CN103057704A - Rotor-type one-man aircraft - Google Patents
Rotor-type one-man aircraft Download PDFInfo
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- CN103057704A CN103057704A CN2013100031607A CN201310003160A CN103057704A CN 103057704 A CN103057704 A CN 103057704A CN 2013100031607 A CN2013100031607 A CN 2013100031607A CN 201310003160 A CN201310003160 A CN 201310003160A CN 103057704 A CN103057704 A CN 103057704A
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Abstract
The invention discloses a rotor-type one-man aircraft comprises a backpack, a rotor, a housing, and a propeller. The rotor is arranged on the upper end of backpack. The housing is arranged on the back of the backpack. The propeller is arranged in the housing. An engine used for driving the propeller is arranged on the housing. The housing is provided with a first hinge point, a second hinge point and a third hinge point. The first hinge point, the second hinge point and the third hinge point form an isosceles triangle, wherein the first hinge point is positioned at the top corner of the isosceles triangle. The first hinge point is connected onto the housing through a first ball joint. Operating levers are arranged on two sides of the housing. Each of the second hinge point and the third hinge point is respectively hinged to one operating lever on one side of the housing. The aircraft provided by the invention is small, light, flexible, and reliable, and has the advantages of simple structure and easy driving. The aircraft provided by the invention can be used in occasions such as investigation, accident emergency escape, aerial photography, forest fire prevention, and the like.
Description
Technical field
The present invention relates to the vehicle technology field, belong to the rotary wind type individual lift device.
Background technology
According to present national defence, the needs of emergency survival and people's lives, people expect a kind of flight safety, economic and practical micro-miniature individual lift device easy to use.Present individual lift device is by autogyro, cyclogyro, fire balloon, dirigible and propeller-parachuting distortion.The individual lift device of autogyro class adopts the twin screw backward rotation mostly for saving the tail-rotor structure, makes Flight Vehicle Structure complicated, involves great expense.The individual lift device cost of fire balloon and dirigible class is high, bulky, is subjected to weather effect large, drives difficulty.Although Aircraft class individual lift device is cheap, drive complexity, poor reliability.Cyclogyro is simple in structure, and only has the back screw propeller to need power, in flight course, even engine breakdown is flame-out, rotor can realize that rotation descends, and safety is also high, be well suited for the prototype as individual lift device, but its driftage control needs the vertical fin motion of rudder, and pitch control subsystem needs the rotor pitching, and structure can't further be simplified, control system is complicated, handle difficulty, though existing some improvement projects that have also need to use fluid control or complex mechanical structure.Simple in structure for realizing individual lift device, the target of easily controlling flexibly, needs propose and study a kind of Flight Vehicle Structure of novelty.
Summary of the invention
The object of the present invention is to provide a kind of small volume and less weight, simple in structure, drive easily and the individual lift device of flexibility and reliability, i.e. a kind of rotary wind type individual lift device.
The technical solution adopted for the present invention to solve the technical problems is:
A kind of rotary wind type individual lift device, comprise knapsack, rotor, outer cover and screw propeller, wherein rotor is arranged on the upper end of described knapsack, described outer cover is arranged on the back side of knapsack, described screw propeller is set in described outer cover, on described outer cover, also be provided with the driving engine of the described screw propeller of a driving, it is characterized in that: be provided with the first hinge-point on the described outer cover, the second hinge-point and the 3rd hinge-point, described the first hinge-point, the second hinge-point and equicrural triangle of the 3rd hinge-point formation and the first hinge-point are positioned at the drift angle of equicrural triangle, wherein the first hinge-point is hinged and connected on the outer cover by the first ball-type, in the outer cover both sides one joystick is set respectively, described the second hinge-point and the 3rd hinge-point are hinged with the joystick of outer cover one side respectively.
In described joystick horizontal component, be provided with chute, in chute, be provided with a spherical slide block, spherical slide block both sides in chute arrange respectively a retracing spring, on described spherical sliding block, also be connected with a connect fixed parts, this connect fixed parts and described knapsack are affixed, at the vertical section of described one of them joystick ignition governor are installed.
The rotor head of described rotor adopts seesaw to connect, rotor connects by the rod shaped structure on bearing and the knapsack, fuel oil is housed in the knapsack, by oil hose oil input is installed in driving engine on the outer cover, be provided with a quarter butt at the described knapsack back side, first spherical hinge of described outer cover by being positioned at the first hinge-point links to each other with quarter butt structure on the knapsack.
