CN204979233U - Four rotor crafts of feather and power transmission system thereof - Google Patents
Four rotor crafts of feather and power transmission system thereof Download PDFInfo
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- CN204979233U CN204979233U CN201520728705.5U CN201520728705U CN204979233U CN 204979233 U CN204979233 U CN 204979233U CN 201520728705 U CN201520728705 U CN 201520728705U CN 204979233 U CN204979233 U CN 204979233U
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- quadrotor
- synchronous pulley
- horn
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Abstract
Four rotor crafts of feather and power transmission system thereof, wherein the engine passes through four intermeshing's of power input shaft gear drive output gear, the coaxial synchronous pulley that is fixed with of every output gear, synchronous pulley with output gear is synchronous to rotate, every synchronous pulley is through the synchronous pulley of a timing belt drive rotor system, with power transmission to each rotor assembly. Through single engine drive multiaxis rotor, use the feather mode attitude control that flies, have long, the effective advantage that task load is big, the control response is fast of time of endurance. Mix transmission system, combined gear and hold -in range, under the prerequisite of guaranteeing the reliability, improved aircraft load performance. Use synchronous belt drive to make the horn can design to folding horn, reduce the aircraft volume, conveniently carry, transport.
Description
Technical field
The utility model belongs to technical field of aerospace, particularly relates to a kind of feather quadrotor and power drive system thereof.
Background technology
Quadrotor relies on that its physical construction is simple, flight stability, processing ease and without features such as landing site's restrictions, is developed rapidly in recent years.The quadrotor of current main flow have employed the power mode of every axle individual drive mostly, drives rotor wing rotation to provide lift respectively by multiple motor, and realizes flight control by changing gyroplane rotate speed.This structure is applicable to small-sized quadrotor, is subject to the restriction of rotor mechanism rotor inertia, and the structure of every axle individual drive is unfavorable for the quadrotor realizing more long wheelbase, constrains the quadrotor application of large mission payload, long continuation of the journey demand.Feather quadrotor adopts the mode alternative change gyroplane rotate speed mode changing rotor pitch to realize flight and controls, not only be not subject to the restriction of rotor mechanism rotor inertia size, compared with controlling with rotating speed, variable pitch control also has control response speed faster.Utilize feather can realize the quadrotor of more long wheelbase, promoting flying vehicles control performance, by adopting single engine oil to move driving engine as Power output, significantly can promote effective mission payload and the flying power of quadrotor.
Summary of the invention
The purpose of this utility model overcomes the technical deficiency of existing quadrotor, propose a kind of quadrotor adopting the variablepiston of single engine mixed drive mode, there is the advantages such as flight stability, control response is fast, effectively mission payload is large, cruise duration is long.
The technical solution of the utility model is: a kind of feather quadrotor power drive system, wherein engine is by power input shaft gear drive four intermeshing output gears, each output gear is coaxially fixed with a synchronous pulley, described synchronous pulley and described output gear synchronous axial system, each described synchronous pulley drives the synchronous pulley of rotor system by a Timing Belt, transmits power to each rotor assembly.
The utility model provides the technical scheme of quadrotor simultaneously, comprising: frame, variablepiston rotor system, power drive system as above and flight control system.
Technique effect of the present utility model is: drive multiaxis rotor by single engine, uses feather mode to carry out flight attitude control, has the advantage that cruise duration is long, effectively mission payload is large, control response is fast.Hybrid powertrain system, combines gear and Timing Belt, under the prerequisite ensureing reliability, improves aircraft load performance.Use toothed belt transmission to make horn can be designed as folding horn, reduce aircraft volume, be convenient for carrying, transport.
Accompanying drawing explanation
Fig. 1 is that the oil of a kind of mixed drive mode of the utility model moves feather quadrotor embodiment 1 overall structure schematic diagram;
Fig. 2 is the structural representation that the oil of a kind of mixed drive mode of the utility model moves feather quadrotor embodiment 1 drive disk assembly;
Fig. 3 is the variablepiston rotor system structural representation that the oil of a kind of mixed drive mode of the utility model moves feather quadrotor embodiment 1;
Fig. 4 is that the horn that the oil of a kind of mixed drive mode of the utility model moves feather quadrotor embodiment 2 folds locking device block diagram;
Fig. 5 is that the horn that the oil of a kind of mixed drive mode of the utility model moves feather quadrotor embodiment 2 folds locking device lateral plan.
Detailed description of the invention
The detailed description of the invention of the utility model embodiment 1 is described below in conjunction with accompanying drawing 1-3.
The oil being illustrated in figure 1 a kind of mixed drive mode of the utility model moves feather quadrotor overall construction drawing, forms primarily of frame, variablepiston rotor system, power drive system and flight control system.
As shown in Figure 2,3, power drive system comprises: engine 1, power input shaft gear 2, four intermeshing output gears 3 and the synchronous pulley 5 be fixed on it on same transmission shaft 4, synchronous pulley 5 engages the synchronous pulley 7 transmitting power to variablepiston rotor system with Timing Belt 6, this synchronous pulley 7 drives rotor assembly to rotate.
