CN105217030A - A kind of composite rotating wing lift unit - Google Patents
A kind of composite rotating wing lift unit Download PDFInfo
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- CN105217030A CN105217030A CN201510721375.1A CN201510721375A CN105217030A CN 105217030 A CN105217030 A CN 105217030A CN 201510721375 A CN201510721375 A CN 201510721375A CN 105217030 A CN105217030 A CN 105217030A
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- fin
- composite
- screw propeller
- rotor head
- lift unit
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Abstract
A kind of composite rotating wing lift unit, belongs to vehicle technology field, and two, three of being evenly distributed on around rotor head or four identical composite wings that comprise main shaft, rotor head, engine installation.Each composite wing comprises the fin screw propeller identical with two, three or four parameters.The leading edge horizontal arrangement of fin, the root of fin is connected with rotor head.The leading edge of fin is higher than the trailing edge of fin.All screw propellers are in " one " word level or turn forward and be arranged in the below of fin.By the screw propeller of an all composite wing of driven by engine, or each screw propeller joins separately a driving engine.Because screw propeller is arranged on the below of fin, can the air-flow above fin be guided into the back lower place during propeller rotational, can postpone the burbling of fin upper surface like this, be conducive to raising the efficiency and stability, and the angle of attack of fin can be comparatively large thus improve the lift that fin unit area produces.Described device is installed and is made lift unit on board the aircraft.
Description
Technical field
A kind of composite rotating wing lift unit, belongs to vehicle technology field, particularly relates to a kind of lift unit.
Background technology
The fin of traditional main rotor for helicopter is one piece of integral structure, to change the line of production raw lift at the Direct driver backspin of driving engine, the efficiency producing lift is not high, the fin that area is less produces lift and raising speed will be leaned on to realize, the requirement of the large height of speed to material is higher, and the rotating speed of main rotor is too high can produce very large noise, and wing tip even sound barrier occurs, efficiency degradation, safety is badly damaged.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional Helicopter Main rotor, invent a kind of slowly run just can produce the efficient composite rotating wing lift unit of high lift.
A kind of composite rotating wing lift unit, and two, three of being evenly distributed on around rotor head or four identical composite wings that comprise main shaft, rotor head, engine installation.If when adopting two composite wings, two composite wings are mutually 180 ° and are arranged on around rotor head; If when adopting three composite wings, three composite wings are mutually 120 ° and are arranged on around rotor head; If when adopting four composite wings, four composite wings are in 90 ° to be mutually arranged on around rotor head.
The concrete structure of composite wing is: each composite wing comprises the fin screw propeller identical with two, three or four parameters.The leading edge horizontal arrangement of fin, the root of fin is connected with rotor head.The leading edge of fin is higher than the trailing edge of fin, and the angle of attack of fin is between 3 ° ~ 15 °.All screw propellers are that " one " word arrangement is in the below of fin, all screw propellers are all in sustained height, the plane of rotation of all screw propellers is all in same plane, and screw propeller horizontal arrangement or the leading edge direction forward downward at fin tilt, and the angle of inclination is not more than 15 °.The chord length of fin is between 0.8 times ~ 1.3 times of diameter of propeller.The length of fin is greater than the diameter sum of all screw propellers in a composite wing.In order to not affect efficiency, screw propeller can not be too near to fin and install, and leaves suitable enough gaps between the two, and the trailing edge of fin is greater than 8mm to the minor increment of screw propeller plane of rotation.
Engine installation has two kinds of forms: by the screw propeller of an all composite wing of driven by engine, and driving engine is installed in rotor head or in body, and power passes to all screw propellers by mechanism by driving engine; Or each screw propeller joins separately a driving engine, during this form, driving engine adopts motor, and the top that motor is installed on corresponding screw propeller is placed in fin.
The principle of work of a kind of composite rotating of this invention wing lift unit is: all propeller rotational of power driven, under the drive of screw propeller, composite wing can rotate around the spindle and produce lift.Lift is produced by the combined action of screw propeller and fin.There is opening angle forward in screw propeller plane of rotation and fin, air can be accelerated to push the back lower place to during propeller rotational, form powerful downwash flow, according to Newton's second law and the 3rd law, described composite rotating wing lift unit will produce the thrust of larger forward upward, is namely equivalent to create lift upwards and thrust forward, under the effect of thrust forward simultaneously, composite wing rotates around the spindle, and the lift that the speed of rotation produces sooner is larger.Described composite rotating wing lift unit is installed and aircraft vertical can be made on board the aircraft to go up to the air.Sail area not quite also can produce enough large lift, as long as the rotating speed of screw propeller is enough high.Plane of rotation due to screw propeller is horizontal or slightly toward top rake, the resistance that during rotation, the screw propeller of described composite rotating wing lift unit is subject to is less, and efficiency is higher.Because screw propeller is arranged on the below of fin, can the air-flow above fin be guided into the back lower place during propeller rotational, can postpone the burbling of fin upper surface like this, be conducive to raising the efficiency and stability, and the angle of attack of fin can be comparatively large thus improve the lift that fin unit area produces.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of a kind of composite rotating wing of the present invention lift unit; Fig. 2 is the structural representation enlarged drawing that the composite wing of a kind of composite rotating wing of the present invention lift unit is observed from wing tip to wing root direction, and Fig. 3 is the principle of work streamline schematic diagram of the composite wing of a kind of composite rotating wing of the present invention lift unit.
