KR100759353B1 - Aircraft temperature measurement device with temperature compensation function and temperature compensation device for thermocouple - Google Patents

Abstract

An apparatus for measuring flying object temperature with a compensation function and an apparatus for compensating temperature for a thermocouple for the same are provided to be suitable to the temperature of a flying object having the limitation of weight and size by being manufactured small and light. An apparatus for measuring flying object temperature with a compensation function includes a thermocouple, a wire unit(20), a junction unit(30), an RTD(Resistance Temperature Detector)(50), a remote measuring unit(80), and a calculating unit. The thermocouple is attached on a flying object to measure the temperature of the flying object. The wire unit of the thermocouple is extended from a temperature measuring point(10) of the thermocouple. The junction unit connects a general wire(40). The RTD is connected to a leading wire(60) of the RTD to measure the temperature of the junction unit. The remote measuring unit having a transmission function receives an output signal of the RTD and the output voltage of the thermocouple. The calculating unit calculates the temperature of the flying object where a measured error is compensated according increasing the temperature of the junction unit as the output signal of the RTD and the output voltage of the thermocouple.

Description

Air vehicle temperature measuring device with correction function and thermocouple temperature compensation device for measuring air temperature {AIRCRAFT TEMPERATURE MEASUREMENT DEVICE WITH TEMPERATURE COMPENSATION FUNCTION AND TEMPERATURE COMPENSATION DEVICE FOR THERMOCOUPLE}

1 is a conceptual diagram illustrating a thermometer measuring method using a conventional thermocouple when a thermocouple is used to measure the temperature of a wall surface rising to 185 ° C. and the temperature of the junction bundle rises to 85 ° C. FIG.

Figure 2 is a conventional thermometer measurement method, when measured using a thermocouple, the experimental data showing the temperature distortion phenomenon occurring in the bunch of junctions.

3 is a conceptual diagram of a vehicle temperature measuring apparatus equipped with a correction function according to the first embodiment of the present invention.

4 is a plan view of a thermocouple temperature compensation device constituting a flying body temperature measuring device equipped with a correction function according to the first embodiment of the present invention.

FIG. 5 is a front view of a thermocouple temperature calibrating device constituting a vehicle temperature measuring device with a calibrating function according to Embodiment 1 of the present invention.

FIG. 6 is a side view of a thermocouple temperature correction device constituting a vehicle temperature measurement device having a correction function according to Embodiment 1 of the present invention.

7 is experimental data showing the actual temperature of the vehicle and the compensated vehicle measurement temperature when the temperature of the vehicle is measured by using the vehicle temperature measuring apparatus equipped with the correction function according to the first embodiment of the present invention.

8 is a conceptual diagram of a vehicle temperature measuring apparatus equipped with a correction function according to the second embodiment of the present invention.

FIG. 9 is a plan view of a thermocouple temperature calibrating device constituting a vehicle temperature measuring device with a calibrating function according to Embodiment 2 of the present invention.

FIG. 10 is a front view of a thermocouple temperature calibrating device constituting a vehicle temperature measuring device with a calibration function according to Embodiment 2 of the present invention.

<Description of the symbols for the main parts of the drawings>

10: temperature measuring point of thermocouple, 20: wire part of thermocouple,

30: junction portion, 40: general wire,

50: RTD sensor, 70: connector,

80: telemetry unit 100: metal case,

130: Bundle of junctions.

The present invention relates to a vehicle temperature measuring device equipped with a correction function and a thermocouple temperature compensation device for measuring the temperature of the aircraft, in particular using a thermocouple having a good response characteristics for measuring the temperature of the aircraft flying at high speed, The present invention relates to a vehicle temperature measuring device equipped with a correction function capable of correcting the effect of temperature on a junction region that meets a general electric wire, and a thermocouple temperature correction device for measuring the temperature of a vehicle.

The most widely used sensor for temperature measurement is the thermocouple, which uses the Seebeck Effect, the principle that electromotive force is generated when heat is applied to areas where different metals are bonded. These thermocouples can be made to allow a wide range of temperature measurements depending on the type of metal used.

