CN207078311U - A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil - Google Patents
A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil Download PDFInfo
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- CN207078311U CN207078311U CN201720185981.0U CN201720185981U CN207078311U CN 207078311 U CN207078311 U CN 207078311U CN 201720185981 U CN201720185981 U CN 201720185981U CN 207078311 U CN207078311 U CN 207078311U
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Abstract
The utility model discloses a kind of folding dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of combined type oil, it mainly includes fuselage, wing, vertical tail, folding rotary shaft, shaft bearing, spindle nut and undercarriage；The utility model mainly solves the problems, such as that conventional composite formula unmanned plane structure space-consuming is big, weight is big；The utility model uses tandem-winged total arrangement form, the aeroperformance before improving under winged pattern；Wing is foldable and wheel assembly is housed, and facilitates ground transport and saves space.
Description
Technical field
Technical field of aerospace is the utility model is related to, more particularly to a kind of folding dynamic four rotors at a high speed of combined type oil
Unmanned aerial vehicle body folding system.
Background technology
With the progress of science and technology of aviation, multi-rotor unmanned aerial vehicle is more and more applied to national economy field, but simultaneously its
Endurance, the deficiency of load-carrying ability also limit its application and development.Fixed-wing VUAV improves
Such case, not only can be with VTOL but also can be high the characteristics of fixed-wing VUAV combination fixed-wing and more rotors
Speed is flat to fly.Existing fixed-wing VUAV mainly includes tiltrotor, tailstock formula unmanned plane and combined type unmanned plane,
It is wherein most widely used for combined type VUAV.In the A (data of publication of application of Chinese patent CN 105539834：
2016.05.04 a kind of composite wing VUAV is described in), it uses fixed wing aircraft and quadrotor phase
With reference to layout, i.e., on the basis of fixed wing aircraft, fourth officer rotor is installed on wing, mainly by fourth officer during VTOL
Rotor provides lift, puts down to move providing lift mainly by wing relative wind when flying；In addition it is provided with variable-pitch propeller on its vertical fin
Oar, driftage control moment during increasing low-speed operations.Foregoing invention is for air angle, the fourth officer that is installed on wing
Rotor and its mounting bracket are irregular blunt form structure, and being substantially improved for the useless resistance of full machine can be caused in flat fly；From structure
For angle, the power transmission burden of wing is more arduous compared to common fixed-wing, and wing is worse off by torsion, it is necessary to be done to wing
Structure does extra reinforcement, greatly increases airframe structure weight, and load-carrying ability declines；From using for angle, fuselage is integrated
Installation, can not be folded, and space-consuming is larger, and ground transport is difficult.
Utility model content
In order to overcome the above-mentioned deficiencies of the prior art, it is dynamic at a high speed to provide a kind of folding combined type oil for the utility model
Four rotor wing unmanned aerial vehicle fuselage folding systems.
Technical scheme is used by the utility model：A kind of dynamic four rotor wing unmanned aerial vehicle machines at a high speed of folding combined type oil
Body folding system, it mainly includes fuselage, wing, vertical tail, folding rotary shaft, shaft bearing, spindle nut and undercarriage.Institute
It is streamlined column structure to state fuselage, and its function is support and connecting components, power sub-system and propeller drive subsystem
It is mounted on fuselage interior.The wing quantity is 4, and 2 wing positions for being placed in front side are slightly below 2 wings of rear side；Often
Individual wing is connected by 2 sets of rotating shaft mechanisms with fuselage, and wing is connected with shaft bearing outer shroud, shaft bearing inner ring and folding rotary shaft
It is connected, folding rotary shaft is connected with fuselage, and spindle nut is connected through a screw thread with folding rotary shaft, prevents folding rotary shaft from being taken off with fuselage
Open；Trailing edge is provided with the pneumatic rudder face of flaperon, to control aspect；Rotary-wing transmission subsystem is installed on inside wing,
Wing plays a supportive role to it.The vertical tail is connected with fuselage, plays that horizontal course is stable and manipulation.The undercarriage is
Wheeled front three-point form, is connected with fuselage.The more rotor subsystem rotors being installed on the wing of front side are installed down, after being installed on
More rotor subsystem rotors on the wing of side are installed upward, to prevent between more rotor subsystems being mutually concerned with during wing-folding
Relate to.
Advantage and effect：Compared with prior art, the beneficial effects of the utility model be solve conventional composite formula nobody
The problem of machine structure space-consuming is big, weight is big.The utility model uses tandem-winged total arrangement form, winged mould before improving
Aeroperformance under formula；Wing is foldable and wheel assembly is housed, and facilitates ground transport and saves space.
