CN109000904A - Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment - Google Patents
Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment Download PDFInfo
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- CN109000904A CN109000904A CN201810558360.1A CN201810558360A CN109000904A CN 109000904 A CN109000904 A CN 109000904A CN 201810558360 A CN201810558360 A CN 201810558360A CN 109000904 A CN109000904 A CN 109000904A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment of the present invention, including equipping ontology, wind direction regulating device, sand guiding device, vibration measurement with laser device and sand circulator, the present invention emits laser beam by laser doppler vialog, via laser guide pipe the first reflective mirror of directive, utilize the second reflective mirror of principle of reflection horizontal sheaf of light, the laser beam of second reflective mirror is via ellipticity thin-walled mirror reflection directive composite material blade point position, the whole scan to composite material blade measuring point is realized by ellipse of revolution shape thin-walled reflective mirror, air-flow size and Orientation is controlled by the flow and flow valve and flabellum of driving motor control excited frequency control sand, realize measurement of the present invention under wind sand environment to the multiple measuring points of composite material blade, acquisition satisfaction works compound under wind sand environment Material blade avoids causing multi-rotor unmanned aerial vehicle can not work normally because of composite material blade destruction, damage, or even leading to safety accident.
Description
Technical field
The invention belongs to the vibration of rotor wing unmanned aerial vehicle composite material blade and reliability test technical fields, and in particular to dust storm
Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under environment.
Background technique
Multi-rotor unmanned aerial vehicle has the characteristics that technically simple, low in cost, design is strong with using flexible, in every profession and trade
Utilization all the most extensively.With the gradually progress of research and development, rotor blade, the important composition portion as multi-rotor unmanned aerial vehicle
Point, there are more strict requirements for its weight and load capacity.The specific strength of bonded composite and its structure is high, compares
Modulus is high, material has many advantages, such as that designability, thermal stability are good, but also has bearing capacity big, light-weight, by composite material
It has been inexorable trend applied to rotor blade.Consider the complex work environment of unmanned plane work, especially wind sand environment is to nobody
Machine composite rotor blade is affected, and easily causes abrasion, damage, influences flight safety, safety accident is even led to when serious.
Therefore, studying the vibration characteristics of composite rotor blade and integrity problem under wind sand environment has important engineering significance.
There are some technical solutions for the experimental study for meeting material blade at present, Chinese patent CN105092191A is introduced
A kind of forced resonance realizes the system and method for blade fatigue test；CN102507275A has invented a kind of suitable for helicopter
The molding helicopter composite material paddle fatigue test piece moulding technique of composite material blade fatigue test piece.
CN105447316B is related to a kind of method for predicting the structure fatigue life of composite material blade containing initial imperfection.In general, also
Do not have it is a kind of for simulating the composite material blade experimental study device and method of practical Service Environment, for composite rotor
Experimental study of the blade under complex environment is still in starting state, it is necessary to research and develop relevant vibration and reliability test dress
It is standby.
Summary of the invention
To achieve the goals above, the present invention adopts the following technical scheme:
Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment, including equipment ontology, wind direction are adjusted
Device, sand guiding device, vibration measurement with laser device and sand circulator, the equipment chamber body middle part are provided with Laser Measuring
Vibrating device, the equipment ontology bottom base plate are provided with the sand circulator positioned at vibration measurement with laser device left end, the equipment
Bodies top is provided with laser doppler vialog, and the equipment bodies top is provided with positioned at laser doppler vialog left end
Wind direction regulating device, the equipment bodies top is provided with the sand guiding device positioned at wind direction regulating device left end, described
Equipment ontology left end side wall is provided with wind direction regulating device, and the equipment ontology right end sidewalls are provided with air outlet.
