CN201716128U - Temperature measuring device for outer surface of high-speed aircraft - Google Patents
Temperature measuring device for outer surface of high-speed aircraft Download PDFInfo
- Publication number
- CN201716128U CN201716128U CN2010202081231U CN201020208123U CN201716128U CN 201716128 U CN201716128 U CN 201716128U CN 2010202081231 U CN2010202081231 U CN 2010202081231U CN 201020208123 U CN201020208123 U CN 201020208123U CN 201716128 U CN201716128 U CN 201716128U
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- heat resistant
- aircraft
- solar heat
- sensing head
- heat protection
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Abstract
The utility model provides a temperature measuring device for the outer surface of a high-speed aircraft. The temperature measuring device comprises a temperature sensor, wherein, a temperature sensor body is installed on a casing of the high-speed aircraft through a cushion block; a sensing head of the temperature sensor extends out of a sensor hole formed on the casing of the aircraft; the top end of the sensing head is positioned inside a heat resistant layer outside the casing of the aircraft, wherein, the top end positioned inside the heat resistant layer ranges from 0.8 to 1mm; a heat resistant annulated column body is positioned between the periphery of the sensing head and the sensor hole in a surrounding manner; and the top end of the sensing head seals up an orifice of the sensor hole through a heat resistant thin sheet. The thickness of the heat resistant thin sheet ranges from 0.8 to 1mm, and the sum of the height of the heat resistant annulated column body and the thickness of the heat resistant thin sheet equals to the thickness of the heat resistant layer outside the casing of the aircraft. The heat resistant thin sheet and the heat resistant annulated column body are made of the same heat resistant material with the heat resistant layer, and are bonded to the heat resistant layer through the same high-temperature resistance glue mutually.
Description
Technical field
The utility model relates to a kind of high-speed aircraft hull-skin temperature measurement mechanism, particularly a kind of device of under the high-speed flight state sensor being damaged and can accurately measure the dynamic variable quantity of outside wall temperature of preventing.
Background technology
When high-speed aircraft flew in atmosphere, because windstream and head are subjected to unexpected compression when meeting, thereby local air flow was blocked; Simultaneously, air has viscosity, is also blocked with the contacted air-flow in surface, and both of these case all makes gas velocity greatly reduce, and makes the kinetic energy in the original air-flow change heat energy into.Thereby the gas flow temperature around the aircraft can raise, and theoretical analysis and test show, square being directly proportional of the temperature in the body airflow on surface boundary layer and gas velocity.
For the thermal environment of giving structural design and equipment provides reliable basis, present stage is mainly by Theoretical Calculation and two kinds of methods of sensor measurement.Under actual conditions, determine the aircraft wall surface temperature mainly by Theoretical Calculation, final, obtain measurement telemetry by flight test, check and improve thermal design.
In reality in-flight, main by stick the temperature that temperature sensor comes the survey room inwall at inwall, must proofread and correct through pneumatic hot calculating but the inside and outside wall temperature difference is big; By processing cabin section, the sensor sensing head is spilt cabin section outside surface, measure its temperature, but the method there are two defectives: one, sensing head is exposed to the outside, and heat shield and air-flow ablated easily when flight destroy, thereby lose temp sensing function; Two, the temperature that sensing head is measured not is the temperature of cabin section outer wall, but the environment temperature of air-flow.
Summary of the invention
The purpose of this utility model is to provide a kind of temperature measuring equipment of high-speed aircraft outer surface structure, can measure the temperature of outer wall accurately and reliably, and avoids the destroyed and indeterminable problem of sensor.
The technical scheme that the utility model is dealt with problems: high-speed aircraft hull-skin temperature measurement mechanism of the present utility model comprises temperature sensor, its temperature sensor body is installed on the high-speed aircraft housing by cushion block, the sensing head of temperature sensor is stretched out by the gauge hole on the aircraft casing, the sensing head top is positioned at the outer heat shield 0.8mm～1mm of aircraft casing, being surrounded by the solar heat protection ring cylinder between the periphery of sensing head and the gauge hole, is obturaged the aperture of gauge hole by the solar heat protection thin slice in the sensing head top.