Brief description of the drawings
The dynamic four rotor wing unmanned aerial vehicle schematic appearances at a high speed of the folding combined type oil of Fig. 1；
The dynamic four rotor wing unmanned aerial vehicle fold mechanism profiles at a high speed of the folding combined type oil of Fig. 2；
Fig. 3 folding operation schematic diagrames；
Fig. 4 folds end-state schematic diagram.
Sign flag is as follows in figure：
1- fuselages；2- wings；3- vertical tails；4- folding rotary shafts；5- shaft bearings；6- spindle nuts；7- undercarriages.
Embodiment
Preferred embodiment of the present utility model is illustrated below in conjunction with the accompanying drawings, it should be understood that described herein preferred
Embodiment is merely to illustrate and explained the utility model, is not used to limit the utility model.
Referring to Fig. 1-Fig. 2, rolled over a kind of folding dynamic four rotor wing unmanned aerial vehicle fuselages at a high speed of combined type oil of the present embodiment
Folded system is related to be mainly consisted of：
The fuselage folding system, including fuselage 1, wing 2, vertical tail 3, folding rotary shaft 4, shaft bearing 5, rotating shaft spiral shell
Mother 6 and undercarriage 7.The fuselage 1 is streamlined column structure, and its function is support and connecting components, power sub-system with
Propeller drive subsystem is mounted on fuselage interior.The quantity of wing 2 is 4, and 2 positions of wing 2 for being placed in front side are lower slightly
In 2 wings 2 of rear side；Each wing 2 is connected by 2 sets of rotating shaft mechanisms with fuselage 1, and wing 2 is consolidated with the outer shroud of shaft bearing 5
Even, the inner ring of shaft bearing 5 is connected with folding rotary shaft 4, and folding rotary shaft 5 is connected with fuselage 1, and spindle nut 6 is logical with folding rotary shaft 4
Threaded connection is crossed, prevents folding rotary shaft 4 from being disengaged with fuselage 1；The trailing edge of wing 2 is provided with the pneumatic rudder face of flaperon, to control aircraft
Posture；Rotary-wing transmission subsystem is installed on inside wing 2, and wing 2 plays a supportive role to it.The vertical tail 3 is solid with fuselage 1
Even, serve horizontal course stabilize and manipulation.The undercarriage 7 is wheeled front three-point form, is connected with fuselage.It is installed on front side machine
More rotor subsystem rotors on the wing 2 are installed down, and the more rotor subsystem rotors being installed on rear side wing 2 are installed upward,
To prevent from interfering with each other between more rotor subsystems during wing-folding.
To save the space of ground transport, the utility model is foldable during ground transport, and concrete operation method is such as
Under：
When needing to fold, spindle nut 6 is pulled down, corresponding folding rotary shaft on each wing is removed.As shown in figure 3,
Each arrow represents each part direction of motion in folding process in figure, and front side wing 2 is folded back, rear side wing 2 is rolled over forward
It is folded, it is fixed on after pressing close to fuselage with rope or foam dam in transport vehicle, final folded state is as shown in Figure 4.
The beneficial effects of the utility model are that solve that conventional composite formula unmanned plane structure space-consuming is big, weight is big asks
Topic.The utility model uses tandem-winged total arrangement form, the aeroperformance before improving under winged pattern；Wing it is foldable and
Equipped with wheel assembly, facilitate ground transport and save space.
Claims (1)
- A kind of 1. dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil, it is characterised in that：It is mainly wrapped Include fuselage (1), wing (2), vertical tail (3), folding rotary shaft (4), shaft bearing (5), spindle nut (6) and undercarriage (7)；The fuselage (1) is streamlined column structure, and its function is support and connecting components, and power sub-system passes with propeller Subsystem is mounted on fuselage interior；Wing (2) quantity be 4, be placed in front side 2 wing (2) positions be slightly below after 2 wings (2) of side；Each wing (2) is connected by 2 sets of rotating shaft mechanisms with fuselage (1), and wing (2) and shaft bearing (5) are outside Ring is connected, and shaft bearing (5) inner ring is connected with folding rotary shaft (4), and folding rotary shaft (4) is connected with fuselage (1), spindle nut (6) It is connected through a screw thread with folding rotary shaft (4), prevents folding rotary shaft (4) from being disengaged with fuselage (1)；Wing (2) trailing edge is provided with flaperon Pneumatic rudder face, to control aspect；Rotary-wing transmission subsystem is installed on wing (2) inside, and wing (2) plays support to it and made With；The vertical tail (3) and fuselage (1) are connected, and play horizontal course and stabilize and manipulation；Before the undercarriage (7) is wheeled Three-point shape formula, is connected with fuselage；The more rotor subsystem rotors being installed on front side wing (2) are installed down, are installed on rear side More rotor subsystem rotors on wing (2) are installed upward, to prevent during wing-folding between more rotor subsystems mutually Interference.