CN203593161U - Variable multi-rotor UAV (unmanned aerial vehicle) - Google Patents
Variable multi-rotor UAV (unmanned aerial vehicle) Download PDFInfo
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- CN203593161U CN203593161U CN201320612752.4U CN201320612752U CN203593161U CN 203593161 U CN203593161 U CN 203593161U CN 201320612752 U CN201320612752 U CN 201320612752U CN 203593161 U CN203593161 U CN 203593161U
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Abstract
The utility model discloses a variable multi-rotor UAV (unmanned aerial vehicle), and belongs to the field of flying machines. The UAV comprises a fuselage platform, two undercarriages, airborne equipment, N plugholes formed in the periphery of the fuselage platform at intervals, N rotor shafts, N motors and N propellers, wherein N is more than or equal to 8; the two undercarriages are mounted on the fuselage platform at an interval; the airborne equipment is fixed on the fuselage platform and positioned between the two undercarriages; one end of each rotor shaft is detachably connected onto the fuselage platform through each plughole; the motors are arranged at the other ends of the rotor shafts; the propellers are mounted on the motors; the rotating directions of two adjacent propellers are opposite. According to the utility model, the stability of the UAV is guaranteed to be high, and in addition, the load capacity of the UAV is increased.
Description
Technical field
The utility model relates to aircraft field, particularly a kind of variable many rotor wing unmanned aerial vehicles.
Background technology
Robot airplane, abbreviation unmanned plane (UAV), is a kind of new concept weapon equipment being in developing rapidly, it has advantages of maneuverability, reaction is quick, nobody flies, operation requirements is low.Unmanned plane, by carrying multiclass sensor, can be realized image real-time Transmission, high-risk regional detecting function, is that the strong of satellite remote sensing and traditional air remote sensing supplements.At present, the range of use of unmanned plane has been widened military affairs, scientific research, civilian three large fields, specifically in electric power, communication, meteorology, agricultural, ocean, exploration, photograph, prevent and reduce natural disasters, the field application such as Crop Estimation, drug law enforcement anti-smuggling, border patrol, public security anti-terrorism is very wide.
Existing a kind of unmanned plane, this unmanned plane mainly comprises: two alighting gears, fuselage, airborne equipment, four motors and two groups of screw propellers, wherein, two alighting gears are fixed on fuselage both sides, airborne equipment can be placed in fuselage interior, two groups of screw propellers are located at respectively fuselage head and afterbody, and each screw propeller connects respectively a motor, thereby can realize normal flight.
Realizing in process of the present utility model, contriver finds that prior art at least exists following problem:
Because current unmanned plane only arranges two groups of screw propellers at head and tail, when after a certain screw propeller fault wherein, will there is air crash danger in aircraft, therefore poor stability, in addition, not this unmanned plane can load carrying ability not high.
Utility model content
Not high in order to solve the load carrying ability of prior art unmanned plane, and the problem of poor stability, the utility model embodiment provides a kind of variable many rotor wing unmanned aerial vehicles.Described technical scheme is as follows:
The utility model embodiment provides a kind of variable many rotor wing unmanned aerial vehicles, described unmanned plane comprises: fuselage platform, two alighting gears, airborne equipment, along a described fuselage platform spaced N jack around, N rotor shaft, N motor and N screw propeller, N >=8, described two alighting gear intervals are arranged on described fuselage platform, described airborne equipment is fixed on described fuselage platform and between described two alighting gears, one end of described rotor shaft is detachably connected on described fuselage platform by described jack, the other end of each described rotor shaft is provided with a described motor, a described screw propeller is installed on each described motor, the switched in opposite of adjacent two described screw propellers.
In a kind of implementation of the utility model embodiment, a described N jack is in the same plane.
In the another kind of implementation of the utility model embodiment, described rotor shaft is carbon fiber axle, and described screw propeller is carbon fiber spiral oar.
In the another kind of implementation of the utility model embodiment, described rotor shaft is retractable spindle.
In the another kind of implementation of the utility model embodiment, the length difference of adjacent two described rotor shaft, the length of two the described rotor shaft adjacent with same described rotor shaft is identical.
In the another kind of implementation of the utility model embodiment, described fuselage platform comprises two parallel and be oppositely arranged carbon fiber board and some aviation fasten aluminiums, described two carbon fiber boards connect by described aviation fasten aluminium, and described aviation fasten aluminium is provided with described jack.
In the another kind of implementation of the utility model embodiment, described airborne equipment comprises The Cloud Terrace, pick up camera, power supply and described power supply is exported and the flight control system of described machine operation for controlling, described pick up camera is located on described The Cloud Terrace, and described pick up camera and described motor are electrically connected with described power supply respectively.
