CN209209059U - A kind of unmanned plane power performance test macro - Google Patents
A kind of unmanned plane power performance test macro Download PDFInfo
- Publication number
- CN209209059U CN209209059U CN201821556093.6U CN201821556093U CN209209059U CN 209209059 U CN209209059 U CN 209209059U CN 201821556093 U CN201821556093 U CN 201821556093U CN 209209059 U CN209209059 U CN 209209059U
- Authority
- CN
- China
- Prior art keywords
- pressure sensor
- unmanned plane
- pedestal
- performance test
- power performance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000011056 performance test Methods 0.000 title claims abstract description 18
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 50
- 239000002184 metal Substances 0.000 claims abstract description 24
- 229910052751 metal Inorganic materials 0.000 claims abstract description 24
- 239000000523 sample Substances 0.000 claims abstract description 16
- 229910001220 stainless steel Inorganic materials 0.000 claims abstract description 12
- 239000010935 stainless steel Substances 0.000 claims abstract description 12
- 238000012360 testing method Methods 0.000 claims abstract description 11
- 238000004891 communication Methods 0.000 claims description 15
- 230000005484 gravity Effects 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims 2
- 241001062009 Indigofera Species 0.000 claims 1
- 238000004458 analytical method Methods 0.000 abstract description 2
- 239000011295 pitch Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000011897 real-time detection Methods 0.000 description 5
- 238000005183 dynamical system Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 238000009411 base construction Methods 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Landscapes
- Arrangements For Transmission Of Measured Signals (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The utility model relates to a kind of unmanned plane power performance test macros, belong to unmanned plane dynamic test technical field.The utility model includes cylindrical chassis, pressure sensor bracket, pressure sensor I, stainless steel pipe clamp, multi-rotor unmanned aerial vehicle, motor, conducting wire, unmanned plane power module, temperature speed probe, pedestal, round metal bars, universal tumbler bearing, pressure sensor II, voltage-current sensor module, prill, track.The utility model structure is simple, can be realized and rises or falls, pitches and lift, pulling force and torsion that when roll generates are measured to unmanned plane complete machine, can obtain the test result of each flight parameter simultaneously.By the wireless transport module of the system, the data value for obtaining and recording in real time each sensor in host computer is realized, provide reliable data support for the analysis of unmanned plane power performance.
Description
Technical field
The utility model relates to a kind of unmanned plane power performance test macros, belong to unmanned plane dynamic test technical field.
Background technique
In recent years, unmanned air vehicle technique is quickly grown, and is widely used in military and civilian field.In actual use,
Need to test dynamical system and tested, obtain test parameters and characteristic, verify reliability, prevent may to occur due to
Crash accident caused by dynamical system.
What current equipment mostly measured is that single motor acts on the pulling force and torsion generated when lower propeller works, for
Complete machine flight, such as integral body generates when flexion-extension, roll, raising and lowering pulling force and torsion lack corresponding test dress
It sets.
Summary of the invention
Technical problem to be solved by the utility model is: the utility model provides a kind of unmanned plane power performance test system
System, the equipment can be realized unmanned plane complete machine is risen or fallen, pitch and lift, pulling force and torsion that when roll generates into
Row measurement, can obtain the test result of each flight parameter simultaneously.By the wireless transport module of the system, realize in host computer reality
When obtain and record the data value of each sensor, provide reliable data support for the analysis of unmanned plane power performance.
Technical solutions of the utility model are: a kind of unmanned plane power performance test macro, including cylindrical chassis 1, pressure
Sensor stand 2, pressure sensor I 4, stainless steel pipe clamp 5, multi-rotor unmanned aerial vehicle 6, motor 7, conducting wire 8, unmanned plane power module
9, temperature speed probe 10, pedestal 11, round metal bars 12, universal tumbler bearing 14, pressure sensor II 15, voltage and current sensing
Device module 17, prill 19, track 20；
The pressure sensor bracket 2, wireless communication system 3, pressure sensor II 15 and voltage-current sensor module
17 are fixed on cylindrical chassis 1, and pressure sensor I 4 is bolted on pressure sensor bracket 2, universal tumbler bearing
14 are bolted on pressure sensor II 15, are in multi-directional ball support 14 built in prill 19,11 following table of pedestal
Face is placed on prill 19 by track 20, and round metal bars 12 are welded on 11 two sides of pedestal, and round metal bars 12 are in pedestal 11
It rotates Shi Nengyu pressure sensor I 4 to contact, multi-rotor unmanned aerial vehicle 6 is fixed on 11 upper surface of pedestal by stainless steel pipe clamp 5, temperature
Degree speed probe 10 is fixed on 7 bracket of motor, and voltage-current sensor module 17 passes through conducting wire 8 and unmanned plane power module
9 are connected.
