CN203958609U - A kind of electronic unmanned plane based on photoelectrical coupler - Google Patents
A kind of electronic unmanned plane based on photoelectrical coupler Download PDFInfo
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- CN203958609U CN203958609U CN201420230287.2U CN201420230287U CN203958609U CN 203958609 U CN203958609 U CN 203958609U CN 201420230287 U CN201420230287 U CN 201420230287U CN 203958609 U CN203958609 U CN 203958609U
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- 238000006243 chemical reaction Methods 0.000 description 2
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Abstract
The utility model relates to a kind of electronic unmanned plane based on photoelectrical coupler.Comprise fuselage and the wing combined, fuselage interior is provided with flight-control computer, is provided with flight attitude control system in wing; Also comprise photoelectrical coupler, photoelectrical coupler comprises optical signal sending end and optical signal receiving end, optical signal sending end is arranged on fuselage, and is connected with flight-control computer, and optical signal sending end comprises the infrarede emitting diode for generation of infrared light pulse; Optical signal receiving end is arranged on wing, and is connected with flight attitude control system, and optical signal receiving end comprises for receiving infrared light pulse, and infrared light pulse is converted into electric signal and sends to the infrared photodiode of flight attitude control system.Electronic unmanned plane of the present utility model has been cancelled connector, and fitting process one step completes and do not exist misplug, leaks the problems such as slotting, and light coupled device can also effectively be blocked the interference between each parts simultaneously, improves the electromagnetic compatibility of unmanned plane.
Description
Technical field
The utility model relates to a kind of electronic unmanned plane, particularly a kind of electronic unmanned plane based on photoelectrical coupler.
Background technology
Modern unmanned plane, in order to meet just and the job requirements of carrying and transporting, generally adopts unitized construction, and this unitized construction can exist the transmission cable of power delivery and control signal transmission between each parts.In order just to fill with folding, existing unmanned plane generally adopts the connector of all size to realize the transmission of signal, such as aviation plug.Because flight-control computer is output as three road PMW signals, Gai San road PMW signal is controlled respectively left elevon steering wheel, brushless power machine governor and right elevon and is realized the control to aircraft, Zhe San road signal adds power source needs the connector of 11 cores control signal and power supply could be delivered to wing section altogether, wherein 9 cores are signal wire (SW), 2 cores are the power lead of large electric current, and this just needs special customized connector could meet operating needs.Although with the structure of locking device and avoiding misinsertion, in actual use procedure, due to patching repeatedly, also there is misplug, leak and insert and the insecure phenomenon of connector in this plug, has a strong impact on flight safety simultaneously; And adopt cable and aviation plug, and can cause complex circuit in aircraft, time attractive in appearance, check also inconvenient.Therefore need to provide a structure without connector, realize the transmission of control signal.In prior art, usually adopting the mode of low frequency close magnetic coupling and frequency electromagnetic waves to realize without connector signal transmits, be sending device as adopted magnet coil at sending end, receiving end carries out the reception of magnetic signal with coil or hall device, this technical scheme anti-electromagnetic interference capability is poor, volume weight is large, has electromagnetic radiation simultaneously, can have interference to other electronic machines.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of electronic unmanned plane based on photoelectrical coupler, solved the misplug that exists when existing electronic unmanned plane adopts connector to carry out control signal transmission, leak insert, connector technical matters unreliable and not attractive in appearance, that be not easy to carry out electrical check.
The technical scheme that the utility model solves the problems of the technologies described above is as follows: a kind of electronic unmanned plane based on photoelectrical coupler, comprise fuselage and the wing combined, described fuselage interior is provided with flight-control computer, is provided with flight attitude control system in described wing; Also comprise photoelectrical coupler, described photoelectrical coupler comprises optical signal sending end and optical signal receiving end, and described optical signal sending end is arranged on fuselage, and is connected with described flight-control computer; Described optical signal receiving end is arranged on wing, and is connected with described flight attitude control system.
The beneficial effects of the utility model are: electronic unmanned plane of the present utility model carries out the transmission of control signal between fuselage and wing by optic coupler, compared with existing connector associated mode, connect up more easy, conveniently carry out interior of aircraft layout; There is no connector, electronic unmanned plane weight alleviates to some extent, convenient on working service simultaneously; In addition, the connector contact oxidation of having stopped electronic unmanned plane of the present utility model causes the risk of bad contact, does not need in the use to go specially the plug-in unit of pegging graft, and whole fitting process one step completes, improve the development rate of electronic unmanned plane, be highly suitable for and need emergent occasion of taking off to use; Light coupled device can also effectively be blocked the interference between the each parts of aircraft simultaneously, makes the electromagnetic compatibility of aircraft better.