The thickness of described solar heat protection thin slice is between 0.8mm～1mm, and the height of solar heat protection ring cylinder adds that the thickness of solar heat protection thin slice equals the thickness of the outer heat shield of aircraft casing.
Described solar heat protection thin slice uses identical heat insulation material with the solar heat protection ring cylinder with heat shield, and it is bonding to use identical high-temperature plastic to carry out each other.
Advantage of the present utility model: solar heat protection thin slice and solar heat protection ring cylinder are selected for use and the heat shield identical materials, have avoided heat conducting otherness between the different materials, so can measure the temperature of heat shield outside surface accurately; Show that through test the solar heat protection thin slice that 0.8mm～1mm is thick during flight can be not ablated simultaneously,, can not destroyed by air-flow and other object so solar heat protection thin slice and solar heat protection cylinder can be protected sensing head; Because in 1mm, the measurement data that obtains hardly differs with outer wall sensing head apart from outer wall, can conveniently eliminate its otherness through aerothermal calculating; At last, this mounting structure can very firm fixation of sensor.
The utility model delicate structure can be widely used in the aircraft surface temperature survey, has higher utility.
Description of drawings
Fig. 1 is the structural representation of surface temperature measurement device.
Embodiment
Below in conjunction with accompanying drawing and example the utility model is described in further detail.
As shown in Figure 1, the temperature sensor body 1 of the utility model high-speed aircraft hull-skin temperature measurement mechanism is installed on the high-speed aircraft housing 7 by cushion block 6, the sensing head 2 of temperature sensor is stretched out by the gauge hole 7a on the aircraft casing 7, sensing head 2 tops are positioned at the heat shield 5 0.8mm～1mm outside the aircraft casing 7, being surrounded by solar heat protection ring cylinder 4 between the periphery of sensing head 2 and the gauge hole 7a, is obturaged the aperture of gauge hole 7a by solar heat protection thin slice 3 in sensing head 2 tops.
The thickness of described solar heat protection thin slice 3 is between 0.8mm～1mm, and the height of solar heat protection ring cylinder 4 adds that the thickness of solar heat protection thin slice 3 equals the thickness of the heat shield 5 outside the aircraft casing 7.
Described solar heat protection thin slice 3 uses identical heat insulation material with solar heat protection ring cylinder 4 with heat shield 5, and it is bonding to use identical high-temperature plastic to carry out each other.The measuring error that is not subjected to materials variances when guaranteeing sensor measurement and is caused.Wherein the thickness of solar heat protection thin slice is 0.8mm～1mm, the gross thickness of solar heat protection thin slice and solar heat protection cylinder and the consistency of thickness of heat shield.
Wherein, sensing head 2 protecting by solar heat protection thin slice 3 and solar heat protection ring cylinder 4.
During sensor installation, also need cushion block 6 as shown in Figure 1, at first the housing 7 of cushion block 6 and aircraft is threaded, and sensor body 1 and cushion block 6 be by being threaded then, thereby realizes the installation of sensor.
Then solar heat protection ring cylinder 4 is put into gauge hole 7a and carried out bondingly, 3 couples of gauge hole 7a of solar heat protection thin slice are sealed and carry out bonding getting final product.The 8th, temperature sensor scheme.
Data to recording need to proofread and correct through pneumatic heat calculating, to eliminate the error that its solar heat protection thin slice is brought at last.Can be when flying with under the data storage of measuring.
Claims (3)
1. high-speed aircraft hull-skin temperature measurement mechanism, comprise temperature sensor, it is characterized in that: temperature sensor body (1) is installed on the high-speed aircraft housing (7) by cushion block (6), the sensing head of temperature sensor (2) is stretched out by the gauge hole (7a) on the aircraft casing (7), sensing head (2) top is positioned at outer heat shield (5) 0.8mm～1mm of aircraft casing (7), being surrounded by solar heat protection ring cylinder (4) between the periphery of sensing head (2) and the gauge hole (7a), is obturaged the aperture of gauge hole (7a) by solar heat protection thin slice (3) in sensing head (2) top.
2. high-speed aircraft hull-skin temperature measurement mechanism according to claim 1, it is characterized in that: the thickness of solar heat protection thin slice (3) is between 0.8mm～1mm, and the height of solar heat protection ring cylinder (4) adds that the thickness of solar heat protection thin slice (3) equals the thickness of the outer heat shield (5) of aircraft casing (7).
3. high-speed aircraft hull-skin temperature measurement mechanism according to claim 1 and 2, it is characterized in that: solar heat protection thin slice (3) uses identical heat insulation material with solar heat protection ring cylinder (4) with heat shield (5), and it is bonding to use identical high-temperature plastic to carry out each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202081231U CN201716128U (en) | 2010-05-25 | 2010-05-25 | Temperature measuring device for outer surface of high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202081231U CN201716128U (en) | 2010-05-25 | 2010-05-25 | Temperature measuring device for outer surface of high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201716128U true CN201716128U (en) | 2011-01-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202081231U Expired - Fee Related CN201716128U (en) | 2010-05-25 | 2010-05-25 | Temperature measuring device for outer surface of high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201716128U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103017927A (en) * | 2012-11-28 | 2013-04-03 | 中国商用飞机有限责任公司 | Mounting method for mounting temperature thermocouple on inner surface of skin |
| CN103821938A (en) * | 2013-09-30 | 2014-05-28 | 中国人民解放军国防科学技术大学 | Rudderpost thermal sealing structure |
| CN104483029A (en) * | 2014-12-01 | 2015-04-01 | 北京振兴计量测试研究所 | Temperature measuring structure applicable to high-temperature environment and installation method thereof |
| CN105444918A (en) * | 2015-12-10 | 2016-03-30 | 中国电子科技集团公司第四十八研究所 | Temperature detecting device for aircraft |
| CN105865658A (en) * | 2015-01-23 | 2016-08-17 | 北京空间飞行器总体设计部 | Ground calibration method of miniature sheathed thermocouple |
| CN106644131A (en) * | 2016-11-14 | 2017-05-10 | 北京临近空间飞行器系统工程研究所 | Thermal protection layer interlayer temperature and carburization degree composite measuring device and method |
| 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 |
| 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 |
-
2010
- 2010-05-25 CN CN2010202081231U patent/CN201716128U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103017927A (en) * | 2012-11-28 | 2013-04-03 | 中国商用飞机有限责任公司 | Mounting method for mounting temperature thermocouple on inner surface of skin |
| CN103821938A (en) * | 2013-09-30 | 2014-05-28 | 中国人民解放军国防科学技术大学 | Rudderpost thermal sealing structure |
| CN104483029A (en) * | 2014-12-01 | 2015-04-01 | 北京振兴计量测试研究所 | Temperature measuring structure applicable to high-temperature environment and installation method thereof |
| CN105865658A (en) * | 2015-01-23 | 2016-08-17 | 北京空间飞行器总体设计部 | Ground calibration method of miniature sheathed thermocouple |
| CN105865658B (en) * | 2015-01-23 | 2018-08-07 | 北京空间飞行器总体设计部 | A kind of ground scaling method of miniature armoured thermocouple |
| CN105444918A (en) * | 2015-12-10 | 2016-03-30 | 中国电子科技集团公司第四十八研究所 | Temperature detecting device for aircraft |
| CN106644131A (en) * | 2016-11-14 | 2017-05-10 | 北京临近空间飞行器系统工程研究所 | Thermal protection layer interlayer temperature and carburization degree composite measuring device and method |
| 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 |
| 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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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110119 Termination date: 20130525 |