The cylinder chassis 1, pedestal 11 and multi-rotor unmanned aerial vehicle 6 require three's central axis to be overlapped when installing.
There are four the radial centre lines that cylindrical chassis 1 is symmetrically mounted on by bolt for the pressure sensor II 15
On, for measuring pressure value when multi-rotor unmanned aerial vehicle 6 rises or falls movement.
Respectively symmetrically there are four pressure sensor brackets for vertical welding for 1 one, chassis of the cylinder radial centre lines two sides
2, the surface of pressure sensor bracket 2 is parallel with vertical section where 1 axis of cylindrical chassis, and pressure sensor I 4 passes through bolt
It is fixed on pressure sensor bracket 2, for measuring the pressure value generated when unmanned plane is axially moved.
It further include wireless communication system 3, host computer PC 13；The wireless communication system 3 respectively with pressure sensor I 4, pressure
Force snesor II 15, voltage-current sensor module 17 and temperature speed probe 10 are connected by several conducting wires, will be acquired
Data host computer PC 13 is passed to by bluetooth.
The wireless communication system 3 is equipped with usb 16, passes for connecting external power supply to pressure sensor I 4, pressure
Sensor II 15, temperature speed probe 10, voltage-current sensor module 17 are powered.
14 bottom of universal tumbler bearing is bolted on pressure sensor II 15, multi-directional ball branch from strap bolt
Smooth prill 19 is equipped with inside seat 14 freely to be rolled in universal 14 inside of tumbler bearing.
The place that 11 bottom of pedestal is connected with prill 19 is provided with track 20, and prill 19 can be in track 20
Interior movement, while the gravity of pedestal 11 is greater than the maximum pull of multi-rotor unmanned aerial vehicle 6, prevent multi-rotor unmanned aerial vehicle 6 is from driving
Pedestal 11 flies up, and 11 axis line position of pedestal is provided with aperture and passes through for conducting wire 8.
The round metal bars 12 rotate Shi Nengyu pressure sensor I 4 in pedestal 11 and contact, for testing multi-rotor unmanned aerial vehicle
The side pressure value generated when 6 rotation, and then calculate the torque of its generation；Product of the torque T equal to power F and arm of force L, i.e. T=
FL, F are the registration of pressure sensor I 4, and L is the horizontal distance that pressure sensor I 4 arrives 11 longitudinal center line of pedestal.
The stainless steel pipe clamp 5 is according to 6 undercarriage size unrestricted choice of multi-rotor unmanned aerial vehicle.
