CN106134439B - Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereof - Google Patents
Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereofInfo
- Publication number
- CN106134439B CN106134439B CN201010052276.6A CN201010052276A CN106134439B CN 106134439 B CN106134439 B CN 106134439B CN 201010052276 A CN201010052276 A CN 201010052276A CN 106134439 B CN106134439 B CN 106134439B
- Authority
- CN
- China
- Prior art keywords
- temperature
- thermocouple
- reference edge
- armoured thermocouple
- thrust chamber
- 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.)
- Expired - Fee Related
Links
Landscapes
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses the high temperature resistant temperature measuring equipment in spacecraft thrust chamber and method, this device comprises armoured thermocouple, reference edge thermistor and temperature measurement circuit box etc. Armoured thermocouple thermometric end is fixed on thrust chamber in spot welding mode, and reference edge and reference edge thermistor are installed on magnetic valve wall. Taking copper conductor as compensating wire. Thermocouple electromotive force is sent TT&C system after temperature measurement circuit box amplifies, and is converted into thermometric end and the reference edge temperature difference. With reference edge thermistor survey reference junction temperature. The temperature difference summation of reference junction temperature and thermometric end and reference edge can obtain thermometric end temperature. Advantage of the present invention: engine high-temperature causes the high temperature resistant temperature-sensitive resistance of former thrust chamber to lose efficacy, former because its in high-temperature region deoxidation, thereby lose thermometric performance. Armoured thermocouple temperature resistant range is-50～900 DEG C, can bear high low temperature alternation 1000 times. Temperature measurement circuit box can amplify small thermocouple electromotive force, and temperature measurement accuracy ± 5 DEG C are convenient to install, detect and are safeguarded.
Description
Technical field
Rocket engine technical field of the present invention, is specifically related to the high temperature resistant survey in a kind of thrust chamberTemperature device and temp measuring method thereof, the method be used for judging whether be heated to before engine ignition neededTemperature, whether working properly after igniting, for thermal control in-orbit, on-orbit fault diagnosis provide and comply with autonomous managementAccording to.
Background technology
Along with the development of unit hydrazine rocket engine technology, unit hydrazine rocket engine is widely used in to be defendedThe attitude and orbit control of star, needs long-term, multiple pulses work. For making its normal work in lifetimeDo, need heatable catalytic bed to reach certain start-up temperature. Therefore, need to come with high temperature resistant temperature sensorWhether monitoring thrust chamber catalytic bed temperature, be heated to needed temperature before judging engine ignition,Whether working properly after igniting. For thermal control in-orbit, on-orbit fault diagnosis provide foundation with autonomous management.
Original rocket engine adopts high temperature resistant temperature-sensitive resistance to measure thrust chamber's temperature. ThisThe measurement category of planting measuring method is limited, the high temperature measurement especially can not contain catalytic bed work time, and propertyCan be also unstable, after experience hot conditions, there will be situation entirely ineffective or that measure error is excessive. ItsReason is that vacuum deaeration can occur in high-temperature region thermistor material, and the character of material has occurred at allChange, thereby lost thermometric performance. For avoiding occurring entirely ineffective or survey after thermistor experience high temperatureThe excessive situation of amount error, also adopted " thermistor is arranged on apart from thrust chamber compared with distant positions place "Measure, on engine support or ring flange. But in this case, the temperature-responsive of thermistorSlowly, the temperature rise of heater when work thermistor is less, cannot accurately and timely reflect the temperature of thrust chamber.Therefore it is essential that the thermometry of, developing high temperature resistant direct measurement thrust chamber temperature becomes.
Summary of the invention
Problem to be solved by this invention is to measure the front temperature of engine ignition, its temperature of monitoring after igniting,And provide temperature information to TT&C system computer on star. The invention provides a kind of rocket engine of measuring pushes awayThe fire resistant apparatus of power room temperature and method.