In the another kind of implementation of the utility model embodiment, N=8.
In the another kind of implementation of the utility model embodiment, the angle between adjacent two described rotor shaft is 45 degree.
In the another kind of implementation of the utility model embodiment, described fuselage platform is oblong, each side of described fuselage platform is installed respectively two described rotor shaft, and two described rotor shaft that are positioned at same side are parallel to each other, between the described rotor shaft of adjacent two sides, be 90 degree angles.
The beneficial effect that the technical scheme that the utility model embodiment provides is brought is:
By at fuselage platform side interval, N jack being set, and be detachably arranged on N screw propeller in jack, and N >=8, the stability that has guaranteed unmanned plane is high, increase the load carrying ability of unmanned plane, because airborne equipment is arranged on fuselage platform below, saved the space of unmanned plane simultaneously.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the utility model embodiment, below the accompanying drawing of required use during embodiment is described is briefly described, apparently, accompanying drawing in the following describes is only embodiment more of the present utility model, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment mono-;
Fig. 2 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment mono-;
Fig. 3 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment mono-;
Fig. 4 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment mono-;
Fig. 5 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment bis-;
Fig. 6 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment bis-;
Fig. 7 is the structural representation of variable many rotor wing unmanned aerial vehicles of providing of the utility model embodiment bis-.
The specific embodiment
For making the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with accompanying drawing, the utility model embodiment is described in further detail.
Embodiment mono-
The utility model embodiment provides a kind of variable many rotor wing unmanned aerial vehicles, referring to Fig. 1-4, this unmanned plane comprises: two alighting gears 11, fuselage platform 12, airborne equipment (scheming not shown), along a fuselage platform 12 spaced N jack 13 around, N rotor shaft 14, N screw propeller 15 and N motor 16, N >=8, two alighting gear 11 intervals are arranged on fuselage platform 12, airborne equipment is fixed on fuselage platform 12 and between two alighting gears 11, one end of rotor shaft 14 be connected on fuselage platform 12 by jack 13 detouchables, the other end of each rotor shaft 14 is provided with a motor 16, a screw propeller 15 is installed on each motor 16, and the switched in opposite of adjacent two screw propellers 15.
Wherein, rotor shaft 14 one end and jack 13 can arrange screw thread simultaneously, connect by screw thread.Certainly, between rotor shaft 14 and jack 13, can also be other connection modes, repeat no more here.
Preferably, rotor shaft 14 can be carbon fiber axle, screw propeller 15 can be carbon fiber spiral oar, fuselage platform 12 can comprise two parallel and be oppositely arranged carbon fiber board and some aviation fasten aluminiums, two carbon fiber boards connect by aviation fasten aluminium, and aviation fasten aluminium is provided with jack 13.Thereby make unmanned plane weight lighter, structure is more firm.
Further, rotor shaft 14 is retractable spindle, and the length that is arranged on the rotor shaft 14 on fuselage 12 can be identical.The length of rotor shaft 13 can be not identical yet, preferably, as Figure 1-3, the length difference of adjacent two rotor shaft 14, the length of two rotor shaft 14 adjacent with same rotor shaft 14 is identical.
As depicted in figs. 1 and 2, above-mentioned jack 13 can arrange in one plane, also can be arranged in two planes or more plane.
Further, as shown in Figure 1, set gradually 4 rotor shaft 14 at the side of circular fuselage platform 12, and 4 rotor shaft 14 length are identical, the angle between two adjacent rotor shaft 14 is identical, and angle between every two adjacent rotor shaft 14 is 90 degree; As shown in Figure 3-4, set gradually 8 rotor shaft 14 at the side of circular fuselage platform 12, and 8 rotor shaft 14 length are not identical, the angle between two adjacent rotor shaft 14 is identical, and angle between every two adjacent rotor shaft 14 is 45 degree.In use, can need to select according to load carrying ability the quantity of the rotor shaft of installing.It should be noted that, fuselage platform 12 is not limited in circle, can also be square, polygon or other shape.
Further, unmanned aerial vehicle onboard equipment is exposed structure, airborne equipment comprises The Cloud Terrace, pick up camera, power supply and for controlling power supply output and N the flight control system that motor 16 is worked, pick up camera is located on The Cloud Terrace, and a pick up camera and N motor 16 is electrically connected with power supply respectively.Because camera is arranged on the below of fuselage platform, and unmanned aerial vehicle onboard equipment is exposed structure, makes unmanned plane camera can carry out 360 degree omnidirectional shootings.Wherein, exposed structure refers to, airborne equipment hangs or hangs and is located at fuselage platform below, and the surrounding of airborne equipment does not arrange baffle plate or other devices.
