CN204688409U - The unmanned vehicle that a kind of many rotors and fixed-wing combine - Google Patents
The unmanned vehicle that a kind of many rotors and fixed-wing combine Download PDFInfo
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- CN204688409U CN204688409U CN201520262942.7U CN201520262942U CN204688409U CN 204688409 U CN204688409 U CN 204688409U CN 201520262942 U CN201520262942 U CN 201520262942U CN 204688409 U CN204688409 U CN 204688409U
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Abstract
The unmanned vehicle that many rotors and fixed-wing combine, comprises fuselage, fixed-wing, motor and screw propeller.Described fixed-wing is symmetricly set in the both sides of described fuselage.Described motor is fixedly mounted on the left and right sides of described fixed-wing respectively.Described motor comprises rotating shaft, and described screw propeller is fixedly mounted in described rotating shaft respectively.The direction of described rotating shaft is: with the perpendicular direction of described fuselage end face for benchmark, to direction, the windward side angle of inclination a of described fixed-wing, a is greater than 0 degree, is less than 30 degree.The utility model provide a kind of flying speed high, long-endurance, can the unmanned vehicle of vertical takeoff and landing or inclination landing.
Description
Technical field
The utility model relates to a kind of unmanned vehicle, particularly relates to the unmanned vehicle of a kind of many rotors and fixed-wing combination.
Background technology
Fixed wing aircraft, refers to that employing can not fold or change the aircraft of the wing of angle awing.It is produced the thrust or pulling force of advancing by engine installation, produce lift by the fixed wing of fuselage.Its flying speed is fast, voyage and the cruise time long, but landing distance, require special quality runway, landing site's restriction is greatly.
Heligyro, refers to by engine drive rotor wing rotation to provide the helicopter of lift.It changes lift by changing propeller speed, and then changes attitude and the working direction of four-rotor helicopter.It can in narrow and small place vertical takeoff and landing, but overcomes aircraft weight due to needs power, and power consumption is large, and onward impulse is less, and flying speed, flying distance and cruise duration are all not so good as fixed wing aircraft.
Refer to Fig. 1, it is many rotor wing unmanned aerial vehicles of the prior art, and it comprises frame 01, transverse link 02, motor 03 and screw propeller 04.Motor 03 is connected with frame 01 by transverse link 02, and drives screw propeller 04 to rotate, the plane parallel at the plane of revolution of screw propeller 04 and frame 01, transverse link 02 place.The flying speed of this many rotor wing unmanned aerial vehicles, flying distance is less, cruise duration is short, and due to the plane of revolution of screw propeller parallel with frame, frame is parallel to the ground, therefore can only take off vertically, take off vertically can when there being load article held stationary better, but its speed is comparatively slow, especially when not having load article without the need to vertical takeoff and landing (VTOL), reduces flight efficiency.
Utility model content
In order to solve the problems of the technologies described above, the utility model provide a kind of flying speed high, long-endurance, can the unmanned vehicle of vertical takeoff and landing or inclination landing.
The technical scheme that the utility model adopts is:
The unmanned vehicle that many rotors and fixed-wing combine, comprise fuselage, fixed-wing, motor, screw propeller, described fixed-wing is symmetricly set in the both sides of described fuselage; Described motor is fixedly mounted on the left and right sides of described fixed-wing respectively; Described motor comprises rotating shaft, and described screw propeller is fixedly mounted in described rotating shaft respectively; The direction of described rotating shaft is: with the perpendicular direction of described fuselage end face for benchmark, to direction, the windward side angle of inclination a of described fixed-wing, a is greater than 0 degree, is less than 30 degree.
The utility model unmanned vehicle, combines the advantage of many rotors and fixed-wing, can utilize the vertical takeoff and landing (VTOL) of many rotors, also can play the high advantage of fixed-wing flight efficiency.Can only compared with vertical takeoff and landing (VTOL) with many rotor wing unmanned aerial vehicles of the prior art, the utility model is obliquely installed by machine shaft and screw propeller, enable unmanned vehicle according to loading state difference, coordinate the situation of the traffic requirements of different article, different landing landform, freely select vertical takeoff and landing or inclination landing.In flight course, then play high, the long-endurance advantage of fixed-wing flying speed, improve flight efficiency.
Further, fixed-wing comprises front fixed-wing and rear fixed-wing, and described front fixed-wing is symmetricly set in the both sides of the head of described fuselage, and described rear fixed-wing is symmetricly set in the both sides of the afterbody of described fuselage.
Further, the angle of inclination a of rotating shaft is 5 to 10 degree.
Further, motor is fixedly mounted on the end of the both sides of described front fixed-wing and rear fixed-wing respectively.
Further, form angle b between the bottom surface of fuselage and end face, b is 5 to 10 degree.
Further, the bottom surface of fuselage is equal with the angle of inclination a of described rotating shaft with the angle b between end face.