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720185981.0U CN207078311U (en) | 2017-02-28 | 2017-02-28 | A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720185981.0U CN207078311U (en) | 2017-02-28 | 2017-02-28 | A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207078311U true CN207078311U (en) | 2018-03-09 |
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| CN201720185981.0U Active CN207078311U (en) | 2017-02-28 | 2017-02-28 | A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592034A (en) * | 2019-01-31 | 2019-04-09 | 上海交通大学 | A kind of diving aircraft and its wing accommodation method |
| CN111976947A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Vertical take-off and landing variable wing cruising heavy-load unmanned aerial vehicle |
| WO2020256571A1 (en) * | 2019-06-20 | 2020-12-24 | Eledia El Arby | Foldable tandem wing aircraft |
| CN112278259A (en) * | 2020-11-11 | 2021-01-29 | 中国科学院沈阳自动化研究所 | Four rotor unmanned aerial vehicle of supplementary flight of foldable fin |
| CN112572765A (en) * | 2020-12-25 | 2021-03-30 | 赵昆 | Mini-type ultramicro folding fixed-wing unmanned aerial vehicle |
| CN112874758A (en) * | 2021-02-08 | 2021-06-01 | 曾昭达 | Membrane wing folding system and membrane wing aircraft thereof |
| US20210214067A1 (en) * | 2020-01-13 | 2021-07-15 | Skydio, Inc. | Autonomous Unmanned Aerial Vehicle With Folding Collapsible Arms |
| CN113895604A (en) * | 2021-10-08 | 2022-01-07 | 重庆交通大学 | Collapsible allosteric unmanned aerial vehicle |
| RU2771195C1 (en) * | 2021-12-17 | 2022-04-28 | Кирилл Николаевич Яковченко | Rotary-wing unmanned aerial vehicle of tandem scheme |
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2017
- 2017-02-28 CN CN201720185981.0U patent/CN207078311U/en active Active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592034B (en) * | 2019-01-31 | 2023-12-19 | 上海交通大学 | Submersible aircraft and wing storage method thereof |
| CN109592034A (en) * | 2019-01-31 | 2019-04-09 | 上海交通大学 | A kind of diving aircraft and its wing accommodation method |
| WO2020256571A1 (en) * | 2019-06-20 | 2020-12-24 | Eledia El Arby | Foldable tandem wing aircraft |
| US20210214067A1 (en) * | 2020-01-13 | 2021-07-15 | Skydio, Inc. | Autonomous Unmanned Aerial Vehicle With Folding Collapsible Arms |
| CN111976947B (en) * | 2020-07-06 | 2022-09-20 | 西安飞机工业（集团）有限责任公司 | Vertical take-off and landing variable wing cruising heavy-load unmanned aerial vehicle |
| CN111976947A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Vertical take-off and landing variable wing cruising heavy-load unmanned aerial vehicle |
| CN112278259A (en) * | 2020-11-11 | 2021-01-29 | 中国科学院沈阳自动化研究所 | Four rotor unmanned aerial vehicle of supplementary flight of foldable fin |
| CN112572765A (en) * | 2020-12-25 | 2021-03-30 | 赵昆 | Mini-type ultramicro folding fixed-wing unmanned aerial vehicle |
| CN112874758A (en) * | 2021-02-08 | 2021-06-01 | 曾昭达 | Membrane wing folding system and membrane wing aircraft thereof |
| CN112874758B (en) * | 2021-02-08 | 2023-10-13 | 曾昭达 | Film wing aircraft |
| CN113895604A (en) * | 2021-10-08 | 2022-01-07 | 重庆交通大学 | Collapsible allosteric unmanned aerial vehicle |
| RU2771195C1 (en) * | 2021-12-17 | 2022-04-28 | Кирилл Николаевич Яковченко | Rotary-wing unmanned aerial vehicle of tandem scheme |
| WO2023113652A1 (en) * | 2021-12-17 | 2023-06-22 | Кирилл Николаевич ЯКОВЧЕНКО | Rotary-wing unmanned aerial vehicle with tandem wing configuration |
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Effective date of registration: 20200617 Address after: Room 108, science and technology entrepreneurship research incubation complex building (Building 5), Baixia high tech Industrial Park, No. 5 Yongzhi Road, Qinhuai District, Nanjing, Jiangsu Province, 210001 Patentee after: Vito (Nanjing) Intelligent Technology Co., Ltd Address before: 300300 No.3B, Tengfei Road, Junliangcheng Industrial Park, Dongli District, Tianjin Patentee before: AVIC WEITUO (TIANJIN) TECHNOLOGY Co.,Ltd. |
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