CN203078753U - Double-rotor-wing unmanned helicopter - Google Patents
Double-rotor-wing unmanned helicopter Download PDFInfo
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- CN203078753U CN203078753U CN 201220755823 CN201220755823U CN203078753U CN 203078753 U CN203078753 U CN 203078753U CN 201220755823 CN201220755823 CN 201220755823 CN 201220755823 U CN201220755823 U CN 201220755823U CN 203078753 U CN203078753 U CN 203078753U
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- rotor
- wing
- unmanned helicopter
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- wings
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Abstract
The utility model relates to a rotor wing type unmanned helicopter, further relates to a double-rotor-wing unmanned helicopter, and aims to solve the problem about synchronism of rotor wing main shafts of the double-rotor-wing unmanned helicopter in the flight process. The utility model adopts the technical scheme that the double-rotor-wing unmanned helicopter comprises a body, two crossed rotor wings, the rotor wing main shafts, main shaft gears which are respectively connected with the rotor wing main shafts, a power source and a synchronous device, wherein the rotor wings are crossed with each other in a state that the two rotor wings are perpendicular to each other when one of the rotor wings is longitudinally perpendicular to the body and the other rotor wing is longitudinally parallel to the body. Compared with the prior art, the double-rotor-wing unmanned helicopter has the advantages that the synchronous device is in a mechanical meshing mode, and the rotating coordination of the two rotor wings is ensured, so that the two rotor wings cannot collide with each other.
Description
Technical field
The present invention relates to the rotary wind type depopulated helicopter, further relate to a kind of bispin wing depopulated helicopter.
Background technology
Shown in accompanying drawing Fig. 2-6, the rotor-hub configuration of helicopter mainly contains single rotor tail-rotor formula, bispin wing lap siding, bispin wing cross-arranging type, bispin wing close coupled type, bispin wing staggered form etc.The distribution form that rotor-hub configuration is very big, different to the influence of helicopter, structure are also different, and great changes will take place can to make the performance of helicopter.Bispin wing staggered form claims " staggered form " again." staggered form " is the same with " cross-arranging type ", and two secondary rotors are identical, along the horizontal left and right arrangement of body, intersects contrarotation but its axis is " v " type.The characteristics of its bright aquatic foods are that two rotors are not parallel, and are outward-dipping respectively.The great advantage of this structure is that good stability, load carrying ability are big, suits to carry out lifting, hang hauling operation.
The position relation that the mast of " staggered form " helicopter must be maintained fixed, otherwise rotor generation mutual action, consequence is very serious.
Summary of the invention
Of the present invention day the synchronism problem that is to solve double-rotary wing pilotless helicopter rotor of two mast drives in flight course.
Technical scheme of the present invention is as follows:
Bispin wing depopulated helicopter, comprise: the rotor of fuselage, 2 intersections, intersect rotor bonded assembly mast 1,5 respectively at 2, the reaction gear 2,6 that links to each other with 2 mast 1,5 respectively, respectively with reaction gear 2,6 bonded assembly propulsions source, the crossing condition of the rotor of described intersection is: when a rotor vertically vertical with fuselage, when another rotor and fuselage parallel longitudinal, two rotors are just in time vertical; Also comprise: a synchronous device, the fixed engagement by 2 reaction gears guarantees; Described synchronous device structure comprises: a pair of spiral bevel gear 3,7 connects 2 reaction gears 2,6; A pair of vertical support plate 4,8 is with vertical support plate 4,8 bonded assembly risers 9, the horizontal plate 10 of supporting vertical plate 9.
There is an angle in described mast, big or small preferred 11 degree of angle.
The present invention is for the advantage of prior art:
(1) bispin wing depopulated helicopter rotor synchronization structure, though the plane of rotation of two width of cloth rotors has intersection, the juxtaposition area is little, so loss of lift is very little; Though rotor shaft has inclination, the angle of inclination is very little, so the loss of making a concerted effort of rotor lift is also little, and can improve the stability, particularly lateral stability of helicopter.
(2) synchronous device is mechanical type engagement, guarantees that forever the phase angle skew can not take place for the two, has guaranteed the harmony of two width of cloth rotors rotations, so can not run foul of each other during their work.
(3) two secondary intersection rotors are symmetry fully, and distance is very near again, so do not have fine difference or the stable problem of extraneous variations in flow influence when being worked basically.In lap siding and side-by-side helicopter, two secondary rotor apart from each others, the fine difference in their whens work or the variation of extraneous air-flow all can have influence on the stability of helicopter.
The lifting line of (four) two secondary rotors is in the shape of the letter V, and this is very favourable to improving lateral stability.Helicopter stable, exactly to lifting, hang operation such as transportation and be of great benefit to.
(5) two of synchronization structure secondary rotor close proximity, thereby an available cover transmission maneuvering system make that like this helicopter structure is simple, the good arrangement, and easy care, weight is also light, and helps keeping body streamline profile.
Description of drawings
Fig. 1 is a structural representation of the present invention.Among the figure, 1,5 represent mast respectively, and 2,6 represent reaction gear respectively, and 3,7 represent spiral bevel gear respectively, and 4,8 represent vertical support plate respectively, and 9 represent riser, and 10 represent horizontal plate.
Fig. 2 is single rotor tail-rotor formula helicopter scheme drawing.
Fig. 3 is the tandem helicopter scheme drawing.
