CN206038204U - Many rotor crafts driving system lift capability test device - Google Patents
Many rotor crafts driving system lift capability test device Download PDFInfo
- Publication number
- CN206038204U CN206038204U CN201621084139.XU CN201621084139U CN206038204U CN 206038204 U CN206038204 U CN 206038204U CN 201621084139 U CN201621084139 U CN 201621084139U CN 206038204 U CN206038204 U CN 206038204U
- Authority
- CN
- China
- Prior art keywords
- feet
- resistance
- circuit
- hx711ad
- electric capacity
- 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
Abstract
The utility model provides a many rotor crafts driving system lift capability test device, it includes MCU processor circuit, the measuring circuit, rotational speed interface circuit and the electricity accent interface circuit that are connected with this MCU processor circuit electricity, wherein the measuring circuit includes the lift measuring circuit, the lift measuring circuit is used for measuring rotor lift, including HX711AD circuit and bridge type pressure sensor circuit, the utility model discloses utilize the bridge type pressure sensor based on resistance strain gauge to measure the lift data, make lift data measurement convenient, carry out many rotor crafts driving system lift performance and discern through directly acquireing the lift data for the rotor lift model that arrives is more accurate.
Description
Technical field
This utility model is related to multi-rotor aerocraft technical field of flight control, and in particular to multi-rotor aerocraft dynamical system
System lift performance testing device.
Background technology
Multi-rotor aerocraft have can VTOL and frame for movement are simple, reliability is high, small volume, it is lightweight, into
The advantages of this is low, easy to use, has at aspects such as aeroplane photography, traffic monitoring, geographical mapping, power-line patrolling and investigations wide
Wealthy application prospect.
Multi-rotor aerocraft controller controls the state of flight of aircraft, is the important component part of aerocraft system.Its
Middle multi-rotor aerocraft dynamical system lift performance parameter is to design the important evidence of multi-rotor aerocraft controller, accurate
Solution Power System of Flight Vehicle lift performance contributes to designing more excellent controller.
Power System of Flight Vehicle lift performance parameter recognize, needs know input Power System of Flight Vehicle control information and
The liter force information of output Power System of Flight Vehicle.But due to lift measurement inconvenience, in the market to aircraft power system
Using the method for measuring indirectly lift more than the method for system lift performance parameter identification, i.e., a small amount of lift is measured first and motor turns
Fast data, calculate the coefficient of lift and motor speed square, then further according to motor speed and the coefficient, calculate substantial amounts of
Force data is risen, Parameter identification is carried out.The following shortcoming of this method generally existing：
(1) record rises force data inconvenience.
(2) calculate lift few with the data bulk selected by the coefficient of motor speed square, it is impossible to exclude random error
Affect.
(3) lift is calculated using round-about way, introduces interference, make the liter force data of acquisition inaccurate.
Utility model content
Technical problem to be solved in the utility model is that existing multi-rotor aerocraft dynamical system lift performance is recognized not
A kind of convenient, inaccurate problem, there is provided multi-rotor aerocraft dynamical system lift performance testing device.
This utility model is provided：A kind of multi-rotor aerocraft dynamical system lift performance testing device, which includes MCU process
Device circuit, the measuring circuit electrically connected with the MCU processor circuits, rotating speed interface circuit and electricity adjust interface circuit, wherein measure
Circuit includes lift measurement circuit,
The lift measurement circuit is used for measuring rotor lift, including HX711AD circuits and bridge pressure sensor circuit；
The rotating speed interface circuit is used for measurement motor rotating speed, and its outfan is input into the intervalometer of MCU processor circuits
Capture-port is connected, and the input of rotating speed interface circuit is connected with brushless motor speed sensor, and the brushless motor speed is passed
Sensor is used for the rotating speed of the motor for detecting brushless electric machine propeller；
The electricity adjusts interface circuit to be used for the PWM ripples of output control brushless motor speed, and electricity adjusts the outfan of interface circuit
The input adjusted with model plane electricity is connected, and electricity adjusts the input of interface circuit and the intervalometer PWM output ports of MCU processor circuits
It is connected, outfan and the motor connection of brushless electric machine propeller that the model plane electricity is adjusted, the power supply termination electricity that the model plane electricity is adjusted
Source.
The bridge pressure sensor circuit is made up of four resistance strain gage pressure sensors.
