CN204214562U - For the temperature measuring equipment of solid propellant rocket - Google Patents
For the temperature measuring equipment of solid propellant rocket Download PDFInfo
- Publication number
- CN204214562U CN204214562U CN201420532098.0U CN201420532098U CN204214562U CN 204214562 U CN204214562 U CN 204214562U CN 201420532098 U CN201420532098 U CN 201420532098U CN 204214562 U CN204214562 U CN 204214562U
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- metal sleeve
- set bolt
- measuring equipment
- temperature measuring
- solid propellant
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Abstract
The utility model relates to temperature test field, is specifically related to a kind of temperature measuring equipment.For the temperature measuring equipment of solid propellant rocket, its technical scheme is, the top of two thermocouple wires (1) is welded and passed through the thermometric intersegmental part that sealing filler (8) is fixed on metal sleeve (2); Thermal protection shield (9) is wrapped in the outer circumference surface of the thermometric section of metal sleeve (2); Gland nut (3), latch segment (4), O-ring seal (5) and set bolt (6) are sleeved on metal sleeve (2) successively, set bolt (6) is threaded onto engine thermometer hole by one side end face, make metal sleeve (2) thermometric section be positioned at engine, and realize the sealing between set bolt (6) and engine thermometer hole by copper washer (7); Working temperature under utilizing the utility model can test solid propellant rocket high temperature, hyperbaric environment.
Description
Technical field
The utility model relates to temperature test field, is specifically related to a kind of temperature measuring equipment.
Background technology
Solid propellant rocket course of work fuel gas temperature up to more than 3500 DEG C, the temperature of the parts such as jet pipe throat lining, expansion segment heat insulation layer when end of burning temperature also more than 2000 DEG C.Meanwhile, the pressure of firing chamber is generally not less than 6MPa.Therefore, the parts such as jet pipe throat lining, expansion segment heat insulation layer be tested more difficult, not only will select pyrometer couple, also will take seal approach, prevent from causing test run failure because of jet pipe gas leakage.
Conventional temperature testing method is the position processing instrument connection that will testing.Thermocouple wire is fixed in threaded metal sleeve, is then fixed in instrument connection by metal sleeve.Although the thermopair cost of the type is low, easy for installation, simple to operate, be difficult to the seal request under guarantee high temperature.Although can by reaching seal request at screw thread place brush high-temperature seal adhesive, the sealing glue solidifying cycle be longer, and sealing effectiveness is difficult to detect.
Summary of the invention
The purpose of this utility model is: for solving in prior art the measurement mechanism that there is no for high temperature under solid propellant rocket High Voltage, propose a kind of temperature measuring equipment, to solve the high temperature test problem of each parts of solid propellant rocket.
The technical solution of the utility model is: for the temperature measuring equipment of solid propellant rocket, it comprises: thermocouple wire, metal sleeve, gland nut, latch segment, O-ring seal, set bolt, copper washer, sealing filler and thermal protection shield;
The quantity of thermocouple wire has two, and the top of two thermocouple wires is welded and is fixed on the thermometric intersegmental part of metal sleeve by sealing filler; Thermal protection shield is wrapped in the outer circumference surface of the thermometric section of metal sleeve; Gland nut, latch segment, O-ring seal and set bolt are sleeved on metal sleeve successively, and latch segment and O-ring seal compress by gland nut and set bolt; Set bolt is threaded onto engine thermometer hole by one side end face, makes metal sleeve thermometric section be positioned at engine, and realizes the sealing between set bolt and engine thermometer hole by copper washer; By unclamping gland nut and set bolt regulates metal sleeve thermometric section to be positioned at in-engine length.
Beneficial effect is: (1) the utility model is coated with thermal protection shield at the outer circumference surface of the thermometric section of its metal sleeve, can protect thermocouple wire and other parts, therefore can test the working temperature under solid propellant rocket high temperature, hyperbaric environment;
(2) metal sleeve of the present utility model adopts latch segment and gland nut combination locking, and therefore MTD can regulate arbitrarily in its length range;
(3) employing O-ring seal of the present utility model and copper washer realize sealing, and sealingly secure is reliable, easy to use, simple to operate.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the structural representation that the present invention is installed on engine thermometer hole place;
Wherein: 1-thermocouple wire, 2-metal sleeve, 3-gland nut, 4-latch segment, 5-O-ring seal, 6-set bolt, 7-copper washer, 8-elevated-temperature seal filling material, 9-thermal protection shield.
Embodiment
See accompanying drawing 1, for the temperature measuring equipment of solid propellant rocket, it comprises: thermocouple wire 1, metal sleeve 2, gland nut 3, latch segment 4, O-ring seal 5, set bolt 6, copper washer 7, sealing filler 8 and thermal protection shield 9;
The quantity of thermocouple wire 1 has two, and the top of two thermocouple wires 1 is welded and is fixed on the thermometric intersegmental part of metal sleeve 2 by sealing filler 8; Thermal protection shield 9 is wrapped in the outer circumference surface of the thermometric section of metal sleeve 2; Gland nut 3, latch segment 4, O-ring seal 5 are sleeved on metal sleeve 2 with set bolt 6 successively, and latch segment 4 and O-ring seal 5 compress by gland nut 3 and set bolt 6; Set bolt 6 is threaded onto engine thermometer hole by one side end face, makes metal sleeve 2 thermometric section be positioned at engine, and realizes the sealing between set bolt 6 and engine thermometer hole by copper washer 7; Metal sleeve 2 thermometric section is regulated to be positioned at in-engine length by unclamping gland nut 3 with set bolt 6.
