CN104816822A - Aircraft with four fixed rotor wings - Google Patents
Aircraft with four fixed rotor wings Download PDFInfo
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- CN104816822A CN104816822A CN201510194611.9A CN201510194611A CN104816822A CN 104816822 A CN104816822 A CN 104816822A CN 201510194611 A CN201510194611 A CN 201510194611A CN 104816822 A CN104816822 A CN 104816822A
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- rotor arm
- rotor wing
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Abstract
The invention discloses an aircraft with four fixed rotor wings. The aircraft comprises a fuselage, rotor wing arms and rotor wing power devices. Four rotor wing arms are arranged on four corners of the fuselage symmetrically; the four rotor wing arms and the fuselage are combined to form a cross structure; one rotor wing power device is fixed to each rotor wing arm; each rotor wing power device is composed of a cylindrical shell, a battery, a direct current motor, a speed governor and one rotor wing; the cylindrical shell is arranged at one end of the corresponding rotor wing arm and integrally formed with the corresponding rotor wing arm; the batteries, the direct current motors and the speed governors are fixed into the cylindrical shells; the batteries are used for providing power supplies for the direct current motors; the speed governors are used for adjusting the rotation speeds of the direct current motors; the direct current motors drive the rotor wings to rotate through transmission mechanisms. The safety and reliability of the aircraft are higher.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of quadrotor.
Background technology
There is following defect in existing aircraft:
One is adopt two or more rotor that can turn to, therefore there is complex structure, shortcoming that safety and reliability is low; Two is interference that communication module is easily subject to the circuit card in fuselage, thus affects the normal operation of aircraft; Three is that volume is relatively large, can take compared with space, therefore be inconvenient to carry and transport; Four is that the load of power plant is determined, according to the fuselage body weight size of reality, can not change different power plants.The partial monopoly document retrieved is as follows:
It is CN203294313U that State Intellectual Property Office discloses publication number on November 20th, 2013, patent name is the patent of police four rotor unmanned aircrafts, this aircraft, comprise four symmetrical horns, horn upper end center is provided with dome-type cover and GPS, horn lower center is provided with power plant, and GPS is connected with power plant; The outside end of each horn is equipped with screw propeller, and each screw propeller connects with corresponding motor respectively; Described horn lower end is connected with three symmetrical support foot rests; Power plant comprises battery and motor.Can cruise duration be long, wind resistance good reaching, be convenient to dismounting, carry, replacing battery is convenient, this aircraft is not only easy to carry, flight stability, full-automatic degree is high, noise is little, disguise is strong, low cost, can also to take off under any environment in the wild operation, reach and launch at any time, aerial work is carried out in lift-off fast.In rescue and relief work, forest fire protection, investigation evidence obtaining, arrest in the police work such as suspect, large-scale activity security and make ground staff obtain high-altitude image, increase work efficiency, reduce the cost, avoid personal casualty.
It is CN203094441U that State Intellectual Property Office discloses publication number on July 31st, 2013, patent name is kind of a patent for improved type quadrotor, it the present invention relates to a kind of improved type quadrotor, this aircraft comprises fuselage (1), four rotors of individual drive and the battery pack be located in fuselage and flight control system, it is characterized in that, in described four rotors, one is main rotor (2), three is secondary rotor (3), wherein, described main rotor (2) is vertically located on the fuselage rotation centerline (4) on fuselage (1) top; Described secondary rotor (3) is evenly distributed on the circumference (5) centered by described fuselage rotation centerline (4), and is connected to the side of fuselage (1) by radial arm (6); Described secondary rotor (3) is positioned at same plane, the plane parallel at this plane and main rotor (2) place; A secondary rotor (3) and drive motor (7) composition steering wheel (8) thereof is had, the drive motor in this steering wheel (8) and be provided with between the radial arm corresponding with it (6) and drive this rotor around the rocking-turn mechanism of radial arm rocking-turn in three described secondary rotors (3).
Summary of the invention
The object of this invention is to provide a kind of four rotor fixed aircraft.The safety and reliability of this aircraft is higher; Four rotors have larger lift, from capacity weight, flying radius and flight stability, are all greatly improved.
For achieving the above object, the technical solution adopted in the present invention is:
Four rotor fixed aircraft, include fuselage, rotor arm and rotor power device, described rotor arm is provided with four, four rotor arm symmetries are located at the corner place of fuselage, four rotor arms and fuselage are combined into " ten " character form structure, each rotor arm is fixed with described rotor power device, rotor power device master is by cylinder-like shell, battery, DC machine, governor and rotor, described cylinder-like shell is located at one end of rotor arm and one-body molded with rotor arm, described battery, DC machine and governor are fixed in cylinder-like shell, battery provides power supply for DC machine, governor is in order to regulate the rotating speed of DC machine, described DC machine drives rotor rotational by transmission device.
Further, also comprise GPS module retractor device, GPS module retractor device is formed primarily of GPS communication module, motor, worm gear and worm screw, described GPS communication module is located at the end of worm screw, motor and worm screw are located on fuselage, driven by motor worm gear wheel, worm gear drives worm screw to move, and worm screw promotes GPS communication module away from fuselage.