On the basis of technique scheme, the utility model can also do following improvement.
Further, described photoelectrical coupler also comprises the combiner being arranged on wing, and described optical signal receiving end connects described flight attitude control system by described combiner.
Adopt the beneficial effect of further technical scheme to be: by combiner is set, in the time that needs carry out multi-way control signals transmission, multi-way control signals can be encoded to a road control signal, be convenient to the transmission of signal.
Further, described optical signal sending end comprises for receiving described flight-control computer control command and producing the infrarede emitting diode of infrared light pulse, and described optical signal receiving end comprises for receiving described infrared light pulse and producing the infrared photodiode of electric signal.
Further, described optical signal receiving end also comprises that described aerotron mouth connects described flight attitude control system for the described infrared photodiode of aerotron input end connection described in the aerotron of amplification signal.
Adopt the beneficial effect of further technical scheme to be: in the time that the electric signal of infrared photodiode conversion is fainter, to adopt aerotron can amplify described faint electric signal, obtain better signal transmission effect.
Further, described flight attitude control system comprises the left elevon steering wheel being arranged in wing, right elevon steering wheel and/or brushless motor governor.
Further, described photoelectrical coupler comprises the first photoelectric coupling structure, the second photoelectric coupling structure and the 3rd photoelectric coupling structure, described the first photoelectric coupling structure comprises the first infrarede emitting diode, the first infrared photodiode and the first aerotron, the input end of described the first infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the first infrared photodiode; The mouth of described the first infrared photodiode connects described the first aerotron, sends to described the first aerotron for described infrared light pulse being converted to electric pulse; Described the first aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described left elevon steering wheel;
Described the second photoelectric coupling structure comprises the second infrarede emitting diode, the second infrared photodiode and the second aerotron, the input end of described the second infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the second infrared photodiode; The mouth of described the second infrared photodiode connects described the second aerotron, sends to described the second aerotron for described infrared light pulse being converted to electric pulse; Described the second aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described right elevon steering wheel;
Described the 3rd photoelectric coupling structure comprises the 3rd infrarede emitting diode, the 3rd infrared photodiode and the 3rd aerotron, the input end of described the 3rd infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the 3rd infrared photodiode; The mouth of described the 3rd infrared photodiode connects described the 3rd aerotron, sends to described the 3rd aerotron for described infrared light pulse being converted to electric pulse; Described the 3rd aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described brushless motor governor.
Further, described photoelectrical coupler also comprises the combiner being arranged on wing, described combiner input end connects respectively described the first aerotron, the second aerotron and the 3rd aerotron, and described combiner mouth connects respectively described left elevon steering wheel, right elevon steering wheel and/or described brushless motor governor.
Further, described fuselage interior is also provided with flying power battery pack, and described wing is provided with the conducting bolt for fixing described wing and fuselage, and described conducting bolt is electrically connected with described flying power battery pack.
Adopt the beneficial effect of further technical scheme to be: by original wing bolt of rear end plate is redesigned, carry out the transmission of power supply taking conducting bolt as conducting medium, making has not had connector completely between fuselage and wing, when user's assembling aircraft, simply to only buckling wing, the conducting bolt of screwing on, has just completed the assembling of aircraft.
Brief description of the drawings
Fig. 1 is the connection diagram of the electronic unmanned plane of the utility model embodiment.
Detailed description of the invention
Below in conjunction with accompanying drawing, principle of the present utility model and feature are described, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
Fig. 1 is the structural representation of the electronic unmanned plane of KC1600 type, the present embodiment taking the electronic unmanned plane of KC1600 type as example illustrates structure of the present utility model and principle.The electronic unmanned plane of described KC1600 type is in order to reach portable object, in structure, having adopted wing and fuselage conveniently to roll over separates and package assembly, flying power battery pack is contained in fuselage, left elevon steering wheel, right elevon steering wheel, brushless motor and brushless motor governor are contained in wing, therefore need with cable, each electric component to be linked up.
As shown in Figure 1, the present embodiment comprises fuselage and the wing combined, described fuselage interior is provided with flight-control computer, is provided with left elevon steering wheel, right elevon steering wheel, brushless motor and the brushless motor governor being connected with described brushless motor in described wing; The electronic unmanned plane of the present embodiment also comprises photoelectrical coupler, and described photoelectrical coupler comprises the first photoelectric coupling structure, the second photoelectric coupling structure and the 3rd photoelectric coupling structure.
Described the first photoelectric coupling structure comprises the first infrarede emitting diode being arranged on fuselage and is arranged on the first infrared photodiode on wing, the input end of described the first infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the first infrared photodiode; The mouth of described the first infrared photodiode connects described left elevon steering wheel, sends to described left elevon steering wheel for described infrared light pulse being converted to electric pulse.
Described the second photoelectric coupling structure comprises the second infrarede emitting diode being arranged on fuselage and is arranged on the second infrared photodiode on wing, the input end of described the second infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the second infrared photodiode; The mouth of described the second infrared photodiode connects right elevon steering wheel, sends to described right elevon steering wheel for described infrared light pulse being converted to electric pulse.
Described the 3rd photoelectric coupling structure comprises the 3rd infrarede emitting diode being arranged on fuselage and is arranged on the 3rd infrared photodiode on wing, the input end of described the 3rd infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the 3rd infrared photodiode; The mouth of described the 3rd infrared photodiode connects described brushless motor governor, sends to described brushless motor governor for described infrared light pulse being converted to electric pulse.
Preferably, on the described wing of the present embodiment, be also provided with the first aerotron, the second aerotron and the 3rd aerotron that are connected with the mouth of the 3rd infrared photodiode with described the first infrared photodiode, the second infrared photodiode respectively, the mouth of described the first aerotron, the second aerotron and the 3rd aerotron is connected respectively described left elevon steering wheel, right elevon steering wheel and described brushless motor governor.Described aerotron all, for after the electric pulse of described infrared photodiode conversion is amplified, is delivered to left and right elevon steering wheel and described brushless motor governor, realizes the control of electronic unmanned plane.
Meanwhile, in the present embodiment, described fuselage interior is also provided with flying power battery pack, and described wing is provided with the conducting bolt for fixing described wing and fuselage, and described conducting bolt is electrically connected with described flying power battery pack.By original wing bolt of rear end plate is redesigned, carry out the transmission of power supply taking conducting bolt as conducting medium, making has not had connector completely between fuselage and wing, when user's assembling aircraft, simply, to only buckling wing, the conducting bolt of screwing on, has just completed the assembling of aircraft.
The PMW pulse-width control signal of flight-control computer output, controls actuating unit as the rotating speed of the angle of steering wheel, motor with the width of pulse, reaches the object of controlling flight.PMW pulse-width control signal drives respectively three infrarede emitting diodes, at this moment the electric pulse of control signal just changes light pulse into, in the time that the optical pulse irradiation from fuselage arrives infrared photodiode, again light pulse is changed into faint electric pulse, after signal being amplified at aerotron, deliver to corresponding actuating unit respectively, realize the control to electronic unmanned plane.In other embodiment, the number of photoelectric coupling structure can be set according to the pulse control signal of flight-control computer, the variation of this number is all disclosed by the utility model, in the scope of the utility model protection.
In the time that other embodiment relate to more multi-path light electric signal transmission, combiner can be set on wing, the input end of combiner connects infrared photosensitive diode or triode, combiner mouth connects left elevon steering wheel, right elevon steering wheel and/or brushless motor governor equal controller, after multi-path signal is combined into a road signal, transmit, transmitting procedure is convenient accurately.
Electronic unmanned plane of the present utility model carries out the transmission of control signal between fuselage and wing by optical coupling structure, compared with existing connector associated mode, connect up more easy, conveniently carries out interior of aircraft layout; There is no connector, electronic unmanned plane weight alleviates to some extent, convenient on working service simultaneously; In addition, the connector contact oxidation of having stopped electronic unmanned plane of the present utility model causes the risk of bad contact, does not need in the use to go specially the plug-in unit of pegging graft, and whole fitting process one step completes, improve the development rate of electronic unmanned plane, be highly suitable for and need emergent occasion of taking off to use; Light coupled device can also effectively be blocked the interference between the each parts of aircraft simultaneously, makes the electromagnetic compatibility of aircraft better.
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 amendment of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (7)
1. the electronic unmanned plane based on photoelectrical coupler, is characterized in that: comprise fuselage and the wing combined, described fuselage interior is provided with flight-control computer, is provided with flight attitude control system in described wing; Also comprise photoelectrical coupler, described photoelectrical coupler comprises optical signal sending end and optical signal receiving end, described optical signal sending end is arranged on fuselage, and be connected with described flight-control computer, described optical signal sending end comprises the instruction for receiving described flight-control computer and produces the infrarede emitting diode of infrared light pulse; Described optical signal receiving end is arranged on wing, and be connected with described flight attitude control system, described optical signal receiving end comprises for receiving described infrared light pulse, and described infrared light pulse is converted into electric signal and sends to the infrared photodiode of described flight attitude control system.
2. electronic unmanned plane according to claim 1, is characterized in that: described photoelectrical coupler also comprises the combiner being arranged on wing, described optical signal receiving end connects described flight attitude control system by described combiner.
