CN204452934U - The double mode aircraft of rotor, fixed-wing - Google Patents
The double mode aircraft of rotor, fixed-wing Download PDFInfo
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- CN204452934U CN204452934U CN201520079994.0U CN201520079994U CN204452934U CN 204452934 U CN204452934 U CN 204452934U CN 201520079994 U CN201520079994 U CN 201520079994U CN 204452934 U CN204452934 U CN 204452934U
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- wing
- ppopeller
- rotor
- jet
- vertical thrust
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- 230000005484 gravity Effects 0.000 claims abstract description 4
- 241000566150 Pandion haliaetus Species 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- KEUKAQNPUBYCIC-UHFFFAOYSA-N ethaneperoxoic acid;hydrogen peroxide Chemical compound OO.CC(=O)OO KEUKAQNPUBYCIC-UHFFFAOYSA-N 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Abstract
The utility model discloses a kind of rotor, the double mode aircraft of fixed-wing, comprise the fuselage and wing with alighting gear, afterbody is equipped with level and advances ppopeller jet, under the wing of fuselage both sides, in front and back, trend is horizontally disposed with a rotor support respectively, the front and back end of rotor support is equipped with a vertical thrust ppopeller jet respectively, line intersection point between two the vertical thrust ppopeller jets wherein arranged in diagonal line overlaps with the center of gravity of aircraft, the hand of rotation of two its blades of vertical thrust ppopeller jet arranged in diagonal line is identical, the hand of rotation of two its blades of vertical thrust ppopeller jet that same rotor support front and back end is arranged is contrary.
Description
Technical field
The utility model relates to a kind of rotor, the double mode aircraft of fixed-wing.
Background technology
1981, the U.S. succeeded in developing practical tiltrotor on the basis of XV-15, and in January, 1985, it was V-22 " osprey " by definite designation.As a kind of tiltrotor, the fuselage of V-22 " osprey ", wing and common fixed wing aircraft basic simlarity, but its airscrew engine being positioned at wing two ends but can be rotated up and down.When airscrew engine forwards plumbness to from horizontality, V-22 " osprey " just can realize vertical takeoff and landing and hovering as helicopter, when airscrew engine is in horizontality, just can gives one, aircraft thrust forward, make it can fly as fixed wing aircraft.When airscrew engine is between this two states, both created lift, created thrust again, aircraft can be made with low-speed operations.Although tiltrotor has compared many advantages with general helicopter with fixed wing aircraft, but also there are many shortcomings, be mainly manifested in following several aspect: 1. technical risk high tiltrotor has wing again because of existing rotor, and realize rotor to vert to upright position from upright position to level attitude or level attitude, therefore the uncertain problem of aerodynamic characteristic in rotor verts process; 2. the aerodynamic interference problem between rotor/wing, rotor/rotor, rotor/body; 3. complex structural designs, when ensureing housing construction intensity: the problem such as weight, material, maintenance, reliability; 4. the dynamics analysis of rotor in the process of verting, rotor/wing coupling live load and stability problem; 5. many technical matterss of the aspect such as maneuvering and control technology and maneuvering system dynamics design; 6. in helicopter mode, because main wing has blocked the air-flow of part rotor, made loss of lift, the problem of hydraulic performance decline.
Summary of the invention
The purpose of this utility model is to provide a kind of rotor, fixed-wing double mode aircraft, can eliminate aerodynamic interference, and structure is simple, is easy to control, can not reduces loss of lift.
The purpose of this utility model realizes like this, a kind of rotor, the double mode aircraft of fixed-wing, comprise the fuselage and wing with alighting gear, afterbody is equipped with level and advances ppopeller jet, under the wing of fuselage both sides, in front and back, trend is horizontally disposed with a rotor support respectively, the front and back end of rotor support is equipped with a vertical thrust ppopeller jet respectively, line intersection point between two the vertical thrust ppopeller jets wherein arranged in diagonal line overlaps with the center of gravity of aircraft, the hand of rotation of two its blades of vertical thrust ppopeller jet arranged in diagonal line is identical, the hand of rotation of two its blades of vertical thrust ppopeller jet that same rotor support front and back end is arranged is contrary.