The vibration measurement with laser device includes support frame, and the top plate bottom of support frame as described above is equipped with servo motor, the branch
Light control turntable is provided at the top of support top plate, the light control is provided with slip ring electrical feedthrough in the middle part of turntable inner cavity, and sliding
It is connected in the middle part of ring electrical feedthrough with servo motor output shaft, the slip ring electrical feedthrough top is provided with the first reflective mirror, and described first
For reflective mirror mirror surface horizontal by 45 °, first reflective mirror middle and lower part side wall is provided with mounting plate, and the mounting plate end is set
It is equipped with reflective mirror micromatic setting, the composite material paddle being provided at the top of light control turntable at the top of first reflective mirror
Leaf, the composite material blade top are provided with foil gauge, and the slip ring electrical feedthrough and foil gauge form strain measurement module, institute
It states composite material blade top middle portion and is provided with laser guide pipe, laser guide tube top portion is provided with laser doppler vibration measuring
Instrument, the laser doppler vialog, laser guide pipe, the first reflective mirror and reflective mirror micromatic setting constitute vibration measurement with laser mould
Block.
The reflective mirror micromatic setting includes turntable, and it is reflective to be symmetrically installed with ellipticity thin-walled at the top of the turntable
Mirror, the turntable top middle portion are provided with bracket, and the bracket center bottom is provided with turntable driving motor, the bracket
Top is equipped with the second reflective mirror.
The sand circulator includes driving motor and exciting rod, and thick connecting rod and thin is equipped between two exciting rods
It is provided with complex excitation face at the top of connecting rod, the thick connecting rod and exciting rod, right end is provided with long thin connecting rod in the exciting rod, and
Long thin connecting rod extension end outer wall is provided with torsional spring, and the thin connecting rod extension end outer wall of length is provided with the first mounting base, and in torsional spring
In the first installation block hole, the driving motor output shaft outer wall is equipped with pendulum, the two pendulum lateral wall driving electricity
Second mounting base is installed on machine output shaft.
The wind direction regulating device includes flabellum, stepper motor and air inlet, is uniformly pacified between the air inlet inner sidewall
Equipped with flabellum, the air inlet lateral wall is equipped with stepper motor, and stepper motor axis and flabellum are horizontally disposed, the air inlet
The flow valve being provided at the top of mouthful right above stepper motor.
The sand guiding device includes sand inlet, and the sand inlet bottom is provided with double-layer grating plate.
The equipment ontology bottom plate is made of horizontal component and sloping portion.
The test method of rotor wing unmanned aerial vehicle composite material blade reliability test under wind sand environment, using wind sand environment backspin
Wing unmanned plane composite material blade reliability test equipment, includes the following steps,
Step 1, composite material blade is mounted on the first reflective mirror top, powered on, it is ensured that composite material blade is just
Often operating, detects whether each component shows normally, is debugged and corrected；
Step 2, trial test is carried out, servo motor is started, is carried out composite material blade blank experiment 30 minutes, is watched with eliminating
Take influence of the motor Thermal Error to test；
Step 3, foil gauge is accurately affixed on composite material blade, and is drawn conducting wire by slip ring electrical feedthrough；
Step 4, laser doppler vialog is adjusted, the laser beam for emitting laser doppler vialog is via laser conduction
Vertical the first reflective mirror of directive is managed, the laser beam horizontal sheaf second being located on the first reflective mirror mirror surface is made using light reflection principle
Reflective mirror, since the second reflective mirror is located at the spatial focal point position of ellipticity thin-walled reflective mirror, due to being projected via a focus
Laser beam, that is, being located at the laser beam on the second reflective mirror mirror surface, via ellipticity thin-walled mirror reflection directive to be located at second burnt
The composite material blade point position of point；
Step 5, start turntable driving motor, ellipse of revolution shape thin-walled reflective mirror realizes the scanning of a measuring point；Lead to again
It is whole along composite material blade radial position to cross adjustment turntable, realizes the whole scan of composite material blade, realization is to compound
The whole scan of material blade measuring point；
Step 6, sand is placed, while starting driving motor and carrying out the supply of wind-force, realizes wind sand environment simulation；
Step 7, it is again started up the servo motor of composite material blade, carries out formal test；
Step 8, change the point position of composite material blade, repeat step 4-6, realize multiple vibrations on composite material blade
The test of point.