The HX711AD circuits are connect by HX711AD conversion chips, Q2 audions, 6 foot pricking with needle connector JC8,4 foot pricking with needle
Plug-in unit JC9, electric capacity C4, electric capacity C5, electric capacity C6, electric capacity C7, electric capacity C8, resistance R8, resistance R9, resistance R12 and resistance R13 groups
Into wherein 8 feet of HX711AD conversion chips and 10 feet distinguish the 4 of series resistance R8 and resistance R9 and 6 foot pricking with needle connector JC8
Foot and the connection of 6 feet, 7 feet and 9 feet of HX711AD conversion chips are connected with 3 feet and 5 feet of 6 foot pricking with needle connector JC8, HX711AD
11 and 12 feet of shunt capacitance C4 and C5, HX711AD conversion chip are distinguished between 7 feet and 8 feet, 9 feet and 10 feet of conversion chip
It is connected with 4 foot pricking with needle connector JC9,2 feet of HX711AD conversion chips connect the base stage of audion Q2, the colelctor electrode of audion Q2
It is grounded and directly connects power supply VCC respectively by electric capacity C6, emitter stage series resistance R12 of audion Q2 connects HX711AD conversions
4 feet of chip, parallel resistance R13 between 4 feet and 5 feet of HX711AD conversion chips, the emitter stage and HX711AD of audion Q2
Shunt capacitance C7 between 5 feet of conversion chip, shunt capacitance C8 between 5 feet and 6 feet of HX711AD conversion chips.
The measuring circuit is additionally provided with tension measuring circuit and current measurement circuit, and the tension measuring circuit and electric current are surveyed
Amount circuit is adjusted with model plane electricity respectively and is connected.
The MCU processor circuits are provided with USB-USART bridgt circuits, for realizing that the agreement between USB and USART turns
Change, one end of USB-USART bridgt circuits is connected with the USB interface of host computer, the other end and MCU processor circuits
USART ports connect, and the USB-USART bridgt circuits are that MCU processor circuits and HX711AD provide 3.3V supply voltages.
The tension measuring circuit is made up of resistance R3, resistance R4, electric capacity C13, and wherein resistance R3 and resistance R4 is constituted and divided
Volt circuit.
The current measurement circuit by OPA348SC chips, resistance R7, resistance R8, resistance R9, resistance R10, electric capacity C16,
Electric capacity C17 is constituted, and 1 foot of wherein OPA348SC chips is sequentially connected in series resistance R8, resistance R7 ground connection, 1 foot of OPA348SC chips
It is grounded by electric capacity C16, is grounded after 3 foot series resistances R9 of OPA348SC chips, 5 feet of OPA348SC chips is respectively by electricity
Hold C17 ground connection and directly meet power supply VCC, 4 feet of OPA348SC chips connect the AD sampling inputs of MCU processor circuits,
Parallel resistance R10 between 4 feet and 3 feet of OPA348SC chips, the wherein junction of resistance R8 and resistance R7 are sampling end.
This utility model rises force data using the bridge pressure sensor measurement based on resistance strain gage, surveys liter force data
Amount is convenient；By direct access rise force data carry out multi-rotor aerocraft dynamical system lift performance identification, so as to get rotor
Lift model is more accurate.
Description of the drawings
Fig. 1 is system principle structure chart of the present utility model.
Fig. 2 is the circuit theory diagrams of MCU processor circuits.
Fig. 3 is the circuit theory diagrams of USB-USART bridgt circuits.
Fig. 4 is the circuit theory diagrams of tension measuring circuit.
Fig. 5 is the circuit theory diagrams of current measurement circuit.
Fig. 6 is the circuit theory diagrams of lift measurement circuit.
Fig. 7 is the circuit theory diagrams that electricity adjusts interface circuit.
Fig. 8 is the circuit theory diagrams of rotating speed interface circuit.
Fig. 9 is the circuit theory diagrams of bridge pressure sensor circuit.
Figure 10 is the circuit theory diagrams of HX711AD circuits.