A kind of process of the test method using the unmanned plane power performance test macro includes the following:
(1), after multi-rotor unmanned aerial vehicle 6 is fixed, power supply at usb 16 is connected, each sensor is started to work, at this point,
First pressure sensor II 151, second pressure sensor II 152, third pressure sensor II 153 and the 4th pressure sensor II
154 initial registrations are respectively a, b, c and d；
When unmanned plane is inactive, first pressure sensor II 151, second pressure sensor II 152, third pressure sensor
II 153 and the 4th pressure sensor II 154 work, new registration a1, b1, c1 and d1 are shown in host computer PC 13, by twice
Registration difference is the weight of multi-rotor unmanned aerial vehicle；
(2), 6 power supply of multi-rotor unmanned aerial vehicle is opened, by unmanned controller, unmanned plane is operated and ramps movement,
First pressure sensor II 151, second pressure sensor II 152, third pressure sensor II 153 and the 4th pressure sensing at this time
II 154 pressure value of device reduces, and registration reduces；When registration and initial registration a, b, c identical with d, unmanned plane lift with from
Body gravity is identical, is in suspended state；Pressure value U and current value I at this time are tested out by voltage-current sensor module 17,
It is equal to voltage U multiplied by I by power P, performance number when unmanned plane suspends can be obtained；
(3), unmanned plane throttle is slowly increased by remote controler, when throttle reaches maximum, shows pressure in host computer PC
When the pressure value that sensor II 15 obtains is reduced to a critical state and no longer changes, unmanned plane reaches maximum power at this time；Note
The numerical value of each sensor obtains realtime power, voltage, electric current, temperature dynamic characteristic value when unmanned plane rises under record；
(4), when doing flexion-extension movement by remote control control unmanned plane, first pressure sensor II 151, second pressure sensing
Device II 152, third pressure sensor II 153 and the 4th pressure sensor II 154 measure pressure value some and become larger, some reductions；
Compare pressure value, obtains power situation of change when unmanned plane does flexion-extension movement；
(5), when being turned left by remote control control unmanned plane, unmanned plane band moving base 11 turns left, and is mounted on 11 left side of pedestal
Round metal bars I 121 contacted with first pressure sensor I 41, round metal bars II 122 are contacted with third pressure sensor I 43, lead to
Cross torque T1Equal to power F1With arm of force L1Product, i.e. T1=F1L1, F1For the registration of first pressure sensor I 41, L1For the first pressure
Force snesor I 41 arrives the horizontal distance of 11 longitudinal center line of pedestal, obtains the torque value generated when unmanned plane turns left.It is slowly increased
Throttle records each sensor values until maximum, can obtain power, voltage, electric current, temperature dynamic when unmanned plane turns left
Characteristic value；
(6), when being turned right by remote control control unmanned plane, unmanned plane band moving base 11 is turned right, round metal bars I 121 and the
The contact of two pressure sensors I 42, round metal bars II 122 are contacted with the 4th pressure sensor I 44, pass through torque T2Equal to power F2With
Arm of force L2Product, i.e. T2= F2L2, F2For the registration of second pressure sensor I 42, L2Pedestal is arrived for second pressure sensor I 42
The horizontal distance of 11 longitudinal center lines obtains the torque value generated when unmanned plane is turned right.Throttle is slowly increased until maximum, record
Under each sensor values, obtain unmanned plane turn right when power, voltage, electric current, temperature dynamic characteristic value；
(7), when unmanned plane executes above-mentioned movement, the temperature and revolving speed of 10 real-time detection motor 7 of temperature speed probe,
To provide reference when unmanned plane during flying；The voltage that 17 real-time detection unmanned plane power module 9 of voltage-current sensor module provides
And electric current, and then obtain instantaneous power value.
The course of work of the utility model is: the usb 16 when work by wireless communication in system 3 powers on,
Each sensor is started to work.6 power supply of multi-rotor unmanned aerial vehicle is opened, it does flare maneuver by remote control control.As rising, hang
When floating and lowering action, the registration of pressure sensor II 15 can change, and production when unmanned plane rises, suspends, declining can be obtained
Raw value of thrust and its variation.When as left rotation and right rotation movement, I 4 registration of pressure sensor changes, available unmanned plane
The torque value generated when left rotation and right rotation.In action process, temperature speed probe 10 can real-time detection unmanned plane motor 7 temperature
Degree and rotation speed change, voltage-current sensor module 17 can measure the voltage value U and current value I of each motor, pass through formula P=UI
Available motor realtime power.
The beneficial effects of the utility model are:
1, simple and compact for structure, modularized design keeps its easy for installation, has good universal；
2, vdiverse in function, support the multi-rotor unmanned aerial vehicle of different model；
3, when can detecte complete machine movement, the situation of change of each parameter, parameter measurement is comprehensive；
4, easy to operate, the operation is stable is cheap, and operating efficiency is high, and failure is few, has promotional value.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the utility model；
Fig. 2 is the testing bench structure schematic diagram of the utility model；
Fig. 3 is the multi-directional ball general structure schematic diagram of the utility model；
Fig. 4 is the base construction schematic diagram of the utility model；
Fig. 5 is the stainless steel tube clamping structure schematic diagram of the utility model；
Fig. 6 is the unmanned plane structural schematic diagram of the utility model.
