CN106052741B - A kind of Multi-axis aircraft sensor batch temperature calibrating installation and its method - Google Patents
A kind of Multi-axis aircraft sensor batch temperature calibrating installation and its method Download PDFInfo
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- CN106052741B CN106052741B CN201610513349.4A CN201610513349A CN106052741B CN 106052741 B CN106052741 B CN 106052741B CN 201610513349 A CN201610513349 A CN 201610513349A CN 106052741 B CN106052741 B CN 106052741B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D18/00—Testing or calibrating apparatus or arrangements provided for in groups G01D1/00 - G01D15/00
- G01D18/008—Testing or calibrating apparatus or arrangements provided for in groups G01D1/00 - G01D15/00 with calibration coefficients stored in memory
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D3/00—Indicating or recording apparatus with provision for the special purposes referred to in the subgroups
- G01D3/028—Indicating or recording apparatus with provision for the special purposes referred to in the subgroups mitigating undesired influences, e.g. temperature, pressure
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Abstract
The invention discloses a kind of Multi-axis aircraft sensor batch temperature calibrating installation and its methods, including controlling bottom plate, Multi-axis aircraft unit is installed on the control bottom plate, the Multi-axis aircraft unit is provided with storage medium on one side, the top and the bottom of another side are respectively equipped with data acquisition indicator light and data processing indicator light, the bottom centre position of the control bottom plate is equipped with power supply, and the both ends of the power supply are respectively equipped with low temperature threshold unit and high temperature threshold value unit.The sensor for the temperature range that the present invention can in batches be customized Multi-axis aircraft is sampled, is preserved automatically.By the Fitting Analysis to capturing data, sensor compensation look-up table at each temperature is made, accurate measured value is provided to the time of running, promotes the precision of flying quality.
Description
Technical field
The present invention relates to sensor fields, and in particular to a kind of Multi-axis aircraft sensor batch temperature calibrating installation and its
Method.
Background technology
With the development of Multi-axis aircraft, to fly in intelligent independent, the application of failure is maked a return voyage etc. is more and more wider, and this
It is higher and higher for the demand of location/velocity etc. accurately controlled.
On the one hand the promotion of precision comes from the embedded type CPU processing capacity of flight control system, selected algorithm
Deng；On the other hand, as the source of data, the precision of sensor determines the reliability of flying quality.On board the aircraft extensively
The sensors such as pressure, angle, speed, acceleration, the compass of application, because of the influence of environment temperature, in same physical characterization
In the case of value, there is variation in the output valve of sensor.
Therefore it is directed to this characteristic, it needs to carry out temperature correction when Multi-axis aircraft dispatches from the factory, to ensure the stability of flight.
In order to promote the flight reliability of Multi-axis aircraft, the precision for promoting sensor is needed.Common way is at present
The transducer range calibration of single is done before flight.
And in practical applications, the output valve of sensor is affected by temperature very big.It is constant in tested physical values
Under the premise of, the output valve diversity ratio of different temperatures lower sensor is larger, inaccurate so as to cause posture/Heading control of flight.
Invention content
It is an object of the invention to overcome problem above of the existing technology, a kind of Multi-axis aircraft sensor batch is provided
Amount temperature calibrating installation and its method.
To realize above-mentioned technical purpose and the technique effect, the invention is realized by the following technical scheme：
A kind of Multi-axis aircraft sensor batch temperature calibrating installation, including bottom plate is controlled, it is installed on the control bottom plate
There are Multi-axis aircraft unit, the Multi-axis aircraft unit to be provided with storage medium, the top and the bottom difference of another side on one side
Indicator light and data processing indicator light are acquired equipped with data, the bottom centre position of the control bottom plate is equipped with power supply, the electricity
The both ends in source are respectively equipped with low temperature threshold unit and high temperature threshold value unit.
Further, the Multi-axis aircraft unit has N number of and N to be more than or equal to 2.
Further, the storage medium is for each Multi-axis aircraft sensor within the scope of storage temperature constant interval
Original value, the data acquisition indicator light and the data processing indicator light indicate current operation mode.
Preferably, the control bottom plate is to each Multi-axis aircraft unit power supply, and passes through the low temperature threshold list
Multi-axis aircraft unit described in the interface notification of the first and described high temperature threshold value unit carries out corresponding operating, the low temperature threshold unit
It is used to specify temperature surveying range with the interface of the high temperature threshold value unit.