Another temperature sensor is RTD (Resistance Temperature Detector), which is a temperature sensor that uses the principle that resistance value changes according to temperature. Measure the temperature. Various metals are used for this Altidi sensor. The Altidi sensor, which can measure stable and accurate temperature and can measure high temperature, is a platinum Altidi sensor.

In order to ensure structural safety during flight of all aircraft, such as missiles and projectiles, the temperature of the aircraft is measured. In particular, in the case of guided missiles and projectiles flying at high speed, high temperature load is an important variable. The main cause of the high temperature in the aircraft is aerodynamic heating (a phenomenon in which the surface of the aircraft is heated by friction and compression of air near the surface of the aircraft). Aerodynamic heating is proportional to the density and the third power of the speed. The higher the speed, the greater aerodynamic heating occurs. Since this aerodynamic heating adds a lot of heat to the aircraft, the temperature rise inevitably occurs in the friction surface of the aircraft in contact with the air, this temperature rise degrades the structural safety of the aircraft. The faster the aircraft, the more important the aerodynamic heating is for its safety. Therefore, the safety of the vehicle must be verified by measuring the temperature of the high-speed aircraft structure.

Since the vehicle does not have a physical line to the ground, all of the thermometer-side equipment must be mounted on the vehicle. Thermometer-equipped equipment on board the vehicle must be a proven equipment that can overcome both the problem of securing space for its installation, the vibration and the internal environment with high temperature. For this reason, conventionally, an Altidi sensor is used rather than a thermocouple as a thermometer measuring method.

1 is a conceptual diagram of a thermometer measuring method using a conventional thermocouple when a thermocouple is used to measure the temperature of a wall surface rising to 185 ° C., and the junction bundle temperature rises to 85 ° C. FIG.

Since the thermocouple has an output voltage of several kHz, is susceptible to vibration, electromagnetic waves and other noises, the thermocouple needs to be transmitted with a signal to the telemetry apparatus 7, and therefore, it is necessary to connect it with a general wire. The position where the electric wire part 4 and the general electric wire 6 meet is called a junction (Junction) 5, and the electromotive force according to the temperature is generated at this junction (5), and the electromotive force generated at the temperature measuring point (3) of the thermocouple Offsets Therefore, it is necessary to convert the temperature of the junction 5 portion into electromotive force to compensate.

2 is experimental data showing a temperature distortion phenomenon occurring in a bundle of junctions 5 when a temperature of a vehicle is measured using a thermocouple by a conventional thermometer method. The vertical axis is temperature and the horizontal axis is time. In addition, the curve denoted by the circular separator is the actual temperature of the aircraft, the curve denoted by the rhombus separator is the measurement temperature of the aircraft, and the curve denoted by the triangle separator is the junction (5) temperature. As can be seen from this graph, there is a large error between the actual and measured temperatures of the aircraft.

For the purpose of compensating the electromotive force according to the temperature of the junction 5 portion of the thermocouple, electronic junction portion temperature compensators used at room temperature of the ground can be used. However, the use environment should be guaranteed at room temperature, and when a thermocouple device is attached to one thermocouple, there is a problem of lack of mounting space inside a vehicle such as a missile, which is not suitable for mounting. In addition, the commercially available electronic junction area temperature treatment device can be used on the ground for room temperature, and one thermocouple is applied to each channel, and the harsh environment (high temperature of 200 ° C to 700 ° C, about 10 to 50 ° C per second) It is very difficult and unproven to apply to a flying aircraft with rapid temperature rise of 100 ~ 2,000Hz.

Therefore, Altidi sensors using resistance instead of electromotive force are widely used for flying temperature measurement. Altidi sensors do not require temperature compensation. However, the Altidi sensor has a smaller operating temperature range than the thermocouple. When there is a high surface temperature rise due to severe aerodynamic heating and a high temperature internal environment, measuring with the Altidi sensor causes many failures and errors. First, since the AltiDy sensor uses a change in resistance according to the temperature of the thin film, an adhesive is required to attach the AltiDy sensor to the surface of the aircraft. However, the commercial commercial adhesive loses the adhesion at 100 to 200 ° C. When thick cement is used, there are cases where the cement absorbs heat and cannot accurately measure the surface temperature.

