CN110186581A - A kind of aircraft surface temperature sensor and sensor probe - Google Patents
A kind of aircraft surface temperature sensor and sensor probe Download PDFInfo
- Publication number
- CN110186581A CN110186581A CN201910556767.5A CN201910556767A CN110186581A CN 110186581 A CN110186581 A CN 110186581A CN 201910556767 A CN201910556767 A CN 201910556767A CN 110186581 A CN110186581 A CN 110186581A
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- surface temperature
- temperature sensor
- probe
- aircraft surface
- aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/08—Protective devices, e.g. casings
- G01K1/12—Protective devices, e.g. casings for preventing damage due to heat overloading
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
- G01K1/143—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations for measuring surface temperatures
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
A kind of aircraft surface temperature sensor and sensor probe, probe use at least two thermocouple wires；And it is sleeved on the alumina ceramic tube at least two thermocouple wires；And it is sleeved on the probe outer wall on alumina ceramic tube；Two thermocouple wires are at least chosen to weld in one end close to external measured surface；Solder joint, the probe outer wall after welding are flushed close to the equal and external measured surface in the end face of external measured surface.The outer surface aperture of temperature sensor of the present invention is small, it ensure that highdensity point layout, installation recess is small to retain aircraft surface pattern completely, it is designed by structure and guarantees that transducer probe face flushes, fast response time, can adapt to convection environment, it can obtain and original turn to twist characteristic, measurement accuracy is high, belongs to aircraft measurement field.
Description
Technical field
The present invention relates to a kind of aircraft surface temperature sensor and sensor probes, belong to aircraft measurement field.
Background technique
Turn the important phenomenon twisted be during aircraft high-speed flight, has significant impact to flight vehicle aerodynamic power/heat.
Turn to twist generation, development and progradation to obtain aircraft under the conditions of live flying, needs to measure the entirety of aircraft outer surface
Calorifics network parameter mainly includes surface temperature parameter.The measurement end diameter of traditional wall-through surface temperature sensor is at least Ф
11mm, biggish exterior surface dimension be unfavorable for high-density large-area arrangement measuring point, this outer sensor installation recess also can to turn twist
The problems such as phenomenon impacts, and also results in measurement accuracy decline.
Summary of the invention
The technical problem to be solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of aircraft surface temperature
Sensor and sensor probe, probe use at least two thermocouple wires；And it is sleeved on the aluminium oxide at least two thermocouple wires
Ceramic tube；And it is sleeved on the probe outer wall on alumina ceramic tube；Two thermocouple wires are at least chosen close to external tested table
It welds the one end in face；Solder joint, the probe outer wall after welding is close to the equal and external measured surface in the end face of external measured surface
It flushes.The outer surface aperture of temperature sensor of the present invention is small, ensure that highdensity point layout, installation recess is small to make aircraft
Surface topography retains completely, is designed by structure and guarantees that transducer probe face flushes, fast response time, can adapt to convection cell
Border, can obtain it is original turn to twist characteristic, measurement accuracy is high.
The object of the invention is achieved by the following technical programs:
A kind of aircraft surface temperature sensor probe, comprising:
At least two thermocouple wires；And it is sleeved on the alumina ceramic tube at least two thermocouple wires；
And it is sleeved on the probe outer wall on alumina ceramic tube；
Two thermocouple wires are at least chosen to weld in one end close to external measured surface；Solder joint, the probe after welding
Outer wall is flushed with external measured surface close to the end face of external measured surface.
Above-mentioned aircraft surface temperature sensor probe, the thermocouple wire are K-type thermocouple wire.
Above-mentioned aircraft surface temperature sensor probe, the probe outer wall are selected but are not limited to stainless steel material.
Above-mentioned aircraft surface temperature sensor probe, the probe outer wall are equipped with screw thread, for connecting with external structure
It connects.
Above-mentioned aircraft surface temperature sensor probe, overall diameter of the probe outer wall close to external measured surface part
For 2.9mm~11mm.
A kind of aircraft surface temperature sensor further includes and institute using above-mentioned aircraft surface temperature sensor probe
State the sensor gland of probe outer wall connection；The probe outer wall forms cavity after connecting with sensor gland；
At least two thermocouple wires are bound the entrance cavity after being pierced by from alumina ceramic tube；Then it is described at least
Two thermocouple wires are pierced by out of described cavity after bending；
The part after at least two thermocouple wires are banded is set with ceramic fiber insulation layer；The ceramic fiber insulation
It is set with stainless steel shielded layer on layer, at least two thermocouple wires, ceramic fiber insulation layer, the stainless steel shielded layer collectively form
Cable.