A kind of Multi-axis aircraft sensor batch temperature calibration method, which is characterized in that include the following steps：
Step 1）Multi-axis aircraft unit is inserted into control bottom plate, remains powered off state；
Step 2）It controls and sets low temperature threshold/high temperature threshold value on bottom plate, be denoted as T_LOW and T_HIGH；
Step 3）Control bottom plate is placed in temperature switch board；
Step 4）Adjust temperature switch board temperature curve, set its temperature changing trend as：
（a）Cool to T_LOW with rapid rate hereinafter, consider surplus, should be lower than the T_LOW number of degrees to ensure examining system energy
Enough reach T_LOW；
（b）It keeps T_LOW 1 minute, gives system temperature stabilization time；
（c）T_HIGH considerations above is gradually warming up to jogging speed to surplus, it should be higher than the T_HIGH number of degrees to be measured to ensure
System can reach T_HIGH.
Step 5）Control bottom plate monitoring reaches T_LOW to temperature, opens power supply, controls bottom plate（1）Notify Multi-axis aircraft
Unit enters calibration mode, and Multi-axis aircraft unit confirms rear indicator light flicker；
Step 6）During temperature switch board slowly heats up, each Multi-axis aircraft unit recycles remains stationary state,
Each sensor values are acquired, are written in storage medium with the combination of temperature, sensor number, sensor values；
Step 7）After system temperature reaches T_HIGH, control bottom plate notifies each Multi-axis aircraft unit to stop data and adopt
Collection, into data analysis phase；
Step 8）After Multi-axis aircraft unit confirms, switching signal lamp instruction, into data analysis phase；
Step 9）After each Multi-axis aircraft unit completes data analysis and temperature compensation table establishment, two indicator lights are kept
It is always on and notifies user；
Step 10）After the completion of all Multi-axis aircraft unit indicator lights indicate to operate, temperature switch board is opened, takes out and surveys
Test system completes this batch operation.
Beneficial effects of the present invention:
The sensor for the temperature range that the present invention can in batches be customized Multi-axis aircraft is sampled, is preserved automatically.It is logical
The Fitting Analysis to capturing data is crossed, sensor compensation look-up table at each temperature is made, is provided to the time of running accurate
Measured value, promote the precision of flying quality.
Description of the drawings
Fig. 1 is Multi-axis aircraft sensor batch temperature calibrating installation schematic diagram of the present invention；
Fig. 2 is that Multi-axis aircraft sensor batch temperature calibrating installation of the present invention is placed on the signal in temperature switch board
Figure；
Fig. 3 is that the control bottom plate monitoring of Multi-axis aircraft sensor batch temperature calibrating installation of the present invention reaches to temperature
" low temperature threshold " state diagram；
Fig. 4 is that the temperature switch board of Multi-axis aircraft sensor batch temperature calibrating installation of the present invention is started to warm up and respectively waited for
It calibrates aircraft and carries out sensor data acquisition and storage schematic diagram；
Fig. 5 is that the control bottom plate monitoring of Multi-axis aircraft sensor batch temperature calibrating installation of the present invention reaches to temperature
Each Multi-axis aircraft unit is notified to carry out data processing schematic diagram when " high temperature threshold value "；
Fig. 6 is that the Multi-axis aircraft unit of Multi-axis aircraft sensor batch temperature calibrating installation of the present invention completes each sensing
Device temperature correction schematic diagram.
Figure label explanation：1, control bottom plate, 2, Multi-axis aircraft unit, 3, storage medium, 4, data acquire indicator light,
5, data processing indicator light, 6, power supply, 7, low temperature threshold unit, 8, high temperature threshold value unit.
Specific implementation mode
It is below with reference to the accompanying drawings and in conjunction with the embodiments, next that the present invention will be described in detail.
As shown in Figure 1, a kind of Multi-axis aircraft sensor batch temperature calibrating installation, which is characterized in that including controlling bottom
Plate 1 is equipped with Multi-axis aircraft unit 2 on the control bottom plate 1, and the Multi-axis aircraft unit 2 is provided with storage on one side
The top and the bottom of medium 3, another side are respectively equipped with data acquisition indicator light 4 and data processing indicator light 5, the control bottom plate 1
Bottom centre position be equipped with power supply 6, the both ends of the power supply are respectively equipped with low temperature threshold unit 7 and high temperature threshold value unit 8.
Further, the Multi-axis aircraft unit 2 has N number of and N to be more than or equal to 2.