Always have four groups of rotors in native system, wherein relative rotor turns to identical, and adjacent rotor turns on the contrary, and its different rotation direction is realized by the engagement between output gear 3.Its objective is that eliminating himself to interact rotates the reactive torque power produced, avoiding aircraft to spin cannot directed fly.
As shown in Figure 3, wherein, variablepiston rotor mechanical system comprises: synchronous pulley 7, rotor rotational input stepped shaft 8, rotor holder 9, pushing disk 10 and connecting rod 11.Rocking arm is driven to drive pushing disk to change the pitch of rotor by Servo-controller.Wherein, synchronous pulley 7 rotarily drives rotor assembly, and while synchronous pulley 7 drives rotor assembly to rotate, steering wheel carries out the upper and lower displacement in vertical direction by driving rocking arm drive pushing disk 10.Rotor holder 9 is connected to stepped shaft 8 top, and rotor holder 9 stretches out two lugs 12, and overhanging two hangers of the pushing disk 10 being arranged in its underpart, lug 12 is undertaken hinged with hanger by connecting rod (11).Steering wheel by controlling the upper and lower displacement of pushing disk, thus realizes, to the control of rotor apart from size, finally reaching the object controlled rotor lift size and torque indirectly.
Engine 1 is combustion engine, and servo driving connecting rod controls the rotating speed that throttle size changes rotor.
Illustrate that the oil of the utility model mixed drive mode moves the embodiment 2 of feather quadrotor below in conjunction with accompanying drawing 4-5.Embodiment 2 and the difference of embodiment 1 are only that have employed folding and self-locking apparatus between mainframe with horn is connected, and other structure is all identical.
The folding and self-locking apparatus of the present embodiment 2 is arranged at the junction of aircraft center main frame and overhanging horn, the second assembly comprising the first assembly and be attached thereto by bearing pin; Described first assembly comprises the side plate 21 be parallel to each other for a pair and the elasticity locking device be arranged between described side plate 21; Described elasticity is locked be installed on comprise be arranged at strut bar 22 between described side plate 21, sliding bar 25 that one end crosses described strut bar 22 slidably, the locked pin 24 be fixedly connected with sliding bar 25 other end, between strut bar 22 and locked pin 24 and the spring 23 be set on sliding bar 25; Side plate 21 has chute 26, for setting up locked pin 24.Described second assembly comprises rotatable positioning member 27 and the support jointing 28 be fixedly connected with it; The angle that described rotatable positioning member 27 has between two grooves, 29, two grooves 29 is 90 °, realizes locked fixing for coordinating with described elasticity locking device.Described locked pin 24 can slide in the chute 26 of described pair of side plates 21, by external force, locked pin 24 is compressed with spring 23, now the second assembly is in loosening state, can selection level or vertical groove, decontroling locked pin 24 with spring 23 combines with groove 29, be in self-locking state, locked pin 24 is stuck with groove 29, and rotor support and mainframe just can be fixed relative to one another.
In the present embodiment, the overhanging horn of rotor is tubular structure, and corresponding horn jointing 8 is pipe clamp.
In order to expendable weight, described side plate 21 adopts engraved structure to design.
When aircraft is in preparation flight or state of flight, the overhanging horn of rotor is in level, when aircraft terminates flight, overhanging for rotor horn can be regained and be in vertically.
The above embodiment is only preferred implementation of the present utility model; not scope of the present utility model is limited; under the prerequisite not departing from the utility model design spirit; the various distortion that those of ordinary skill in the art make the technical solution of the utility model and improvement, all should fall in protection domain that claims of the present utility model determine.
Claims (10)
1. a feather quadrotor power drive system, it is characterized in that, engine (1) drives four intermeshing output gears (3) by power input shaft gear (2), each output gear (3) is coaxially fixed with a synchronous pulley (5), described synchronous pulley (5) and described output gear (3) synchronous axial system, each described synchronous pulley (5) drives the synchronous pulley (7) of rotor system by a Timing Belt (6), transmits power to each rotor assembly.
2. a feather quadrotor, comprises frame, variablepiston rotor system, power drive system according to claim 1 and flight control system.
3. feather quadrotor according to claim 2, is characterized in that, described frame comprises by outward extending four horns of center main frame, and horn length is identical, and every bar horn end installs a set of variablepiston rotor system; Described four intermeshing output gears (3) are arranged on central host rack position.
4. feather quadrotor according to claim 3, is characterized in that, described variablepiston rotor system comprises Servo-controller, pitch-changing mechanism and rotor.
