CN201444089U - Aerospace low-temperature sensor - Google Patents
Aerospace low-temperature sensor Download PDFInfo
- Publication number
- CN201444089U CN201444089U CN2008201706708U CN200820170670U CN201444089U CN 201444089 U CN201444089 U CN 201444089U CN 2008201706708 U CN2008201706708 U CN 2008201706708U CN 200820170670 U CN200820170670 U CN 200820170670U CN 201444089 U CN201444089 U CN 201444089U
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- temperature sensor
- metal sleeve
- sealing bulb
- aerospace
- temperature
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Abstract
The utility model relates to an aerospace low-temperature sensor which is mainly characterized in that: (1) the large-diameter end of a reducing metal sleeve is welded with a nut sealing bulb with a movable outer cover; (2) the working end is exposed; (3)a thermocouple wire is built in the reducing metal sleeve with the sealing bulb, and low-temperature sealant is filled in the spacing through a special pressurized filling method; (4) a lead wire which is made of the same material with the thermocouple wire and provided with a metal shield serves as an extension cord; and the shield is grounded and connected with the reducing metal sleeve through a reference end fixing nut. The grounding resistance is less than 0.3 ohm. The aerospace low-temperature sensor can realizes the temperature measuring scope from minus 270 DEG C to 0 DEG C, +/-0.3 DEG C of measuring precision, shorter than or equal to 30ms of response time, 4g of anti-vibration capability, and the pressure resistant performance of blocking hydrogen medium from penetrating under 30Mpa, and can meet the aerospace temperature measuring requirements.
Description
Technical field
The utility model belongs to the measurement instrument technical field, particularly a kind of space flight cryogenic temperature sensor.
Technical background
Thermopair be measure, the primary element of control temperature, be to constitute by protection metal pipe, insulating material, thermocouple wire.Connect compensating wire by working end welding, reference end and form the simplest temperature sensor.The temperature sensor working end is divided into insulated type, reveals end type and body contact type etc.
Insulated type temperature sensor working end pad is filled insulating mediums such as magnesia powder, protection tube reference end epoxy sealing between thermocouple wire and protection tube in the protection tube of end seal.Insulated type thermopair resistance to pressure, corrosion resistance and anti-electromagnetic interference (EMI) are best, but measurement sensitivity is lower.
Reveal end type temperature sensor working end pad and expose outside the protection tube of open-ended, fill insulating mediums such as magnesia powder between thermocouple wire and protection tube, protection tube reference end epoxy sealing.It is the highest to reveal the sensitivity of end type temperature sensor measurement, and anti-electromagnetic interference performance is also better, but corrosion resistance and resistance to pressure are relatively poor.
Body contact type temperature sensor working end pad and protection tube end are welded together, and fill insulating mediums such as magnesia powder between thermocouple wire and protection tube, protection tube reference end epoxy sealing.The anti-electromagnetic interference (EMI) of body contact type temperature sensor is poor, and resistance to pressure is good, and it is good to measure the remolding sensitivity insulated type, and the end type is poor than revealing.
Space industry generally adopts the liquid hydrogen liquid oxygen to do fuel, is used for the cryogenic temperature sensor of space industry, requires temperature-measuring range-270～0 ℃, temperature measurement accuracy ± 0.3 ℃, and response time≤30ms, antivibration 4g, withstand voltage: as to stop that the hydrogen atom medium penetrates under the 30MPa.The thermocouple temperature sensor of present three kinds of structure types all can not satisfy above every index request simultaneously.
The utility model content
The utility model aims to provide a kind of cryogenic temperature sensor at many weak points that present thermopair class temperature sensor exists, and especially is applicable to the industrial high temperature sensor of space flight and aviation.
The utility model feature is that movable cap nut sealing bulb is with in the welding of diameter metal sleeve pipe bigger diameter end, reveal end type thermocouple wire, diameter metal sleeve pipe, sealing bulb gap filling low temperature seal glue, adopt the same model compensation lead of thermocouple, and by the fastening grounding nut crimping metallic shield ground wire on the sealing bulb.
Described diameter metal sleeve pipe is the knot that is connected with the sealing bulb, as welding.
Described movable cap nut compresses the sealing bulb and the measured medium container joint is tightly connected.
The utility model beneficial effect is that the low-temperature test temperature-measuring range is wide, temperature measurement accuracy is high, is quick on the draw, and especially antivibration, good pressure-resistant performance meet the space industry needs fully, and the specific performance index is as follows:
1, temperature-measuring range :-200～0 ℃
2, temperature measurement accuracy: ± 0.4 ℃
3, the response time :≤30ms
4, antivibration: 4g
5, withstand voltage: 20Mpa.