Further, also comprise retractable frame, described retractable frame is flexibly connected with the bottom surface of described fuselage, and described retractable frame can be received into described fuselage interior or stretch out described external fuselage.
Further, retractable frame is arranged on the bottom surface of the afterbody of described fuselage.
In order to understand better and implement, describe the utility model in detail below in conjunction with accompanying drawing.
Accompanying drawing explanation
Fig. 1 is many rotor wing unmanned aerial vehicles of the prior art;
Fig. 2 is the structural representation of unmanned vehicle of the present utility model;
Fig. 3 is the left view of unmanned vehicle of the present utility model.
Detailed description of the invention
Refer to Fig. 2, it is the structural representation of the unmanned vehicle that many rotors of the present utility model and fixed-wing combine.Unmanned vehicle of the present utility model comprises fuselage 1, front fixed-wing 21, rear fixed-wing 22, motor 3, screw propeller 4 and retractable frame 5.Wherein, front fixed-wing 21 is fixedly connected with fuselage 1 with rear fixed-wing 22, and motor 3 is arranged on front fixed-wing 21 and rear fixed-wing 22, and screw propeller 4 is fixed on motor 3, and retractable frame 5 is flexibly connected with fuselage 1.
Particularly, fuselage 1 comprises head 11, afterbody 12, end face 13 and bottom surface 14.Please refer to Fig. 3, it is the left view of unmanned vehicle.Form angle b between end face 13 and bottom surface 14, the height of fuselage 1 is reduced gradually from head 11 to afterbody 12.B is preferably 5-10 degree.Retractable frame 5 is flexibly connected with bottom surface 14, and it is arranged on afterbody 12 place.This retractable frame 5 can be received into the inside of fuselage 1 when not using, stretch out the outside of fuselage 1 in use, for supporting fuselage 1, makes end face 13 parallel to the ground.
Front fixed-wing 21 and rear fixed-wing 22 are symmetricly set on the head 11 of fuselage and the both sides of afterbody 12 respectively.Four motors 3 are fixedly mounted on the end of the both sides of front fixed-wing 21 and rear fixed-wing 22 respectively.Motor 3 comprises rotating shaft, and rotating shaft is by the Power output of motor 3.Screw propeller 4 is fixedly mounted in rotating shaft, make motor 3 drive screw propeller 4 to rotate, and the plane of revolution of screw propeller 4 is perpendicular to machine shaft.With the perpendicular direction of the end face 13 with fuselage for benchmark, by the windward side direction angle of inclination a of reference direction to fixed-wing, be the direction of this rotating shaft.A is greater than 0 degree, is less than 30 degree, preferred 5-10 degree.In the present embodiment, the angle of inclination a of rotating shaft is equal with the angle of inclination b of bottom surface 14.
Unmanned vehicle of the present utility model operationally, has two kinds of modes of taking off: one is take off vertically, and now retractable frame does not use, and is received in fuselage, and the bottom surface of fuselage lies against ground.Because the leaning angle between the bottom surface of fuselage and end face is b, and the angle between machine shaft and the perpendicular reference direction of fuselage end face is a, and a and b is equal, and therefore machine shaft is now perpendicular to the ground, makes the plane of revolution of screw propeller parallel to the ground.Now screw propeller is with electric machine rotation, and unmanned vehicle just can vertical uplift, and when it has hung article, vertical uplift mode can make article steadily rise.After unmanned vehicle takes off, the direction of adjustment fuselage, make the end face of fuselage parallel to the ground, unmanned vehicle can be advanced fast by fixed-wing.Meanwhile, because fuselage end face is parallel to the ground, hang article on end face can in flight course maintenance level, transport more steady.
Two is tilt to take off, and now retractable frame stretches out external fuselage, supports body bottom surface, make fuselage end face parallel to the ground, machine shaft is in the state of the angle a that turns forward simultaneously, and screw propeller rotarily drives air-flow generation component forward, and ground is flown away from unmanned vehicle and tiltable.This mode of taking off, for the state without loading, due to the component forward that screw propeller rotates, enables unmanned vehicle take off fast, improves flight efficiency.Landing mode of operation with take off similar, can vertical landing or tilt landing.
Unmanned vehicle of the present utility model, combines the advantage of many rotors and fixed-wing, can utilize the vertical takeoff and landing (VTOL) of many rotors, also can play the high advantage of fixed-wing flight efficiency.Can only compared with vertical takeoff and landing (VTOL) with many rotor wing unmanned aerial vehicles of the prior art, the utility model is obliquely installed by machine shaft and screw propeller, enable unmanned vehicle according to loading state difference, coordinate the situation of the traffic requirements of different article, different landing landform, freely select vertical takeoff and landing or inclination landing.In flight course, then play high, the long-endurance advantage of fixed-wing flying speed, improve flight efficiency.
