CN205098469U - Gyroplane verts - Google Patents
Gyroplane verts Download PDFInfo
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- CN205098469U CN205098469U CN201520833566.2U CN201520833566U CN205098469U CN 205098469 U CN205098469 U CN 205098469U CN 201520833566 U CN201520833566 U CN 201520833566U CN 205098469 U CN205098469 U CN 205098469U
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- tiliting axis
- fuselage
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- transmission
- rotary mechanism
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Abstract
The utility model discloses a gyroplane verts, include fuselage, rotor, set up the wing on the fuselage and set up in the undercarriage of fuselage bottom, still include vert mechanism and collapsible paddle, vert the establishment of institution in the fore -body, it includes the tiliting axis and is used for driving tiliting axis pivoted driving piece to vert the mechanism, stretch out at tiliting axis traversing fuselage and both ends, the rotor symmetry sets up the both ends of tiliting axis, collapsible paddle setting is in the bottom of fuselage tail end, collapsible paddle includes pivot, driving piece, paddle mounting disc and paddle, pivot one end is connected set up on the driving piece other end in the paddle mounting disc. The utility model discloses compare with prior art's structure, set up driving piece and tiliting axis, simplified the structure greatly on the basis of guaranteeing original function to driving piece and tiliting axis all are common part, greatly reduced the cost.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly relates to a kind of tiltrotor.
Background technology
Along with the fast development of unmanned plane industry, aircraft is more and more advanced, and the kind of aircraft is also more and more various, main based on fixed wing aircraft and autogyro at present.For fixed wing aircraft, most fixed wing aircraft needs longer plane track, can not vertical takeoff and landing and hovering, although and helicopter can vertical takeoff and landing and hovering, its flying distance is shorter, therefore, the tiltrotor with both advantages is arisen at the historic moment, but existing tiltrotor all complex structures, keep in repair loaded down with trivial details, price is high.
Utility model content
Technical problem to be solved in the utility model is: provide the tiltrotor that a kind of structure is simple, with low cost.
In order to solve the problems of the technologies described above, the technical solution adopted in the utility model is: provide a kind of tiltrotor, comprise fuselage, rotor, be arranged at the wing on fuselage and be arranged at the alighting gear of fuselage bottom, also comprise inclining rotary mechanism, described inclining rotary mechanism is arranged at described forebody, described inclining rotary mechanism comprises tiliting axis and the actuator for driving tiliting axis to rotate, and described tiliting axis is horizontally through fuselage and two ends are stretched out, and described rotor is symmetricly set on the two ends of described tiliting axis;
Described collapsible blade is arranged on the bottom of fuselage tail end, described collapsible blade comprises rotating shaft, actuator, blade subpanel and blade, described blade is articulated with in described blade subpanel, and described rotating shaft one end connects on the described actuator other end and arranges in described blade subpanel.
Further, described driver train comprises drive motor, and the output shaft of described drive motor connects the first Transmission, described tiliting axis is provided with the second Transmission, and described first Transmission and the second Transmission are in transmission connection.
Further, described first Transmission is worm screw, and described second Transmission is turbine, and described Cover For A Turbine is connected on described tiliting axis, described worm and wheel engagement.
Further, described tiliting axis is provided with angular transducer.
The beneficial effects of the utility model are: the utility model tiltrotor comprises inclining rotary mechanism and collapsible blade, inclining rotary mechanism is arranged at forebody, tiliting axis is horizontally through fuselage and two ends are stretched out, rotor is symmetricly set on the two ends of described tiliting axis, collapsible blade is arranged on the bottom of fuselage tail end, under inclining rotary mechanism and collapsible blade mating reaction, cyclogyro takes off, when horizontal flight, inclining rotary mechanism turns to correct position, utilize worm-and-wheel gear have self-locking characteristic ensure vert after rotor be stabilized in current location, this inclining rotary mechanism can not cause the change of rotor angle because of outer unpredictable external force, and under the effect of collapsible blade air-flow in the horizontal direction, blade can carry out auto-folder along the opposite sense in aircraft flight direction, the utility model compares the structure with prior art, actuator and tiliting axis are set, the basis ensureing original function enormously simplify structure, and actuator and tiliting axis are all common part, greatly reduce cost, simultaneously, adopt the structure that collapsible blade matches with inclining rotary mechanism, effectively can promote lift coefficient when taking off, and effectively can reduce the resistance of cyclogyro when flying.
Accompanying drawing explanation
Fig. 1 is the structural representation of the tiltrotor of the utility model embodiment;
Fig. 2 is the structural representation of the inclining rotary mechanism of the tiltrotor of the utility model embodiment;
Fig. 3 is the structural representation of the collapsible blade of the tiltrotor of the utility model embodiment.