The present invention has been made to solve the above-mentioned conventional problems, and as a result of examining the possibility of using a thermocouple to measure the temperature of a vehicle in the following harsh environment, it is possible to replace the Altidi sensor with a thermocouple having excellent stability and good response characteristics. By applying a temperature compensator to compensate for the rise in temperature at the new junction, the aircraft thermostat with this temperature compensator will work well in the following harsh environments and safely It aims at making it possible to measure the surface temperature and the temperature of the payload.

       A) Rapid temperature rise of surface temperature 10 ~ 50 ℃ per second

       B) Maximum temperature rise on the surface of the gas 200 ~ 700 ℃

       C) Air temperature 100 ~ 300 ℃ of junction area due to internal heating

       D) combustion and flight vibrations between 100 and 2,000 Hz;

In order to achieve the above object, the aircraft temperature measuring apparatus equipped with a correction function according to the present invention, and a thermocouple attached to the vehicle for measuring the temperature of the aircraft; A junction part connecting the wire part and the general electric wire of the thermocouple to each other; An ALTI sensor connected to an ALTI sensor wire and configured to measure a temperature of the junction unit; A telemetry unit having a transmission function capable of receiving the output voltage of the thermocouple and the output signal of the ALTI sensor and transmitting the signal; A calculation unit configured to calculate a temperature of a vehicle in which a measurement error according to a temperature rise in the junction is compensated by the received output voltage of the thermocouple and an output signal of the ALTI sensor; Characterized in that comprises a.

According to the present invention, a connector for electrically connecting the general wire and the ALTI sensor wire with the telemetry unit may be further included.

)에 정션부 온도상승에 따른 전압 강하량(

)을 더한 값을 파라미터로 하는 수학식으로부터 정션부의 온도상승에 따른 측정오차가 보상된 비행체의 온도(

)를 계산하도록 이루어질 수 있다. In addition, the calculation unit, the voltage measured at the end of the general wire (

Voltage drop due to junction temperature rise

The temperature of the aircraft whose measurement error is compensated for the rise of the temperature of the junction from the equation

) Can be calculated.

)은, 알티디 센서에서 측정된 저항값을 파라미터로 하는 수학식에 의해 계산될 수 있다. In addition, the voltage drop amount (

) May be calculated by a formula that uses the resistance value measured by the Altidi sensor as a parameter.

)은, 알티디 센서에서 측정된 저항값을 열전대의 전압으로 환산하기 위한 다항식 계수(

)를 포함하는 다항식 형태의 수학식으로 계산될 수 있다. In addition, the voltage drop amount (

) Is a polynomial coefficient () for converting the resistance value measured by the Altidi sensor into the voltage of the thermocouple.

It can be calculated as a polynomial equation including).

)는, 전압을 온도로 환산하기 위한 다항식 계수(

)를 포함하는 다항식 형태 의 수학식으로 계산될 수 있다. In addition, the temperature of the vehicle compensated for the measurement error caused by the temperature rise of the junction (

) Is a polynomial coefficient (

It can be calculated as a polynomial equation including).

In addition, the thermocouple temperature compensation device for measuring the temperature of the aircraft according to the present invention, a plurality of junctions each connecting the wire portion and the general wire of the thermocouple, and an Altidy sensor that can measure the temperature of the junction portion one It is made of a junction bundle, characterized in that the junction bundle is built in a metal case provided with a connector mounting portion.

In the thermocouple temperature compensation device for measuring the temperature of the aircraft of the present invention, it is preferable that the junction portion and the ALTI sensor are coated with a shrink tube.

In addition, the junction bundle may be formed by winding the junction part and the ALTI sensor with a silicone tape and injecting silicon into the gap.

