CN104691749A - Transversely staggered four-rotor aircraft - Google Patents
Transversely staggered four-rotor aircraft Download PDFInfo
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- CN104691749A CN104691749A CN201510097268.6A CN201510097268A CN104691749A CN 104691749 A CN104691749 A CN 104691749A CN 201510097268 A CN201510097268 A CN 201510097268A CN 104691749 A CN104691749 A CN 104691749A
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- hold
- fuselage
- down arm
- lockout mechanism
- quadrotor
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Abstract
The invention discloses a transversely staggered four-rotor aircraft mainly comprising a fuselage, supporting arms, a motor, rotors and a landing gear. Each two supporting arms among four supporting arms are distributed on both sides of the fuselage; the two supporting arms on the same side are installed up and down in a staggered manner; one end of each supporting arm is connected with the fuselage through a hinge mechanism, and a supporting seat is installed on the other end of the supporting arm; a motor is fixedly installed above the supporting seat; the rotors are installed on the rotating shaft of the motor; the landing gear is further installed below the supporting seat. When the aircraft works, the supporting arms and the landing gear are unfolded, and the positions of the supporting arms are kept by locking mechanisms, so that normal flight can be implemented; in a non-working state, the landing gear is folded, the supporting arms are folded transversely in a staggered manner, and the positions of the supporting arms are kept by the locking mechanisms, so that the volume is reduced for convenient carrying and transporting.
Description
Technical field
the present invention relates to aircraft field, particularly the horizontal interfolded quadrotor of one.
Background technology
Quadrotor compared to other aircraft flight more steadily, can fly in hovering, side to switch rapidly between the state of flight such as inverted flight, takeoff and landing performance and maneuvering performance good, be suitable for very much performing the tasks such as fixed point is scouted, taken photo by plane, aerial mapping, there is military affairs and civil use widely.
Flight support arm and the alighting gear of tradition quadrotor adopt fixing version usually, and this just makes aircraft have larger volume, can bring inconvenience to carrying with transportation.Although some quadrotor also adopts accordion structure, the such as MD4-1000 type aircraft of Germany, its accordion structure adopted is that half hold-down arm folds downwards, and the volume after it is folding is still very large, makes troubles to transport and use.Also some folding schemes improved are had in prior art, the laterally folded scheme of half hold-down arm such as, proposed in patent CN103625641A, its volume after folding reduces to some extent than MD4-1000, but being surrounded on fuselage surrounding after its half hold-down arm is folding, fails to be fully used in the space on the one hand after folding around fuselage, below hold-down arm; On the other hand the equipment such as its capacity weight such as The Cloud Terrace can only be installed on below fuselage in actual applications, can bring defects such as having tunnel vision.Propose a kind of folding quadrotor in patent CN203528812U, its hold-down arm is doubling in opposite directions to the inside, and this just requires fuselage to have longer length to hold two hold-down arms placements, and therefore this quadrotor inherently has larger volume.Propose a kind of folding quadrotor in patent CN302779997S, its hold-down arm is doubling in opposite directions laterally, although this folding mode reduces the transverse width of aircraft, but adds the longitudinal length of aircraft after folding.Therefore, although several folding schemes related in above-mentioned patent reduce the volume of quadrotor all to a certain extent, but all have employed flat-folded scheme, its folding joint is all confined in same plane, do not make full use of the available space around fuselage in maximum.
Summary of the invention
The object of the invention is to overcome the problems referred to above, the horizontal interfolded quadrotor that a kind of structure is simple, volume is little, be convenient for carrying and transport is provided.
For achieving the above object, the method that the present invention adopts is: a kind of horizontal interfolded quadrotor, comprise fuselage, hold-down arm, motor, rotor, alighting gear, it is characterized in that: described hold-down arm is provided with four, article four, hold-down arm is distributed in fuselage both sides between two, two hold-down arms of the same side are staggered installation of up and down, one end of every bar hold-down arm is connected with fuselage, the other end is provided with supporting seat, supporting seat is installed with motor, rotor is fixedly installed on electric machine rotational axis, alighting gear is arranged on the supporting seat on hold-down arm, every bar hold-down arm in four described hold-down arms independently can carry out unitary rotation around the junction of hold-down arm and fuselage, complete expansion or folding movement.