Label declaration:
1, fuselage; 2, rotor; 3, wing; 4, alighting gear; 5, inclining rotary mechanism; 51, tiliting axis; 52, actuator; 53, angular transducer; 6, wing flap; 7, the first Transmission; 8, the second Transmission; 9, collapsible blade; 91, rotating shaft; 92, actuator; 93, blade subpanel; 94, blade.
Detailed description of the invention
By describing technology contents of the present utility model in detail, realized object and effect, accompanying drawing is coordinated to be explained in detail below in conjunction with embodiment.
The design of the utility model most critical is: the utility model tiltrotor, comprise inclining rotary mechanism 5 and collapsible blade 9, wherein inclining rotary mechanism 5 comprises actuator 52 and tiliting axis 51, tiliting axis 51 is horizontally through fuselage 1 and arranges rotor 2 at two ends, collapsible blade 9 can fold when horizontal flight, the utility model structure is simple, easy to maintenance, and resistance when effectively can reduce horizontal flight.
Refer to Fig. 1 and Fig. 3, the utility model tiltrotor, comprise fuselage 1, rotor 2, the alighting gear 4 that is arranged at the wing 3 on fuselage 1 and is arranged at bottom fuselage 1, also comprise inclining rotary mechanism 5, it is anterior that described inclining rotary mechanism 5 is arranged at described fuselage 1, described inclining rotary mechanism 5 comprises tiliting axis 51 and the actuator 52 for driving tiliting axis 51 to rotate, and described tiliting axis 51 is horizontally through fuselage 1 and two ends are stretched out, and described rotor 2 is symmetricly set on the two ends of described tiliting axis 51;
Described collapsible blade 9 is arranged on the bottom of fuselage 1 tail end, described collapsible blade 9 comprises rotating shaft 91, actuator 92, blade subpanel 93 and blade 94, described blade 94 is articulated with in described blade subpanel 93, and described rotating shaft 91 one end connects on described actuator 92 other end and arranges in described blade subpanel 93.
From foregoing description, the beneficial effects of the utility model are: the utility model tiltrotor comprises inclining rotary mechanism 5 and collapsible blade 9, it is anterior that inclining rotary mechanism 5 is arranged at fuselage 1, its tiliting axis 51 is horizontally through fuselage 1 and two ends are stretched out, rotor 2 is symmetricly set on the two ends of described tiliting axis 51, collapsible blade 9 is arranged on the bottom of fuselage 1 tail end, under inclining rotary mechanism 5 and collapsible blade 9 mating reaction, cyclogyro takes off, when horizontal flight, inclining rotary mechanism 5 turns to correct position, under the effect of collapsible blade 9 air-flow in the horizontal direction, blade 94 can carry out auto-folder along the opposite sense in aircraft flight direction, the utility model compares the structure with prior art, actuator 52 and tiliting axis 51 are set, the basis ensureing original function enormously simplify structure, and actuator 52 and tiliting axis 51 are all common part, greatly reduce cost, simultaneously, adopt the structure that collapsible blade 9 matches with inclining rotary mechanism 5, effectively can promote lift coefficient when taking off, and effectively can reduce the resistance of cyclogyro when flying.
In the present embodiment, there is corresponding internal relation in angle a and angle b, when angle a is constant, during angle b deflection 50 ~ 60 degree, lift coefficient approximately can be made to increase 65% ~ 75%.Wherein, the change scope of angle a mainly by rotor and bottom surface apart from and with the impact of wing distance.
Further, described driver train comprises drive motor, and the output shaft of described drive motor connects the first Transmission 7, described tiliting axis 51 is provided with the second Transmission 8, and described first Transmission 7 and the second Transmission 8 are in transmission connection.
Further, described first Transmission 7 is worm screw, and described second Transmission 8 is turbine, and described Cover For A Turbine is connected on described tiliting axis 51, described worm and wheel engagement.
Seen from the above description, between the actuator 52 of the present embodiment and tiliting axis 51, worm gear and worm drive is adopted, certainly, also can with servomotor or the component such as gear and tooth bar in some other embodiment.
Further, described tiliting axis 51 is provided with angular transducer 53.
Seen from the above description, whether rotated to desired location by sensor Real-Time Monitoring tiliting axis 51, be of value to the utility model tiltrotor and take off in optimum regime or hover.
Please refer to Fig. 1 and Fig. 2, embodiment one of the present utility model is: the present embodiment tiltrotor aircraft, comprise fuselage 1, rotor 2, wing 3, alighting gear 4, inclining rotary mechanism 5, wing flap 6 and collapsible blade 9, wing 3 is symmetrical arranged on the fuselage 1, alighting gear 4 is arranged on the bottom of fuselage 1, inclining rotary mechanism 5 is arranged at described fuselage 1 front portion also and between wing 3 has gap, and wing flap 6 is arranged on the trailing edge of wing 3.