Further, the coupling end of described rotor arm is provided with threaded connection, and rotor arm is threaded with fuselage by threaded connection.
Further, the bottom of described rotor arm is provided with foot rest.
Further, described four rotor arms are provided with flashing light.
Further, described fuselage is provided with pick up camera.
Further, the rotor arm with different loads rotor for subsequent use is also comprised.
Beneficial effect of the present invention is as follows:
1, because rotor arm and rotor power device have employed fixing installation form, rotor power device is fixing relative to fuselage, and aircraft, when flying, is the rotating speed by change four rotors, come controlled motion direction, therefore the safety and reliability of this aircraft is higher; Four rotors have larger lift, from capacity weight, flying radius and flight stability, are all greatly improved.This aircraft can realize three kinds of offline mode, and namely helicopter mode, transition mode and level advance pattern, have that structure is simple, intensity is high, the features such as reliable function realization.
2, owing to adopting the GPS module retractor device of Worm-gear type, during work, GPS communication module can be made away from fuselage, thus away from the circuit card in fuselage, to reduce the signal disturbing of circuit card to GPS communication module, substantially increase flight stability, ensure that aircraft and normal work.
3, owing to have employed the separable joint of rotor arm and fuselage, when not using, rotor arm is separated with fuselage, thus decreases taking up room of whole body, greatly facilitate and carry or transport, also facilitate installation.
4, above-mentioned separable joint form is adopted, can according to different demands, carry out the rotor arm with different loads rotor that abutting joint is for subsequent use, varions type load is larger, the rotor of design is longer, now, in order to ensure the installing space of rotor, just must ensure that rotor arm has enough length, therefore the design of separable joint, very simple at first view, meaning is very great actually, and this version is change different loads power plant for subsequent use to provide possibility.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:
Fig. 1 is structural representation of the present invention;
The structural representation that Fig. 2 amplifies for the device of rotor power shown in Fig. 1.
In figure: 1, fuselage; 2, rotor arm; 3, rotor; 4, threaded connection; 5, foot rest; 6, GPS communication module; 7, rotor power device; 8, motor; 9, worm gear; 10, worm screw; 11, cylinder-like shell; 12, battery; 13, DC machine; 14, governor.
Detailed description of the invention
As Fig. 1, shown in 2, four rotor fixed aircraft, include fuselage 1, rotor arm 2 and rotor power device 7, described rotor arm 2 is provided with four, four rotor arm 2 symmetries are located at the corner place of fuselage 1, four rotor arms 2 are combined into " ten " character form structure with fuselage, each rotor arm 2 is fixed with described rotor power device 7, rotor power device 7 master is by cylinder-like shell 11, battery 12, DC machine 13, governor 14 and rotor 3, described cylinder-like shell 11 is located at one end of rotor arm 2 and one-body molded with rotor arm 2, described battery 12, DC machine 13 and governor 14 are fixed in cylinder-like shell 11, battery 12 provides power supply for DC machine 13, governor 14, in order to regulate the rotating speed of DC machine 13, described DC machine 13 drives rotor 3 to rotate by transmission device.
The coupling end of described rotor arm 2 is provided with threaded connection 4, and rotor arm 2 is threaded with fuselage 1 by threaded connection 4.Certainly, also comprise the rotor arm with different loads rotor for subsequent use, according to the weight of the distinct device that fuselage is installed, carry out the rotor arm that abutting joint is different, to ensure that aircraft has enough power.
The bottom of described rotor arm 2 is provided with foot rest 5, and four rotor arms 2 are also provided with flashing light.
Described fuselage 1 is provided with GPS communication module 6 and pick up camera.
Also comprise GPS module retractor device, GPS module retractor device is formed primarily of GPS communication module 6, motor 8, worm gear 9 and worm screw 10, described GPS communication module 6 is located at the end of worm screw 10, motor 8 and worm screw 10 are established on the fuselage 1, motor 8 drives worm gear 9 to rotate, worm gear 9 drives worm screw 10 to move, and worm screw 10 promotes GPS communication module 6 away from fuselage, with away from the circuit card in fuselage.To reduce the signal disturbing of circuit card to GPS communication module, substantially increase flight stability.
The above is the preferred embodiment of the present invention; certainly the interest field of the present invention can not be limited with this; should be understood that; for those skilled in the art; technical scheme of the present invention is modified or equivalent replacement, do not depart from the protection domain of technical solution of the present invention.
Claims (7)
1. a rotor fixed aircraft, include fuselage, rotor arm and rotor power device, described rotor arm is provided with four, four rotor arm symmetries are located at the corner place of fuselage, four rotor arms and fuselage are combined into " ten " character form structure, it is characterized in that: each rotor arm is fixed with described rotor power device, rotor power device master is by cylinder-like shell, battery, DC machine, governor and rotor, described cylinder-like shell is located at one end of rotor arm and one-body molded with rotor arm, described battery, DC machine and governor are fixed in cylinder-like shell, battery provides power supply for DC machine, governor is in order to regulate the rotating speed of DC machine, described DC machine drives rotor rotational by transmission device.