The unmanned plane that the utility model provides, by N jack being set at fuselage platform side interval, and be detachably arranged on N screw propeller in jack, and N >=8, the stability that has guaranteed unmanned plane is high, increase the load carrying ability of unmanned plane, because airborne equipment is arranged on fuselage platform below, saved the space of unmanned plane simultaneously.
Embodiment bis-
The utility model embodiment provides a kind of variable many rotor wing unmanned aerial vehicles, referring to Fig. 5-7, this unmanned plane comprises: two alighting gears 21, fuselage platform 22, airborne equipment (scheming not shown), along a fuselage platform 22 spaced N jack 23 around, N rotor shaft 24, N screw propeller 25 and N motor 26, N >=8, two alighting gear 21 intervals are arranged on fuselage platform 22, airborne equipment is fixed on fuselage platform 22 and between two alighting gears 21, one end of rotor shaft 23 is connected with fuselage platform 22 by jack 23, the other end of each rotor shaft 24 is provided with a motor 26, a screw propeller 25 is installed on each motor 26, and the switched in opposite of adjacent two screw propellers 25.
Wherein, rotor shaft 24 one end and jack 23 can arrange screw thread simultaneously, connect by screw thread.Certainly, between rotor shaft 24 and jack 23, can also be other connection modes, repeat no more here.
Preferably, rotor shaft 24 can be carbon fiber rotor shaft, screw propeller 25 can be carbon fiber spiral oar, fuselage platform 22 can comprise two parallel and be oppositely arranged carbon fiber board and some aviation fasten aluminiums, two carbon fiber boards connect by aviation fasten aluminium, and aviation fasten aluminium is provided with jack 23.Thereby make unmanned plane weight lighter, more firm.
Further, rotor shaft 24 is retractable spindle, and the length that is arranged on the rotor shaft 24 on fuselage 22 can be identical.The length of rotor shaft 24 can be not identical yet, preferably, as shown in Fig. 4-5, the length difference of adjacent two rotor shaft 24, the length of two rotor shaft 24 adjacent with same rotor shaft 24 is identical.
As illustrated in Figures 5 and 6, above-mentioned jack 23 can arrange in one plane, also can be arranged in two planes or more plane.
Further, as shown in Figure 5, a rotor shaft 24 is installed respectively on each side of oblong fuselage 22, between adjacent two rotor shaft 24, angle is 90 degree; As shown in Figure 7, at each side of rectangular fuselage platform 22, two rotor shaft 24 are installed respectively, two rotor shaft 24 that are positioned at same side are parallel to each other, and are 90 degree angles between the rotor shaft 24 of adjacent two sides.Above-mentioned two rotor shaft 24 that are positioned at the same side can be separately positioned on two end points of this side.In use, can need to select according to load carrying ability the quantity of the rotor shaft of installing.It should be noted that, fuselage platform 22 is not limited in oblong, can also be circle, polygon or other shape.
Between certainly, above-mentioned rotor shaft 24 length and rotor shaft 24, angle also can irregularly arrange.
Further, unmanned aerial vehicle onboard equipment is exposed structure, airborne equipment comprises The Cloud Terrace, pick up camera, power supply and for controlling power supply output and N the flight control system that motor 26 is worked, pick up camera is located on The Cloud Terrace, and a pick up camera and N motor 26 is electrically connected with power supply respectively.Because camera is arranged on the below of fuselage platform, and unmanned aerial vehicle onboard equipment is exposed structure, makes unmanned plane camera can carry out 360 degree omnidirectional shootings.Wherein, exposed structure refers to, airborne equipment hangs or hangs and is located at fuselage platform below, and the surrounding of airborne equipment does not arrange baffle plate or other devices.
The unmanned plane that the utility model provides, by N jack being set at fuselage platform side interval, and be detachably arranged on N screw propeller in jack, and N >=8, the stability that has guaranteed unmanned plane is high, increase the load carrying ability of unmanned plane, because airborne equipment is arranged on fuselage platform below, saved the space of unmanned plane simultaneously.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (10)
1. variable many rotor wing unmanned aerial vehicles, it is characterized in that, described unmanned plane comprises: fuselage platform, two alighting gears, airborne equipment, along a described fuselage platform spaced N jack around, N rotor shaft, N motor and N screw propeller, N >=8, described two alighting gear intervals are arranged on described fuselage platform, described airborne equipment is fixed on described fuselage platform and between described two alighting gears, one end of described rotor shaft is detachably connected on described fuselage platform by described jack, the other end of each described rotor shaft is provided with a described motor, a described screw propeller is installed on each described motor, the switched in opposite of adjacent two described screw propellers.