The invention has the beneficial effects as follows: small volume and less weight, simple in structure, drive easily and flexibility and reliability, can realize that by manual control the direction of individual lift device driftage pitching is controlled, simplified the cyclogyro steering control modes.Can be used as individual's flight vehicle and be used for investigation, the contingency emergency escape is taken photo by plane, the occasions such as forest fire protection.
Description of drawings
Fig. 1 is structure External view of the present invention.
Fig. 2 is joystick horizontal segment schematic perspective view.(internal chute top is concealed with show internal structure)
Fig. 3 is spherical slide block degree of freedom scheme drawing in the joystick.
Fig. 4 is the inner structure scheme drawing.
Fig. 5 is the A-A section-drawing of Fig. 4.
Fig. 6 is the ignition governor schematic perspective view.
Fig. 7 is the present invention's the second spherical hinge section and outer cover relative position scheme drawing.
Operating control schematic side view and the machine stress figure of Fig. 8 when to be the present invention to aircraft bow control.
Operating control schematic side view and the machine stress figure of Fig. 9 when to be the present invention to aircraft face upward head control.
Operating control schematic top plan view and the machine stress figure of Figure 10 when to be the present invention to aircraft do dextrad driftage control.
Operating control schematic top plan view and the machine stress figure of Figure 11 when to be the present invention to aircraft do left-hand driftage control.
Among the figure: 1, rotor, 2, knapsack, 3, braces, 4, quick-release mechanism, 5, ignition governor, 6, joystick, 7, outer cover, 8, screw propeller, the 9, first spherical hinge, 10, driving engine, 11, oil hose, the 12, second spherical hinge, 13, retracing spring, 14, internal chute, 15, spherical slide block, 16, connect fixed parts.
The specific embodiment
Be elaborated below in conjunction with the technical scheme of accompanying drawing to invention:
Referring to accompanying drawing 1, the present invention includes rotor 1, knapsack 2, braces 3, quick-release mechanism 4, ignition governor 5, joystick 6, outer cover 7, screw propeller 8, the first spherical hinges 9, driving engine 10, oil hose 11, the second spherical hinge 12, retracing spring 13, internal chute 14, spherical slide block 15, connect fixed parts 16.Wherein the rotor head of rotor 1 adopts seesaw to connect, and can reach moving stable when attitude of flight vehicle changes.Rotor 1 connects by the rod shaped structure on bearing and the knapsack 2, in the knapsack 2 fuel oil is housed, and can the oil input be installed in driving engine on the outer cover 7 by oil hose 11, and driving engine 10 drives back screw propellers 8 and rotates, and power is provided.Outer cover 7 links to each other with quarter butt structure on the knapsack 2 by the first spherical hinge 9.Joystick 6 connects by ball the first hinge 9 with outer cover 7, can realize the direction control of individual lift device driftage pitching by manual push-and-pull joystick 6 tilting propellers 8.
Referring to accompanying drawing 2, joystick 6 is by retracing spring 13, internal chute 14, and spherical slide block 15 forms.Internal chute 14 built-in spherical slide block 15 and retracing springs 13 wherein, and spherical slide block 15 is affixed by connect fixed parts 16 and knapsack 2.
Referring to accompanying drawing 3, spherical slide block 15 has rotational freedom (ROTY, ROTZ) at Y and Z direction in internal chute 14, at directions X one-movement-freedom-degree (UX) is arranged.
Referring to accompanying drawing 4 and Fig. 5, the internal chute 14 built-in retracing springs 13 of joystick 6 are not when joystick is controlled by the operator, because spring-force driven dual, spherical slide block 15 can be realized resetting automatically, and back screw propeller 8 thereby recovery horizontal thrust continue to realize cruising flight.
The aircraft takeoff mode, can realize by ignition governor 5 startup and the speed governing of aircraft, ignition governor 5 is positioned on the vertical section of right side joystick 6, and startup can start by the press-button structure of ignition governor 5, and speed governing can be regulated by the rotational structure of ignition governor 5.Driving engine 10 drives back screw propeller 8 and rotates, and gives forward thrust of personnel, and personnel's run-up moves ahead fast, and line speed can make rotor produce horizontal direction aerodynamic force and vertical direction aerodynamic force before the level, and the horizontal direction aerodynamic drag is rotated rotor and accelerated.The horizontal forward movement of rotor and rotation cause the vertical direction aerodynamic lift constantly to increase, until 1 tool lift of rotor is during greater than gravity, and aircraft takeoff.