2. four rotor fixed aircraft according to claim 1, is characterized in that: the coupling end of described rotor arm is provided with threaded connection, and rotor arm is threaded with fuselage by threaded connection.
3. four rotor fixed aircraft according to claim 2, is characterized in that: also comprise the rotor arm with different loads rotor for subsequent use.
4. four rotor fixed aircraft according to claim 1, is characterized in that: the bottom of described rotor arm is provided with foot rest.
5. four rotor fixed aircraft according to claim 1, it is characterized in that: also comprise GPS module retractor device, GPS module retractor device is formed primarily of GPS communication module, motor, worm gear and worm screw, described GPS communication module is located at the end of worm screw, motor and worm screw are located on fuselage, driven by motor worm gear wheel, worm gear drives worm screw to move, and worm screw promotes GPS communication module away from fuselage.
6. four rotor fixed aircraft according to claim 1, is characterized in that: described four rotor arms are provided with flashing light.
7. want four rotor fixed aircraft described in 1 according to right, it is characterized in that: described fuselage is provided with pick up camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510194611.9A CN104816822A (en) | 2015-04-23 | 2015-04-23 | Aircraft with four fixed rotor wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510194611.9A CN104816822A (en) | 2015-04-23 | 2015-04-23 | Aircraft with four fixed rotor wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104816822A true CN104816822A (en) | 2015-08-05 |
Family
ID=53727354
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510194611.9A Pending CN104816822A (en) | 2015-04-23 | 2015-04-23 | Aircraft with four fixed rotor wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104816822A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105527966A (en) * | 2016-01-29 | 2016-04-27 | 重庆德新机器人检测中心有限公司 | Automated vehicle remote control operation platform |
| CN106882356A (en) * | 2017-01-22 | 2017-06-23 | 衡阳云雁航空科技有限公司 | Many rotor remote control distributor unmanned plane casings of charged pool case |
| CN109649652A (en) * | 2018-11-01 | 2019-04-19 | 广西康纳环保有限公司 | A kind of unmanned plane and fire-extinguishing |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011149544A1 (en) * | 2010-05-26 | 2011-12-01 | Aerovironment Inc. | Reconfigurable battery-operated vehicle system |
| CN202966657U (en) * | 2012-10-24 | 2013-06-05 | 北京中科飞鸿科技有限公司 | Multi-rotor craft capable of changing rotors |
| CN203294313U (en) * | 2013-06-06 | 2013-11-20 | 儋州市公安局 | Police quadrotor type unmanned aerial vehicle |
| CN203318680U (en) * | 2012-10-29 | 2013-12-04 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203461118U (en) * | 2013-09-04 | 2014-03-05 | 重庆金泰航空工业有限公司 | Aircraft body and rotor wing combination for agricultural four-shaft aircraft |
| CN203681867U (en) * | 2013-12-04 | 2014-07-02 | 徐今 | Separation type multi-rotor aircraft |
| CN204078069U (en) * | 2014-10-16 | 2015-01-07 | 深圳市科卫泰实业发展有限公司 | There are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity |
| CN204623833U (en) * | 2015-04-23 | 2015-09-09 | 张�杰 | Four rotor fixed aircraft |
-
2015
- 2015-04-23 CN CN201510194611.9A patent/CN104816822A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011149544A1 (en) * | 2010-05-26 | 2011-12-01 | Aerovironment Inc. | Reconfigurable battery-operated vehicle system |
| CN202966657U (en) * | 2012-10-24 | 2013-06-05 | 北京中科飞鸿科技有限公司 | Multi-rotor craft capable of changing rotors |
| CN203318680U (en) * | 2012-10-29 | 2013-12-04 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203294313U (en) * | 2013-06-06 | 2013-11-20 | 儋州市公安局 | Police quadrotor type unmanned aerial vehicle |
| CN203461118U (en) * | 2013-09-04 | 2014-03-05 | 重庆金泰航空工业有限公司 | Aircraft body and rotor wing combination for agricultural four-shaft aircraft |
| CN203681867U (en) * | 2013-12-04 | 2014-07-02 | 徐今 | Separation type multi-rotor aircraft |
| CN204078069U (en) * | 2014-10-16 | 2015-01-07 | 深圳市科卫泰实业发展有限公司 | There are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity |
| CN204623833U (en) * | 2015-04-23 | 2015-09-09 | 张�杰 | Four rotor fixed aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105527966A (en) * | 2016-01-29 | 2016-04-27 | 重庆德新机器人检测中心有限公司 | Automated vehicle remote control operation platform |
| CN106882356A (en) * | 2017-01-22 | 2017-06-23 | 衡阳云雁航空科技有限公司 | Many rotor remote control distributor unmanned plane casings of charged pool case |
| CN106882356B (en) * | 2017-01-22 | 2023-11-03 | 江苏诚益达智能科技有限公司 | Multi-rotor remote control flying unmanned aerial vehicle shell with battery box |
| CN109649652A (en) * | 2018-11-01 | 2019-04-19 | 广西康纳环保有限公司 | A kind of unmanned plane and fire-extinguishing |
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| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150805 |