CN204452934U - The double mode aircraft of rotor, fixed-wing - Google Patents

The double mode aircraft of rotor, fixed-wing Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
wing
ppopeller
rotor
jet
vertical thrust
Prior art date
Application number
CN201520079994.0U
Other languages
Chinese (zh)
Inventor
仉军
Original Assignee
仉军
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 仉军 filed Critical 仉军
Priority to CN201520079994.0U priority Critical patent/CN204452934U/en
Application granted granted Critical
Publication of CN204452934U publication Critical patent/CN204452934U/en

Links

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

The double mode aircraft of rotor, fixed-wing

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.
CN201520079994.0U 2015-02-05 2015-02-05 The double mode aircraft of rotor, fixed-wing CN204452934U (en)

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

Family

ID=53659857

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201520079994.0U 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 (15)

* Cited by examiner, † Cited by third party
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
CN105197236A (en) * 2015-10-30 2015-12-30 佛山市神风航空科技有限公司 Compound lifting device
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
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
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
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
CN105235894A (en) * 2015-10-30 2016-01-13 佛山市神风航空科技有限公司 Aerodynamic device
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
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
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

Cited By (18)

* Cited by examiner, † Cited by third party
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
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
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
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
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
CN105235894A (en) * 2015-10-30 2016-01-13 佛山市神风航空科技有限公司 Aerodynamic device
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
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
CN105197233A (en) * 2015-10-30 2015-12-30 佛山市神风航空科技有限公司 Double-engine aircraft
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
CN105197236A (en) * 2015-10-30 2015-12-30 佛山市神风航空科技有限公司 Compound lifting device
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

Similar Documents

Publication Publication Date Title
CN106005400B (en) Fixed Wing AirVehicle takes off vertically auxiliary system
CN107074358B (en) Vertical take-off and landing aircraft
CN204489181U (en) Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane
US9499266B1 (en) Five-wing aircraft to permit smooth transitions between vertical and horizontal flight
WO2014081082A1 (en) Multi-stage tilting and multi-rotor flying car
US20140217229A1 (en) Unmanned aerial vehicle
CN200995782Y (en) Airplane
US9321526B2 (en) Compound helicopter
CN201923320U (en) Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle
CN102133926B (en) Tailstock type vertical take-off and landing unmanned aerial vehicle
CN104290906B (en) A kind of vertically taking off and landing flyer
CN104276284B (en) A kind of series type fan rotor aircraft layout
CN202728575U (en) Composite aircraft with fixed wing and electric multi-rotor-wing combined
RU141669U1 (en) Vertical takeoff and landing flight
CN103979104B (en) One can variant X-type wing vertical landing minute vehicle
US20070246601A1 (en) Manned/unmanned V.T.O.L. flight vehicle
CN205440869U (en) Fixed chord flight time aircraft of canard configuration of VTOL
CN103043212A (en) Combined aircraft composed of fixed wing and electric multi-rotor wing
CN202011472U (en) Tilting duct unmanned aerial vehicle
CN204250360U (en) Culvert type verts aircraft
CN105473443A (en) Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable
CN103935512A (en) High endurable multi-rotor craft
CN206417197U (en) A kind of tandem wing vertically mixes landing aircraft
WO2014062097A1 (en) Convertiplane (variants)
FR2993859A1 (en) Push and pull propelled multi-planar aircraft i.e. transport aircraft, has propellers arranged to produce pushing forces directed according to longitudinal direction and directed forwardly along movement direction of aircraft during flight

Legal Events

Date Code Title Description
GR01 Patent grant
C14 Grant of patent 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: Zhang Jun

C41 Transfer of patent application or patent right or utility model