The high temperature resistant temperature measuring equipment of thrust chamber of rocket engine of the present invention, comprises armoured thermocouple, temperature-sensitive electricityResistance, compensating wire, temperature measurement circuit box, described armoured thermocouple top is thermometric end, bottom is referenceEnd, its armouring part is fixed in thrust chamber mounting groove by spot welding mode, and temperature measurement fraction is at armoured thermocoupleActive section in; Described thermistor is that reference edge is arranged on magnetic valve, by reference to end temperature withArmoured thermocouple thermometric end and the summation of the reference edge temperature difference obtain thermometric end temperature; Described compensating wire 4 willThe thermoelectromotive force of two go between thermometric end and reference edges of armoured thermocouple is guided to connecing of thermometric circuit boxOn line end, complete the voltage signal output of thermocouple; Described temperature measurement circuit box 5 is put electromotive force processAfter large, send TT&C system computer on star to.
The high temperature resistant temp measuring method of thrust chamber of rocket engine of the present invention comprises the steps:
A) first the end of two extension leads of armoured thermocouple is welded on to one by the mode of meltingRise, then anode extension lead (nickel filament) is cut off from centre, this solder joint is exactly reference edge. HeatThe thermometric end of galvanic couple is in the active section of armoured thermocouple.
B) secondly the armouring part of armoured thermocouple is fixed on to thrust chamber peace by stainless steel foil spot welding modeIn tankage, and thermocouple reference edge is sticked on engine electromagnetic valve outer wall with GD414 silicon rubber.
C) again two lead-in wires of armoured thermocouple are guided to the terminals of thermometric circuit box by compensating wire 4Upper, and the voltage signal of thermocouple outputs to TT&C system the most at last.
D) also stick on engine electromagnetic valve outer wall with GD414 silicon rubber with reference to end thermistor.
E) two lead-in wires of thermistor are guided to TT&C system by silver-plated copper wire.
F) obtain reference junction temperature and armoured thermocouple thermometric end and the reference edge temperature difference by TT&C system;
G) by reference to holding temperature and armoured thermocouple thermometric end and the summation of the reference edge temperature difference to obtain thermometric end temperatureDegree.
Above-mentioned armoured thermocouple is encapsulated by thermocouple temperature measurement end external application stainless steel outer sleeve, and filling MgO is heat-resistingMaterial forms, and its lead-out wire is shielded conductor.
Above-mentioned compensating wire 4 is silver-plated copper wire.
It is master chip that above-mentioned thermometric circuit box adopts instrument amplifier AD620SQ/883B, has solved thermoelectricityEven tiny signal amplifies and voltage transitions problem. Primary power source+28V is carried out to electricity by DC/DC modulePress conversion, generation ± 12V is to instrument amplifier AD620 power supply, and DC/DC adopts two-way paralleling model; ?The thermoelectrical potential signal that how can receive No. 22 thermocouples, by instrument amplifier, AD620 amplifies signal;The output voltage of AD620SQ/883B is adjusted with reference voltage source AD580, voltage range is transformed to0～5V, send TT&C system by conversion Hou 22 road magnitudes of voltage and secondary power supply remote measurement value.
It is MF51 or MF501 that above-mentioned thermistor adopts model.
The high temperature resistant temperature measuring equipment in spacecraft motor power of the present invention chamber and measuring method thereof, owing to having adoptedHigh temperature resistant temperature sensor and amplifying circuit for tiny signal, compared with prior art, its advantage and effect are:Temperature resistant capability is strong, and armoured thermocouple bearing temperature scope is-50 DEG C～900 DEG C, stable performance, experience 1000Inferior high low temperature cycles test also there will not be inefficacy or measure error to become large situation. Thermometric circuit box can be realThe now amplification to small voltage signal and voltage transitions. Temperature measurement accuracy is high, and certainty of measurement ± 5 DEG C (coordinateMeasurement circuitry box). Be convenient to reliable installation, detection and maintenance. Vibration while being able to take rocket launching andImpact, can meet the requirement of thrust chamber thermometric.