The invention has the advantages that:
The present invention emits laser beam by the laser doppler vialog at the top of device noumenon, and laser beam is via laser guide
The first reflective mirror of pipe directive keeps the laser beam horizontal sheaf second being located on the first reflective mirror mirror surface anti-using the principle of reflection of light
Light microscopic, since the second reflective mirror is located at the spatial focal point position of ellipticity thin-walled reflective mirror, on the second reflective mirror mirror surface
Laser beam is located at the composite material blade point position of the second focus via ellipticity thin-walled mirror reflection directive again, and
By the effect of turntable driving motor, ellipse of revolution shape thin-walled reflective mirror realizes the scanning of a measuring point；Again by adjusting rotation
Turntable is whole to realize the whole scan of composite material blade along composite material blade radial position, realizes to composite material blade
The whole scan of measuring point；Excited frequency is controlled by the revolving speed of the driving motor in control sand circulator, and then is controlled husky
The flow of subcycle controls air-flow size by the flow valve on wind direction regulating device, and the direction of air-flow is controlled by flabellum, real
Under wind sand environment, measurement and observation to the multiple measuring points of composite material blade obtain and meet in dust storm ring existing apparatus of the present invention
The composite material blade to work under border avoids causing multi-rotor unmanned aerial vehicle can not normal work because of composite material blade destruction, damage
Make, or even leads to safety accident.
Detailed description of the invention
Rotor wing unmanned aerial vehicle composite material blade reliability test equipment configuration schematic diagram under Fig. 1 wind sand environment of the present invention；
Fig. 2 is that rotor wing unmanned aerial vehicle composite material blade reliability test equips internal structure signal under wind sand environment of the present invention
Figure；
Fig. 3 is rotor wing unmanned aerial vehicle composite material blade reliability test equipment configuration top view under wind sand environment of the present invention；
Fig. 4 is vibration measurement with laser apparatus structure schematic diagram of the present invention；
Fig. 5 is reflective mirror micromatic setting structural schematic diagram of the present invention；
Fig. 6 is sand circulator structural schematic diagram of the present invention；
Fig. 7 is wind direction regulating device structural schematic diagram of the present invention；
1- equips ontology, 2- vibration measurement with laser device, 3- sand circulator, 4- laser doppler vialog, 5- wind direction tune
Regulating device, 6- sand guiding device, 7- air outlet, 8- support frame, 9- servo motor, 10- light control turntable, and 11- slip ring draws
Electric appliance, the first reflective mirror of 12-, 13- mounting plate, 14- reflective mirror micromatic setting, 15- composite material blade, 16- foil gauge, 17-
Laser guide pipe, 18- turntable, 19- ellipticity thin-walled reflective mirror, 20- bracket, 21- turntable driving motor, 22- second are anti-
Light microscopic, 23- driving motor, 24- exciting rod, the thick connecting rod of 25-, the thin connecting rod of 26-, 27- complex excitation face, the thin connecting rod of 28- long, 29-
Torsional spring, the first mounting base of 30-, 31- pendulum, the second mounting base of 32-, 33- flabellum, 34- stepper motor, 35- air inlet, 36- stream
Measure valve, 37- sand inlet, 38- double-layer grating plate.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.
As shown in Figure 1-3, rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment, including equipment is originally
Body 1, wind direction regulating device 5, sand guiding device 6, vibration measurement with laser device 2 and sand circulator 3, in the equipment ontology 1
It is provided with vibration measurement with laser device 2 in the middle part of chamber, equipment 1 bottom base plate of ontology is provided with positioned at 2 left end of vibration measurement with laser device
Sand circulator 3 is provided with laser doppler vialog 4 at the top of the equipment ontology 1, is arranged at the top of the equipment ontology 1
There is the wind direction regulating device 5 positioned at 4 left end of laser doppler vialog, is provided at the top of the equipment ontology 1 positioned at wind direction tune
The sand guiding device 6 of 5 left end of regulating device, the 1 left end side wall of equipment ontology are provided with wind direction regulating device 5, the equipment
1 right end sidewalls of ontology are provided with air outlet 7.