2. unmanned plane as claimed in claim 1, is characterized in that, a described N jack is in the same plane.
3. unmanned plane as claimed in claim 1, is characterized in that, described rotor shaft is carbon fiber axle, and described screw propeller is carbon fiber spiral oar.
4. unmanned plane as claimed in claim 1, is characterized in that, described rotor shaft is retractable spindle.
5. unmanned plane as claimed in claim 4, is characterized in that, the length difference of adjacent two described rotor shaft, and the length of two the described rotor shaft adjacent with same described rotor shaft is identical.
6. unmanned plane as claimed in claim 1, it is characterized in that, described fuselage platform comprises two parallel and be oppositely arranged carbon fiber board and some aviation fasten aluminiums, and described two carbon fiber boards connect by described aviation fasten aluminium, and described aviation fasten aluminium is provided with described jack.
7. unmanned plane as claimed in claim 1, it is characterized in that, described airborne equipment comprises The Cloud Terrace, pick up camera, power supply and described power supply is exported and the flight control system of described machine operation for controlling, described pick up camera is located on described The Cloud Terrace, and described pick up camera and described motor are electrically connected with described power supply respectively.
8. the unmanned plane as described in claim 1-7 any one, is characterized in that N=8.
9. unmanned plane as claimed in claim 8, is characterized in that, the angle between adjacent two described rotor shaft is 45 degree.
10. unmanned plane as claimed in claim 8, it is characterized in that, described fuselage platform is oblong, each side of described fuselage platform is installed respectively two described rotor shaft, and two described rotor shaft that are positioned at same side are parallel to each other, between the described rotor shaft of adjacent two sides, be 90 degree angles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320612752.4U CN203593161U (en) | 2013-09-29 | 2013-09-29 | Variable multi-rotor UAV (unmanned aerial vehicle) |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320612752.4U CN203593161U (en) | 2013-09-29 | 2013-09-29 | Variable multi-rotor UAV (unmanned aerial vehicle) |
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| Publication Number | Publication Date |
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| CN203593161U true CN203593161U (en) | 2014-05-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320612752.4U Expired - Fee Related CN203593161U (en) | 2013-09-29 | 2013-09-29 | Variable multi-rotor UAV (unmanned aerial vehicle) |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554726A (en) * | 2014-12-01 | 2015-04-29 | 嵊州领航信息科技有限公司 | Special intelligent unmanned aerial vehicle for agriculture and forestry |
| CN104828245A (en) * | 2015-04-30 | 2015-08-12 | 何春旺 | Aircraft |
| CN104925248A (en) * | 2015-06-04 | 2015-09-23 | 杭州锐翼科技有限公司 | Multi-rotor-wing unmanned aerial vehicle with novel pneumatic layout and motor control method thereof |
| CN105857587A (en) * | 2016-03-31 | 2016-08-17 | 英华达（上海）科技有限公司 | Multi-axis unmanned aerial vehicle and flight method thereof |
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108033000A (en) * | 2017-12-05 | 2018-05-15 | 长沙展朔轩兴信息科技有限公司 | Variable multi-rotor unmanned aerial vehicle |
-
2013
- 2013-09-29 CN CN201320612752.4U patent/CN203593161U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554726A (en) * | 2014-12-01 | 2015-04-29 | 嵊州领航信息科技有限公司 | Special intelligent unmanned aerial vehicle for agriculture and forestry |
| CN104828245A (en) * | 2015-04-30 | 2015-08-12 | 何春旺 | Aircraft |
| CN104925248A (en) * | 2015-06-04 | 2015-09-23 | 杭州锐翼科技有限公司 | Multi-rotor-wing unmanned aerial vehicle with novel pneumatic layout and motor control method thereof |
| CN104925248B (en) * | 2015-06-04 | 2017-01-25 | 杭州锐翼科技有限公司 | Multi-rotor-wing unmanned aerial vehicle with novel pneumatic layout and motor control method thereof |
| CN105857587A (en) * | 2016-03-31 | 2016-08-17 | 英华达（上海）科技有限公司 | Multi-axis unmanned aerial vehicle and flight method thereof |
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108033000A (en) * | 2017-12-05 | 2018-05-15 | 长沙展朔轩兴信息科技有限公司 | Variable multi-rotor unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140514 Termination date: 20140929 |
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| EXPY | Termination of patent right or utility model |