大学 | High-speed coaxial unmanned helicopter additionally provided with double tail thrusters |
| EP3882142A1 (en) | 2020-03-17 | 2021-09-22 | Airbus Helicopters | Method for protecting a margin for controlling the thrust attitude of a hybrid helicopter and a hybrid helicopter |
| CN114162319A (en) * | 2021-12-16 | 2022-03-11 | 北京海空行科技有限公司 | Control system of combined coaxial helicopter |
| CN114590400A (en) * | 2022-03-09 | 2022-06-07 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
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| CN107472519A (en) * | 2017-06-26 | 2017-12-15 | 南京航空航天大学 | A kind of device for coaxial double-rotor helicopter ground resonance test |
| CN209852581U (en) * | 2018-12-25 | 2019-12-27 | 南京航空航天大学 | Ducted propeller thrust coaxial dual-rotor helicopter |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111003154A (en) * | 2019-12-28 | 2020-04-14 | 长安大学 | Propeller |
| CN111169630A (en) * | 2020-02-20 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Vector coaxial double-propeller unmanned aerial vehicle |
| EP3882142A1 (en) | 2020-03-17 | 2021-09-22 | Airbus Helicopters | Method for protecting a margin for controlling the thrust attitude of a hybrid helicopter and a hybrid helicopter |
| FR3108311A1 (en) * | 2020-03-17 | 2021-09-24 | Airbus Helicopters | method of protecting a margin of control of the yaw attitude of a hybrid helicopter and a hybrid helicopter. |
| US11447240B2 (en) | 2020-03-17 | 2022-09-20 | Airbus Helicopters | Method of protecting a margin for controlling the yaw attitude of a hybrid helicopter, and a hybrid helicopter |
| CN113401341A (en) * | 2021-08-05 | 2021-09-17 | 北京航空航天大学 | High-speed coaxial unmanned helicopter additionally provided with double tail thrusters |
| CN114162319A (en) * | 2021-12-16 | 2022-03-11 | 北京海空行科技有限公司 | Control system of combined coaxial helicopter |
| CN114162319B (en) * | 2021-12-16 | 2023-11-28 | 北京海空行科技有限公司 | Control system of composite coaxial helicopter |
| CN114590400A (en) * | 2022-03-09 | 2022-06-07 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
| CN114590400B (en) * | 2022-03-09 | 2022-12-20 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
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