The utility model 1. can in the high altitude region landing flight of rarefaction of air; 2. can in city, forest, desert etc. fly without the small space landing of runway; 3. have maneuverability and the vertical takeoff and landing function of cyclogyro concurrently, have the function of the high energy efficiency of fixed wing aircraft, long voyage, heavy－duty simultaneously; 4. the Flight Vehicle Structure of this rotor, the double mode combination of fixed-wing is when ensureing housing construction intensity: weight is the lightest, materials are minimum, windage is minimum, structure is simple, be convenient to maintenance, wind resistance is strong; 5. the Flight Vehicle Structure of this rotor, the double mode combination of fixed-wing is convenient to the safe transition between vertical takeoff and landing pattern and horizontal flight pattern.
6.four outstanding wings of the double mode aircraft of this rotor, fixed-wing are in the below of fixed-wing, and therefore in helicopter mode, main wing can not block the air-flow of rotor, solves loss of lift, the problem of hydraulic performance decline.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Fig. 1 is main TV structure schematic diagram of the present utility model;
Fig. 2 of the present utility modelly looks up structural representation.
Detailed description of the invention
A kind of rotor, the double mode aircraft of fixed-wing, as Fig. 1, shown in Fig. 2, comprise the fuselage and wing 6 with alighting gear, afterbody is equipped with level and advances ppopeller jet 5, under the wing of fuselage both sides, in front and back, trend is horizontally disposed with a rotor support 9 respectively, the front and back end of rotor support 9 is equipped with a vertical thrust ppopeller jet 1 respectively, 2, 3, 4, two the vertical thrust ppopeller jets 1 wherein arranged in diagonal line, 3 and 2, line intersection point between 4 overlaps with the center of gravity 8 of aircraft, two the vertical thrust ppopeller jets 1 arranged in diagonal line, the hand of rotation of 3 its blades is identical, two the vertical thrust ppopeller jets 2 arranged in diagonal line, the hand of rotation of 4 its blades is identical, two vertical thrust ppopeller jets 1 that same rotor support front and back end is arranged, the hand of rotation of 4 its blades is contrary, two vertical thrust ppopeller jets 2 that same rotor support front and back end is arranged, the hand of rotation of 3 its blades is contrary.
Claims (1)
1. a rotor, the double mode aircraft of fixed-wing, comprise the fuselage and wing with alighting gear, afterbody is equipped with level and advances ppopeller jet, it is characterized in that: under the wing of fuselage both sides, in front and back, trend is horizontally disposed with a rotor support respectively, the front and back end of rotor support is equipped with a vertical thrust ppopeller jet respectively, line intersection point between two the vertical thrust ppopeller jets wherein arranged in diagonal line overlaps with the center of gravity of aircraft, the hand of rotation of two its blades of vertical thrust ppopeller jet arranged in diagonal line is identical, the hand of rotation of two its blades of vertical thrust ppopeller jet that same rotor support front and back end is arranged is contrary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520079994.0U CN204452934U (en) | 2015-02-05 | 2015-02-05 | The double mode aircraft of rotor, fixed-wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520079994.0U CN204452934U (en) | 2015-02-05 | 2015-02-05 | The double mode aircraft of rotor, fixed-wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204452934U true CN204452934U (en) | 2015-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520079994.0U Expired - Fee Related CN204452934U (en) | 2015-02-05 | 2015-02-05 | The double mode aircraft of rotor, fixed-wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204452934U (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151273A (en) * | 2015-10-30 | 2015-12-16 | 佛山市神风航空科技有限公司 | Multi-propeller airplane |
| CN105197235A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Double-propeller combined wing |