The utility model is not limited to above-mentioned embodiment, if do not depart from spirit and scope of the present utility model to various change of the present utility model or distortion, if these are changed and distortion belongs within claim of the present utility model and equivalent technologies scope, then the utility model is also intended to comprise these changes and distortion.
Claims (8)
1. the unmanned vehicle that rotor more than and fixed-wing combine, it is characterized in that, comprise fuselage, fixed-wing, motor, screw propeller, described fixed-wing is symmetricly set in the both sides of described fuselage; Described motor is fixedly mounted on the left and right sides of described fixed-wing respectively; Described motor comprises rotating shaft, and described screw propeller is fixedly mounted in described rotating shaft respectively; The direction of described rotating shaft is: with the perpendicular direction of described fuselage end face for benchmark, to direction, the windward side angle of inclination a of described fixed-wing, a is greater than 0 degree, is less than 30 degree.
2. the unmanned vehicle of many rotors according to claim 1 and fixed-wing combination, it is characterized in that, described fixed-wing comprises front fixed-wing and rear fixed-wing, described front fixed-wing is symmetricly set in the both sides of the head of described fuselage, and described rear fixed-wing is symmetricly set in the both sides of the afterbody of described fuselage.
3. the unmanned vehicle of many rotors according to claim 2 and fixed-wing combination, is characterized in that, the angle of inclination a of described rotating shaft is 5 to 10 degree.
4. the unmanned vehicle of many rotors according to claim 2 and fixed-wing combination, it is characterized in that, described motor is fixedly mounted on the end of the both sides of described front fixed-wing and rear fixed-wing respectively.
5. the unmanned vehicle of many rotors according to claim 2 and fixed-wing combination, is characterized in that, form angle b between the bottom surface of described fuselage and end face, and b is 5 to 10 degree.
6. the unmanned vehicle of many rotors according to claim 5 and fixed-wing combination, it is characterized in that, the bottom surface of described fuselage is equal with the angle of inclination a of described rotating shaft with the angle b between end face.
7. the unmanned vehicle of many rotors according to claim 2 and fixed-wing combination, it is characterized in that, also comprise retractable frame, described retractable frame is flexibly connected with the bottom surface of described fuselage, and described retractable frame can be received into described fuselage interior or stretch out described external fuselage.
8. the unmanned vehicle of many rotors according to claim 7 and fixed-wing combination, it is characterized in that, described retractable frame is arranged on the bottom surface of the afterbody of described fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520262942.7U CN204688409U (en) | 2015-04-27 | 2015-04-27 | The unmanned vehicle that a kind of many rotors and fixed-wing combine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520262942.7U CN204688409U (en) | 2015-04-27 | 2015-04-27 | The unmanned vehicle that a kind of many rotors and fixed-wing combine |
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| CN204688409U true CN204688409U (en) | 2015-10-07 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882953A (en) * | 2016-05-17 | 2016-08-24 | 亿航智能设备（广州）有限公司 | Aircraft |
| CN106428549A (en) * | 2016-11-21 | 2017-02-22 | 苏州曾智沃德智能科技有限公司 | Carrying device for unmanned aerial vehicle |
| WO2017198082A1 (en) * | 2016-05-17 | 2017-11-23 | 亿航智能设备（广州）有限公司 | Aerial vehicle |
| CN108750081A (en) * | 2018-06-05 | 2018-11-06 | 中国人民解放军国防科技大学 | Tilting four-rotor-wing deformable aircraft |
| CN109436311A (en) * | 2018-12-21 | 2019-03-08 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110036298A (en) * | 2016-10-07 | 2019-07-19 | 卡沃斯巴加泰勒管理有限公司 | It is measured by the wind of multi-rotor aerocraft |
| CN110525643A (en) * | 2019-09-18 | 2019-12-03 | 深圳飞马机器人科技有限公司 | A kind of vertical take-off and landing drone and its manufacturing method |
-
2015
- 2015-04-27 CN CN201520262942.7U patent/CN204688409U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882953A (en) * | 2016-05-17 | 2016-08-24 | 亿航智能设备（广州）有限公司 | Aircraft |
| WO2017198082A1 (en) * | 2016-05-17 | 2017-11-23 | 亿航智能设备（广州）有限公司 | Aerial vehicle |
| CN110036298A (en) * | 2016-10-07 | 2019-07-19 | 卡沃斯巴加泰勒管理有限公司 | It is measured by the wind of multi-rotor aerocraft |
| CN106428549A (en) * | 2016-11-21 | 2017-02-22 | 苏州曾智沃德智能科技有限公司 | Carrying device for unmanned aerial vehicle |
| CN108750081A (en) * | 2018-06-05 | 2018-11-06 | 中国人民解放军国防科技大学 | Tilting four-rotor-wing deformable aircraft |
| CN109436311A (en) * | 2018-12-21 | 2019-03-08 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110525643A (en) * | 2019-09-18 | 2019-12-03 | 深圳飞马机器人科技有限公司 | A kind of vertical take-off and landing drone and its manufacturing method |
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