As shown in figure 4, the vibration measurement with laser device 2 includes support frame 8, the top plate bottom of support frame as described above 8, which is equipped with, to be watched
Motor 9 is taken, light control turntable 10 is provided at the top of 8 top plate of support frame as described above, the light control is set in the middle part of 10 inner cavity of turntable
It is equipped with slip ring electrical feedthrough 11, and 11 middle part of slip ring electrical feedthrough is connected with 9 output shaft of servo motor, 11 top of slip ring electrical feedthrough
It is provided with the first reflective mirror 12,12 mirror surface of the first reflective mirror is horizontal by 45 °, the 12 middle and lower part side of the first reflective mirror
Wall is provided with mounting plate 13, and 13 end of mounting plate is provided with reflective mirror micromatic setting 14,12 top of the first reflective mirror
It is provided with the composite material blade 15 through 10 top of light control turntable, is provided with strain at the top of the composite material blade 15
Piece 16, the slip ring electrical feedthrough 11 and foil gauge 16 form strain measurement module, and 15 top middle portion of composite material blade is set
It is equipped with laser guide pipe 17, laser doppler vialog 4 is provided at the top of the laser guide pipe 17, the laser doppler is surveyed
Vibration Meter 4, laser guide pipe 17, the first reflective mirror 12 and reflective mirror micromatic setting 14 constitute vibration measurement with laser module.
As shown in figure 5, the reflective mirror micromatic setting 14 includes turntable 18, it is symmetrically installed at the top of the turntable 18
Ellipticity thin-walled reflective mirror 19,18 top middle portion of turntable are provided with bracket 20, and 20 center bottom of bracket is provided with
Turntable driving motor 21,20 top of bracket are equipped with the second reflective mirror 22.
As shown in fig. 6, the sand circulator 3 include driving motor 23 and exciting rod 24, two exciting rods 24 it
Between thick connecting rod 25 and thin connecting rod 26 are installed, be provided with complex excitation face 27 at the top of the thick connecting rod 25 and exciting rod 24, it is compound
The face 27 that impulses is set as the surface with elastomer, is conducive to raising for sand, and right end is provided with long thin in the exciting rod 24
Connecting rod 28, the thin 28 extension end outer wall of connecting rod of length are provided with torsional spring 29, and the thin 28 extension end outer wall of connecting rod of length is provided with
One mounting base 30, and torsional spring 29 is embedded in 30 through-hole of the first mounting base, the 23 output shaft outer wall of driving motor is equipped with pendulum
It hammers 31 into shape, the second mounting base 32 is installed on two 31 lateral wall driving motor of pendulum, 23 output shafts, when the sand of release is along tiltedly
When face is rolled back on complex excitation face 27, excitation of the sand by exciting rod 24 and complex excitation face 27, so that sand raises, and
Continue to act on composite material blade 15 under wind action, realizes the circulation-supplied of sand.Meanwhile it can be driven by control
The revolving speed of motor 23 controls excited frequency, finally to control the flow of sand circulation.
As shown in fig. 7, the wind direction regulating device 5 includes flabellum 33, stepper motor 34 and air inlet 35, the air inlet
Flabellum 33 is uniformly installed between 35 inner sidewalls, the direction of air-flow, the air inlet 35 are controlled by the reciprocally swinging of flabellum 33
Lateral wall is equipped with stepper motor 34, and 34 axis of stepper motor and flabellum 33 are horizontally disposed, are arranged at the top of the air inlet 35
There is the flow valve 36 being located at right above stepper motor 34, flow valve 36 is used to control the size of input air-flow, adjusts by wind direction
Device 5 realizes the multi-faceted wind direction simulation of multi-angle.
The sand guiding device 6 includes sand inlet 37, and 37 bottom of sand inlet is provided with double-layer grating plate 38, passes through
The position for adjusting double-layer grating plate 38, discharges sand by certain flow, and cooperation wind direction regulating device 5 realizes the mould of wind sand environment
It is quasi-.
1 bottom plate of equipment ontology is made of horizontal component and sloping portion, is conducive to the sand of release along rake
Divide and return to 27 top of complex excitation face, to be recycled.