As a kind of improvement of the present utility model, reveal the end thermopair and adopt nickel chromium triangle-Jin iron thermopair, temperature-measuring range may extend into-270～0 ℃, measuring accuracy: ± 0.3 ℃
Description of drawings
Fig. 1 is the utility model diagrammatic cross-section
Fig. 2 is the utility model thermometric end section enlarged diagram
Among the figure, 1-working end pad, the 2-thermocouple wire, 3-low temperature seal glue, 4-diameter metal sleeve pipe, 5-seals bulb, the movable cap nut of 6-, 7-reference end hold-down nut, 8-technology nut, the 9-pad, the 10-metal protects spring, 11-conductor shielding net, 12-extended line.
Embodiment
In conjunction with the accompanying drawings, the utility model embodiment is as follows:
Diameter metal sleeve pipe 4 bigger diameter ends embed sealing bulb 5 sphere ends and by being welded to connect.
A kind of low temperature seal glue 3 is filled in thermocouple wire 2, diameter metal sleeve pipe 4 gaps.
Thermocouple wire 2 is connected with extended line 12, and extended line passes metal and protects spring 10 and reference end hold-down nut 7.
Reference end hold-down nut 7 is by sealing bulb 5 thread end crimping conductor shielding nets 11.
During use, movable cap nut 6 compresses sealing bulb 5 and is tightly connected with measured medium container joint (accompanying drawing is not shown).
Claims (3)
1. space flight cryogenic temperature sensor, it is characterized in that diameter metal sleeve pipe bigger diameter end welding is with movable cap nut sealing bulb, reveal end type thermocouple wire, diameter metal sleeve pipe, sealing bulb gap filling low temperature seal glue, adopt the same model compensation lead of thermocouple, and by the fastening grounding nut crimping metallic shield ground wire on the sealing bulb.
2. according to the described space flight cryogenic temperature sensor of claim 1, it is characterized in that described diameter metal sleeve pipe and sealing bulb are the knot that is connected, as welding.
3. according to the described space flight cryogenic temperature sensor of claim 1, it is characterized in that described movable cap nut compresses the sealing bulb and the measured medium container joint is tightly connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008201706708U CN201444089U (en) | 2008-12-29 | 2008-12-29 | Aerospace low-temperature sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008201706708U CN201444089U (en) | 2008-12-29 | 2008-12-29 | Aerospace low-temperature sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201444089U true CN201444089U (en) | 2010-04-28 |
Family
ID=42548773
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008201706708U Expired - Fee Related CN201444089U (en) | 2008-12-29 | 2008-12-29 | Aerospace low-temperature sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201444089U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104101438A (en) * | 2013-04-03 | 2014-10-15 | 北京航天试验技术研究所 | Rapid response thermocouple temperature sensor |
| CN108036871A (en) * | 2018-01-12 | 2018-05-15 | 南京航空航天大学 | A kind of spring-pressing fix type thermocouple |
| CN108088580A (en) * | 2018-01-19 | 2018-05-29 | 锦州精微仪表有限公司 | The temperature element of small slotting deep accurate measurement can be achieved |
| CN109855754A (en) * | 2017-11-30 | 2019-06-07 | 北京航天试验技术研究所 | A kind of temperature sensor |
| CN111595476A (en) * | 2020-05-25 | 2020-08-28 | 西安航天动力试验技术研究所 | Temperature measurement assembly for process pipeline of liquid oxygen kerosene engine test system |
-
2008
- 2008-12-29 CN CN2008201706708U patent/CN201444089U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104101438A (en) * | 2013-04-03 | 2014-10-15 | 北京航天试验技术研究所 | Rapid response thermocouple temperature sensor |
| CN109855754A (en) * | 2017-11-30 | 2019-06-07 | 北京航天试验技术研究所 | A kind of temperature sensor |
| CN108036871A (en) * | 2018-01-12 | 2018-05-15 | 南京航空航天大学 | A kind of spring-pressing fix type thermocouple |
| CN108088580A (en) * | 2018-01-19 | 2018-05-29 | 锦州精微仪表有限公司 | The temperature element of small slotting deep accurate measurement can be achieved |
| CN108088580B (en) * | 2018-01-19 | 2024-06-07 | 锦州精微仪表有限公司 | Temperature measuring element capable of realizing small insertion depth precision measurement |
| CN111595476A (en) * | 2020-05-25 | 2020-08-28 | 西安航天动力试验技术研究所 | Temperature measurement assembly for process pipeline of liquid oxygen kerosene engine test system |
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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: 20100428 Termination date: 20121229 |