CN205396527U - Many heligyro of letter way formula power - Google Patents
Many heligyro of letter way formula power Download PDFInfo
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- CN205396527U CN205396527U CN201620174788.2U CN201620174788U CN205396527U CN 205396527 U CN205396527 U CN 205396527U CN 201620174788 U CN201620174788 U CN 201620174788U CN 205396527 U CN205396527 U CN 205396527U
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Abstract
The utility model relates to a many rotor unmanned aerial vehicle specifically are many heligyro of letter way formula power. The utility model provides a current many rotor unmanned aerial vehicle screw inefficiency, the poor problem of flight safety nature. Many heligyro of letter way formula power carries equipment part including rack section, fuselage part, machine, the rack section includes the hyperbola letter way body, horn mount pad, electronic equipment storehouse bracket, task load bracket, the fuselage part includes main arm, coaxial rotary joint, turns to arm, steering wheel, lift motor, lifting propeller, turns to motor, screw -rudder, the machine carries equipment part and includes power battery, electronic equipment storehouse, task load. The utility model is suitable for a take photo by plane, field such as plant protection, control.
Description
Technical field
This utility model relates to many rotor wing unmanned aerial vehicles, specifically a kind of exhausting formula power multirotor helicopter.
Background technology
Many rotor wing unmanned aerial vehicles are excellent with its flight controlling, can hover in any spatial point, landing without features such as place supports, be widely used in taking photo by plane by every profession and trade, plant protection, the various fields such as monitoring.Under prior art conditions, the commonly used exposed arrangement form of propeller of many rotor wing unmanned aerial vehicles, there are the following problems to cause it: one, many rotor wing unmanned aerial vehicles are when flight, and propeller pushes down on air continuously, owing to propeller adopts exposed arrangement form, the partial air being subject to propeller promotion can't be flowed downward, but side can be disappeared in along with rough air, thereby result in power and run off, thus causing that propeller efficiency reduces.Its two, many rotor wing unmanned aerial vehicles are when flight, owing to propeller adopts exposed arrangement form so that propeller, once rupture, departing from the faults such as fuselage, high speed will fly out and hurt sb.'s feelings under effect of inertia, thus cause that flight safety is poor.Based on this, it is necessary to invent a kind of brand-new many rotor wing unmanned aerial vehicles, to solve the problems referred to above that existing many rotor wing unmanned aerial vehicles exist.
Summary of the invention
This utility model is in order to solve the existing problem that many rotor wing unmanned aerial vehicles propeller efficiency is low, flight safety is poor, it is provided that a kind of exhausting formula power multirotor helicopter.
This utility model adopts the following technical scheme that realization:
Exhausting formula power multirotor helicopter, including rack section, fuselage sections, airborne equipment part；
Described rack section includes hyperbola exhausting body, horn mounting seat, electronic equipment storehouse bracket, mission payload bracket；The number of horn mounting seat is two；Two horn mounting seats are individually fixed in lateral surface left part and the lateral surface right part of hyperbola exhausting body；The lateral surface that electronic equipment storehouse bracket is fixed on hyperbola exhausting body is anterior；Mission payload bracket is fixed on the lateral surface rear portion of hyperbola exhausting body；
Described fuselage sections includes principal arm, Coaxial rotary joint, steering arm, steering wheel, lift motor, lifting propeller, steer motor, screw-rudder；The number of principal arm is two；The tail end of two principal arms is individually fixed in two horn mounting seats；The axis of two principal arms overlaps, and the axis of two principal arms all intersects vertically with the axis of hyperbola exhausting body；The number of Coaxial rotary joint is two；The number of steering arm is two；The tail end of two steering arms is coaxially connected respectively through the head end of two Coaxial rotary joints and two principal arms；The number of steering wheel is two；Two steering wheels are respectively arranged in the head end of two principal arms, and the output shaft of two steering wheels is connected with two Coaxial rotary joints respectively；The number of lift motor is two；Two lift motor reverse-fittings are in the inner chamber of hyperbola exhausting body, and the axis of two lift motors all overlaps with the axis of hyperbola exhausting body；The number of lifting propeller is two；Two lifting propellers are connected with the output shaft of two lift motors respectively；The number of steer motor is two；Two steer motor are respectively arranged in the head end side of two steering arms, and the axis of two steer motor intersects vertically with the axis of two steering arms respectively；The number of screw-rudder is two；Two screw-rudders are connected with the output shaft of two steer motor respectively；
Described airborne equipment part includes electrokinetic cell, electronic equipment storehouse, mission payload；Electrokinetic cell is installed on the upper surface of horn mounting seat；Electrokinetic cell power supply outfan respectively with the energization input of two steering wheels, the energization input of two lift motors, two steer motor energization input be connected；Electronic equipment storehouse is installed on the upper surface of electronic equipment storehouse bracket；Mission payload is installed on the upper surface of mission payload bracket.