Each label in Fig. 1-6: 1- cylinder chassis, 2- pressure sensor bracket, 3- wireless communication system, 4- pressure sensing
Device I, 41- first pressure sensor I, 42- second pressure sensor I, 43- third pressure sensor I, the 4th pressure sensing of 44-
Device I, 5- stainless steel pipe clamp, 6- multi-rotor unmanned aerial vehicle, 7- motor, 8- conducting wire, 9- unmanned plane power module, 10- temperature revolving speed pass
Sensor, 11- pedestal, 12- round metal bars, 121- round metal bars I, 122- round metal bars II, 13- host computer PC, 14- multi-directional ball branch
Seat, 15- pressure sensor II, 151- first pressure sensor II, 152- second pressure sensor II, 153- third pressure sensing
Device II, the 4th pressure sensor II of 154-, 16-USB interface, 17- voltage-current sensor module, 18- testboard, 19- metal
Bead, 20- track.
Specific embodiment
Utility model will be further explained below with reference to the attached drawings and specific embodiments.
Embodiment 1: as shown in figures 1 to 6, a kind of unmanned plane power performance test macro, including cylindrical chassis 1, pressure pass
Sensor bracket 2, pressure sensor I 4, stainless steel pipe clamp 5, multi-rotor unmanned aerial vehicle 6, motor 7, conducting wire 8, unmanned plane power module 9,
Temperature speed probe 10, pedestal 11, round metal bars 12, universal tumbler bearing 14, pressure sensor II 15, voltage-current sensor
Module 17, prill 19, track 20；
The pressure sensor bracket 2, wireless communication system 3, pressure sensor II 15 and voltage-current sensor module
17 are fixed on cylindrical chassis 1, and pressure sensor I 4 is bolted on pressure sensor bracket 2, universal tumbler bearing
14 are bolted on pressure sensor II 15, are in multi-directional ball support 14 built in prill 19,11 following table of pedestal
Face is placed on prill 19 by track 20, and round metal bars 12 are welded on 11 two sides of pedestal, and round metal bars 12 are in pedestal 11
It rotates Shi Nengyu pressure sensor I 4 to contact, multi-rotor unmanned aerial vehicle 6 is fixed on 11 upper surface of pedestal by stainless steel pipe clamp 5, temperature
Degree speed probe 10 is fixed on 7 bracket of motor, and voltage-current sensor module 17 passes through conducting wire 8 and unmanned plane power module
9 are connected.
Further, three's central axis is required when the cylindrical chassis 1, pedestal 11 and multi-rotor unmanned aerial vehicle 6 are installed
It is overlapped.
Further, there are four the diameters that cylindrical chassis 1 is symmetrically mounted on by bolt for the pressure sensor II 15
To on center line, for measuring pressure value when multi-rotor unmanned aerial vehicle 6 rises or falls movement.
Further, respectively symmetrically there are four pressure for vertical welding for cylindrical 1 one, the chassis radial centre lines two sides
Sensor stand 2, the surface of pressure sensor bracket 2 is parallel with vertical section where 1 axis of cylindrical chassis, pressure sensor
I 4 are bolted on pressure sensor bracket 2, for measuring the pressure value generated when unmanned plane is axially moved.
It further, further include wireless communication system 3, host computer PC 13；The wireless communication system 3 is passed with pressure respectively
Sensor I 4, pressure sensor II 15, voltage-current sensor module 17 and temperature speed probe 10 are connected by several conducting wires
It connects, the data of acquisition is passed into host computer PC 13 by bluetooth.
Further, the wireless communication system 3 is equipped with usb 16, for connecting external power supply to pressure sensor I
4, pressure sensor II 15, temperature speed probe 10, voltage-current sensor module 17 are powered.
Further, 14 bottom of universal tumbler bearing is bolted on pressure sensor II 15 from strap bolt,
Smooth prill 19 is equipped with inside universal tumbler bearing 14 freely to be rolled in universal 14 inside of tumbler bearing.
Further, the place that 11 bottom of pedestal is connected with prill 19 is provided with track 20, prill 19
It can be moved in track 20, while the gravity of pedestal 11 is greater than the maximum pull of multi-rotor unmanned aerial vehicle 6, so that multi-rotor unmanned aerial vehicle
6 cannot fly up with moving base 11, and 11 axis line position of pedestal is provided with aperture and passes through for conducting wire 8.