Further, the storage medium 3 is for each Multi-axis aircraft sensor within the scope of storage temperature constant interval
Original value, data acquisition indicator light 4 and the data processing indicator light 5 indicate current operation mode.
Preferably, the control bottom plate 1 is powered to each Multi-axis aircraft unit 2, and passes through the low temperature threshold
Multi-axis aircraft unit 2 described in the interface notification of unit 7 and the high temperature threshold value unit 8 carries out corresponding operating, the low temperature threshold
The interface of value cell 7 and the high temperature threshold value unit 8 is used to specify temperature surveying range.
A kind of Multi-axis aircraft sensor batch temperature calibration method, includes the following steps：
Step 1）Multi-axis aircraft unit 2 is inserted into control bottom plate 1, remains powered off state；
Step 2）It controls and sets low temperature threshold/high temperature threshold value on bottom plate 1, be denoted as T_LOW and T_HIGH；
Step 3）Control bottom plate 1 is placed in temperature switch board as shown in Figure 2；
Step 4）Adjust temperature switch board temperature curve, set its temperature changing trend as：
（a）Cool to T_LOW with rapid rate hereinafter, consider surplus, should be lower than the T_LOW number of degrees to ensure examining system energy
Enough reach T_LOW；
（b）It keeps T_LOW 1 minute, gives system temperature stabilization time；
（c）T_HIGH considerations above is gradually warming up to jogging speed to surplus, it should be higher than the T_HIGH number of degrees to be measured to ensure
System can reach T_HIGH.
Step 5）Control bottom plate 1 detects that temperature reaches T_LOW, opens power supply 6 as shown in figure 3, control bottom plate 1 notifies
Multi-axis aircraft unit 2 enters calibration mode, and Multi-axis aircraft unit 2 confirms rear indicator light flicker；
Step 6）During temperature switch board slowly heats up, each Multi-axis aircraft unit 2 recycles remains stationary state,
Each sensor values are acquired, are written in storage medium 3 with the combination of temperature, sensor number, sensor values, as shown in Figure 4；
Step 7）After system temperature reaches T_HIGH, control bottom plate 1 notifies each Multi-axis aircraft unit 2 to stop data and adopt
Collection, into data analysis phase；
Step 8）As shown in figure 5, after Multi-axis aircraft unit 2 confirms, switching signal lamp instruction, into data analysis rank
Section；
Step 9）After each Multi-axis aircraft unit 2 completes data analysis and temperature compensation table establishment, two instructions are kept
Lamp, which is always on, notifies user；
Step 10）After the completion of all 2 indicator lights of Multi-axis aircraft unit indicate to operate, temperature switch board is opened, is taken out
Test system, completes this batch operation.
Embodiment：
The establishment of temperature compensation table
In above process, each Multi-axis aircraft unit 2 has been automatically performed the acquisition and analysis of data, wherein for fortune
What the row moment had critical significance is temperature compensation table.
Due to remaining static in a calibration process, the corresponding actual physical value of each sensor is constant, passes through at this time
The sensor sample value under different temperatures is acquired, following table 1 can be obtained (for purposes of illustration only, it is analysis object to take sensor 1
And acquire 3 data at each temperature).
To the data average treatment at each temperature, following table 2 is obtained：
In the aircraft time of running, for some sensor, sensor values exists centainly with actual physical value
Functional operation relationship（At typical temperature, when such as 20 degree）：
Val_real=f(val_sensor@20°C).
Assuming that temperature at this time is t. (T_LOW<= t <= T_HIGH)
According to the temperature correction table of table 2, values of the current sensor to required temperature when can be more easily converted：
val_sensor@20°C=val_sensor@t°C + (0x180–0x202)..
Formula f as above (20 °C of val_sensor@) is further substituted into, accurate val_real values can be obtained.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, any made by repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (4)
1. a kind of Multi-axis aircraft sensor batch temperature calibrating installation, which is characterized in that including controlling bottom plate（1）, the control
Bottom plate processed（1）On Multi-axis aircraft unit is installed（2）, the Multi-axis aircraft unit（2）Be provided with storage medium on one side
（3）, the top and the bottom of another side are respectively equipped with data acquisition indicator light（4）With data processing indicator light（5）, the control bottom plate
（1）Bottom centre position be equipped with power supply（6）, the both ends of the power supply are respectively equipped with low temperature threshold unit（7）And high temperature threshold value
Unit（8）；
Further include a kind of Multi-axis aircraft sensor batch temperature calibration method, this approach includes the following steps：
Step 1）By Multi-axis aircraft unit（2）It is inserted into control bottom plate（1）, remain powered off state；
Step 2）Control bottom plate（1）Upper setting low temperature threshold/high temperature threshold value, is denoted as T_LOW and T_HIGH；
Step 3）Bottom plate will be controlled（1）It is placed in temperature switch board；
Step 4）Adjust temperature switch board temperature curve, set its temperature changing trend as：
（a）Cool to T_LOW with rapid rate hereinafter, consider surplus, should be lower than the T_LOW number of degrees to ensure that examining system can reach
To T_LOW；
（b）It keeps T_LOW 1 minute, gives system temperature stabilization time；
（c）T_HIGH considerations above is gradually warming up to jogging speed to surplus, it should be higher than the T_HIGH number of degrees to ensure examining system
T_HIGH can be reached；
Step 5）Control bottom plate（1）It detects that temperature reaches T_LOW, opens power supply（6）, control bottom plate（1）Notify multiaxis flight
Device unit（2）Into calibration mode, Multi-axis aircraft unit（2）Confirm rear indicator light flicker；
Step 6）During temperature switch board slowly heats up, each Multi-axis aircraft unit（2）Remains stationary state is recycled, is adopted
Collect each sensor values, storage medium is written with the combination of temperature, sensor number, sensor values（3）In；
Step 7）After system temperature reaches T_HIGH, bottom plate is controlled（1）Notify each Multi-axis aircraft unit（2）Stop data adopting
Collection, into data analysis phase；
Step 8）Multi-axis aircraft unit（2）After confirmation, switching signal lamp instruction, into data analysis phase；
Step 9）Each Multi-axis aircraft unit（2）After completing data analysis and temperature compensation table establishment, two indicator lights are kept
It is always on and notifies user；
Step 10）In all Multi-axis aircraft units（2）After the completion of indicator light instruction operation, temperature switch board is opened, takes out and surveys
Test system completes this batch operation.
2. Multi-axis aircraft sensor batch temperature calibrating installation according to claim 1, which is characterized in that the multiaxis
Aircraft unit（2）There is N number of and N to be more than or equal to 2.
3. Multi-axis aircraft sensor batch temperature calibrating installation according to claim 1, which is characterized in that the storage
Medium（3）For the original value of each Multi-axis aircraft sensor within the scope of storage temperature constant interval, the data acquisition refers to
Show lamp（4）With the data processing indicator light（5）Indicate current operation mode.
4. Multi-axis aircraft sensor batch temperature calibrating installation according to claim 1, which is characterized in that the control
Bottom plate（1）To each Multi-axis aircraft unit（2）Power supply, and pass through the low temperature threshold unit（7）With the high temperature threshold
Value cell（8）Interface notification described in Multi-axis aircraft unit（2）Carry out corresponding operating, the low temperature threshold unit（7）And institute
State high temperature threshold value unit（8）Interface be used to specify temperature surveying range.
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| CN106052741B true CN106052741B (en) | 2018-07-20 |
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| CN204439112U (en) * | 2015-01-29 | 2015-07-01 | 东莞市李群自动化技术有限公司 | A kind of calibration detects tool |
| CN204831625U (en) * | 2015-05-20 | 2015-12-02 | 安徽驰程仪表科技有限公司 | Batch temperature transmitter calibration operation platform |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592466B (en) * | 2013-12-03 | 2015-05-20 | 中北大学 | Automatic lot sizing static rolling testing device for MEMS acceleration sensor |
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2016
- 2016-07-04 CN CN201610513349.4A patent/CN106052741B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102147264A (en) * | 2010-12-30 | 2011-08-10 | 东莞易步机器人有限公司 | Method for calibrating gyroscope modules in batch |
| CN103017785A (en) * | 2011-09-26 | 2013-04-03 | 东莞易步机器人有限公司 | Gyroscope sensor calibrating device and calibrating method |
| CN103776468A (en) * | 2014-02-21 | 2014-05-07 | 深圳乐行天下科技有限公司 | Gyroscope and accelerometer batch calibration device and gyroscope and accelerometer batch calibration method |
| CN204439112U (en) * | 2015-01-29 | 2015-07-01 | 东莞市李群自动化技术有限公司 | A kind of calibration detects tool |
| CN204831625U (en) * | 2015-05-20 | 2015-12-02 | 安徽驰程仪表科技有限公司 | Batch temperature transmitter calibration operation platform |
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| CN106052741A (en) | 2016-10-26 |
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