Fig. 4 is a bispin wing side-by-side helicopter scheme drawing.
Fig. 5 is the coaxial helicopter scheme drawing.
Fig. 6 is the synchropter scheme drawing.
The specific embodiment
Contrast Fig. 1 illustrates implementation procedure of the present invention.
Bispin wing depopulated helicopter, comprise: the rotor of fuselage, 2 intersections, intersect rotor bonded assembly mast 1,5 respectively at 2, the reaction gear 2,6 that links to each other with 2 mast 1,5 respectively, respectively with reaction gear 2,6 bonded assembly propulsions source, the crossing condition of the rotor of described intersection is: when a rotor vertically vertical with fuselage, when another rotor and fuselage parallel longitudinal, two rotors are just in time vertical; Also comprise: a synchronous device, the fixed engagement by 2 reaction gears guarantees; Described synchronous device structure comprises: a pair of spiral bevel gear 3,7 connects 2 reaction gears 2,6; A pair of vertical support plate 4,8 is with vertical support plate 4,8 bonded assembly risers 9, the horizontal plate 10 of supporting vertical plate 9.
There is an angle in described mast, big or small preferred 11 degree of angle.
Reaction gear 2,6 provides power by two propulsions source respectively, two cover rotor co-operation, and rotor does not disturb mutually, and when a propulsion source breaks down, another propulsion source can independently be born the power input, can guarantee that still rotor adheres to rotation, and promote safety.
Claims (2)
1. bispin wing depopulated helicopter, comprise: the rotor of fuselage, 2 intersections, intersect rotor bonded assembly mast (1,5) respectively at 2, the reaction gear (2,6) that links to each other with 2 mast (1,5) respectively is respectively with reaction gear (2,6) bonded assembly propulsion source.It is characterized in that when a rotor is vertically vertical with fuselage, when another rotor and fuselage parallel longitudinal, two rotors are just in time vertical; Also comprise: a synchronous device, the fixed engagement by 2 reaction gears guarantees; The synchronous device structure comprises: a pair of spiral bevel gear (3,7) connects 2 reaction gears (2,6); A pair of vertical support plate (4,8), with vertical support plate (4,8) bonded assembly risers (9), the horizontal plate (10) of supporting vertical plate (9).
2. according to the described bispin wing of claim 1 depopulated helicopter, it is characterized in that there is an angle in described mast (1,5), angle is 11 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220755823 CN203078753U (en) | 2012-12-31 | 2012-12-31 | Double-rotor-wing unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220755823 CN203078753U (en) | 2012-12-31 | 2012-12-31 | Double-rotor-wing unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203078753U true CN203078753U (en) | 2013-07-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220755823 Expired - Lifetime CN203078753U (en) | 2012-12-31 | 2012-12-31 | Double-rotor-wing unmanned helicopter |
Country Status (1)
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| CN (1) | CN203078753U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104097768A (en) * | 2014-08-05 | 2014-10-15 | 杨克伟 | Longitudinally crossed dual-rotor helicopter |
| JP2016026946A (en) * | 2014-06-26 | 2016-02-18 | 国立大学法人 名古屋工業大学 | Ground traveling flight vehicle having function for horizontalizing flight vehicle body independently of inclination of protection frame axis |
| TWI633915B (en) * | 2017-05-26 | 2018-09-01 | 尚皇科技有限公司 | Control method of flight direction of remote control aircraft |
| WO2020259570A1 (en) * | 2019-06-24 | 2020-12-30 | 南京航空航天大学 | Modular intermeshing and tandem unmanned helicopter and working method thereof |
-
2012
- 2012-12-31 CN CN 201220755823 patent/CN203078753U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016026946A (en) * | 2014-06-26 | 2016-02-18 | 国立大学法人 名古屋工業大学 | Ground traveling flight vehicle having function for horizontalizing flight vehicle body independently of inclination of protection frame axis |
| CN104097768A (en) * | 2014-08-05 | 2014-10-15 | 杨克伟 | Longitudinally crossed dual-rotor helicopter |
| CN104097768B (en) * | 2014-08-05 | 2016-09-14 | 杨克伟 | Crossed longitudinally formula DCB Specimen depopulated helicopter |
| TWI633915B (en) * | 2017-05-26 | 2018-09-01 | 尚皇科技有限公司 | Control method of flight direction of remote control aircraft |
| WO2020259570A1 (en) * | 2019-06-24 | 2020-12-30 | 南京航空航天大学 | Modular intermeshing and tandem unmanned helicopter and working method thereof |
| GB2594816A (en) * | 2019-06-24 | 2021-11-10 | Univ Nanjing Aeronautics & Astronautics | Modular intermeshing and tandem unmanned helicopter and working method thereof |
| GB2594816B (en) * | 2019-06-24 | 2023-07-19 | Univ Nanjing Aeronautics & Astronautics | Modular intermeshing and tandem unmanned helicopter and working method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Assignor: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd.|Zhao Runhong Contract record no.: 2017990000070 Denomination of utility model: Crossed type dual-rotor unmanned helicopter Granted publication date: 20130724 License type: Exclusive License Record date: 20170307 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170428 Address after: 300000 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Address before: No. 300151 Tianjin road Hebei District City, Wang Chuanchang Hospital No. 62 Co-patentee before: Zhao Runhong Patentee before: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130724 |