Further, the round metal bars 12 rotate Shi Nengyu pressure sensor I 4 in pedestal 11 and contact, more for testing
The side pressure value that rotor wing unmanned aerial vehicle 6 generates when rotating, and then calculate the torque of its generation；Torque T is equal to power F's and arm of force L
Product, i.e. T=FL, F are the registration of pressure sensor I 4, L be pressure sensor I 4 to 11 longitudinal center line of pedestal it is horizontal away from
From.
Further, the stainless steel pipe clamp 5 is according to 6 undercarriage size unrestricted choice of multi-rotor unmanned aerial vehicle.
A kind of process of the test method using the unmanned plane power performance test macro includes the following:
Check whether each device is normal, be then completed each device according to shown in each attached drawing, unmanned plane is not installed first.
Host computer PC 13 is opened, and is adjusted to working interface.Power supply is connected by usb 16, observed pressure sensor I 4,
Whether temperature speed probe 10, pressure sensor II 15 and voltage-current sensor module 17 can work normally.
It is errorless to detect each sensor, pressure sensor II 15 includes first pressure sensor II 151, second pressure biography at this time
Sensor II 152, third pressure sensor II 153 and the 4th pressure sensor II 154 have started and by initial registration a,
B, system 3 is transmitted to host computer PC 13 and shows c and d by wireless communication.
Power supply at usb 16 is disconnected, multi-rotor unmanned aerial vehicle 6 is firmly fixed by stainless steel pipe clamp 5 using bolt
On the base 11.
After multi-rotor unmanned aerial vehicle 6 is fixed, power supply at usb 16 is connected, each sensor is started to work.Unmanned plane at this time
It is inactive, first pressure sensor II 151, second pressure sensor II 152, third pressure sensor II 153 and the 4th pressure
Sensor II 154 works, and shows new registration a1, b1, c1 and d1 in host computer PC 13.It is more rotations by registration difference twice
The weight of wing unmanned plane.
6 power supply of multi-rotor unmanned aerial vehicle is opened, by unmanned controller, unmanned plane is operated and ramps movement, at this time
First pressure sensor II 151, second pressure sensor II 152, third pressure sensor II 153 and the 4th pressure sensor II
154 pressure values reduce, and registration reduces.When registration and initial registration a, b, c identical with d, unmanned plane lift and itself weight
Power is identical, is in suspended state.Pressure value U and current value I at this time are tested out by voltage-current sensor module 17, is passed through
Power P is equal to voltage U multiplied by I, and performance number when unmanned plane suspends can be obtained.
It is slowly increased unmanned plane throttle by remote controler, when throttle reaches maximum, shows pressure sensing in host computer PC
When the pressure value that device II 15 obtains is reduced to a critical state and no longer changes, unmanned plane reaches maximum power at this time.It records
The numerical value of each sensor can obtain the dynamic characteristics values such as realtime power, voltage, electric current, the temperature when unmanned plane rises.
When doing flexion-extension movement by remote control control unmanned plane, first pressure sensor II 151, second pressure sensor II
152, third pressure sensor II 153 and the 4th pressure sensor II 154 measure pressure value some and become larger, some reductions.Compare
Pressure value, power situation of change when available unmanned plane does flexion-extension movement.
When being turned left by remote control control unmanned plane, unmanned plane band moving base 11 turns left, and is mounted on the gold in 11 left side of pedestal
Belong to pole I 121 to contact with first pressure sensor I 41, round metal bars II 122 are contacted with third pressure sensor I 43, pass through torsion
Square T1Equal to power F1With arm of force L1Product, i.e. T1=F1L1, F1For the registration of first pressure sensor I 41, L1For first pressure biography
Sensor I 41 arrives the horizontal distance of 11 longitudinal center line of pedestal, obtains the torque value generated when unmanned plane turns left.It is slowly increased throttle
Until it is maximum, each sensor values are recorded, power, voltage, electric current, temperature dynamic characteristic when unmanned plane turns left can be obtained
Value.
When being turned right by remote control control unmanned plane, unmanned plane band moving base 11 is turned right, round metal bars I 121 and the second pressure
Force snesor I 42 contacts, and round metal bars II 122 are contacted with the 4th pressure sensor I 44, passes through torque T2Equal to power F2With the arm of force
L2Product, i.e. T2= F2L2, F2For the registration of second pressure sensor I 42, L211 axis of pedestal is arrived for second pressure sensor I 42
To the horizontal distance of center line, the torque value generated when unmanned plane is turned right is obtained.Throttle is slowly increased until maximum, is recorded each
Sensor values can obtain power, voltage, electric current, temperature dynamic characteristic value when unmanned plane is turned right.