In figure, 1-main shaft, 2-rotor head, 3-engine installation, 4-composite wing, 41-fin, the leading edge of 411-fin, the trailing edge of 412-fin, 42-screw propeller, 5-streamline.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of composite rotating wing lift unit, comprise main shaft 1, rotor head 2, engine installation 3 and be evenly distributed on two composite wings 4 around rotor head 2.Two composite wings 4 are mutually 180 ° and are arranged on rotor head 2 around.The concrete structure of composite wing 4 is: each composite wing 4 comprises fin 41 screw propeller 42 identical with two parameters.The leading edge horizontal arrangement of fin 41, the root of fin 41 is connected with rotor head 2.The leading edge 411 of fin is higher than the trailing edge 412 of fin, and the angle of attack of fin 41 is 10 °.Two screw propellers 42 are that " one " word arrangement is in the below of fin 41, two screw propellers 42 are all in sustained height, the plane of rotation of two screw propellers 42 is all in same plane, and screw propeller 42 horizontal arrangement or the leading edge 411 direction forward downward at fin tilt, and the angle of inclination is 5 °.The chord length of fin 41 is 1.1 times of screw propeller 42 diameter.The length of fin 41 is greater than the diameter sum of two screw propellers 42 in composite wing 4.In order to not affect efficiency, screw propeller 42 can not be too near to fin 4 and install, and should stay appropriate gap between the two, and the trailing edge 412 of fin is greater than 8mm to the minor increment of screw propeller 42 plane of rotation.Engine installation has two kinds of forms: by the screw propeller 42 of an all composite wing 4 of driven by motor, and motor is installed in rotor head 2 or in body, and power passes to all screw propellers 42 by mechanism by motor; Or each screw propeller 42 joins separately a motor, the top that motor is installed on corresponding screw propeller 42 is placed in fin 41.
Composite rotating wing lift unit of the present invention produces beneficial effect like this: all screw propellers 42 of power driven rotate, and under the drive of screw propeller 42, composite wing 4 can rotate around main shaft 1 and produce lift.Lift is produced by the combined action of screw propeller 42 and fin 41.There is opening angle forward in screw propeller 42 plane of rotation and fin 41, air can be accelerated to push the back lower place to when screw propeller 42 rotates, form powerful downwash flow, according to Newton's second law and the 3rd law, described composite rotating wing lift unit will produce the thrust of larger forward upward, is namely equivalent to create lift upwards and thrust forward, under the effect of thrust forward simultaneously, composite wing 4 rotates around main shaft 1, and the lift that the speed of rotation produces sooner is larger.Described composite rotating wing lift unit is installed and aircraft vertical can be made on board the aircraft to go up to the air.Fin 41 area not quite also can produce enough large lift, as long as the rotating speed of screw propeller 42 is enough high.Plane of rotation due to screw propeller 42 is horizontal or slightly toward top rake, the resistance that during rotation, the screw propeller 42 of described composite rotating wing lift unit is subject to is less, and efficiency is higher.Because screw propeller 42 is arranged on the below of fin 41, can the air-flow above fin 42 be guided into the back lower place when screw propeller 42 rotates, the burbling of fin 41 upper surface can be postponed like this, be conducive to raising the efficiency and stability, and the angle of attack of fin 41 can be comparatively large thus improve the lift that fin 41 unit area produces.
Claims (7)
1. a composite rotating wing lift unit, is characterized in that: comprise main shaft (1), rotor head (2), engine installation (3) and be evenly distributed on rotor head (2) around two, three or four identical composite wings (4); Each composite wing (4) comprises fin (41) screw propeller (42) identical with two, three or four parameters; The leading edge horizontal arrangement of fin (41), the root of fin (41) is connected with rotor head (2); The leading edge (411) of fin is higher than the trailing edge (412) of fin; All screw propellers (42) are that " one " word arrangement is in the below of fin (41), all screw propellers (42) are all in sustained height, the plane of rotation of all screw propellers (42) is all in same plane, and screw propeller (42) horizontal arrangement or leading edge (411) the direction forward downward at fin tilt; The chord length of fin (41) is between 0.8 times ~ 1.3 times of screw propeller (42) diameter; The length of fin (41) is greater than the diameter sum of all screw propellers (42) in a composite wing (4); Gap is left between screw propeller (42) and fin (4).