Specific embodiment
Below in conjunction with the accompanying drawings this utility model embodiment is described further：
As illustrated, this utility model provides a kind of multi-rotor aerocraft dynamical system lift performance testing device 100, its
Including MCU processor circuits 107, the measuring circuit electrically connected with the MCU processor circuits 107, rotating speed interface circuit 105 and electricity
Interface circuit 104 is adjusted,
The MCU processor circuits 107, are connected with voltage detecting circuit, current detection circuit by AD sampling input pins
Connect, realize that model plane electricity adjusts input voltage, model plane electricity to adjust the measurement of input current；Detected with lift by GPIO mouths (PA5, PB10)
Circuit connects, and realizes the measurement of rotor lift；Adjust interface circuit to be connected by intervalometer PWM output ports and electricity, realize control
Motor speed；It is connected with rotating speed interface circuit by intervalometer input capture interface, realizes the measurement of motor speed；Pass through
USART interfaces are connected with USB-USART bridgt circuits, realize the protocol conversion between USB and USART.
MCU processor circuits 107 are by MCU processors, OBSCILLATOR crystal oscillators, JTAG download interfaces, electric capacity C5, electric capacity
C6, electric capacity C7, electric capacity C8, electric capacity C9, electric capacity C10, electric capacity C11, electric capacity C12, resistance R2 compositions, MCU processor chips are adopted
Based on Cortex-M3 kernels 32 embedded microcontroller chips STM32F100CBT6 of ST Microelectronics's production,
OBSCILLATOR crystal oscillators provide outside 8MHZ clocks, jtag interface for STM32F100CBT6 microcontrollers to be used for downloading slave computer
To control chip STM32F100CBT6, electric capacity C5, C6, C7, C8, C9, C10, C11 play pressure stabilization function, electric capacity C12 and rise program
To coupling, BOOT0 is connected to ground through resistance R2, makes program performing from the beginning of Flash.
Wherein measuring circuit includes lift measurement circuit 103, and the lift measurement circuit 103 is used for measuring rotor lift,
Including HX711AD circuits and bridge pressure sensor circuit, the bridge pressure sensor circuit includes bridge pressure sensor；
The rotating speed interface circuit 105 is used for the timing of measurement motor rotating speed, its outfan and MCU processor circuits 107
Device input capture port is connected, and the input of rotating speed interface circuit is connected with brushless motor speed sensor, the brushless electric machine
Speed probe is used for the rotating speed of the motor for detecting brushless electric machine propeller.Rotating speed interface circuit 105 is by three foot of 2.54mm spacing
Pricking with needle connector RPM_IN constitute, wherein pin 1 be brushless motor speed sensor signal input port, pin 2 connection 5V power supplys,
Pin 3 is grounded.
The electricity adjusts interface circuit to be used for the PWM ripples of output control brushless motor speed, and electricity adjusts the outfan of interface circuit
The input adjusted with model plane electricity is connected, and electricity adjusts the input of interface circuit and the intervalometer PWM output ports of MCU processor circuits
It is connected, outfan and the motor connection of brushless electric machine propeller that the model plane electricity is adjusted, the power supply termination that the model plane electricity is adjusted are outer
Put power supply, it is the abbreviation of model airplane electron speed regulator that model plane electricity is adjusted, English name Air-modeling ESC.
Electricity adjusts interface circuit 104 to be made up of three foot pricking with needle connector PWM_Out of 2.54mm spacing, and wherein 1 pin is timing
Device PWM delivery outlets, 2 pins are hanging, 3 pins ground connection.
The bridge pressure sensor circuit is made up of 4 resistance strain gage pressure sensors R_1, R_2 R_3 and R_4,
The lift measurement circuit 103, is connected by input of the outfan of resistance-strain bridge pressure sensor with HX711AD modules
Connect, the input of HX711AD circuits is connected with the GPIO mouths (PA5, PB10) of MCU processor circuits, realizes lift measurement.
The lift measurement circuit 103 is made up of four foot pricking with needle connector Lift_in of 2.54mm spacing, and wherein pin 1 is
HX711AD conversion command control ends, pin 2 are HX711D data input pins, and pin 3 connects 3.3V voltages, and pin 4 is grounded.