Unmanned plane execute above-mentioned movement when, temperature speed probe 10 can with the temperature and revolving speed of real-time detection motor 7,
To provide reference when unmanned plane during flying.What voltage-current sensor module 17 can be provided with real-time detection unmanned plane power module 9
Voltage and current, and then obtain instantaneous power value.
Specific embodiment of the utility model is explained in detail above in conjunction with attached drawing, but the utility model and unlimited
In above-described embodiment, within the knowledge of a person skilled in the art, the utility model can also not departed from
Various changes can be made under the premise of objective.
Claims (9)
1. a kind of unmanned plane power performance test macro, it is characterised in that: including cylindrical chassis (1), pressure sensor bracket
(2), pressure sensor I (4), stainless steel pipe clamp (5), multi-rotor unmanned aerial vehicle (6), motor (7), conducting wire (8), unmanned electromechanical source mould
Block (9), temperature speed probe (10), pedestal (11), round metal bars (12), universal tumbler bearing (14), pressure sensor II
(15), voltage-current sensor module (17), prill (19), track (20)；
The pressure sensor bracket (2), wireless communication system (3), pressure sensor II (15) and voltage-current sensor mould
Block (17) is fixed on cylindrical chassis (1), and pressure sensor I (4) is bolted on pressure sensor bracket (2),
Universal tumbler bearing (14) is bolted on pressure sensor II (15), and prill (19) is built-in to be multi-directional ball support
(14) inner, pedestal (11) lower surface is placed on prill (19) by track (20), and round metal bars (12) are welded on pedestal
(11) two sides, round metal bars (12) are contacted in pedestal (11) rotation Shi Nengyu pressure sensor I (4), and multi-rotor unmanned aerial vehicle (6) is logical
It crosses stainless steel pipe clamp (5) and is fixed on pedestal (11) upper surface, temperature speed probe (10) is fixed on motor (7) bracket, electricity
Current voltage sensor module (17) is connected by conducting wire (8) with unmanned plane power module (9).
2. unmanned plane power performance test macro according to claim 1, it is characterised in that: the cylinder chassis (1),
Pedestal (11) and multi-rotor unmanned aerial vehicle (6) require three's central axis to be overlapped when installing.
3. unmanned plane power performance test macro according to claim 1, it is characterised in that: the pressure sensor II
(15) there are four being symmetrically mounted on by bolt in the radial centre lines of cylindrical chassis (1), for measure more rotors nobody
Machine (6) rises or falls pressure value when movement.
4. unmanned plane power performance test macro according to claim 1, it is characterised in that: the cylinder chassis (1)
One radial centre lines two sides respectively symmetrically vertical welding there are four pressure sensor bracket (2), pressure sensor bracket (2)
Surface is parallel with vertical section where cylindrical chassis (1) axis, and pressure sensor I (4) is bolted on pressure sensing
On device bracket (2), for measuring the pressure value generated when unmanned plane is axially moved.
5. unmanned plane power performance test macro according to claim 1, it is characterised in that: further include wireless communication system
(3), host computer PC (13)；The wireless communication system (3) respectively with pressure sensor I (4), pressure sensor II (15), electricity
Current voltage sensor module (17) and temperature speed probe (10) are connected by several conducting wires, and the data of acquisition are passed through indigo plant
Tooth passes to host computer PC (13).
6. unmanned plane power performance test macro according to claim 5, it is characterised in that: the wireless communication system
(3) USB interface (16) are equipped with, for connecting external power supply to pressure sensor I (4), pressure sensor II (15), temperature revolving speed
Sensor (10), voltage-current sensor module (17) power supply.
7. unmanned plane power performance test macro according to claim 1, it is characterised in that: the universal tumbler bearing (14)
Bottom is bolted on pressure sensor II (15) from strap bolt, is equipped with inside universal tumbler bearing (14) smooth
Prill (19) can freely roll inside universal tumbler bearing (14).