Above-mentioned aircraft surface temperature sensor, the cavity are provided with 538 high-temp glues；For fixed at least two described
Thermocouple wire.
Above-mentioned aircraft surface temperature sensor, further includes electric connector；The electric connector and the cable connection.
Above-mentioned aircraft surface temperature sensor, the temperature-measuring range of the aircraft surface temperature sensor is -30 DEG C~+
500 DEG C, the response time is 80ms~90ms.
Above-mentioned aircraft surface temperature sensor, when aircraft surface temperature be no more than 375 DEG C, the aircraft surface temperature
The measurement error for spending sensor is ± 1.5 DEG C；When aircraft surface temperature is more than 375 DEG C, the aircraft surface temperature is passed
The measurement error of sensor is ± 0.004 | t |, wherein | t | it is the thermometric maximum value of the aircraft surface temperature sensor.
The present invention has the following beneficial effects: compared with the prior art
(1) it is highdensity to can be realized aircraft outer surface by the surface temperature sensor of small design by the present invention
Point layout, it is complete that 0.01mm grades of installation recess retains aircraft surface pattern, can obtain and original turn to twist characteristic；
(2) it is designed by structure, guarantees that transducer probe face flushes, response speed reaches 80ms, can adapt to convection current
Environment；
(3) on the one hand the present invention ensure that each group using the structure design of thermocouple wire, alumina ceramic tube, outer wall of popping one's head in
It is flushed after part assembling with aircraft surface, avoids the influence for twisting characteristic to original turn, while improving measurement accuracy；It is another
Aspect greatly reduces the size of probe, is conducive to large area installation application；
(4) present invention probe outer wall has selected 1Cr18Ni9Ti stainless steel, consistent with the material of aircraft outer surface, guarantees
Thermal characteristics it is consistent, furthermore 538 high-temp glues can the long-term work at 500 DEG C, ensure that being reliably fixed for cable；
(5) present invention with standard transducer compare verifying, the results showed that in temperature ramp de, standard transducer and
The measurement temperature difference is no more than ± 1.5 DEG C between tested sensor.The temperature-responsive situation from oscillograph, standard transducer and quilt
It is consistent to survey sensor response curve, ascending curve is overlapped.
Detailed description of the invention
Fig. 1 is 3 surface temperature sensor shape of the embodiment of the present invention and schematic diagram of internal structure.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to implementation of the invention
Mode is described in further detail.
Embodiment 1:
A kind of aircraft surface temperature sensor probe, comprising: at least two thermocouple wires；And it is sleeved at least two heat
Alumina ceramic tube 5 on thermo wires；And it is sleeved on the probe outer wall 6 on alumina ceramic tube 5；
Two thermocouple wires are at least chosen to weld in one end close to external measured surface；Solder joint, the probe after welding
Outer wall 6 is flushed with external measured surface close to the end face of external measured surface.
The thermocouple wire is K-type thermocouple wire；The probe outer wall 6 is selected but is not limited to stainless steel material, the probe
Outer wall 6 is equipped with screw thread, for being connect with external structure, overall diameter of the probe outer wall 6 close to external measured surface part
For 2.9mm~11mm.
Embodiment 2:
A kind of aircraft surface temperature sensor further includes being electrically connected using above-mentioned aircraft surface temperature sensor probe
The sensor gland 3 for connecing device 1, being connect with the probe outer wall 6；The probe outer wall 6 forms chamber after connecting with sensor gland 3
Body；
At least two thermocouple wires are bound after being pierced by from alumina ceramic tube 5 enters the cavity, and binding is using pottery
Porcelain fibrous covering；Then at least two thermocouple wires are pierced by out of described cavity after bending；The cavity is provided with 538
High-temp glue 4；For fixed at least two thermocouple wires.
The part after at least two thermocouple wires are banded is set with ceramic fiber insulation layer；The ceramic fiber insulation
It is set with stainless steel shielded layer on layer, at least two thermocouple wires, ceramic fiber insulation layer, the stainless steel shielded layer collectively form
Cable 2.
The electric connector 1 is connect with the cable 2.
The temperature-measuring range of the aircraft surface temperature sensor be -30 DEG C~+500 DEG C, the response time be 80ms~
90ms.When aircraft surface temperature is no more than 375 DEG C, the measurement error of the aircraft surface temperature sensor is ± 1.5 DEG C；
When aircraft surface temperature is more than 375 DEG C, the measurement error of the aircraft surface temperature sensor is ± 0.004 | t |,
In | t | it is the thermometric maximum value of the aircraft surface temperature sensor.
Embodiment 3:
It 1, is the surface temperature sensor of the present embodiment proposition as shown in Figure 1.Probe outer wall 6 is cylinder step, probe
Overall diameter of the outer wall 6 close to external measured surface part is Ф 3mm.Alumina ceramic tube 5 includes a pair of of K-type thermocouple wire, thermometric
Range is -30 DEG C~+500 DEG C, and measurement accuracy is 375 DEG C or less ± 1.5 DEG C, 375 DEG C or more ± 0.004 | t |.
2, in terms of thermal response, alumina ceramic tube 5 is used inside outer wall 6 of popping one's head in, 5 thermal coefficient of alumina ceramic tube is
20W/mK is in same magnitude with cabin stainless steel, can satisfy the faster response time.Sensor is using the structure for revealing end formula
Form, measurement end pad are exposed, and guarantee that the thermometric response time is most fast.After actual measurement, the response time 80ms of temperature sensor
~90ms.
3, minimum in order to make to influence caused by measured surface, the probe outer wall 6 of probe tip face is concordant with sensitive end pad.
Sensor side centriciput is equipped with the solder joint that pit is used to place thermocouple wire, so that thermocouple wire bonds is in transducer probe face placed in the middle
Position, and guarantee that thermocouple wire bonds are flushed with sensor side head surface.
4, thermocouple wire protection aspect, 5 fusing point of aluminium oxide ceramics are 2050 DEG C, have good insulation performance at high temperature,
Therefore insulating effect is played to thermocouple wire using alumina ceramic tube 5 in wall-through part, while guaranteeing the adaptability under convection environment.It
Thermocouple wire surface is set with ceramic fiber insulation layer afterwards, it is ensured that the good insulation performance at 800 DEG C.Ceramic fiber insulation layer
Outside is woven with stainless steel shielded layer again, forms cable 2, and electric connector 1 is welded in 2 rear end of cable.
5,3 inner space of sensor gland filling, 538 high-temp glue, 4,538 high-temp glue 4 being capable of the long-term work at 500 DEG C.
Outer wall 6 of popping one's head in selects the 1Cr18Ni9Ti stainless steel with aircraft outer surface same material, guarantees that thermal characteristics is consistent, simultaneously
1Cr18Ni9Ti stainless steel has stable antioxygenic property in 800 DEG C~900 DEG C or less air.
It 6, is the consistency for verifying surface temperature sensor measurements and aircraft stainless steel surface temperature, by sensor
Be mounted on one section of stainless steel bar, and tested sensor proximity be welded a standard couple sensor, using alcolhol burner away from
Stainless steel bar is heated at sensor 20mm, monitors the measurement knot of two-way sensor output simultaneously with thermocouple temperature measurement instrument and oscillograph
Fruit.In temperature ramp de, about ± 1.5 DEG C of the temperature difference are measured between standard transducer and tested sensor.From on oscillograph
Temperature-responsive situation, standard transducer and tested sensor response curve are almost the same, and ascending curve can be overlapped.As a result table
Bright, temperature sensor can preferably reflect that the cabin surface temperature as caused by heat transfer changes.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. a kind of aircraft surface temperature sensor probe characterized by comprising
At least two thermocouple wires；And it is sleeved on the alumina ceramic tube (5) at least two thermocouple wires；
And it is sleeved on the probe outer wall (6) on alumina ceramic tube (5)；
Two thermocouple wires are at least chosen to weld in one end close to external measured surface；Solder joint, the probe outer wall after welding
(6) it is flushed with external measured surface close to the end face of external measured surface.
2. a kind of aircraft surface temperature sensor probe according to claim 1, which is characterized in that the thermocouple wire is
K-type thermocouple wire.
3. a kind of aircraft surface temperature sensor probe according to claim 1, which is characterized in that the probe outer wall
(6) it selects but is not limited to stainless steel material.
4. a kind of aircraft surface temperature sensor probe according to claim 1, which is characterized in that the probe outer wall
(6) it is equipped with screw thread, for connecting with external structure.
5. a kind of aircraft surface temperature sensor probe according to claim 1, which is characterized in that the probe outer wall
(6) overall diameter close to external measured surface part is 2.9mm~11mm.
6. a kind of aircraft surface temperature sensor, which is characterized in that using aircraft table described in one of Claims 1 to 5
Face temperature sensor probe further includes the sensor gland (3) connecting with probe outer wall (6)；The probe outer wall (6) with
Cavity is formed after sensor gland (3) connection；
At least two thermocouple wires are bound the entrance cavity after being pierced by from alumina ceramic tube (5)；Then it is described at least
Two thermocouple wires are pierced by out of described cavity after bending；
The part after at least two thermocouple wires are banded is set with ceramic fiber insulation layer；On the ceramic fiber insulation layer
It is set with stainless steel shielded layer, at least two thermocouple wires, ceramic fiber insulation layer, the stainless steel shielded layer collectively form cable
(2)。
7. a kind of aircraft surface temperature sensor according to claim 6, which is characterized in that the cavity is provided with
538 high-temp glues (4)；For fixed at least two thermocouple wires.
8. a kind of aircraft surface temperature sensor according to claim 6, which is characterized in that further include electric connector
(1)；The electric connector (1) connect with the cable (2).
9. a kind of aircraft surface temperature sensor according to claim 6, which is characterized in that the aircraft surface temperature
The temperature-measuring range for spending sensor is -30 DEG C~+500 DEG C, and the response time is 80ms~90ms.
10. a kind of aircraft surface temperature sensor according to claim 6, which is characterized in that
When aircraft surface temperature is no more than 375 DEG C, the measurement error of the aircraft surface temperature sensor is ± 1.5 DEG C；
When aircraft surface temperature is more than 375 DEG C, the measurement error of the aircraft surface temperature sensor is ± 0.004 | t |,
In | t | it is the thermometric maximum value of the aircraft surface temperature sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910556767.5A CN110186581A (en) | 2019-06-25 | 2019-06-25 | A kind of aircraft surface temperature sensor and sensor probe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910556767.5A CN110186581A (en) | 2019-06-25 | 2019-06-25 | A kind of aircraft surface temperature sensor and sensor probe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110186581A true CN110186581A (en) | 2019-08-30 |
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ID=67723418
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910556767.5A Pending CN110186581A (en) | 2019-06-25 | 2019-06-25 | A kind of aircraft surface temperature sensor and sensor probe |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179522A (en) * | 2020-09-14 | 2021-01-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Aircraft surface temperature sensor testing system and testing method |
| CN112577639A (en) * | 2020-10-30 | 2021-03-30 | 北京临近空间飞行器系统工程研究所 | Modularized slice type heat flow identification device and measurement method |
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|---|---|---|---|---|
| SU484413A1 (en) * | 1973-12-29 | 1975-09-15 | Предприятие П/Я В-2877 | Thermocouple |
| CN207019808U (en) * | 2017-07-31 | 2018-02-16 | 久茂自动化(大连)有限公司 | Abrasion resistant thermocouple |
| CN108020333A (en) * | 2017-11-27 | 2018-05-11 | 中国电子科技集团公司第四十八研究所 | A kind of temp probe and assembly method for aircraft |
| CN207610794U (en) * | 2017-12-06 | 2018-07-13 | 陕西电器研究所 | A kind of stratification temperature sensor |
| CN109580162A (en) * | 2018-12-20 | 2019-04-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of high enthalpy flow field heat-flow measurement device under the magnetic environment for forceful electric power |
-
2019
- 2019-06-25 CN CN201910556767.5A patent/CN110186581A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU484413A1 (en) * | 1973-12-29 | 1975-09-15 | Предприятие П/Я В-2877 | Thermocouple |
| CN207019808U (en) * | 2017-07-31 | 2018-02-16 | 久茂自动化(大连)有限公司 | Abrasion resistant thermocouple |
| CN108020333A (en) * | 2017-11-27 | 2018-05-11 | 中国电子科技集团公司第四十八研究所 | A kind of temp probe and assembly method for aircraft |
| CN207610794U (en) * | 2017-12-06 | 2018-07-13 | 陕西电器研究所 | A kind of stratification temperature sensor |
| CN109580162A (en) * | 2018-12-20 | 2019-04-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of high enthalpy flow field heat-flow measurement device under the magnetic environment for forceful electric power |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179522A (en) * | 2020-09-14 | 2021-01-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Aircraft surface temperature sensor testing system and testing method |
| CN112577639A (en) * | 2020-10-30 | 2021-03-30 | 北京临近空间飞行器系统工程研究所 | Modularized slice type heat flow identification device and measurement method |
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Application publication date: 20190830 |
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