Brief description of the drawings
Below with reference to drawings and embodiments, the invention will be further described.
Fig. 1 is the high temperature resistant measurement mechanism schematic diagram in motor power of the present invention chamber.
In figure: the 1st, armoured thermocouple thermometric end, the 2nd, armoured thermocouple reference edge, the 3rd, reference edge temperature-sensitiveResistance, 4 compensating wires, the 5th, temperature measurement circuit box.
Fig. 2 is the sketch of armoured thermocouple.
In figure: the 6th, armoured thermocouple anode extension lead (nickel filament), the 7th, armoured thermocouple negative terminal prolongsLong lead (nisiloy silk), the 8th, extension lead section, the 9th, sealing section, the 10th, changeover portion, the 11st, workSection.
Fig. 3 is armoured thermocouple sealing segment structure.
In figure: the 12nd, the solder joint of thermocouple wire, the 13rd, stainless steel outer sleeve, the 14th, nickel filament, the 15th, treeFat, the 16th, heat-shrink tube, the 17th, nisiloy silk, the 18th, glass reinforced plastic sleeve.
Fig. 4 is the amplifier schematic diagram of measurement circuitry box.
Detailed description of the invention
The high temperature resistant measurement mechanism schematic diagram in motor power of the present invention chamber as shown in Figure 1: comprise armouring thermoelectricityIdol 1, thermistor 3, compensating wire 4, temperature measurement circuit box 5, in figure, armoured thermocouple 1 top is thermometricEnd 1, bottom is reference edge 2, its armouring part is fixed in thrust chamber mounting groove by spot welding mode, thermometricPart is in the active section of armoured thermocouple 1; Thermistor 3, for reference edge is arranged on magnetic valve, passes throughReference junction temperature and armoured thermocouple 1 thermometric end and the summation of the reference edge temperature difference obtain thermometric end temperature;
Be the sketch of armoured thermocouple 1 as shown in Figure 2, in figure, armoured thermocouple 1 is anode extension lead 6Adopt nickel filament, armoured thermocouple 1 adopts nisiloy silk 14 for negative terminal extension lead 7, extension lead section 8Adopt shielded conductor to be respectively sealing section 9, changeover portion 10, active section 11.
Be armoured thermocouple 1 sealing segment structure as shown in Figure 3, comprise the solder joint 12 of thermocouple wire, stainlessSteel sleeve 13, nickel filament 14, resin 15, heat-shrink tube 16, nisiloy silk 17, glass reinforced plastic sleeve 18.
Compensating wire 4 draws the thermoelectromotive force of two of armoured thermocouple 1 go between thermometric end and reference edgesTo the terminals of thermometric circuit box, complete the voltage signal output of thermocouple; Described temperature measurement circuit box5 send electromotive force on star TT&C system computer after amplifying.
Be the amplifier schematic diagram of measurement circuitry box as shown in Figure 4, amplifier AD620SQ/883B is main coreSheet, carries out voltage transformation by primary power source+28V by DC/DC module, and generation ± 12V is to instrument amplifierAD620 power supply, DC/DC adopts two-way paralleling model; Can receive at most the thermoelectrical potential signal of No. 22 thermocouples,By instrument amplifier, AD620 amplifies signal; With reference voltage source AD580 to AD620SQ/883BOutput voltage adjust, voltage range is transformed to 0～5V, by conversion after magnitude of voltage and secondary electricitySource remote measurement value is sent TT&C system, and the tiny signal that has solved thermocouple amplifies and voltage transitions problem.