The test method of rotor wing unmanned aerial vehicle composite material blade reliability test under wind sand environment, using wind sand environment backspin
Wing unmanned plane composite material blade reliability test equipment, includes the following steps,
Step 1, composite material blade 15 is mounted on 12 top of the first reflective mirror, powered on, it is ensured that composite material paddle
Leaf 15 runs well, and detects whether each component shows normally, is debugged and corrected；
Step 2, trial test is carried out, servo motor 9 is started, is carried out 15 blank experiment of composite material blade 30 minutes, to disappear
Influence except 9 Thermal Error of servo motor to test；
Step 3, foil gauge 16 is accurately affixed on composite material blade 15, and is drawn conducting wire by slip ring electrical feedthrough 11
Out；
Step 4, laser doppler vialog 4 is adjusted, the laser beam for emitting laser doppler vialog 4 is led via laser
To vertical the first reflective mirror of directive 12 of pipe 17, keep the laser beam being located on 12 mirror surface of the first reflective mirror horizontal using light reflection principle
The second reflective mirror of directive 22, since the second reflective mirror 22 is located at the spatial focal point position of ellipticity thin-walled reflective mirror 19, due to warp
The laser beam projected by a focus is located at the laser beam on 22 mirror surface of the second reflective mirror via ellipticity thin-walled reflective mirror 19
Reflection directive is located at 15 point position of composite material blade of the second focus；
Step 5, start turntable driving motor 21, ellipse of revolution shape thin-walled reflective mirror 19 realizes the scanning of a measuring point；
The whole scan of composite material blade 15 is realized along 15 radial position of composite material blade again by adjusting turntable 18 is whole,
Realize the whole scan of 15 respective point of composite material blade；
Step 6, sand is placed, while starting driving motor 23 and carrying out the supply of wind-force, realizes wind sand environment mould
It is quasi-.
Step 7, it is again started up the servo motor 9 of composite material blade 15, carries out formal test；
Step 8, change the point position of composite material blade 15, repeat step 4-6, realize more on composite material blade 15
The test of a vibration point.
Claims (8)
1. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment, which is characterized in that including equipping ontology,
Wind direction regulating device, sand guiding device, vibration measurement with laser device and sand circulator, equipment chamber body middle part setting
There is vibration measurement with laser device, the equipment ontology bottom base plate is provided with the sand circulator positioned at vibration measurement with laser device left end,
The equipment bodies top is provided with laser doppler vialog, and the equipment bodies top is provided with to be surveyed positioned at laser doppler
The wind direction regulating device of Vibration Meter left end, the equipment bodies top are provided with the sand guiding dress positioned at wind direction regulating device left end
It sets, equipment ontology left end side wall is provided with wind direction regulating device, and the equipment ontology right end sidewalls are provided with air outlet.
2. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 1, special
Sign is: the vibration measurement with laser device includes support frame, and the top plate bottom of support frame as described above is equipped with servo motor, the support
Light control turntable is provided at the top of frame top plate, the light control is provided with slip ring electrical feedthrough, and slip ring in the middle part of turntable inner cavity
It is connected in the middle part of electrical feedthrough with servo motor output shaft, the first reflective mirror is provided at the top of the slip ring electrical feedthrough, described first is anti-
For light microscopic mirror surface horizontal by 45 °, first reflective mirror middle and lower part side wall is provided with mounting plate, the mounting plate end setting
There is reflective mirror micromatic setting, the composite material blade being provided at the top of first reflective mirror at the top of light control turntable,
Foil gauge is provided at the top of the composite material blade, the slip ring electrical feedthrough and foil gauge form strain measurement module, described
Composite material blade top middle portion is provided with laser guide pipe, and laser guide tube top portion is provided with laser doppler vibration measuring
Instrument, the laser doppler vialog, laser guide pipe, the first reflective mirror and reflective mirror micromatic setting constitute vibration measurement with laser mould
Block.
3. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 2, special
Sign is: the reflective mirror micromatic setting includes pedestal, is symmetrically installed with ellipticity thin-walled reflective mirror at the top of the pedestal, described
It is provided with turntable bracket in the middle part of Chuck top, the turntable bracket center bottom is provided with turntable driving motor, described
Turntable cantilever tip is equipped with the second reflective mirror.
4. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 1, special
Sign is: the sand circulator includes driving motor and exciting rod, and thick connecting rod and thin is equipped between two exciting rods
It is provided with complex excitation face at the top of connecting rod, the thick connecting rod and exciting rod, right end is provided with long thin connecting rod in the exciting rod, and
Long thin connecting rod extension end outer wall is provided with torsional spring, and the thin connecting rod extension end outer wall of length is provided with the first mounting base, and in torsional spring
In the first installation block hole, the driving motor output shaft outer wall is equipped with pendulum, the two pendulum lateral wall driving electricity
Second mounting base is installed on machine output shaft.
5. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 1, special
Sign is: the wind direction regulating device includes flabellum, stepper motor and air inlet, is uniformly installed between the air inlet inner sidewall
There is flabellum, the air inlet lateral wall is equipped with stepper motor, and stepper motor axis and flabellum are horizontally disposed, the air inlet
Top is provided with the flow valve right above stepper motor.
6. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 1, special
Sign is: the sand guiding device includes sand inlet, and the sand inlet bottom is provided with double-layer grating plate.
7. rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment according to claim 1, special
Sign is: the equipment ontology bottom plate is made of horizontal component and sloping portion.
8. the test method of rotor wing unmanned aerial vehicle composite material blade reliability test under wind sand environment, using described in claim 1
Wind sand environment under rotor wing unmanned aerial vehicle composite material blade reliability test equip, it is characterised in that: include the following steps,
Step 1, composite material blade is mounted on the first reflective mirror top, powered on, it is ensured that composite material blade is normally transported
Turn, detects whether each component shows normally, debugged and corrected；
Step 2, trial test is carried out, servo motor is started, is carried out composite material blade blank experiment 30 minutes, to eliminate servo electricity
Influence of the machine Thermal Error to test；
Step 3, foil gauge is accurately affixed on composite material blade, and is drawn conducting wire by slip ring electrical feedthrough；
Step 4, laser doppler vialog is adjusted, the laser beam for emitting laser doppler vialog hangs down via laser contact tube
Direct projection keeps the laser beam horizontal sheaf second being located on the first reflective mirror mirror surface reflective to the first reflective mirror, using light reflection principle
Mirror, since the second reflective mirror is located at the spatial focal point position of ellipticity thin-walled reflective mirror, since that projects via a focus swashs
Light beam, that is, the laser beam being located on the second reflective mirror mirror surface are located at the second focus via ellipticity thin-walled mirror reflection directive
Composite material blade point position；
Step 5, start turntable driving motor, ellipse of revolution shape thin-walled reflective mirror realizes the scanning of a measuring point；Pass through tune again
Whole turntable is whole to realize the whole scan of composite material blade along composite material blade radial position, realizes to composite material
The whole scan of blade measuring point；
Step 6, sand is placed, while starting driving motor and carrying out the supply of wind-force, realizes wind sand environment simulation；
Step 7, it is again started up the servo motor of composite material blade, carries out formal test；
Step 8, change the point position of composite material blade, repeat step 4-6, realize multiple vibration points on composite material blade
Test.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810558360.1A CN109000904B (en) | 2018-06-01 | 2018-06-01 | Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment |
| PCT/CN2018/096959 WO2019227639A1 (en) | 2018-06-01 | 2018-07-25 | Reliability testing device for composite material propeller blade of rotor unmanned aerial vehicle in windy and sandy environments |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810558360.1A CN109000904B (en) | 2018-06-01 | 2018-06-01 | Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment |
Publications (2)
| Publication Number | Publication Date |
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| CN109000904A true CN109000904A (en) | 2018-12-14 |
| CN109000904B CN109000904B (en) | 2019-10-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810558360.1A Expired - Fee Related CN109000904B (en) | 2018-06-01 | 2018-06-01 | Rotor wing unmanned aerial vehicle composite material blade reliability test is equipped under wind sand environment |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109000904B (en) |
| WO (1) | WO2019227639A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335558A (en) * | 2021-05-28 | 2021-09-03 | 合肥飞豪通信科技有限公司 | Remote measurement type small unmanned aerial vehicle wind pressure test system |
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Also Published As
| Publication number | Publication date |
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| WO2019227639A1 (en) | 2019-12-05 |
| CN109000904B (en) | 2019-10-25 |
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