The HX711AD circuits are connect by HX711AD conversion chips, Q2 audions, 6 foot pricking with needle connector JC8,4 foot pricking with needle
Plug-in unit JC9, electric capacity C4, electric capacity C5, electric capacity C6, electric capacity C7, electric capacity C8, resistance R8, resistance R9, resistance R12 and resistance R13 groups
Into wherein 8 feet of HX711AD conversion chips and 10 feet distinguish the 4 of series resistance R8 and resistance R9 and 6 foot pricking with needle connector JC8
Foot and the connection of 6 feet, 7 feet and 9 feet of HX711AD conversion chips are connected with 3 feet and 5 feet of 6 foot pricking with needle connector JC8, HX711AD
11 and 12 feet of shunt capacitance C4 and C5, HX711AD conversion chip are distinguished between 7 feet and 8 feet, 9 feet and 10 feet of conversion chip
It is connected with 4 foot pricking with needle connector JC9,2 feet of HX711AD conversion chips connect the base stage of audion Q2, the colelctor electrode of audion Q2
It is grounded and directly connects power supply VCC respectively by electric capacity C6, emitter stage series resistance R12 of audion Q2 connects HX711AD conversions
4 feet of chip, parallel resistance R13 between 4 feet and 5 feet of HX711AD conversion chips, the emitter stage and HX711AD of audion Q2
Shunt capacitance C7 between 5 feet of conversion chip, shunt capacitance C8 between 5 feet and 6 feet of HX711AD conversion chips.Wherein electric capacity
C4, C5, C6, C7 play a part of voltage stabilizing, and C8 plays coupling, and in HX711AD chips, mu balanced circuit is by outer three poles of chip
Pipe Q2 and divider resistance R12, R13 provide stable low-noise simulation voltage to sensor and A/D converter.6 foot pricking with needle are patched
1 foot of part JC8 be connected to AVDD, 2 feet be connected to GND, 3 feet be connected to passage A-, 4 feet be connected to passage A+, 5 feet be connected to it is logical
Road B-, 6 feet are connected to passage B+, and 4 foot pricking with needle connector JC9 passages 1 are connected to VCC, passage 2 and are connected to PD_SCK, passage 3 and connect
It is connected to DOUT, passage 4 and is connected to GND.
The measuring circuit is additionally provided with tension measuring circuit 101 and current measurement circuit 102, the tension measuring circuit
101 and current measurement circuit 102 respectively with model plane electricity adjust be connected.
The voltage detecting circuit 101 is adjusted the AD interfaces after 1/10 partial pressure of supply voltage with MCU processors by model plane electricity
(PA0) connect, realize the voltage measurement to regulated power supply；The tension measuring circuit 101 is by resistance R3, resistance R4, electric capacity C13
Composition, wherein resistance R3 and resistance R4 constitute bleeder circuit, and electric capacity C13 plays a part of voltage stabilizing.
The current detection circuit 102, accesses the power end that model plane electricity is adjusted, outfan and MCU processors by input
AD interfaces (PA3) connection of circuit, realizes current measurement；The current measurement circuit 102 by OPA348SC chips, resistance R7,
Resistance R8, resistance R9, resistance R10, electric capacity C16, electric capacity C17 compositions, 1 foot of wherein OPA348SC chips are sequentially connected in series resistance
R8, resistance R7 are grounded, and 1 foot of OPA348SC chips is grounded by electric capacity C16, after 3 foot series resistances R9 of OPA348SC chips
Ground connection, 5 feet of OPA348SC chips are grounded and directly connect power supply VCC, 4 feet of OPA348SC chips respectively by electric capacity C17
Connect the AD sampling inputs of MCU processor circuits, parallel resistance R10, wherein resistance between 4 feet and 3 feet of OPA348SC chips
The junction of R8 and resistance R7 is sampling end.OPA348SC chips are precision operational-amplifier, and R7 is current sensing resistor, by electricity
Stream signal is converted to voltage signal, and R8, R9, R10, C16 and OPA348SC chip constitutes the accurate fortune that amplification is 99 times
Calculate amplifying circuit, C16, C17 and play pressure stabilization function.
The MCU processor circuits 107 are provided with USB-USART bridgt circuits 106, for realizing between USB and USART
Protocol conversion, one end of USB-USART bridgt circuits are connected with the USB interface of host computer, and the other end is electric with MCU processors
The USART ports connection on road, the USB-USART bridgt circuits provide 3.3V for MCU processor circuits and HX711AD and power electricity
Pressure.