During work, the inner chamber in electronic equipment storehouse is provided with flight control system, and the control output end of flight control system respectively with two steering wheels control input, two lift motors control input, the control input of two steer motor is connected.Specific works process is as follows: ground staff sends remote signal to flight control system, and flight control system controls two steering wheels respectively according to the remote signal received, two lift motors, two steer motor rotate.Control mode includes: one, two steering wheels drive two Coaxial rotary joints to turn an angle respectively, two Coaxial rotary joints thus drive two steering arms to turn an angle around the axis of principal arm respectively, and two steering arms thus drive two steer motor and two screw-rudders to turn an angle around the axis of principal arm respectively.Two, two lift motors drive two lifting propellers to carry out reversely rotating respectively (opposite torques that two lift motors produce when rotating is cancelled out each other, thus without producing yawing), two lifting propellers thus provide vertical lift (hyperbola exhausting body ensure that lift air-flow velocity that two lifting propellers produce uniformly, concentrate reach minimum so that the efficiency of lift air-flow reaches maximum, loss).Three, two steer motor drive two screw-rudders to carry out rotating Vortex or reversing differential rotation respectively, and two screw-rudders thus provide horizontal propulsive force on the one hand, provide vertical lift on the other hand.Under the combined effect of vertical lift and horizontal propulsive force, helicopter can realize various flare maneuver (such as advance, retrogressing, left and right turn, pivot stud etc.).
Based on said process, compared with existing many rotor wing unmanned aerial vehicles, exhausting formula power multirotor helicopter described in the utility model is by adopting exhausting formula dynamic structure, possesses following advantage: one, air-flow is retrained by this utility model by adopting hyperbola exhausting body, having stopped cross-flow generation (makes the air being subject to propeller promotion all flow downward, without disappearing in side along with rough air), thus thoroughly avoid power to run off, thus propeller efficiency is greatly improved.Its two, this utility model by adopt hyperbola exhausting body propeller is protected so that even if propeller ruptures, departs from the faults such as fuselage, also can cannot fly out under the restriction of hyperbola exhausting body and hurt sb.'s feelings, thus drastically increase flight safety.
This utility model is rational in infrastructure, it is ingenious to design, and efficiently solves the existing problem that many rotor wing unmanned aerial vehicles propeller efficiency is low, flight safety is poor, it is adaptable to take photo by plane, plant protection, the field such as monitoring.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the top view of Fig. 1.
In figure: 11-hyperbola exhausting body, 12-horn mounting seat, 13-electronic equipment storehouse bracket, 14-mission payload bracket, 21-principal arm, 22-Coaxial rotary joint, 23-steering arm, 24-steering wheel, 25-lift motor, 26-lifting propeller, 27-steer motor, 28-screw-rudder, 31-electrokinetic cell.
Detailed description of the invention
Exhausting formula power multirotor helicopter, including rack section, fuselage sections, airborne equipment part；
Described rack section includes hyperbola exhausting body 11, horn mounting seat 12, electronic equipment storehouse bracket 13, mission payload bracket 14；The number of horn mounting seat 12 is two；Two horn mounting seats 12 are individually fixed in lateral surface left part and the lateral surface right part of hyperbola exhausting body 11；The lateral surface that electronic equipment storehouse bracket 13 is fixed on hyperbola exhausting body 11 is anterior；Mission payload bracket 14 is fixed on the lateral surface rear portion of hyperbola exhausting body 11；
Described fuselage sections includes principal arm 21, Coaxial rotary joint 22, steering arm 23, steering wheel 24, lift motor 25, lifting propeller 26, steer motor 27, screw-rudder 28；The number of principal arm 21 is two；The tail end of two principal arms 21 is individually fixed in two horn mounting seats 12；The axis of two principal arms 21 overlaps, and the axis of two principal arms 21 all intersects vertically with the axis of hyperbola exhausting body 11；The number of Coaxial rotary joint 22 is two；The number of steering arm 23 is two；The tail end of two steering arms 23 is coaxially connected respectively through the head end of two Coaxial rotary joints 22 and two principal arms 21；The number of steering wheel 24 is two；Two steering wheels 24 are respectively arranged in the head end of two principal arms 21, and the output shaft of two steering wheels 24 is connected with two Coaxial rotary joints 22 respectively；The number of lift motor 25 is two；Two lift motor 25 reverse-fittings are in the inner chamber of hyperbola exhausting body 11, and the axis of two lift motors 25 all overlaps with the axis of hyperbola exhausting body 11；The number of lifting propeller 26 is two；Two lifting propellers 26 are connected with the output shaft of two lift motors 25 respectively；The number of steer motor 27 is two；Two steer motor 27 are respectively arranged in the head end side of two steering arms 23, and the axis of two steer motor 27 intersects vertically with the axis of two steering arms 23 respectively；The number of screw-rudder 28 is two；Two screw-rudders 28 are connected with the output shaft of two steer motor 27 respectively；
Described airborne equipment part includes electrokinetic cell 31, electronic equipment storehouse, mission payload；Electrokinetic cell 31 is installed on the upper surface of horn mounting seat 12；Electrokinetic cell 31 power supply outfan respectively with the energization input of two steering wheels 24, the energization input of two lift motors 25, two steer motor 27 energization input be connected；Electronic equipment storehouse is installed on the upper surface of electronic equipment storehouse bracket 13；Mission payload is installed on the upper surface of mission payload bracket 14.