In practice, thermocouple wire 1 can adopt thermometric higher (maximum temperature can reach 1600 DEG C, and short-period used can reach 1800 DEG C), platinum rhodium that price is more expensive as required according to test specification and integrated cost
30-platinum rhodium
6thermocouple wire or thermometric relatively low (short-term is measured can reach 1200 DEG C), low-cost nickel chromium-nickel silicon thermocouple silk; Sealing filler 8 can adopt glue and the material that high silica cloth mixes or glue mixes with phenolic powder; Thermocouple wire 1 is placed in metal sleeve 2, utilizes the sealing filler 8 mixed fill and solidify, during solidification, ensure that the thermometric end of thermocouple wire 1 exceeds the barrel 0.2-0.5mm of metal sleeve 2; First metal sleeve 2 is moved to Len req when this temperature measuring equipment is installed, then tighten gland nut 3 and set bolt 6, under force latch segment 4 compressive deformation, prevent metal sleeve 2 from sliding, O-ring seal 5 is compacted simultaneously, the gap of sealing set bolt 6 and metal sleeve 2; High-temp. measurer set bolt 6 hot junction of locking is threaded onto engine thermometer hole, and seals the gap of high-temp. measurer and thermometer hole with copper washer 7; Elevated-temperature seal filling material 8, copper washer 7 and O-ring seal 5 common guarantee this temperature measuring equipment sealing under high pressure; The external diameter Ф of metal sleeve 2
2, gland nut 3 endoporus aperture Ф
3, latch segment 4 internal orifice dimension Ф
4, O-ring seal 5 internal diameter Ф
51, set bolt 6 internal orifice dimension Ф
6meet: Ф
2+ 0.1=Ф
3=Ф
4=Ф
51+ 0.1=Ф
6; Gland nut 3 internal thread M
3with with its set bolt 6 external thread M be connected
61meet: M
3=M
61.
Claims (4)
1. for the temperature measuring equipment of solid propellant rocket, it is characterized in that, it comprises: thermocouple wire (1), metal sleeve (2), gland nut (3), latch segment (4), O-ring seal (5), set bolt (6), copper washer (7), sealing filler (8) and thermal protection shield (9);
The quantity of described thermocouple wire (1) has two, and the top of two described thermocouple wires (1) is welded and passed through the thermometric intersegmental part that described sealing filler (8) is fixed on described metal sleeve (2); Described thermal protection shield (9) is wrapped in the outer circumference surface of the thermometric section of described metal sleeve (2); Described gland nut (3), described latch segment (4), described O-ring seal (5) and described set bolt (6) are sleeved on described metal sleeve (2) successively, and described latch segment (4) and described O-ring seal (5) compress by described gland nut (3) and described set bolt (6); Described set bolt (6) is threaded onto engine thermometer hole by one side end face, make described metal sleeve (2) thermometric section be positioned at described engine, and realize the sealing between set bolt (6) and described engine thermometer hole by described copper washer (7); Described metal sleeve (2) thermometric section is regulated to be positioned at described in-engine length by unclamping described gland nut (3) with described set bolt (6).
2. as claimed in claim 1 for the temperature measuring equipment of solid propellant rocket, it is characterized in that, described thermal protection shield (9) adopts asbestos or phenolic materials.
3. as claimed in claim 1 or 2 for the temperature measuring equipment of solid propellant rocket, it is characterized in that, described thermocouple wire (1) adopts platinum rhodium
30-platinum rhodium
6thermocouple wire or nickel chromium-nickel silicon thermocouple silk.
4. as claimed in claim 1 or 2 for the temperature measuring equipment of solid propellant rocket, it is characterized in that, described sealing filler (8) adopts glue and the material that high silica cloth mixes or glue mixes with phenolic powder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420532098.0U CN204214562U (en) | 2014-09-17 | 2014-09-17 | For the temperature measuring equipment of solid propellant rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420532098.0U CN204214562U (en) | 2014-09-17 | 2014-09-17 | For the temperature measuring equipment of solid propellant rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204214562U true CN204214562U (en) | 2015-03-18 |
Family
ID=52983227
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420532098.0U Active CN204214562U (en) | 2014-09-17 | 2014-09-17 | For the temperature measuring equipment of solid propellant rocket |
Country Status (1)
| Country | Link |
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| CN (1) | CN204214562U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063491A (en) * | 2017-05-05 | 2017-08-18 | 淮北矿业股份有限公司 | A kind of coke oven temperature measuring device |
| CN107860481A (en) * | 2017-10-18 | 2018-03-30 | 西安航天动力试验技术研究所 | A kind of conventional liq engine wall warms thermo wires sensor fixing means |
| CN109959464A (en) * | 2019-04-23 | 2019-07-02 | 安徽天康(集团)股份有限公司 | A kind of multi-point average thermometer |
| CN110631729A (en) * | 2019-08-13 | 2019-12-31 | 西北工业大学 | Armored thermocouple sealing and position regulating device suitable for rocket engine |
-
2014
- 2014-09-17 CN CN201420532098.0U patent/CN204214562U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063491A (en) * | 2017-05-05 | 2017-08-18 | 淮北矿业股份有限公司 | A kind of coke oven temperature measuring device |
| CN107860481A (en) * | 2017-10-18 | 2018-03-30 | 西安航天动力试验技术研究所 | A kind of conventional liq engine wall warms thermo wires sensor fixing means |
| CN107860481B (en) * | 2017-10-18 | 2020-05-29 | 西安航天动力试验技术研究所 | Fixing method for wall temperature thermocouple wire sensor of conventional liquid engine |
| CN109959464A (en) * | 2019-04-23 | 2019-07-02 | 安徽天康(集团)股份有限公司 | A kind of multi-point average thermometer |
| CN110631729A (en) * | 2019-08-13 | 2019-12-31 | 西北工业大学 | Armored thermocouple sealing and position regulating device suitable for rocket engine |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |