CN206155804U - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
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- CN206155804U CN206155804U CN201621035402.6U CN201621035402U CN206155804U CN 206155804 U CN206155804 U CN 206155804U CN 201621035402 U CN201621035402 U CN 201621035402U CN 206155804 U CN206155804 U CN 206155804U
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- unmanned plane
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Abstract
The utility model relates to an aircraft technical field, in particular to unmanned aerial vehicle. This unmanned aerial vehicle include fuselage, undercarriage, flight control unit and install in the detection device that takes off and land on the undercarriage, take off and land detection device with flight control unit electricity is connected, the detection device that takes off and land is used for detecting unmanned aerial vehicle's liftoff and landing, when unmanned aerial vehicle lands, the detection device that takes off and land is oppressed to open and produces the signal of telecommunication, when unmanned aerial vehicle is liftoff, the detection device that takes off and land resets and closes. This unmanned aerial vehicle can the liftoff or landing of accurate judgement through the detection device that takes off and land.
Description
Technical field
The utility model is related to vehicle technology field, more particularly to a kind of unmanned plane.
Background technology
Unmanned plane (UAV, UAV) is using radio robot and the programed flight control unit provided for oneself
The not manned aircraft for manipulating.From technical standpoint, unmanned plane can be divided into unmanned fixed-wing aircraft, unmanned VTOL machine, nobody fly
Ship, depopulated helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..
At present, unmanned plane is widely used for taking photo by plane, agricultural, plant protection, auto heterodyne, express transportation, disaster relief, observes wild
Animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field, and with
The development and progress of science and technology, the market demand of unmanned plane can be increasing.During the use of unmanned plane, unmanned plane rise
Fly and landing is highly important link, have statistics to show, 80% accident all occurs rising in aircraft in aviation history
Depression of order section.
In the prior art, the landing detection of taking off of unmanned plane is mostly by acceleration transducer, barometer, GPS
The means such as (Global Positioning System, global positioning system), external remote control signal carrying out, for example, in landing
During, flight control units read remote controller signal, when remote control throttle signal less than maximum 20% and unmanned plane is vertical
The close acceleration of gravity of directional acceleration does not stably change, then it is assumed that unmanned plane successfully lands；And in take-off process, then it is sharp
Calculate the relative altitude of unmanned plane with acceleration transducer and barometer, judged by height change unmanned plane whether from
Ground.
Discovery is analyzed by the landing technology to existing unmanned plane, existing unmanned plane is by electronic sensor and calculation
The mode that method is combined judging whether unmanned plane lands or liftoff indirectly, because barometer is vulnerable to air pressure fluctuation, temperature change
Affect, acceleration transducer is vulnerable to vibration influence, and GPS, the signal of remote control are easily interfered, therefore, existing unmanned plane
Easily occur landing or liftoff wrong report.
Utility model content
The utility model provide a kind of unmanned plane, the unmanned plane by landing detection means can accurately judge it is liftoff or
Land.
To reach above-mentioned purpose, the utility model provides technical scheme below：
A kind of unmanned plane, including fuselage, undercarriage and flight control units, also including be installed on the undercarriage rise
Drop detection means, the landing detection means is electrically connected with the flight control units；
The landing detection means is used to detect the liftoff of the unmanned plane and lands, wherein：
During the UAV Landing, the landing detection means is oppressed to open and produces electric signal；
When the unmanned plane is liftoff, the landing detection means resets and closes.
Above-mentioned unmanned plane is provided with the landing detection means for detecting the liftoff of unmanned plane and land on undercarriage, and
And in UAV Landing, landing detection means can pass through the oppressed unlatching of the Action of Gravity Field of undercarriage or unmanned plane and produce electricity
Signal；In UAV Landing, the oppressed unlatching of landing detection means, and reset and close when liftoff, landing detection dress
The driving put by frame for movement realization, is not easily susceptible to the interference of air pressure, temperature, vibrations or signal, detects can landing
Device is accurately opened in UAV Landing, and in the same manner, landing detection means can be closed accurately when unmanned plane is liftoff, and to
The flight control units of landing detection means electrical connection send electric signal.
Therefore, the unmanned plane judges the liftoff of unmanned plane or landing, landing by the opening and closing of landing detection means
The control of detection means is difficult to be disturbed by air pressure, temperature, vibrations or signal, therefore, the unmanned plane passes through landing detection means
Can accurately judge liftoff or land.
Preferably, the landing detection means is microswitch or pressure-detecting device.
The landing detection means of above-mentioned unmanned plane is microswitch or pressure-detecting device, due to microswitch contact between
It is higher away from smaller or pressure-detecting device accuracy of detection, therefore, the remolding sensitivity of microswitch or pressure-detecting device compared with
Height, in UAV Landing, microswitch or pressure-detecting device can be by undercarriage drivings or the gravity compressing of unmanned plane
Accurately open, and when unmanned plane is liftoff, microswitch is closed because losing the driving of undercarriage or the gravity compressing of unmanned plane,
And then enable unmanned plane further to judge exactly to land and liftoff.
Preferably, when the landing detection means is the pressure-detecting device, the pressure-detecting device is fixedly connected
In the lower surface of the undercarriage, and open and produce when the pressure that the pressure-detecting device is detected exceedes setting value
Raw electric signal.
Because pressure-detecting device is fixedly connected on the lower surface of undercarriage, pressure-detecting device is located at undercarriage and ground
Between face, therefore, in UAV Landing, unmanned plane is supported in ground by pressure-detecting device, and pressure-detecting device is in nothing
Pressure signal is deformed and generated under man-machine Action of Gravity Field, and now, the pressure that pressure-detecting device is detected is unmanned plane
Gravity, when the pressure that pressure-detecting device is detected for unmanned plane gravity when, unmanned plane lands, now, unmanned plane
Gravity exceedes the setting value of pressure-detecting device, and pressure-detecting device is opened, and electric signal is sent to into flight control units；When
When unmanned plane is liftoff, pressure-detecting device is because losing the contact with ground, and pressure-detecting device loses the gravity of unmanned plane
Act on and reset, the pressure that pressure-detecting device is detected is less than setting value, pressure-detecting device resets and closes；Due to pressure
Detection means is fixedly connected on the bottom of undercarriage, therefore, pressure-detecting device is easy for installation, design is simple, and then makes nobody
The simple structure of machine.
Preferably, the landing detection means is at least two.
Preferably, when the landing detection means is the microswitch, the undercarriage is described including being fixedly connected on
The housing of fuselage and the support for being rotationally connected with the housing；The microswitch is fixedly connected on the housing；Wherein：
The housing is provided with position limiting structure, and the position limiting structure is used to limit Support Position of the support when landing
Rotate and punctured position when liftoff between；
The support is located at the Support Position in the UAV Landing, for supporting the unmanned plane and in gravity
The effect lower pressing microswitch, so that the microswitch is pressed unlatching；
The support is located at the punctured position when the unmanned plane is liftoff, and away from the microswitch, so that institute
State microswitch to reset and close.
The undercarriage of above-mentioned unmanned plane includes housing and support, and undercarriage is fixedly connected on fuselage by housing, and passes through
Unmanned plane is supported in ground by the support for being rotationally connected with housing, and microswitch is fixedly connected on housing, and support can be in housing
Position limiting structure in rotate, the slewing area of support is limited between Support Position and punctured position by position limiting structure；Nothing
During man-machine landing, under the Action of Gravity Field of unmanned plane, holder pivots drive microswitch to turn on to Support Position,
And then electric signal is produced, to judge that unmanned plane is in landing state；When unmanned plane is liftoff, support loses the work of unmanned plane gravity
With, and punctured position is can be turned to, microswitch is closed because losing the driving of support, and then loses electric signal, to judge nothing
It is man-machine in liftoff state.
During landing or be liftoff, the holder pivots of undercarriage are to corresponding Support Position or contraction for above-mentioned unmanned plane
Position, so that microswitch is turned on and off, and sends electric signal when microswitch is opened to flight control units, by propping up
Frame drives microswitch, therefore, the unmanned plane can accurately judge liftoff or land.
Preferably, the undercarriage also includes being arranged between the housing and the support and being in all the time extended state
Elastic component；
When the unmanned plane is liftoff, the elastic component drives makes the support turn to the receipts from the Support Position
Condense and put.
Due to being provided between housing and support all the time in the elastic component of extended state, therefore, support can be in elasticity
There is all the time the moment of torsion for turning to punctured position in the presence of part, could be in the work of unmanned plane gravity only in UAV Landing
Support is overcome the elastic force of elastic component and is turned to Support Position with, and then drive microswitch to open, therefore, by arranging
Elastic component between housing and support can make support UAV Landing or it is liftoff when respectively be located at corresponding position, make
Microswitch is turned on and off exactly, and then unmanned plane is judged exactly liftoff or is landed.
Preferably, the elastic component is spring.
Preferably, the position limiting structure is the spacing gap for being formed at the housing, and one end of the support rotates connection
The bottom surface of the housing is stretched out through the spacing gap in the housing, the other end.
Preferably, the undercarriage is also fixedly connected on the touching structure of the housing, the touching structure including one end
The other end be located at and between the support and the microswitch and elastic deformation can be produced, the holder pivots are to Support Position
When drive the touching structure to produce elastic deformation, and the microswitch is driven by the touching structure.
Preferably, the touching structure is flexure strip.
Description of the drawings
Fig. 1 is in the structural representation of liftoff state for the unmanned plane that a kind of embodiment of the utility model is provided；
Fig. 2 is in the structural representation of landing state for the unmanned plane that a kind of embodiment of the utility model is provided；
The control principle drawing of the unmanned plane that Fig. 3 is provided for a kind of embodiment of the utility model；
Fig. 4 is in the structural representation of landing state for the unmanned plane that the utility model another kind embodiment is provided；
Fig. 5 is working state schematic representation of the unmanned plane in the undercarriage of liftoff state in Fig. 1；
Fig. 6 is working state schematic representation of the unmanned plane in the undercarriage of landing state in Fig. 1.
Specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment for being obtained, belongs to the scope of the utility model protection.
The utility model embodiment provides a kind of unmanned plane, and the unmanned plane is by undercarriage or the GRAVITY CONTROL of unmanned plane
The unlatching of landing detection means, because the driving of landing detection means is realized by frame for movement, is not easily susceptible to air pressure, temperature
Degree, vibrations or the interference of signal, therefore, the unmanned plane can accurately judge liftoff or land by landing detection means.
Wherein, Fig. 1, Fig. 2 and Fig. 4, the unmanned plane 1 that a kind of embodiment of the utility model is provided, including fuselage be refer to
11st, undercarriage 12 and flight control units 13, also including the landing detection means 14 being installed on undercarriage 12, such as Fig. 4 structures
Shown landing detection means 14 is arranged at the lower surface of undercarriage 12, and the landing detection means shown in Fig. 5 and Fig. 6 structures
14 housings 121 for being arranged at undercarriage 12, landing detection means 14 is electrically connected with flight control units 13, as shown in Fig. 3 structures；
Landing detection means 14 is used to detect the liftoff of unmanned plane 1 and lands, wherein：
When unmanned plane 1 lands, the oppressed unlatching of landing detection means 14 simultaneously produces electric signal；
When unmanned plane 1 is liftoff, landing detection means 14 resets and closes.
Above-mentioned unmanned plane 1 is provided with the landing detection dress for detecting the liftoff of unmanned plane 1 and landing on undercarriage 12
14 are put, the landing detection means 14 as shown in Fig. 4 structures is installed on the bottom of undercarriage 12, and the landing shown in Fig. 5 and Fig. 6 structures
Detection means 14 is installed on the housing 121 of undercarriage 12, and when unmanned plane 1 lands, landing detection means 14 can pass through
Fall to frame 12 or by the oppressed unlatching of the Action of Gravity Field of unmanned plane 1 and producing electric signal；When unmanned plane 1 lands, landing detection dress
14 oppressed unlatchings are put, and are resetted and is closed when liftoff, the driving of landing detection means 14 is realized by frame for movement,
The interference of air pressure, temperature, vibrations or signal is not easily susceptible to, landing detection means 14 can be made accurately to open when unmanned plane 1 lands
Open, in the same manner, landing detection means 14 can be closed accurately when unmanned plane 1 is liftoff, and by being electrically connected with landing detection means 14
The flight control units 13 for connecing send electric signal.
Therefore, the unmanned plane 1 judges the liftoff of unmanned plane 1 or landing by the opening and closing of landing detection means 14,
The control of landing detection means 14 is difficult to be disturbed by air pressure, temperature, vibrations or signal, therefore, the unmanned plane 1 is examined by landing
Surveying device 14 can accurately judge liftoff or land.
In a kind of specific embodiment, landing detection means 14 is microswitch or pressure-detecting device.
The landing detection means 14 of above-mentioned unmanned plane 1 is microswitch or pressure-detecting device, due to touching for microswitch
Dot spacing is smaller or accuracy of detection of pressure-detecting device is higher, therefore, the sensitivity of microswitch or pressure-detecting device
Comparison is high, when unmanned plane 1 lands, microswitch or pressure-detecting device can by undercarriage 12 drive or unmanned plane 1 weight
Power is oppressed and accurately opened, and when unmanned plane 1 is liftoff, microswitch is because losing the driving of undercarriage 12 or the weight of unmanned plane 1
The compressing of power and close, and then enable unmanned plane 1 further exactly judge land and it is liftoff.
According to the difference and the difference of the structure of undercarriage 12 of landing detection means 14, above-mentioned unmanned plane 1 has following two
Embodiment：
Mode one, as shown in Fig. 4 structures, when landing detection means 14 is pressure-detecting device, pressure-detecting device is fixed
The lower surface of undercarriage 12 is connected to, and is opened and is produced when the pressure that pressure-detecting device is detected exceedes setting value
Electric signal.
Because pressure-detecting device is fixedly connected on the lower surface of undercarriage 12, therefore, pressure-detecting device is located at
Fall between frame 12 and ground G, when unmanned plane 1 lands, unmanned plane 1 is supported in ground G, pressure detecting by pressure-detecting device
Device is deformed and generates pressure signal under the Action of Gravity Field of unmanned plane 1, now, the pressure that pressure-detecting device is detected
For the gravity of unmanned plane 1, when gravity of the pressure that pressure-detecting device is detected for unmanned plane, unmanned plane 1 lands, now,
The gravity of unmanned plane 1 exceedes the setting value of pressure-detecting device, and pressure-detecting device is opened, and the electric signal of generation is sent to
Flight control units 13；When unmanned plane 1 is liftoff, pressure-detecting device is because losing the contact with ground G, and pressure-detecting device
Lose the effect of the gravity of unmanned plane 1 and reset, the pressure that pressure-detecting device is detected is less than setting value, pressure-detecting device
Reset and close；Because pressure-detecting device is fixedly connected on the bottom of undercarriage 12, therefore, pressure-detecting device installation side
Just, design simple, and then make the simple structure of unmanned plane 1.
On the basis of aforesaid way one, landing detection means 14 can be at least two, nobody as shown in Fig. 4 structures
Machine 1 is provided with two pressure-detecting devices, it is also possible to as the case may be, or in order to improve the accurate of pressure-detecting device test
Property, it is also possible in the lower surface of undercarriage 12, multiple pressure-detecting devices are set, further improving unmanned plane 1 to liftoff or
The accurate judgement landed.
Mode two, as shown in Figure 1, Figure 2, shown in Fig. 5 or Fig. 6 structures, when landing detection means 14 is microswitch, undercarriage 12
Including being fixedly connected on the housing 121 of fuselage 11 and being rotationally connected with the support 122 of housing 121, as shown in Fig. 5 and Fig. 6 structures,
One end of support 122 is rotationally connected with housing 121 by rotating shaft 124, enable the other end of support 122 around the shaft 124 axle
Heart O is rotated；Microswitch is fixedly connected on housing 121；Wherein：
Housing 121 is provided with position limiting structure, and position limiting structure is used for Support Position of the limit bracket 122 when landing and liftoff
When punctured position between rotate, as shown in Fig. 5 and Fig. 6 structures, because housing 121 is provided with position limiting structure, unmanned plane 1 is liftoff
When, when support 122 is in punctured position under the action of the spring, the axial line of support 122 overlaps with center line OB, support 122
When being in Support Position under the Action of Gravity Field of unmanned plane 1, support 122 turns to axial line and overlaps with center line OA along axle center O；
Support 122 is located at Support Position when unmanned plane 1 lands, for supporting unmanned plane 1 and pressing under gravity
Microswitch, so that microswitch is pressed unlatching, as shown in Fig. 6 structures, when unmanned plane 1 lands, support 122 is in unmanned plane 1
Action of Gravity Field under can rotate along axle center O so that support 122 turns to OA positions, i.e. support 122 in Support Position, now,
Support 122 can just directly drive microswitch or the touching structure 125 by being arranged between microswitch and support 122
Microswitch is driven, so that microswitch is pressed opens and produce electric signal；
Support 122 is located at punctured position when unmanned plane 1 is liftoff, and away from microswitch, so that microswitch resets simultaneously
Close, as shown in Fig. 5 structures, now, away from microswitch, microswitch resets and closes support 122, stops to flight control
Unit 13 sends electric signal.
The undercarriage 12 of above-mentioned unmanned plane 1 includes housing 121 and support 122, and undercarriage 12 is fixedly connected by housing 121
In fuselage 11, and unmanned plane 1 is supported in into ground by being rotationally connected with the support 122 of housing 121, microswitch is fixedly connected
In housing 121, support 122 can be rotated in the position limiting structure of housing 121, by position limiting structure by the rotation model of support 122
Enclose and be limited between Support Position and punctured position；When unmanned plane 1 lands, under the Action of Gravity Field of unmanned plane 1,122 turns of support
Move to Support Position, and drive microswitch to turn on, and then produce electric signal, to judge that unmanned plane 1 is in landing shape
State；When unmanned plane 1 is liftoff, support 122 loses the effect of the gravity of unmanned plane 1, and can be turned to punctured position, and microswitch is because losing
Go the driving of support 122 and close, and then lose electric signal, to judge that unmanned plane 1 is in liftoff state.
During landing or be liftoff, the support 122 of undercarriage 12 turns to corresponding Support Position to above-mentioned unmanned plane 1
Or punctured position, so that microswitch is turned on and off, and telecommunications is sent to flight control units 13 when microswitch is opened
Number, microswitch is driven by support 122, therefore, the unmanned plane 1 can accurately judge liftoff or land.
On the basis of aforesaid way two, as shown in Fig. 5 and Fig. 6 structures, undercarriage 12 also includes being arranged at the He of housing 121
Between support 122 and all the time in the elastic component 123 of extended state；
When unmanned plane 1 is liftoff, elastic component 123 drives makes support 122 turn to punctured position from Support Position.
Due to being provided between housing 121 and support 122 all the time in the elastic component 123 of extended state, therefore, support
122 can all the time have the moment of torsion for turning to punctured position in the presence of elastic component 123, only when unmanned plane 1 lands
Support 122 can be made in the presence of the gravity of unmanned plane 1 to overcome the elastic force of elastic component 123 and turn to Support Position, and then driven
Microswitch is opened, therefore, support 122 can be made in nothing by the elastic component 123 being arranged between housing 121 and support 122
Man-machine 1 is located at respectively corresponding position when landing or be liftoff, microswitch is turned on and off exactly, and then makes unmanned plane
1 can exactly judge liftoff or land.
Specifically, as shown in Fig. 5 and Fig. 6 structures, elastic component 123 can be spring, such as：Helical spring, extension spring
Deng.
On the basis of aforesaid way two, as shown in Fig. 5 and Fig. 6 structures, position limiting structure is be formed at housing 121 spacing
Gap 126, one end of support 122 is rotationally connected with the bottom surface that the housing 121, other end stretches out housing 121 through spacing gap.
The slewing area of support 122 is limited by being arranged on the spacing gap 126 of housing 121, makes 122, support
Can rotate in the range of certain angle a, angle a can be 0～5 °, such as 1 °, 2 °, 3 °, 4 °, 5 °.
In order that support 122 can be driven in time to microswitch, and as shown in Fig. 5 and Fig. 6 structures, undercarriage 12
May also include the touching structure 125 that one end is fixedly connected on housing 121, the other end for touching structure 125 is located at support 122 and micro-
Move between switch and elastic deformation can be produced, drive touching structure 125 to produce elastic change when support 122 turns to Support Position
Shape, and drive microswitch by touching structure 125.