Preferred as one of the present invention, be connected by hinge arrangement with between fuselage at described hold-down arm.
Preferred as one of the present invention, the nearly fuselage end of described hold-down arm is provided with lockout mechanism parts, is fixedly connected with after opening in entirety or folding with the lockout mechanism parts on fuselage.
Preferred as one of the present invention, described lockout mechanism parts comprise the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage; Lockout mechanism parts on described hold-down arm are hold-down arms, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member; Lockout mechanism parts on described fuselage be fuselage is installed for carry out coordinating, be fixedly connected with the lockout mechanism parts on hold-down arm C shape, one in U-shaped draw-in groove or electromagnetism class locking member.
Preferred as one of the present invention, two hold-down arms of described the same side to stagger certain distance in the installation of vertical direction.
Preferred as one of the present invention, described alighting gear be plug-in type or collapsible in one, its one end is fixedly connected with the supporting seat of hold-down arm end, and the other end is for ground supports.
Beneficial effect:
Technical solution of the present invention compares traditional fixed sturcture rotor craft, and volume after folding reduces, and is convenient for carrying and transports.In some flat-folded schemes compared to existing technology, folding joint is all confined to the situation in same plane, technical solution of the present invention adopts the mode of the horizontal interfolded in space, make full use of fuselage side-lower space, improve space availability ratio, volume after folding reduces further, makes to carry and transport convenient.The plug-in type adopted in technical solution of the present invention or collapsible alighting gear are separated with fuselage or also fold after hold-down arm is folding, also make folding rear aircraft volume be reduced further.In addition, the folding mode simple possible that technical solution of the present invention adopts, easy to operate, its hold-down arm can fast folding with fixing, alighting gear can carry out loading and unloading or folding fast, decreases the setup time before equipment use.
Accompanying drawing explanation
Fig. 1 is the front view after horizontal interfolded quadrotor launches;
Fig. 2 is the lateral plan after horizontal interfolded quadrotor launches;
Fig. 3 is that horizontal interfolded quadrotor launches rear isometric view;
Fig. 4 is horizontal interfolded quadrotor folded configuration front view;
Fig. 5 is horizontal interfolded quadrotor folded configuration lateral plan;
Fig. 6 does not add rotor shaft after horizontal interfolded quadrotor folds to survey view.
In figure: 1, fuselage, 2, hold-down arm, 3, motor, 4, rotor, 5, alighting gear, 6, linkage, 7, supporting seat, 8, lockout mechanism, 81, hold-down arm folds C shape groove Lock Part on rear body, 82, hold-down arm launches on rear body C shape groove Lock Part.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, illustrate the present invention further, the present embodiment is implemented under premised on technical solution of the present invention, should understand these embodiments and only be not used in for illustration of the present invention and limit the scope of the invention.
Embodiment 1:
As shown in accompanying drawing 1 to accompanying drawing 6, the invention discloses a kind of horizontal interfolded quadrotor, comprise fuselage 1, hold-down arm 2, motor 3, rotor 4, alighting gear 5, linkage 6, supporting seat 7, lockout mechanism 8.
As shown in Figures 1 and 2, for the front view after horizontal interfolded quadrotor expansion of the present invention and lateral plan, in figure, article four, hold-down arm 2 is distributed in fuselage 1 both sides between two, two hold-down arms about 2 of the same side are staggered installation of, two hold-down arms 2 of the same side to stagger certain distance in the installation of vertical direction, to ensure that all parts is not interfered mutually.One end of every bar hold-down arm 2 is connected with fuselage, and the other end is provided with supporting seat 7, and in the present embodiment, hold-down arm 2 is connected with fuselage 1 by linkage.Article four, the every bar hold-down arm 2 in hold-down arm 2 independently can carry out unitary rotation around end hinge mechanism 6, completes expansion or folding movement.