8. unmanned plane power performance test macro according to claim 1, it is characterised in that: pedestal (11) bottom with
The place that prill (19) is connected is provided with track (20), and prill (19) can move in track (20), while pedestal
(11) gravity is greater than the maximum pull of multi-rotor unmanned aerial vehicle (6), so that multi-rotor unmanned aerial vehicle (6) cannot fly with moving base (11)
It rises, pedestal (11) axis line position is provided with aperture and passes through for conducting wire (8).
9. unmanned plane power performance test macro according to claim 1, it is characterised in that: the round metal bars (12) exist
Pedestal (11) rotates Shi Nengyu pressure sensor I (4) contact, for testing the side generated when multi-rotor unmanned aerial vehicle (6) rotation
Pressure value, and then calculate the torque of its generation；Torque T is equal to the product of power F and arm of force L, i.e. T=FL, F are pressure sensor I
(4) registration, L are the horizontal distance that pressure sensor I (4) arrives pedestal (11) longitudinal center line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821556093.6U CN209209059U (en) | 2018-09-25 | 2018-09-25 | A kind of unmanned plane power performance test macro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821556093.6U CN209209059U (en) | 2018-09-25 | 2018-09-25 | A kind of unmanned plane power performance test macro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209209059U true CN209209059U (en) | 2019-08-06 |
Family
ID=67454545
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821556093.6U Expired - Fee Related CN209209059U (en) | 2018-09-25 | 2018-09-25 | A kind of unmanned plane power performance test macro |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209209059U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN111874260A (en) * | 2020-06-24 | 2020-11-03 | 中山大学 | Aircraft lifting force and torque testing device and method |
-
2018
- 2018-09-25 CN CN201821556093.6U patent/CN209209059U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN109229421B (en) * | 2018-09-25 | 2023-09-26 | 昆明理工大学 | Unmanned aerial vehicle power performance test system and method |
| CN111874260A (en) * | 2020-06-24 | 2020-11-03 | 中山大学 | Aircraft lifting force and torque testing device and method |
| CN111874260B (en) * | 2020-06-24 | 2022-09-23 | 中山大学 | Aircraft lifting force and torque testing device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109229421A (en) | A kind of unmanned plane power performance test macro and method | |
| CN109443689B (en) | Wind tunnel test measuring device and measuring method for dynamic aerodynamic force of radar antenna during rotating work | |
| CN108506172B (en) | Online detection system for health state of wind power generation blade | |
| CN209209059U (en) | A kind of unmanned plane power performance test macro | |
| CN206725141U (en) | A kind of propeller dynamic test platform | |
| CN205738142U (en) | A kind of many rotor wing unmanned aerial vehicles test platform | |
| CN206460072U (en) | A kind of apparatus for measuring air quantity | |
| CN103076462B (en) | Multi-direction wind speed measuring device | |
| CN207550485U (en) | Unmanned plane and the environmental monitoring system based on the unmanned plane | |
| CN108438250A (en) | Serial mixed power aircraft power system testboard bay | |
| CN206872200U (en) | A kind of elevator brake parameter detecting instrument | |
| CN210710213U (en) | Device for detecting inclination angle of elevator car based on six-axis acceleration sensor | |
| CN203464997U (en) | Automatic test system of motor noises | |
| CN205898470U (en) | Vehicle comprehensive properties detecting system | |
| CN107024307A (en) | Ball screw assembly, moment detector | |
| CN110606223B (en) | Coaxial dual-rotor unmanned aerial vehicle ground flight test platform and test method | |
| CN106560685A (en) | Airfoil-shaped dynamic aerodynamic characteristic test bench for horizontal-axis wind turbine | |
| CN206096179U (en) | Fast sensor performance parameters testing arrangement of portable car wheel | |
| CN207336024U (en) | Ocean nuclear power platform single point mooring system testing device | |
| CN110426136A (en) | The mobile temperature-detecting device of solid-state layering fermentation | |
| CN202886105U (en) | Platform for testing engine thrust of aerostat | |
| CN206248726U (en) | Wind power hub slip ring detecting system | |
| CN201335687Y (en) | Motor vehicle wheel steering angle testing instrument with loading device | |
| CN113586963A (en) | Pipeline heat preservation automatic checkout device | |
| CN115371741B (en) | System and method for detecting thrust, rotating speed and torque of propulsion motor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190806 Termination date: 20200925 |