2. a kind of composite rotating wing lift unit according to claim 1, is characterized in that: when adopting two composite wing (4), two composite wings (4) are mutually 180 ° and are arranged on rotor head (2) around; When adopting three composite wing (4), three composite wings (4) are mutually 120 ° and are arranged on rotor head (2) around; When adopting four composite wing (4), four composite wings (4) are in 90 ° is mutually arranged on rotor head (2) around.
3. a kind of composite rotating wing lift unit according to claim 1, is characterized in that: the angle of attack of fin (41) is between 3 ° ~ 15 °.
4. a kind of composite rotating wing lift unit according to claim 1, is characterized in that: the angle that screw propeller (42) tilts at leading edge (411) the direction forward downward of fin is not more than 15 °.
5. a kind of composite rotating wing lift unit according to claim 1, is characterized in that: the trailing edge (412) of fin is greater than 8mm to the minor increment of screw propeller (42) plane of rotation.
6. a kind of composite rotating wing lift unit according to claim 1 or 2 or 3 or 4, it is characterized in that: engine installation has two kinds of forms: by the screw propeller (42) of an all composite wing of driven by engine (4), driving engine is installed in rotor head (2) or in body, and power passes to all screw propellers (42) by mechanism by driving engine; Or each screw propeller (42) joins separately a driving engine.
7. a kind of composite rotating wing lift unit according to claim 1 or 2 or 3 or 4, is characterized in that: each screw propeller (42) is driven by a motor, the top that described motor is installed on corresponding screw propeller (42) is placed in fin (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721375.1A CN105217030B (en) | 2015-10-30 | 2015-10-30 | A kind of composite rotating wing lift unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721375.1A CN105217030B (en) | 2015-10-30 | 2015-10-30 | A kind of composite rotating wing lift unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105217030A true CN105217030A (en) | 2016-01-06 |
| CN105217030B CN105217030B (en) | 2018-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510721375.1A Active CN105217030B (en) | 2015-10-30 | 2015-10-30 | A kind of composite rotating wing lift unit |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1274886A (en) * | 1917-09-05 | 1918-08-06 | Henry V Nurmi | Airship-propeller. |
| US2589826A (en) * | 1949-05-26 | 1952-03-18 | Glenn L Martin Co | Epicyclic helicopter rotor system |
| US3181816A (en) * | 1962-09-12 | 1965-05-04 | Bolkow Entwicklungen Kg | Fettered rotary wing aircraft |
| DE2305856A1 (en) * | 1973-02-02 | 1974-08-15 | Markes & Co Kg | FREE-FLYING TOY HELICOPTER |
| US5634839A (en) * | 1994-11-23 | 1997-06-03 | Donald Dixon | Toy aircraft and method for remotely controlling same |
| US7497759B1 (en) * | 2001-03-28 | 2009-03-03 | Steven Davis | Directionally controllable, self-stabilizing, rotating flying vehicle |
| GB2495562A (en) * | 2011-10-15 | 2013-04-17 | Torix Peter Bennett | Helicopter multi rotor system |
| CN104176235A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Rotatable wing of rotor craft |
| CN205131662U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Compound rotatory wing lift arrangement |
-
2015
- 2015-10-30 CN CN201510721375.1A patent/CN105217030B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1274886A (en) * | 1917-09-05 | 1918-08-06 | Henry V Nurmi | Airship-propeller. |
| US2589826A (en) * | 1949-05-26 | 1952-03-18 | Glenn L Martin Co | Epicyclic helicopter rotor system |
| US3181816A (en) * | 1962-09-12 | 1965-05-04 | Bolkow Entwicklungen Kg | Fettered rotary wing aircraft |
| DE2305856A1 (en) * | 1973-02-02 | 1974-08-15 | Markes & Co Kg | FREE-FLYING TOY HELICOPTER |
| US5634839A (en) * | 1994-11-23 | 1997-06-03 | Donald Dixon | Toy aircraft and method for remotely controlling same |
| US7497759B1 (en) * | 2001-03-28 | 2009-03-03 | Steven Davis | Directionally controllable, self-stabilizing, rotating flying vehicle |
| GB2495562A (en) * | 2011-10-15 | 2013-04-17 | Torix Peter Bennett | Helicopter multi rotor system |
| CN104176235A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Rotatable wing of rotor craft |
| CN205131662U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Compound rotatory wing lift arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105217030B (en) | 2018-03-06 |
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Effective date of registration: 20190605 Address after: 100039 Building No. 1, 51 Yongding Road, Haidian District, Beijing Patentee after: Beijing Remote Sensing Equipment Institute Address before: 528500 room 402, Fu Wan Jiangwan Road, Hecheng street, Gaoming District, Foshan, Guangdong, China, 78 Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City |
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