USB-USART bridgt circuits 106 are by USB-F interfaces, FT232R chips, resistance R1, electric capacity C1, electric capacity C2, electric capacity
C3, electric capacity C4 are constituted, and USB interface is used for connecting USB line, and FT232 chips are used for the conversion of usb signal and USART signals, resistance
R1 is 0 Ω resistance, and effect can be that selectivity connects this root wire, and electric capacity C1, electric capacity C2, electric capacity C3 play the work of burning voltage
With.
Embodiment is not construed as to restriction of the present utility model, but any based on changing that spirit of the present utility model is made
Enter, all should be within protection domain of the present utility model.
Claims (7)
1. a kind of multi-rotor aerocraft dynamical system lift performance testing device, it is characterised in that：Which includes MCU processors electricity
Interface circuit, wherein measuring circuit are adjusted in road, the measuring circuit electrically connected with the MCU processor circuits, rotating speed interface circuit and electricity
Including lift measurement circuit,
The lift measurement circuit is used for measuring rotor lift, including HX711AD circuits and bridge pressure sensor circuit；
The rotating speed interface circuit is used for the intervalometer input capture of measurement motor rotating speed, its outfan and MCU processor circuits
Port is connected, and the input of rotating speed interface circuit is connected with brushless motor speed sensor, the brushless motor speed sensor
For detecting the rotating speed of the motor of brushless electric machine propeller；
The electricity adjusts interface circuit to be used for the PWM ripples of output control brushless motor speed, and electricity adjusts the outfan of interface circuit and boat
The input of interface circuit and the intervalometer PWM output port phases of MCU processor circuits are adjusted in the input connection that mould electricity is adjusted, electricity
Even, the model plane electricity is adjusted outfan and motor connection, the power supply termination power that the model plane electricity is adjusted.
2. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 1, it is characterised in that：
The bridge pressure sensor circuit is made up of four resistance strain gage pressure sensors.
3. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 1 and 2, its feature exist
In：The HX711AD circuits are by HX711AD conversion chips, Q2 audions, 6 foot pricking with needle connector JC8,4 foot pricking with needle connectors
JC9, electric capacity C4, electric capacity C5, electric capacity C6, electric capacity C7, electric capacity C8, resistance R8, resistance R9, resistance R12 and resistance R13 composition,
Wherein 8 feet of HX711AD conversion chips and 10 feet difference series resistance R8 and resistance R9 and 6 foot pricking with needle connector JC8 4 feet and
6 feet connect, and 7 feet and 9 feet of HX711AD conversion chips are connected with 3 feet and 5 feet of 6 foot pricking with needle connector JC8, HX711AD conversions
11 and 12 feet and 4 feet of shunt capacitance C4 and C5, HX711AD conversion chip are distinguished between 7 feet and 8 feet, 9 feet and 10 feet of chip
Pricking with needle connector JC9 is connected, and 2 feet of HX711AD conversion chips connect the base stage of audion Q2, and the colelctor electrode of audion Q2 leads to respectively
Cross electric capacity C6 ground connection and directly meet power supply VCC, emitter stage series resistance R12 of audion Q2 connects the 4 of HX711AD conversion chips
Foot, parallel resistance R13 between 4 feet and 5 feet of HX711AD conversion chips, emitter stage and the HX711AD conversion chips of audion Q2
5 feet between shunt capacitance C7, shunt capacitance C8 between 5 feet and 6 feet of HX711AD conversion chips.
4. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 1, it is characterised in that：
The measuring circuit is additionally provided with tension measuring circuit and current measurement circuit, the tension measuring circuit and current measurement circuit point
Do not adjust with model plane electricity and be connected.
5. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 1, it is characterised in that：
The MCU processor circuits are provided with USB-USART bridgt circuits, for realizing the protocol conversion between USB and USART, USB-
One end of USART bridgt circuits is connected with the USB interface of host computer, the USART ports of the other end and MCU processor circuits
Connection, the USB-USART bridgt circuits are that MCU processor circuits and HX711AD provide 3.3V supply voltages.
6. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 4, it is characterised in that：
The tension measuring circuit is made up of resistance R3, resistance R4, electric capacity C13, and wherein resistance R3 and resistance R4 constitutes bleeder circuit.
7. a kind of multi-rotor aerocraft dynamical system lift performance testing device according to claim 4, it is characterised in that：
The current measurement circuit is by OPA348SC chips, resistance R7, resistance R8, resistance R9, resistance R10, electric capacity C16, electric capacity C17 groups
Into 1 foot of wherein OPA348SC chips is sequentially connected in series resistance R8, resistance R7 ground connection, and 1 foot of OPA348SC chips passes through electric capacity
C16 is grounded, and is grounded after 3 foot series resistances R9 of OPA348SC chips, and 5 feet of OPA348SC chips are connect by electric capacity C17 respectively
Ground and directly meet power supply VCC, 4 feet of OPA348SC chips connect the AD sampling inputs of MCU processor circuits, OPA348SC cores
Parallel resistance R10 between 4 feet and 3 feet of piece, the wherein junction of resistance R8 and resistance R7 are sampling end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621084139.XU CN206038204U (en) | 2016-09-27 | 2016-09-27 | Many rotor crafts driving system lift capability test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621084139.XU CN206038204U (en) | 2016-09-27 | 2016-09-27 | Many rotor crafts driving system lift capability test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206038204U true CN206038204U (en) | 2017-03-22 |
Family
ID=58296751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621084139.XU Expired - Fee Related CN206038204U (en) | 2016-09-27 | 2016-09-27 | Many rotor crafts driving system lift capability test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206038204U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466796A (en) * | 2018-12-30 | 2019-03-15 | 东北农业大学 | The unmanned plane tensile test platform of low current alarm |
| CN110641731A (en) * | 2019-09-29 | 2020-01-03 | 江苏科技大学 | Rotor motor lift force measuring device for multi-rotor unmanned aerial vehicle |
| CN116062202A (en) * | 2023-03-20 | 2023-05-05 | 北京瀚科智翔科技发展有限公司 | Combined coaxial double-rotor unmanned aerial vehicle system |
-
2016
- 2016-09-27 CN CN201621084139.XU patent/CN206038204U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466796A (en) * | 2018-12-30 | 2019-03-15 | 东北农业大学 | The unmanned plane tensile test platform of low current alarm |
| CN110641731A (en) * | 2019-09-29 | 2020-01-03 | 江苏科技大学 | Rotor motor lift force measuring device for multi-rotor unmanned aerial vehicle |
| CN116062202A (en) * | 2023-03-20 | 2023-05-05 | 北京瀚科智翔科技发展有限公司 | Combined coaxial double-rotor unmanned aerial vehicle system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206038204U (en) | Many rotor crafts driving system lift capability test device | |
| CN103398793A (en) | Temperature measuring device based on thermocouple cold end compensation technology | |
| CN203025340U (en) | Test fixture detecting system | |
| CN105785131A (en) | Testing device and method for low ohm chip resistors | |
| CN205720565U (en) | A kind of batch testing plate for testing signal condition chip | |
| CN103293566B (en) | Signal detection circuit of atmospheric ozone sonde | |
| CN106908750A (en) | A kind of electric energy meter pulse error detection method and device | |
| CN109445362A (en) | A kind of five-hole probe measuring system of integrated nominal data | |
| CN205785059U (en) | Angular transducer based on hall device | |
| CN208751744U (en) | A kind of temperature sensor AD 590 quick comparison test device | |
| CN203930003U (en) | A kind of simulating signal excitation system for chip detection | |
| CN203798816U (en) | Sensorless direct current brush motor speed measuring device | |
| CN103543741B (en) | A kind of motor controller test box | |
| CN203479906U (en) | Four-wire system Pt100 resistor measuring circuit | |
| CN202494375U (en) | Laser speed measurement instrument of elastic body | |
| CN203053614U (en) | Pressure detection apparatus | |
| CN103455400A (en) | Method for testing SMI2 (intel scalable memory interface 2) signals of internal memory | |
| CN103335706A (en) | Method for online detecting characteristics of engine vibration sensor | |
| CN204346459U (en) | The wafer test system of micro-mechanical gyroscope | |
| CN204228286U (en) | A kind of Moisture Meter temperature collection circuit | |
| CN204065384U (en) | A kind of device detecting hall sensor | |
| CN104316209B (en) | Aero-engine inlet temperature measurement apparatus and its measuring method | |
| CN102520027A (en) | Dual-probe pork humidity detector | |
| CN209028456U (en) | A kind of five-hole probe measuring system of integrated nominal data | |
| CN106814304A (en) | A kind of gyroscope block plate aging testing system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| 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: 20170322 Termination date: 20190927 |