The high temperature resistant temp measuring method of thrust chamber of rocket engine of the present invention comprises the steps:
A) first the end of two extension leads of armoured thermocouple 1 is welded on to one by the mode of meltingRise, then anode extension lead (nickel filament) is cut off from centre, this solder joint is exactly reference edge. HeatThe thermometric end of galvanic couple is in the active section of armoured thermocouple 1;
B) secondly the armouring part of armoured thermocouple 1 is fixed on to thrust chamber by stainless steel foil spot welding modeIn mounting groove, and thermocouple reference edge is sticked on engine electromagnetic valve outer wall with GD414 silicon rubber;
C) again two lead-in wires of armoured thermocouple 1 are guided to the terminals of thermometric circuit box by compensating wire 4Upper, and the voltage signal of thermocouple outputs to TT&C system the most at last;
D) also stick on engine electromagnetic valve outer wall with GD414 silicon rubber with reference to end thermal resistance 3;
E) two lead-in wires of thermal resistance 3 are guided to TT&C system by silver-plated copper wire;
F) obtain reference junction temperature and armoured thermocouple 1 thermometric end and the reference edge temperature difference by TT&C system;
G) by reference to holding temperature and armoured thermocouple 1 thermometric end and the summation of the reference edge temperature difference to obtain thermometric endTemperature;
Above-mentioned armoured thermocouple 1 is encapsulated by thermocouple temperature measurement end external application stainless steel outer sleeve, and filling MgO is resistance toHot material forms, and its lead-out wire is shielded conductor;
Above-mentioned compensating wire 4 is silver-plated copper wire.
It is master chip that above-mentioned thermometric circuit box adopts instrument amplifier AD620SQ/883B, by primary power source+ 28V carries out voltage transformation by DC/DC module, and generation ± 12V powers to instrument amplifier AD620,DC/DC adopts two-way paralleling model; The thermoelectrical potential signal that can receive at most No. 22 thermocouples, passes through instrumentAmplifier AD620 amplifies signal; Output electricity with reference voltage source AD580 to AD620SQ/883BCompress into row adjustment, voltage range is transformed to 0～5V, will convert Hou 22 road magnitudes of voltage and secondary power supply distantMeasured value send TT&C system. The tiny signal that has solved thermocouple amplifies and voltage transitions problem.
It is MF51 or MF501 that above-mentioned thermal resistance 3 adopts model.
Obviously, those skilled in the art, can carry out various changes and distortion and not depart from the present inventionThe spirit and scope of the present invention. Like this, if these amendments and distortion belong to the claims in the present invention andWithin the scope of equivalent technologies, the present invention is also intended to comprise these changes and is out of shape interior.
Claims (4)
1. the high temperature resistant temperature measuring equipment in thrust chamber, is characterized in that: comprise armouring thermoelectricityEven [1], thermistor [3], compensating wire [4], temperature measurement circuit box [5], described armoured thermocouple [1]Top is thermometric end, and bottom is reference edge A, and its armouring part is fixed on thrust chamber mounting groove by spot welding modeIn, temperature measurement fraction is in the active section of armoured thermocouple; Described thermistor [3] is reference edge B installationOn magnetic valve, thermocouple reference edge A is sticked on engine electromagnetic valve outer wall with GD414 silicon rubber,By reference to holding B temperature and armoured thermocouple thermometric end and the summation of the reference edge A temperature difference to obtain thermometric end temperature;Described compensating wire [4] passes through two lead-in wires of armoured thermocouple by the thermoelectric of thermometric end and reference edge AKinetic potential is guided on the terminals of temperature measurement circuit box [5], completes the voltage signal output of thermocouple; DescribedTemperature measurement circuit box [5] adopts the amplifying circuit that instrument amplifier AD620 is master chip, by primary power source+28VCarry out voltage transformation by DC/DC module, generation ± 12V is to instrument amplifier AD620 power supply, DC/DC mouldPiece adopts two-way paralleling model.
2. the high temperature resistant temperature measuring equipment in a kind of thrust chamber according to claim 1, its featureBe: described armoured thermocouple [1] thermometric end stainless steel outer sleeve encapsulates, and fill the heat-resisting material of MgOMaterial.
3. the high temperature resistant temperature measuring equipment in a kind of thrust chamber according to claim 1, its featureBe: described compensating wire [4] is silver-plated copper wire.