Further, above-mentioned touching structure 125 can be flexure strip, by support 122 in the axle center O along rotating shaft 124
Flexure strip is extruded when turning to Support Position, microswitch is controlled by flexure strip and is opened, and when support 122 resets,
Flexure strip sets back automatically, closes microswitch, therefore, it is possible to more accurately control the switch of microswitch, and then
The liftoff of unmanned plane 1 can exactly be judged or landed.
Obviously, those skilled in the art the utility model embodiment can be carried out it is various change and modification without deviating from
Spirit and scope of the present utility model.So, if these modifications of the present utility model and modification belong to the utility model right
Within the scope of requirement and its equivalent technologies, then the utility model is also intended to comprising these changes and modification.
Claims (10)
1. a kind of unmanned plane, including fuselage, undercarriage and flight control units, it is characterised in that also including being installed on described rising
The landing detection means fallen on frame, the landing detection means is electrically connected with the flight control units；
The landing detection means is used to detect the liftoff of the unmanned plane and lands, wherein：
During the UAV Landing, the landing detection means is oppressed to open and produces electric signal；
When the unmanned plane is liftoff, the landing detection means resets and closes.
2. unmanned plane according to claim 1, it is characterised in that the landing detection means is that microswitch or pressure are examined
Survey device.
3. unmanned plane according to claim 2, it is characterised in that the landing detection means is the pressure-detecting device
When, the pressure-detecting device is fixedly connected on the lower surface of the undercarriage, and when pressure-detecting device detection
To pressure exceed setting value when open and produce electric signal.
4. unmanned plane according to claim 3, it is characterised in that the landing detection means is at least two.
5. unmanned plane according to claim 2, it is characterised in that when the landing detection means is the microswitch,
The undercarriage includes being fixedly connected on the housing of the fuselage and is rotationally connected with the support of the housing；The microswitch
It is fixedly connected on the housing；Wherein：
The housing is provided with position limiting structure, the position limiting structure be used to limiting Support Position of the support when landing and from
Rotate between punctured position during ground；
The support is located at the Support Position in the UAV Landing, for supporting the unmanned plane and in Action of Gravity Field
It is lower to press the microswitch, so that the microswitch is pressed unlatching；
The support is located at the punctured position when the unmanned plane is liftoff, and away from the microswitch, so that described micro-
Dynamic switch resets and closes.
6. unmanned plane according to claim 5, it is characterised in that the undercarriage also includes being arranged at the housing and institute
State between support and all the time in the elastic component of extended state；
When the unmanned plane is liftoff, the elastic component drives makes the support turn to the punctured bit from the Support Position
Put.
7. unmanned plane according to claim 6, it is characterised in that the elastic component is spring.
8. unmanned plane according to claim 5, it is characterised in that the position limiting structure is be formed at the housing spacing
Gap, one end of the support is rotationally connected with the bottom that the housing, the other end stretch out the housing through the spacing gap
Face.
9. the unmanned plane according to any one of claim 5-8, it is characterised in that the undercarriage also includes that one end is fixed and connects
The touching structure of the housing is connected to, the other end of the touching structure is located between the support and the microswitch and energy
Elastic deformation is produced, drives the touching structure to produce elastic deformation when the holder pivots are to Support Position, and by described
Touching structure drives the microswitch.
10. unmanned plane according to claim 9, it is characterised in that the touching structure is flexure strip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621035402.6U CN206155804U (en) | 2016-08-31 | 2016-08-31 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621035402.6U CN206155804U (en) | 2016-08-31 | 2016-08-31 | Unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN206155804U true CN206155804U (en) | 2017-05-10 |
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ID=58650407
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| CN201621035402.6U Active CN206155804U (en) | 2016-08-31 | 2016-08-31 | Unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107364584A (en) * | 2017-07-27 | 2017-11-21 | 钱月珍 | Unmanned plane fall protection system |
-
2016
- 2016-08-31 CN CN201621035402.6U patent/CN206155804U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107364584A (en) * | 2017-07-27 | 2017-11-21 | 钱月珍 | Unmanned plane fall protection system |
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