| CN105197233A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Double-engine aircraft |
| CN105197234A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Combined aircraft provided with empennage |
| CN105197236A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Compound lifting device |
| CN105217028A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type autogiro |
| CN105217022A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type delta-wing aircraft |
| CN105235894A (en) * | 2015-10-30 | 2016-01-13 | 佛山市神风航空科技有限公司 | Aerodynamic device |
| CN105270615A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Multi-axle aircraft with front wing and rear wing |
| CN105270623A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | High lift aircraft |
| CN105270614A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Symmetric eight-axle aircraft |
| CN105346714A (en) * | 2015-09-29 | 2016-02-24 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned plane |
| CN106347657A (en) * | 2016-09-30 | 2017-01-25 | 扬州锐德飞科技有限公司 | Unmanned aerial vehicle for surveying geographic information and working method thereof |
| CN106394856A (en) * | 2016-10-28 | 2017-02-15 | 北京尖翼科技有限公司 | Composite wing unmanned aerial vehicle |
| CN106564589A (en) * | 2015-10-07 | 2017-04-19 | 申俊勇 | Fixed rotary wing rotary aircraft |
| CN113784891A (en) * | 2019-03-25 | 2021-12-10 | 力福特空气有限公司 | Flying apparatus |
-
2015
- 2015-02-05 CN CN201520079994.0U patent/CN204452934U/en not_active Expired - Fee Related
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346714A (en) * | 2015-09-29 | 2016-02-24 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned plane |
| CN106564589A (en) * | 2015-10-07 | 2017-04-19 | 申俊勇 | Fixed rotary wing rotary aircraft |
| CN105270614A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Symmetric eight-axle aircraft |
| CN105197233A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Double-engine aircraft |
| CN105197236A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Compound lifting device |
| CN105217028A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type autogiro |
| CN105217022A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type delta-wing aircraft |
| CN105235894A (en) * | 2015-10-30 | 2016-01-13 | 佛山市神风航空科技有限公司 | Aerodynamic device |
| CN105270615A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Multi-axle aircraft with front wing and rear wing |
| CN105270623A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | High lift aircraft |
| CN105151273A (en) * | 2015-10-30 | 2015-12-16 | 佛山市神风航空科技有限公司 | Multi-propeller airplane |
| CN105197234A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Combined aircraft provided with empennage |
| CN105235894B (en) * | 2015-10-30 | 2017-11-17 | 佛山市神风航空科技有限公司 | A kind of air generation plants |
| CN105197235A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Double-propeller combined wing |
| CN106347657A (en) * | 2016-09-30 | 2017-01-25 | 扬州锐德飞科技有限公司 | Unmanned aerial vehicle for surveying geographic information and working method thereof |
| CN106347657B (en) * | 2016-09-30 | 2019-02-19 | 扬州锐德飞科技有限公司 | A kind of unmanned plane and its working method for geography information exploration |
| CN106394856A (en) * | 2016-10-28 | 2017-02-15 | 北京尖翼科技有限公司 | Composite wing unmanned aerial vehicle |
| CN106394856B (en) * | 2016-10-28 | 2019-07-02 | 北京尖翼科技有限公司 | A kind of composite wing unmanned plane |
| CN113784891A (en) * | 2019-03-25 | 2021-12-10 | 力福特空气有限公司 | Flying apparatus |
| EP3947144A1 (en) * | 2019-03-25 | 2022-02-09 | Lift Air GmbH | Aircraft |
| DE102019107593B4 (en) | 2019-03-25 | 2024-11-07 | Lift Air Gmbh | flying device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160112 Address after: 830011 room 1601, Xinfa building, No. 442 South Beijing Road, the Xinjiang Uygur Autonomous Region, Urumqi Patentee after: XINJIANG JIAHANG ELECTRONIC TECHNOLOGY Co.,Ltd. Address before: 830011 the Xinjiang Uygur Autonomous Region Urumqi city Beijing Road No. 226 fashion Tsui District No. 4 North building six unit 201 Patentee before: Army |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150708 |