4. one kind adopts the thermometric side of the high temperature resistant temperature measuring equipment in thrust chamber claimed in claim 1Method, is characterized in that comprising the steps:
A) first the end of two extension leads of armoured thermocouple [1] is welded on by the mode of meltingTogether, then anode extension lead is cut off from centre, this solder joint is exactly reference edge A, thermocouple temperature measurementEnd is in armoured thermocouple active section;
B) secondly the armouring part of armoured thermocouple is fixed on to thrust chamber peace by stainless steel foil spot welding modeIn tankage, and thermocouple reference edge A is sticked on engine electromagnetic valve outer wall with GD414 silicon rubber;
C) again two lead-in wires of armoured thermocouple [1] are guided to connecing of temperature measurement circuit box by compensating wire [4]On line end, and the voltage signal of thermocouple outputs to TT&C system the most at last;
D) thermistor is also sticked on engine electromagnetic valve outer wall with GD414 silicon rubber;
E) two lead-in wires of thermistor are guided to TT&C system by silver-plated copper wire;
F) obtain reference edge B temperature and armoured thermocouple [1] thermometric end and reference edge A temperature by TT&C systemPoor;
G) by reference to holding B temperature and armoured thermocouple [1] thermometric end and the summation of the reference edge A temperature difference to be surveyedTemperature end temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010052276.6A CN106134439B (en) | 2010-12-10 | 2010-12-10 | Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010052276.6A CN106134439B (en) | 2010-12-10 | 2010-12-10 | Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134439B true CN106134439B (en) | 2014-03-19 |
Family
ID=57251064
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010052276.6A Expired - Fee Related CN106134439B (en) | 2010-12-10 | 2010-12-10 | Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134439B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2010
- 2010-12-10 CN CN201010052276.6A patent/CN106134439B/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106531245B (en) | Used in nuclear power station in-pile instrument sheath assembly | |
| EP2291625A1 (en) | High vibration thin film rtd sensor | |
| US9442203B2 (en) | Neutron monitoring system | |
| US8827553B2 (en) | Autonomous temperature transmitter | |
| CN108917962B (en) | A kind of thin stick narrow gap wall temperature temperature measuring equipment under moving condition | |
| US20100091816A1 (en) | Temperature sensor | |
| US10006814B2 (en) | Temperature detecting device | |
| US8790008B2 (en) | Device for measuring the temperature of a substrate | |
| CN106134439B (en) | Thrust chamber is high temperature resistant temperature measuring equipment and temp measuring method thereof | |
| CN206194382U (en) | Reactor core appearance gauge sleeve pipe assembly for nuclear power station | |
| CN104316221B (en) | Calibration device for contact type high temperature sensor | |
| US20220307915A1 (en) | Temperature-Measuring Device | |
| CN201795874U (en) | Thermoelectric couple for vacuum high-temperature measurement and control | |
| US8806970B2 (en) | Sealing device for a device for measuring the fill level in a fluid container | |
| CN106352995A (en) | Thermocouple-based temperature measurement device | |
| CN201653577U (en) | Thermocouple temperature sensor | |
| CN103698042B (en) | A kind of high temperature sensor | |
| CN206573251U (en) | High temperature teletransmission pressure difference transmitter | |
| JP3462885B2 (en) | Reactor power measurement apparatus and method of manufacturing the same | |
| CN210441993U (en) | Temperature detector based on thermoelectric effect | |
| CN201837481U (en) | Temperature sensor | |
| RU178693U1 (en) | DEVICE FOR TESTING SYSTEMS INCLUDING ELECTRIC IGNITION DEVICE ON THE PROTECTION OF HAZARDOUS CIRCUITS FROM EXPOSURE TO ELECTROMAGNETIC FIELDS | |
| CN205246245U (en) | A calibrating device for contact high -temperature gas temperature sensor | |
| CN104457358B (en) | High-temperature heat pipe cavity pressure real-time measurement system based on U-tube | |
| CN208125288U (en) | A kind of nuclear power multipoint thermocouple |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140319 Termination date: 20201210 |