5. feather quadrotor according to claim 4, it is characterized in that, described pitch-changing mechanism comprises the pushing disk (10) be enclosed within rotor rotational input stepped shaft (8), be connected to the rotor holder (9) of rotor rotational input stepped shaft (8) upper end, be fixed on the rotor on rotor holder (9); Described pushing disk (10) is arranged on rotor holder (9) bottom and overhanging two symmetrical hangers, and described each rotor holder (9) is provided with overhanging lug (12), hinged by connecting rod (11) between described lug (12) and corresponding hanger; Described pushing disk (10) is driven the movement carrying out upper-lower position by Servo-controller, thus drives rotor holder (9) to rotate to control pitch size.
6. feather quadrotor according to claim 5, is characterized in that, engine (1) is combustion engine, uses servos control throttle size to change the rotating speed of rotor.
7. the feather quadrotor according to any one of claim 3 to 6, is characterized in that, is provided with folding and self-locking apparatus between described mainframe and horn.
8. feather quadrotor according to claim 7, is characterized in that, the second assembly that described folding and self-locking apparatus is comprised the first assembly and is attached thereto by bearing pin; Described first assembly comprises the side plate (21) be parallel to each other for a pair and the elasticity locking device be arranged between described side plate (21); Described second assembly comprises rotatable positioning member (27) and the horn jointing (28) be fixedly connected with it; Described rotatable positioning member (27) has two grooves (29) that angle is each other 90 °, realizes locked fixing for coordinating with described elasticity locking device.
9. feather quadrotor according to claim 8, it is characterized in that, described elasticity is locked be installed on comprise be arranged at strut bar (22) between described side plate (21), sliding bar (25) that one end crosses described strut bar (22) slidably, the locked pin (24) be fixedly connected with sliding bar (25) other end, between strut bar (22) and locked pin (24) and the spring (23) be set on sliding bar (25); Described pair of side plates (21) has chute (26), for setting up locked pin (24); Described locked pin (24) can be slided in described chute (26), and coordinates with the groove (29) of described rotatable positioning member (27) under locking state.
10. feather quadrotor according to claim 9, is characterized in that, described horn jointing (28) is pipe clamp, and described side plate (21) has engraved structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520728705.5U CN204979233U (en) | 2015-09-21 | 2015-09-21 | Four rotor crafts of feather and power transmission system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520728705.5U CN204979233U (en) | 2015-09-21 | 2015-09-21 | Four rotor crafts of feather and power transmission system thereof |
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| Publication Number | Publication Date |
|---|---|
| CN204979233U true CN204979233U (en) | 2016-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520728705.5U Active CN204979233U (en) | 2015-09-21 | 2015-09-21 | Four rotor crafts of feather and power transmission system thereof |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986009A (en) * | 2017-03-08 | 2017-07-28 | 贾杰 | Redundance dynamical system super large loads many rotor flying platforms |
| WO2017132808A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle irregular-shaped arm folding device |
| CN107323193A (en) * | 2017-08-04 | 2017-11-07 | 代国栋 | One kind can fly empty land convertible car |
| CN108248819A (en) * | 2016-12-28 | 2018-07-06 | 昊翔电能运动科技(昆山)有限公司 | A kind of coordinated type folds horn unmanned plane |
| CN109533305A (en) * | 2017-09-22 | 2019-03-29 | 波音公司 | Foldable rotor assemblies for fixed-wing vertically taking off and landing flyer |
| CN110481767A (en) * | 2019-08-28 | 2019-11-22 | 三峡大学 | A kind of foldable varying pitch quadrotor and application method based on oil electric mixed dynamic |
| CN112520026A (en) * | 2020-12-23 | 2021-03-19 | 中国民用航空飞行学院 | Novel variant aircraft |
-
2015
- 2015-09-21 CN CN201520728705.5U patent/CN204979233U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017132808A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle irregular-shaped arm folding device |
| CN108248819A (en) * | 2016-12-28 | 2018-07-06 | 昊翔电能运动科技(昆山)有限公司 | A kind of coordinated type folds horn unmanned plane |
| CN106986009A (en) * | 2017-03-08 | 2017-07-28 | 贾杰 | Redundance dynamical system super large loads many rotor flying platforms |
| CN107323193A (en) * | 2017-08-04 | 2017-11-07 | 代国栋 | One kind can fly empty land convertible car |
| CN109533305A (en) * | 2017-09-22 | 2019-03-29 | 波音公司 | Foldable rotor assemblies for fixed-wing vertically taking off and landing flyer |
| CN110481767A (en) * | 2019-08-28 | 2019-11-22 | 三峡大学 | A kind of foldable varying pitch quadrotor and application method based on oil electric mixed dynamic |
| CN112520026A (en) * | 2020-12-23 | 2021-03-19 | 中国民用航空飞行学院 | Novel variant aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180105 Address after: 100080 Beijing Haidian District North Fourth Ring Road West, No. 9 2106-030 Patentee after: The fast online Science and Technology Ltd. in Beijing three Address before: 100191 Haidian Haidian District street, No. 1, building 10,, 3 1001-52 Patentee before: BEIJING HAOHENG JOURNEY AVIATION TECHNOLOGY CO., LTD. |
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| TR01 | Transfer of patent right |