Supporting seat 7 is installed with motor 3, and rotor 4 is fixedly installed on the S. A. of motor 3.Alighting gear 5 is arranged on the supporting seat 7 on hold-down arm 2, and alighting gear 5 is alighting gear that is collapsible or plug-in, and alighting gear 5 is plug-in alighting gear in the present embodiment.Plug-in type alighting gear 5 one end can be inserted in the pore of supporting seat 7 side of hold-down arm 2 end, and its connection mode is interference fit; The other end is used for ground supports.
Be that horizontal interfolded quadrotor launches rear isometric view as shown in Figure 3, one end that fuselage 1 installs linkage 6 is provided with lockout mechanism parts, and lockout mechanism comprises the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage.Wherein, the lockout mechanism parts on hold-down arm are hold-down arms itself, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member.In the present embodiment, adopt the locking scheme of C shape ring, after hold-down arm 2 entirety is launched, the C shape groove Lock Part 82 that this hold-down arm 2 and hold-down arm launch on rear body is fixedly connected with, and ensures that hold-down arm 2 and fuselage 1 are fixedly linked.
After hold-down arm 2 foldable integral, the C shape groove Lock Part 81 that this hold-down arm 2 and hold-down arm fold on rear body is fixedly connected with, and ensures that hold-down arm 2 and fuselage 1 are fixedly linked.
Technical solution of the present invention compares traditional fixed sturcture rotor craft, and volume after folding reduces, and is convenient for carrying and transports.In some flat-folded schemes compared to existing technology, folding joint is all confined to the situation in same plane, technical solution of the present invention adopts the mode of the horizontal interfolded in space, make full use of fuselage side-lower space, improve space availability ratio, volume after folding reduces further, makes to carry and transport convenient.The plug-in type adopted in technical solution of the present invention or collapsible alighting gear are separated with fuselage or also fold after hold-down arm is folding, also make folding rear aircraft volume be reduced further.In addition, the folding mode simple possible that technical solution of the present invention adopts, easy to operate, its hold-down arm can fast folding with fixing, alighting gear can carry out loading and unloading or folding fast, decreases the setup time before equipment use.
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also comprises the technical scheme be made up of above technical characteristic combination in any.The above is the specific embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (6)
1. a horizontal interfolded quadrotor, comprise fuselage, hold-down arm, motor, rotor, alighting gear, it is characterized in that: described hold-down arm is provided with four, article four, hold-down arm is distributed in fuselage both sides between two, two hold-down arms of the same side are staggered installation of up and down, one end of every bar hold-down arm is connected with fuselage, the other end is provided with supporting seat, supporting seat is installed with motor, rotor is fixedly installed on electric machine rotational axis, alighting gear is arranged on the supporting seat on hold-down arm, every bar hold-down arm in four described hold-down arms independently can carry out unitary rotation around the junction of hold-down arm and fuselage, complete expansion or folding movement.
2. the horizontal interfolded quadrotor of one according to claim 1, be is characterized in that: be connected by hinge arrangement with between fuselage at described hold-down arm.
3. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: the nearly fuselage end of described hold-down arm is provided with lockout mechanism parts, is fixedly connected with after opening in entirety or folding with the lockout mechanism parts on fuselage.
4. the horizontal interfolded quadrotor of one according to claim 3, is characterized in that: described lockout mechanism parts comprise the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage; Lockout mechanism parts on described hold-down arm are hold-down arms itself, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member; Lockout mechanism parts on described fuselage be fuselage is installed, C shape for carrying out coordinating, be fixedly connected with the lockout mechanism parts on hold-down arm, one in U-shaped draw-in groove or electromagnetism class locking member.
5. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: two hold-down arms of described the same side to stagger certain distance in the installation of vertical direction.
6. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: described alighting gear be plug-in type or collapsible in one, its one end is fixedly connected with the supporting seat of hold-down arm end, the other end be used for ground supports.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510097268.6A CN104691749A (en) | 2015-03-05 | 2015-03-05 | Transversely staggered four-rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510097268.6A CN104691749A (en) | 2015-03-05 | 2015-03-05 | Transversely staggered four-rotor aircraft |
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| CN104691749A true CN104691749A (en) | 2015-06-10 |
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| CN201510097268.6A Pending CN104691749A (en) | 2015-03-05 | 2015-03-05 | Transversely staggered four-rotor aircraft |
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| CN105173058A (en) * | 2015-09-25 | 2015-12-23 | 联想(北京)有限公司 | Electronic equipment |
| CN105314088A (en) * | 2015-11-06 | 2016-02-10 | 珠海华迈航空科技有限公司 | Four-rotor craft |
| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
| CN106043664A (en) * | 2016-06-22 | 2016-10-26 | 宁波蓝飞鹂航空科技有限公司 | Novel folding deformable aircraft |
| CN106094857A (en) * | 2016-08-22 | 2016-11-09 | 京东方科技集团股份有限公司 | The flight control method of unmanned plane, wearable device and unmanned plane, device |
| WO2017020225A1 (en) * | 2015-08-03 | 2017-02-09 | 北京艾肯拓科技有限公司 | Unmanned helicopter |
| CN106394884A (en) * | 2015-07-31 | 2017-02-15 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| WO2017113090A1 (en) * | 2015-12-29 | 2017-07-06 | 深圳市大疆创新科技有限公司 | Rotor mechanism, rotating device, unmanned aerial vehicle, and control system and operation method therefor |
| WO2017120654A1 (en) * | 2016-01-12 | 2017-07-20 | Dragan, Zenon | Multi-rotor uav with compact folding rotor arms |
| EP3210660A1 (en) * | 2016-02-25 | 2017-08-30 | Parrot Drones | Drone with foldable link arms |
| WO2017143643A1 (en) * | 2016-02-22 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Frame of unmanned aerial vehicle, unmanned aerial vehicle, and use method therefor |
| CN107585297A (en) * | 2016-07-06 | 2018-01-16 | 襄阳联航动力技术有限公司 | A kind of more rotor parallel type hybrid dynamic unmanned planes |
| CN107985581A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of dynamic rotor structure of new type foldable oil |
| EP3202662A4 (en) * | 2015-07-31 | 2018-05-16 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle |
| CN108545170A (en) * | 2018-04-03 | 2018-09-18 | 新疆大学 | Folding unmanned plane rack |
| CN109110118A (en) * | 2017-06-23 | 2019-01-01 | 昊翔电能运动科技(昆山)有限公司 | Unmanned plane and its frame assembly |
| FR3070607A1 (en) * | 2017-09-07 | 2019-03-08 | Parrot Drones | ROTARY SAILING DRONE COMPRISING A FOLDING DRONE STRUCTURE |
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| CN106394884A (en) * | 2015-07-31 | 2017-02-15 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| US10526087B2 (en) | 2015-07-31 | 2020-01-07 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
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| CN105173058A (en) * | 2015-09-25 | 2015-12-23 | 联想(北京)有限公司 | Electronic equipment |
| CN105173058B (en) * | 2015-09-25 | 2017-05-24 | 联想(北京)有限公司 | Electronic equipment |
| CN105314088A (en) * | 2015-11-06 | 2016-02-10 | 珠海华迈航空科技有限公司 | Four-rotor craft |
| WO2017113090A1 (en) * | 2015-12-29 | 2017-07-06 | 深圳市大疆创新科技有限公司 | Rotor mechanism, rotating device, unmanned aerial vehicle, and control system and operation method therefor |
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| WO2017143643A1 (en) * | 2016-02-22 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Frame of unmanned aerial vehicle, unmanned aerial vehicle, and use method therefor |
| US11427319B2 (en) | 2016-02-22 | 2022-08-30 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
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| CN114212242A (en) * | 2016-02-22 | 2022-03-22 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
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| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
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| CN106094857A (en) * | 2016-08-22 | 2016-11-09 | 京东方科技集团股份有限公司 | The flight control method of unmanned plane, wearable device and unmanned plane, device |
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