When needing diving flight, referring to accompanying drawing 8, pusher both sides joystick 6 simultaneously, joystick 6 outer cover 7 of ining succession drives screw propellers 8 and is inclined upwardly, and produces a downward component, make aircraft bow and move downward, after reaching predetermined altitude, loosen the control to joystick 6, spherical slide block 15 can be realized resetting automatically, back screw propeller 8 thereby recovery horizontal thrust continue to realize cruising flight.
In the time of need to upwards climbing, referring to accompanying drawing 9, draw both sides joystick 6 simultaneously, joystick 6 is ined succession, and to drive screw propellers 8 downward-sloping for outer cover 7, produces a component that makes progress, make aircraft face upward head, after rising to predetermined altitude, loosen the control to joystick 6, spherical slide block 15 can be realized resetting automatically, back screw propeller 8 thereby recovery horizontal thrust continue to realize cruising flight.
When needing left-hand driftage control, referring to accompanying drawing 10, left hand is to pusher joystick 6, and the right hand draws forward joystick 6, in succession outer cover 7 of joystick 6 drives screw propellers 8 and is tilted to the left, generation one component left makes the driftage of aircraft left-hand, after the left-hand departure distance reaches requirement, loosen the control to joystick 6, spherical slide block 15 can be realized resetting automatically, and back screw propeller 8 thereby recovery horizontal thrust continue to realize cruising flight.
When needing the dextrad driftage, referring to accompanying drawing 11, left hand draws forward joystick 6, and the right hand is to pusher joystick 6, in succession outer cover 7 of joystick 6 drives screw propellers 8 lateral inclinations, generation one component to the right makes the driftage of aircraft dextrad, after the dextrad departure distance reaches requirement, loosen the control to joystick 6, spherical slide block 15 can be realized resetting automatically, and back screw propeller 8 thereby recovery horizontal thrust continue to realize cruising flight.
Claims (3)
1. rotary wind type individual lift device, comprise knapsack (2), rotor (1), outer cover (7) and screw propeller (8), wherein rotor (1) is arranged on the upper end of described knapsack (2), described outer cover (7) is arranged on the back side of knapsack (2), described screw propeller (8) is set in described outer cover (7), on described outer cover (7), also be provided with the driving engine (10) of a described screw propeller of driving (8), it is characterized in that: described outer cover is provided with the first hinge-point on (7), the second hinge-point and the 3rd hinge-point, described the first hinge-point, the second hinge-point and equicrural triangle of the 3rd hinge-point formation and the first hinge-point are positioned at the drift angle of equicrural triangle, wherein the first hinge-point is hinged and connected on the outer cover (7) by the first ball-type, in outer cover (7) both sides one joystick (6) is set respectively, described the second hinge-point and the 3rd hinge-point are hinged with the joystick (6) of outer cover (7) one sides respectively.
2. according to claims 1 described rotary wind type individual lift device, it is characterized in that: in described joystick (6) horizontal component, be provided with chute (14), in chute (14), be provided with a spherical slide block (15), spherical slide block (15) both sides in chute (14) arrange respectively a retracing spring (13), on described spherical sliding block (15), also be connected with a connect fixed parts (16), this connect fixed parts (16) is affixed with described knapsack (2), at the vertical section of described one of them joystick ignition governor (5) is installed.