This inclining rotary mechanism 5 comprises tiliting axis 51 and the drive motor for driving tiliting axis 51 to rotate, and the output shaft connecting worm of this drive motor, tiliting axis 51 is socketed with turbine, and this worm and wheel is in transmission connection.This tiliting axis 51 is horizontally through fuselage 1 and two ends are stretched out, and rotor 2 is symmetricly set on the two ends of described tiliting axis 51, and tiliting axis 51 is provided with angular transducer 53.
This collapsible blade 9 is arranged on the bottom of fuselage 1 tail end, described collapsible blade 9 comprises rotating shaft 91, actuator 92, blade subpanel 93 and blade 94, described blade 94 is articulated with in described blade subpanel 93, and described rotating shaft 91 one end connects on described actuator 92 other end and arranges in described blade subpanel 93.
In sum, the tiltrotor that the utility model provides, structure is simple, greatly reduce manufacturing cost, flies more safe and reliable simultaneously.
The foregoing is only embodiment of the present utility model; not thereby the scope of the claims of the present utility model is limited; every equivalents utilizing the utility model specification sheets and accompanying drawing content to do; or be directly or indirectly used in relevant technical field, be all in like manner included in scope of patent protection of the present utility model.
Claims (4)
1. a tiltrotor, comprise fuselage, rotor, be arranged at the wing on fuselage and be arranged at the alighting gear of fuselage bottom, it is characterized in that, also comprise inclining rotary mechanism and collapsible blade, described inclining rotary mechanism is arranged at described forebody, described inclining rotary mechanism comprises tiliting axis and the actuator for driving tiliting axis to rotate, and described tiliting axis is horizontally through fuselage and two ends are stretched out, and described rotor is symmetricly set on the two ends of described tiliting axis;
Described collapsible blade is arranged on the bottom of fuselage tail end, and described collapsible blade comprises rotating shaft, actuator, blade subpanel and blade, and described rotating shaft one end connects on the described actuator other end and arranges in described blade subpanel.
2. tiltrotor according to claim 1, it is characterized in that, described driver train comprises drive motor, and the output shaft of described drive motor connects the first Transmission, described tiliting axis is provided with the second Transmission, described first Transmission and the second Transmission are in transmission connection.
3. tiltrotor according to claim 2, is characterized in that, described first Transmission is worm screw, and described second Transmission is turbine, and described Cover For A Turbine is connected on described tiliting axis, described worm and wheel engagement.
4. the tiltrotor according to any one of claim 1-3, is characterized in that, described tiliting axis is provided with angular transducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520833566.2U CN205098469U (en) | 2015-10-26 | 2015-10-26 | Gyroplane verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520833566.2U CN205098469U (en) | 2015-10-26 | 2015-10-26 | Gyroplane verts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205098469U true CN205098469U (en) | 2016-03-23 |
Family
ID=55514270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520833566.2U Active CN205098469U (en) | 2015-10-26 | 2015-10-26 | Gyroplane verts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205098469U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| CN107458575A (en) * | 2016-06-06 | 2017-12-12 | 比亚迪股份有限公司 | Unmanned plane |
| CN107985583A (en) * | 2017-11-17 | 2018-05-04 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN109131871A (en) * | 2018-09-26 | 2019-01-04 | 沈阳无距科技有限公司 | Unmanned plane and inclining rotary mechanism |
| CN109204806A (en) * | 2017-07-06 | 2019-01-15 | 深圳市道通智能航空技术有限公司 | Aircraft, driving mechanism of verting and its control method |
| WO2020125523A1 (en) * | 2018-12-18 | 2020-06-25 | 深圳市格上格创新科技有限公司 | Foldable multi-rotor unmanned aerial vehicle |
| CN114302847A (en) * | 2019-09-20 | 2022-04-08 | 株式会社爱隆未来 | Flying body |
-
2015
- 2015-10-26 CN CN201520833566.2U patent/CN205098469U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458575A (en) * | 2016-06-06 | 2017-12-12 | 比亚迪股份有限公司 | Unmanned plane |
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| CN109204806A (en) * | 2017-07-06 | 2019-01-15 | 深圳市道通智能航空技术有限公司 | Aircraft, driving mechanism of verting and its control method |
| CN107985583A (en) * | 2017-11-17 | 2018-05-04 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN109131871A (en) * | 2018-09-26 | 2019-01-04 | 沈阳无距科技有限公司 | Unmanned plane and inclining rotary mechanism |
| WO2020125523A1 (en) * | 2018-12-18 | 2020-06-25 | 深圳市格上格创新科技有限公司 | Foldable multi-rotor unmanned aerial vehicle |
| CN114302847A (en) * | 2019-09-20 | 2022-04-08 | 株式会社爱隆未来 | Flying body |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |