CN105444918A - Temperature detecting device for aircraft - Google Patents
Temperature detecting device for aircraft Download PDFInfo
- Publication number
- CN105444918A CN105444918A CN201510910264.5A CN201510910264A CN105444918A CN 105444918 A CN105444918 A CN 105444918A CN 201510910264 A CN201510910264 A CN 201510910264A CN 105444918 A CN105444918 A CN 105444918A
- Authority
- CN
- China
- Prior art keywords
- temperature
- housing
- detecting device
- aircraft
- core body
- 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.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
Abstract
The invention discloses a temperature detecting device for an aircraft. The temperature detecting device for an aircraft comprises a housing, a temperature-sensitive core and a fixed assembly, wherein one end of the housing is provided with a fastening assembly which is fastened on a detected surface; a line hole is formed in one end of the housing and is used for letting a signal line of the temperature-sensitive core to penetrate; a mounting surface which is matched with the detected surface is arranged on the housing; an opening is formed in the mounting surface; the line hole is connected with the opening; the temperature-sensitive core is arranged on the fixed assembly; the fixed assembly is arranged in the opening, and one end of the fixed assembly stretches into the line hole; and the line hole and the opening are filled with high temperature glue. The temperature detecting device for an aircraft has the advantages of being simple and reliable in structure, being high in the thermal response speed, and being high in antivibration performance.
Description
Technical field
The present invention relates generally to space flight and aviation technical field, refers in particular to a kind of temperature-detecting device for aircraft.
Background technology
The aircraft such as guided missile need the temperature implementing monitoring inner surface of outer cover in flight course, for the temperature health environment of aircraft provides effective Monitoring Data.Aircraft have in flight course temperature rise be exceedingly fast, temperature is high and shake the features such as violent, existing temperature sensor temp probe generally adopts closure casing and overall high-temp glue of filling with to encapsulate, but by high-temp glue and housing heat, the restriction that response coefficient is too small, cannot meet the requirement that aircraft skin internal surface temperature responds fast; Or adopt the form of nude film directly temperature-sensitive core body high-temp glue to be pasted onto measuring point, the problem of response fast can be solved so to a certain extent, but the problems such as antivibration moment and instability can be brought.
Summary of the invention
The technical problem to be solved in the present invention is just: the technical matters existed for prior art, the invention provides a kind of simple and reliable for structure, thermal response speed is fast and anti-seismic performance is good temperature-detecting device for aircraft.
For solving the problems of the technologies described above, the technical scheme that the present invention proposes is:
A kind of temperature-detecting device for aircraft, comprise housing, temperature-sensitive core body and fixation kit, one end of described housing is provided with the fastening assembly for being fastened on tested surface, one end of described housing is provided with the string holes of the signal wire for wearing temperature-sensitive core body, described housing is provided with the installed surface matched with tested surface, described installed surface is provided with opening, described string holes and described open communication, described temperature-sensitive core body is installed on described fixation kit, described fixation kit is arranged in opening and one end stretches in described string holes, all high-temp glue is filled with in described string holes and opening.
Further improvement as technique scheme:
Described fixation kit comprises body, the through hole passed for signal wire is provided with in described body, the periphery of one end of described body is provided with a groove, described temperature-sensitive core body is glued in described groove, and the temperature-sensitive face of described temperature-sensitive core body is parallel and higher than described installed surface.
The external diameter of described body and the string holes internal diameter of described housing match.
Described body is ceramic pipe.
One end that described housing is provided with string holes is provided with the line ball pipe for fixing described signal wire.
The installed surface of described housing scribbles glue-line, and described glue-line is mutually concordant with the temperature-sensitive face of described temperature-sensitive core body.
Described fastening assembly comprises the mounting hole being located at described shell one end, is provided with bolt or screw in described mounting hole.
Compared with prior art, the invention has the advantages that:
Temperature-detecting device for aircraft of the present invention, carries out thermometric, therefore, it is possible to rapid thermal response owing to directly being contacted with tested surface in the temperature-sensitive face of temperature-sensitive core body; Temperature-sensitive core body is fixed on fixation kit in addition, and fixation kit is installed in housing by high-temp glue is fastening again, and housing is fastened on tested surface again, ensure that anti-seismic performance.
Accompanying drawing explanation
Fig. 1 is sectional structure schematic diagram of the present invention.
Fig. 2 is the perspective view of middle shell of the present invention.
Fig. 3 is the perspective view of fixation kit in the present invention.
Number in the figure represents: 1, housing; 11, installed surface; 12, opening; 13, string holes; 14, line ball pipe; 2, fixation kit; 21, body; 22, groove; 23, through hole; 3, temperature-sensitive core body; 31, signal wire; 4, fastening assembly; 41, mounting hole; 5, high-temp glue.
Embodiment
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As shown in Figure 1 to Figure 3, the temperature-detecting device for aircraft of the present embodiment, comprise housing 1, temperature-sensitive core body 3 and fixation kit 2, one end of housing 1 is provided with the fastening assembly 4 for being fastened on by housing 1 on tested surface, one end of housing 1 is provided with the string holes 13 of the signal wire 31 for wearing temperature-sensitive core body 3, housing 1 is provided with the installed surface 11(surface level matched with tested surface), installed surface 11 is provided with opening 12, string holes 13 is communicated with opening 12, temperature-sensitive core body 3 is installed on fixation kit 2, fixation kit 2 is arranged in opening 12 and one end stretches in string holes 13, and be all filled with high-temp glue 5 in string holes 13 and opening 12, thus fixation kit 2 is fixed in housing 1.Temperature-detecting device for aircraft of the present invention, directly contacts the temperature-sensitive face of temperature-sensitive core body 3 with tested surface and carries out thermometric, fast response time, quick and precisely can measure the actual temperature of tested surface; Each parts are fastening installation in addition, and namely temperature-sensitive core body 3 is fixed on fixation kit 2, and fixation kit 2 is fixed on housing 1, and housing 1 is fastened on tested surface, simple and reliable for structure, thus ensure anti-seismic performance.
As shown in figures 1 and 3, in the present embodiment, fixation kit 2 comprises body 21, the through hole 23 passed for signal wire 31 is provided with in body 21, the periphery of one end of body 21 is provided with a groove 22, temperature-sensitive core body 3 is glued in groove 22, and the temperature-sensitive face of temperature-sensitive core body 3 is parallel and higher than installed surface 11, can ensure that the temperature-sensitive face of temperature-sensitive core body 3 reliably contacts with tested surface.The external diameter of body 21 and string holes 13 internal diameter of housing 1 match, thus ensure the fastness that fixation kit 2 is installed further.Body 21 is ceramic pipe in addition, can withstand high temperatures, and ensures the insulativity of temperature-sensitive core body 3 and signal wire 31 thereof.
As depicted in figs. 1 and 2, in the present embodiment, one end that housing 1 is provided with string holes 13 is provided with the line ball pipe 14 for fixed signal line 31, after assembling, press line ball pipe 14 by Crimping Pliers, signal wire 31 can be fixed, improve integrally-built reliability further.The installed surface 11 of housing 1 in addition scribbles glue-line (not shown), and glue-line is mutually concordant with the temperature-sensitive face of temperature-sensitive core body 3, thus housing 1 and tested surface entirety contacts, its shock resistance of raising further.
In the present embodiment, fastening assembly 4 comprises the mounting hole 41 being located at housing 1 one end, is provided with bolt or screw (not shown) in mounting hole 41, when mounted, is fastened on tested surface by bolt or screw by housing 1, easy for installation.
Assembling process is as follows: signal wire 31 entirety inserted from line ball pipe 14, pass from opening 12 after the string holes 13 of housing 1, then two of signal wire 31 cores and insulation course are each passed through the through hole 23 of ceramic pipe, the lead-in wire of temperature-sensitive core body 3 is welded on two cores by the mode of upset butt welding, appropriate high-temp glue is applied at groove 22 place of ceramic pipe, above temperature-sensitive core body 3 is pasted onto, again according to the signal wire 31 of the outline bending temperature-sensitive core body 3 of ceramic pipe, signal wire 31 is made to be close to the end face of ceramic pipe, then high-temp glue 5 is poured into encapsulating device at housing 1 internal voids place, again the outlet direction propelling certain distance of ceramic pipe toward string holes 13, one end of ceramic pipe is made to stretch in string holes 13, finally make high-temp glue 5 surface concordant with the installed surface 11 of housing 1, and the temperature-sensitive face of temperature-sensitive core body 3 exceeds installed surface 11 certain altitude, high-temp glue 5 compresses line ball pipe 14 with Crimping Pliers after solidifying completely again, whole device has assembled.
Below be only the preferred embodiment of the present invention, protection scope of the present invention be not only confined to above-described embodiment, all technical schemes belonged under thinking of the present invention all belong to protection scope of the present invention.It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principles of the present invention, should be considered as protection scope of the present invention.
Claims (7)
1. the temperature-detecting device for aircraft, it is characterized in that, comprise housing (1), temperature-sensitive core body (3) and fixation kit (2), one end of described housing (1) is provided with the fastening assembly (4) for being fastened on tested surface, one end of described housing (1) is provided with the string holes (13) of the signal wire (31) for wearing temperature-sensitive core body (3), described housing (1) is provided with the installed surface (11) matched with tested surface, described installed surface (11) is provided with opening (12), described string holes (13) is communicated with described opening (12), described temperature-sensitive core body (3) is installed on described fixation kit (2), described fixation kit (2) is arranged in opening (12) and one end stretches in described string holes (13), high-temp glue (5) is all filled with in described string holes (13) and opening (12).
2. the temperature-detecting device for aircraft according to claim 1, it is characterized in that, described fixation kit (2) comprises body (21), the through hole (23) passed for signal wire (31) is provided with in described body (21), the periphery of one end of described body (21) is provided with a groove (22), described temperature-sensitive core body (3) is glued in described groove (22), and the temperature-sensitive face of described temperature-sensitive core body (3) is parallel and higher than described installed surface (11).
3. the temperature-detecting device for aircraft according to claim 2, is characterized in that, the external diameter of described body (21) and string holes (13) internal diameter of described housing (1) match.
4. the temperature-detecting device for aircraft according to Claims 2 or 3, is characterized in that, described body (21) is ceramic pipe.
5. the temperature-detecting device for aircraft as claimed in any of claims 1 to 3, is characterized in that, one end that described housing (1) is provided with string holes (13) is provided with the line ball pipe (14) for fixing described signal wire (31).
6. the temperature-detecting device for aircraft as claimed in any of claims 1 to 3, is characterized in that, the installed surface (11) of described housing (1) scribbles glue-line, and described glue-line is mutually concordant with the temperature-sensitive face of described temperature-sensitive core body (3).
7. the temperature-detecting device for aircraft as claimed in any of claims 1 to 3, it is characterized in that, described fastening assembly (4) comprises the mounting hole (41) being located at described housing (1) one end, and described mounting hole is provided with bolt or screw in (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510910264.5A CN105444918A (en) | 2015-12-10 | 2015-12-10 | Temperature detecting device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510910264.5A CN105444918A (en) | 2015-12-10 | 2015-12-10 | Temperature detecting device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105444918A true CN105444918A (en) | 2016-03-30 |
Family
ID=55555380
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510910264.5A Pending CN105444918A (en) | 2015-12-10 | 2015-12-10 | Temperature detecting device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105444918A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2529225Y (en) * | 2002-03-11 | 2003-01-01 | 北京航空航天大学 | Deivice for measuring transient temp. of ceramic warhead surface of guided missile high-speed thermal shock test |
| JP3749135B2 (en) * | 2001-03-13 | 2006-02-22 | 横河電子機器株式会社 | Temperature measuring device |
| CN1936525A (en) * | 2006-10-17 | 2007-03-28 | 北京航空航天大学 | Carbon-fiber composite material high-speed air-craft rectifying cover surface transient temperature measuring apparatus |
| CN201025458Y (en) * | 2007-02-15 | 2008-02-20 | 北京航空航天大学 | Thermocouple temperature measurement protection device for high-speed aerocraft high-temperature pneumatic thermal simulation test |
| CN201716128U (en) * | 2010-05-25 | 2011-01-19 | 湖北航天技术研究院总体设计所 | Temperature measuring device for outer surface of high-speed aircraft |
| CN202002747U (en) * | 2011-03-16 | 2011-10-05 | 北京航空航天大学 | High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts |
| CN102353469A (en) * | 2011-09-29 | 2012-02-15 | 西北工业大学 | Online measurement device of high temperature of outer surface of high-speed aircraft, and preparation and measurement methods thereof |
| CN102809438A (en) * | 2012-08-16 | 2012-12-05 | 北京航空航天大学 | Measuring device for high surface temperature of cylindrical nonmetallic housing of high-speed aircraft |
-
2015
- 2015-12-10 CN CN201510910264.5A patent/CN105444918A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3749135B2 (en) * | 2001-03-13 | 2006-02-22 | 横河電子機器株式会社 | Temperature measuring device |
| CN2529225Y (en) * | 2002-03-11 | 2003-01-01 | 北京航空航天大学 | Deivice for measuring transient temp. of ceramic warhead surface of guided missile high-speed thermal shock test |
| CN1936525A (en) * | 2006-10-17 | 2007-03-28 | 北京航空航天大学 | Carbon-fiber composite material high-speed air-craft rectifying cover surface transient temperature measuring apparatus |
| CN201025458Y (en) * | 2007-02-15 | 2008-02-20 | 北京航空航天大学 | Thermocouple temperature measurement protection device for high-speed aerocraft high-temperature pneumatic thermal simulation test |
| CN201716128U (en) * | 2010-05-25 | 2011-01-19 | 湖北航天技术研究院总体设计所 | Temperature measuring device for outer surface of high-speed aircraft |
| CN202002747U (en) * | 2011-03-16 | 2011-10-05 | 北京航空航天大学 | High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts |
| CN102353469A (en) * | 2011-09-29 | 2012-02-15 | 西北工业大学 | Online measurement device of high temperature of outer surface of high-speed aircraft, and preparation and measurement methods thereof |
| CN102809438A (en) * | 2012-08-16 | 2012-12-05 | 北京航空航天大学 | Measuring device for high surface temperature of cylindrical nonmetallic housing of high-speed aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9322718B2 (en) | Temperature sensor | |
| CN102680127A (en) | Negative temperature coefficient (NTC) temperature sensor | |
| CN108253923B (en) | Preassembling calibration device | |
| CN105444918A (en) | Temperature detecting device for aircraft | |
| CN104132960A (en) | Test system for simulating thermal insulation performance of pipeline under deepwater environment | |
| CN103033280A (en) | High-sensitivity thermal-response platinum resistor temperature sensor | |
| CN108020333A (en) | A kind of temp probe and assembly method for aircraft | |
| CN103698042B (en) | A kind of high temperature sensor | |
| CN204085722U (en) | Gas flow temperature proving installation in pipe under high-temperature vibrating environment | |
| CN205719333U (en) | A kind of cable plug head | |
| CN204301890U (en) | A kind of rubber sheath formula temperature sensor | |
| CN205283045U (en) | It twists formula suspension clamp in advance to have monitor function | |
| CN207248381U (en) | Full-plastics sealed thermal resistance temperature sensor based on deformation migration protection | |
| CN203798530U (en) | Icing wind tunnel wind velocity pipe | |
| CN109974869A (en) | A kind of metal outer wall temperature measurement device | |
| CN104457358B (en) | High-temperature heat pipe cavity pressure real-time measurement system based on U-tube | |
| CN204269252U (en) | Temperature sensor | |
| CN209340889U (en) | A kind of flexible hose structure and hose detection system | |
| CN209471819U (en) | Transformer temperature controller based on optical fiber temperature-measurement | |
| CN106644137A (en) | Three-probe motor temperature sensor with adapter box | |
| CN208399039U (en) | A kind of fast joint type temperature detecting resistance | |
| CN205580616U (en) | Armoured thermocouple cable of reducing | |
| CN207007368U (en) | A kind of new heat flow transducer based on unsteady-state heat transfer model | |
| CN206787620U (en) | Temperature-humidity monitoring tape deck under pipe insulating layer | |
| CN106556471B (en) | Insert permeability type temperature sensor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160330 |
|
| RJ01 | Rejection of invention patent application after publication |