3. according to claims 1 or 2 described rotary wind type individual lift devices, it is characterized in that: the rotor head of described rotor (1) adopts seesaw to connect, rotor (1) connects by the rod shaped structure on bearing and the knapsack (2), knapsack is equipped with fuel oil in (3), by oil hose (11) oil input is installed in driving engine on the outer cover (7), be provided with a quarter butt at described knapsack (2) back side, first spherical hinge (9) of described outer cover (7) by being positioned at the first hinge-point links to each other with quarter butt structure on the knapsack (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310003160.7A CN103057704B (en) | 2013-01-07 | 2013-01-07 | Rotor-type one-man aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310003160.7A CN103057704B (en) | 2013-01-07 | 2013-01-07 | Rotor-type one-man aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103057704A true CN103057704A (en) | 2013-04-24 |
| CN103057704B CN103057704B (en) | 2015-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310003160.7A Expired - Fee Related CN103057704B (en) | 2013-01-07 | 2013-01-07 | Rotor-type one-man aircraft |
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| CN (1) | CN103057704B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103480126A (en) * | 2013-09-24 | 2014-01-01 | 李先强 | Wall surface assisting crawl device |
| CN106904277A (en) * | 2017-04-18 | 2017-06-30 | 佛山市神风航空科技有限公司 | A kind of run-up device |
| CN106986025A (en) * | 2017-04-18 | 2017-07-28 | 佛山市神风航空科技有限公司 | A kind of wearable thruster |
| CN106995057A (en) * | 2017-04-18 | 2017-08-01 | 佛山市神风航空科技有限公司 | One kind is help others load device |
| CN106995056A (en) * | 2017-04-18 | 2017-08-01 | 佛山市神风航空科技有限公司 | A kind of wearable power assisting device |
| CN109050939A (en) * | 2018-01-24 | 2018-12-21 | 容科培 | A kind of umbellate form high altitude escape aircraft |
| CN110844086A (en) * | 2019-12-19 | 2020-02-28 | 高洪江 | Power umbrella based on electric multi-propeller power device |
Citations (9)
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| US5160100A (en) * | 1991-07-01 | 1992-11-03 | Snyder Stephen Louis | Airfoil canopy aircraft |
| DE10008678A1 (en) * | 2000-02-24 | 2001-08-30 | Baumann Ul Sportgeraete Entwic | Cockpit construction for ultra-light aircraft, which can be connected to a various different airfoils |
| CN2714419Y (en) * | 2004-05-27 | 2005-08-03 | 赵清武 | Light-duty propcopter |
| KR200437753Y1 (en) * | 2006-11-30 | 2008-01-02 | 이순헌 | Trike of power-paraglider |
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| CN201354151Y (en) * | 2009-02-10 | 2009-12-02 | 叶鹤皋 | Electric one-man aircraft |
| WO2009151351A1 (en) * | 2008-06-11 | 2009-12-17 | Vasiliyj Andreevich Uvarov | Paramotor |
| CN102627147A (en) * | 2012-04-24 | 2012-08-08 | 赵辉 | One-man flight vehicle being capable of lifting vertically and provided with fixed wings |
| CN202464126U (en) * | 2011-12-13 | 2012-10-03 | 北京君研院科技有限公司 | Rotor wing blade tip jet one-man flight vehicle |
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2013
- 2013-01-07 CN CN201310003160.7A patent/CN103057704B/en not_active Expired - Fee Related
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5160100A (en) * | 1991-07-01 | 1992-11-03 | Snyder Stephen Louis | Airfoil canopy aircraft |
| DE10008678A1 (en) * | 2000-02-24 | 2001-08-30 | Baumann Ul Sportgeraete Entwic | Cockpit construction for ultra-light aircraft, which can be connected to a various different airfoils |
| CN2714419Y (en) * | 2004-05-27 | 2005-08-03 | 赵清武 | Light-duty propcopter |
| KR200437753Y1 (en) * | 2006-11-30 | 2008-01-02 | 이순헌 | Trike of power-paraglider |
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| WO2009151351A1 (en) * | 2008-06-11 | 2009-12-17 | Vasiliyj Andreevich Uvarov | Paramotor |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103480126A (en) * | 2013-09-24 | 2014-01-01 | 李先强 | Wall surface assisting crawl device |
| CN106904277A (en) * | 2017-04-18 | 2017-06-30 | 佛山市神风航空科技有限公司 | A kind of run-up device |
| CN106986025A (en) * | 2017-04-18 | 2017-07-28 | 佛山市神风航空科技有限公司 | A kind of wearable thruster |
| CN106995057A (en) * | 2017-04-18 | 2017-08-01 | 佛山市神风航空科技有限公司 | One kind is help others load device |
| CN106995056A (en) * | 2017-04-18 | 2017-08-01 | 佛山市神风航空科技有限公司 | A kind of wearable power assisting device |
| CN109050939A (en) * | 2018-01-24 | 2018-12-21 | 容科培 | A kind of umbellate form high altitude escape aircraft |
| CN110844086A (en) * | 2019-12-19 | 2020-02-28 | 高洪江 | Power umbrella based on electric multi-propeller power device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103057704B (en) | 2015-07-29 |
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Granted publication date: 20150729 Termination date: 20210107 |