3. electronic unmanned plane according to claim 1, it is characterized in that: described optical signal receiving end also comprises the aerotron for amplifying described electric signal, described aerotron input end connects described infrared photodiode, and described aerotron mouth connects described flight attitude control system.
4. electronic unmanned plane according to claim 1, is characterized in that: described flight attitude control system comprises the left elevon steering wheel being arranged in wing, right elevon steering wheel and/or brushless motor governor.
5. electronic unmanned plane according to claim 4, it is characterized in that: described photoelectrical coupler comprises the first photoelectric coupling structure, the second photoelectric coupling structure and the 3rd photoelectric coupling structure, described the first photoelectric coupling structure comprises the first infrarede emitting diode, the first infrared photodiode and the first aerotron, the input end of described the first infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the first infrared photodiode; The mouth of described the first infrared photodiode connects described the first aerotron, sends to described the first aerotron for described infrared light pulse being converted to electric pulse; Described the first aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described left elevon steering wheel;
Described the second photoelectric coupling structure comprises the second infrarede emitting diode, the second infrared photodiode and the second aerotron, the input end of described the second infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the second infrared photodiode; The mouth of described the second infrared photodiode connects described two aerotrons, sends to described the second aerotron for described infrared light pulse being converted to electric pulse; Described the second aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described right elevon steering wheel;
Described the 3rd photoelectric coupling structure comprises the 3rd infrarede emitting diode, the 3rd infrared photodiode and the 3rd aerotron, the input end of described the 3rd infrarede emitting diode connects described flight-control computer, for generation of infrared light pulse and be irradiated to described the 3rd infrared photodiode; The mouth of described the 3rd infrared photodiode connects described the 3rd aerotron, sends to described the 3rd aerotron for described infrared light pulse being converted to electric pulse; Described the 3rd aerotron is used for amplifying described electric pulse, and the electric pulse after amplifying is sent to described brushless motor governor.
6. electronic unmanned plane according to claim 5, it is characterized in that: described photoelectrical coupler also comprises the combiner being arranged on wing, described combiner input end connects respectively described the first aerotron, the second aerotron and the 3rd aerotron, and described combiner mouth connects respectively described left elevon steering wheel, right elevon steering wheel and/or described brushless motor governor.
7. according to the arbitrary described electronic unmanned plane of claim 1～6, it is characterized in that: described fuselage interior is also provided with flying power battery pack, described wing is provided with the conducting bolt for fixing described wing and fuselage, and described conducting bolt is electrically connected with described flying power battery pack.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420230287.2U CN203958609U (en) | 2014-05-07 | 2014-05-07 | A kind of electronic unmanned plane based on photoelectrical coupler |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420230287.2U CN203958609U (en) | 2014-05-07 | 2014-05-07 | A kind of electronic unmanned plane based on photoelectrical coupler |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105553603A (en) * | 2015-12-25 | 2016-05-04 | 北京中飞艾维航空科技有限公司 | Anti-electromagnetic interference unmanned aerial vehicle and inspection method thereof |
| CN107635872A (en) * | 2015-06-01 | 2018-01-26 | 深圳市大疆创新科技有限公司 | Brushless pump electric system |
| CN109754548A (en) * | 2018-12-24 | 2019-05-14 | 天津航天中为数据系统科技有限公司 | A kind of unmanned plane locator tracing system with removable acousto-optic cigarette alarm |
| CN111152933A (en) * | 2019-12-31 | 2020-05-15 | 洛阳安怀达智能科技有限公司 | Electromagnetic compatibility design method for steering engine control driving system of unmanned aerial vehicle |
-
2014
- 2014-05-07 CN CN201420230287.2U patent/CN203958609U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107635872A (en) * | 2015-06-01 | 2018-01-26 | 深圳市大疆创新科技有限公司 | Brushless pump electric system |
| CN105553603A (en) * | 2015-12-25 | 2016-05-04 | 北京中飞艾维航空科技有限公司 | Anti-electromagnetic interference unmanned aerial vehicle and inspection method thereof |
| CN109754548A (en) * | 2018-12-24 | 2019-05-14 | 天津航天中为数据系统科技有限公司 | A kind of unmanned plane locator tracing system with removable acousto-optic cigarette alarm |
| CN111152933A (en) * | 2019-12-31 | 2020-05-15 | 洛阳安怀达智能科技有限公司 | Electromagnetic compatibility design method for steering engine control driving system of unmanned aerial vehicle |
| CN111152933B (en) * | 2019-12-31 | 2021-03-16 | 洛阳安怀达智能科技有限公司 | Electromagnetic compatibility design method for steering engine control driving system of unmanned aerial vehicle |
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Granted publication date: 20141126 |