When being embodied as, the power of the power of two lift motors 25 and two steer motor 27 is identical.The consistent size of the size of two lifting propellers 26 and two screw-rudders 28.Electrokinetic cell 31 is lithium polymer battery, and the number of electrokinetic cell 31 is two.Mission payload includes camera, videocorder etc..
Claims (1)
1. an exhausting formula power multirotor helicopter, it is characterised in that: include rack section, fuselage sections, airborne equipment part；
Described rack section includes hyperbola exhausting body (11), horn mounting seat (12), electronic equipment storehouse bracket (13), mission payload bracket (14)；The number of horn mounting seat (12) is two；Two horn mounting seats (12) are individually fixed in lateral surface left part and the lateral surface right part of hyperbola exhausting body (11)；The lateral surface that hyperbola exhausting body (11) is fixed in electronic equipment storehouse bracket (13) is anterior；Mission payload bracket (14) is fixed on the lateral surface rear portion of hyperbola exhausting body (11)；
Described fuselage sections includes principal arm (21), Coaxial rotary joint (22), steering arm (23), steering wheel (24), lift motor (25), lifting propeller (26), steer motor (27), screw-rudder (28)；The number of principal arm (21) is two；The tail end of two principal arms (21) is individually fixed on two horn mounting seats (12)；The axis of two principal arms (21) overlaps, and the axis of two principal arms (21) all intersects vertically with the axis of hyperbola exhausting body (11)；The number of Coaxial rotary joint (22) is two；The number of steering arm (23) is two；The tail end of two steering arms (23) is coaxially connected respectively through the head end of two Coaxial rotary joints (22) Yu two principal arms (21)；The number of steering wheel (24) is two；Two steering wheels (24) are respectively arranged in the head end of two principal arms (21), and the output shaft of two steering wheels (24) is connected with two Coaxial rotary joints (22) respectively；The number of lift motor (25) is two；Two lift motor (25) reverse-fittings are in the inner chamber of hyperbola exhausting body (11), and the axis of two lift motors (25) all overlaps with the axis of hyperbola exhausting body (11)；The number of lifting propeller (26) is two；Two lifting propellers (26) are connected with the output shaft of two lift motors (25) respectively；The number of steer motor (27) is two；Two steer motor (27) are respectively arranged in the head end side of two steering arms (23), and the axis of two steer motor (27) intersects vertically with the axis of two steering arms (23) respectively；The number of screw-rudder (28) is two；Two screw-rudders (28) are connected with the output shaft of two steer motor (27) respectively；
Described airborne equipment part includes electrokinetic cell (31), electronic equipment storehouse, mission payload；Electrokinetic cell (31) is installed on the upper surface of horn mounting seat (12)；The power supply outfan of electrokinetic cell (31) respectively with the energization input of two steering wheels (24), the energization input of two lift motors (25), two steer motor (27) energization input be connected；Electronic equipment storehouse is installed on the upper surface in electronic equipment storehouse bracket (13)；Mission payload is installed on the upper surface of mission payload bracket (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620174788.2U CN205396527U (en) | 2016-03-08 | 2016-03-08 | Many heligyro of letter way formula power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620174788.2U CN205396527U (en) | 2016-03-08 | 2016-03-08 | Many heligyro of letter way formula power |
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| Publication Number | Publication Date |
|---|---|
| CN205396527U true CN205396527U (en) | 2016-07-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620174788.2U Expired - Fee Related CN205396527U (en) | 2016-03-08 | 2016-03-08 | Many heligyro of letter way formula power |
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| Country | Link |
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| CN (1) | CN205396527U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927031A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
| WO2018113134A1 (en) * | 2016-12-20 | 2018-06-28 | 深圳市元征科技股份有限公司 | Multi-rotor unmanned aerial vehicle |
-
2016
- 2016-03-08 CN CN201620174788.2U patent/CN205396527U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018113134A1 (en) * | 2016-12-20 | 2018-06-28 | 深圳市元征科技股份有限公司 | Multi-rotor unmanned aerial vehicle |
| CN106927031A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160727 Address after: 030600, room 5, floor 506, Yingbin West Street and Tian Tian business building, Jinzhong Development Zone, Shanxi Patentee after: Shanxi Shipule General Aviation Technology Co. Ltd. Address before: 030603, Shanxi Jinzhong District, Yuci Yingbin West Street and Tian commercial building 5 Patentee before: Tian Chunyu |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160727 Termination date: 20170308 |