In addition, the space between the metal case and the junction bunch may be filled with silicon.

In addition, the connector mounting portion is a connector is mounted, the terminal of the connector is connected to the wires for general wires and ALTI sensor, the junction bundle is preferably located in the center of the metal case.

The features and advantages of the present invention will become more apparent from the following detailed description based on the accompanying drawings. Prior to this, the terms or words used in the present specification and claims are defined in the technical spirit of the present invention on the basis of the principle that the inventor can appropriately define the concept of the term in order to explain his invention in the best way. It must be interpreted to mean meanings and concepts.

In constructing a vehicle temperature measuring device equipped with a correction function of the present invention, the present inventors have examined the possibility of using a thermocouple to measure the temperature of a vehicle in a harsh environment as follows, the thermocouple is relatively stable and has a good response characteristics As an alternative to the Altidi sensor, the company designed a temperature compensation device that compensates for the temperature rise in the new junction area, which must be followed by thermocouples.

       A) Rapid temperature rise of surface temperature 10 ~ 50 ℃ per second

       B) Maximum temperature rise on the surface of the gas 200 ~ 700 ℃

       C) Air temperature 100 ~ 300 ℃ of junction area due to internal heating

       D) combustion and flight vibrations between 100 and 2,000 Hz;

First, to look at the theoretical characteristics, we will look at how to calculate the temperature using a thermocouple.

Temperature conversion equation using a thermocouple, as is well known as follows.

는 전압을 온도로 환산하기 위한 다항식 계수이고,

는 열전대에서 발생한 전압이며,

는 계측된 온도이다.here,

Is a polynomial coefficient for converting voltage to temperature,

Is the voltage generated by the thermocouple,

Is the measured temperature.

In the thermocouple, if there is no error due to the junction, it can be calculated as follows.

은 계측하고자 하는 온도이다.here,

Is the temperature to be measured.

In practice, there is always a difference in electromotive force due to the junction.

는 일반전선 끝단에서 측정된 전압,

는 정션의 기전력에 의한 전압 강하량,

는 일반전선에서 환산한 온도이다.here,

Is the voltage measured at the end of

Is the voltage drop due to the electromotive force of the junction,

Is the temperature converted from the general wire.

Because of this electromotive force difference, as can be seen in Equation 3, the value measured in the general wire can not be converted to the actual temperature. For this reason, there must be compensation for the junction.

On the other hand, since the temperature generated at the junction can be measured by the Altidi sensor, the following equation can be made by using the relation between the Altidi sensor and the temperature and the relation between the temperature and the thermocouple electromotive force.

는 온도에 따른 알티디 센서의 저항을 환산한 전압,

는 알티디 센서의 저항을 열전대의 전압으로 환산하는 다항식 계수,

는 알티디 센서로 측정된 정션 부위의 저항값이다.here,

Is the voltage converted from the resistance of the Altidi sensor according to the temperature,

Is a polynomial coefficient that converts the resistance of the Altidi sensor to the voltage of a thermocouple,

Is the resistance value of the junction region measured by the Altidi sensor.

)과 같은 값이다.The resistance measured by the Altidi sensor is converted into voltage, and the voltage drop caused by the temperature rise in the junction (

Is the same value as

Therefore, you can get the actual temperature by compensating as follows.

는 보정(또는, 보상)된 비행체의 온도이다. 원격측정장치는 열전대에서 발생한 기전력 출력인 일반전선의

값과 알티디 센서에서 측정된 저항값을 지상으로 송신하게 되고 지상에서는 수학식 5를 이용하여 실제 온도를 계산하게 된다.

Is the temperature of the corrected (or compensated) vehicle. The telemetry device is used for general electric wire, which is the electromotive force output generated by thermocouple.

The value and the resistance measured by the Altidi sensor are transmitted to the ground, and the ground calculates the actual temperature using Equation 5.

3 is a conceptual diagram of a vehicle temperature measuring apparatus equipped with a correction function according to an embodiment of the present invention.

In order to solve the temperature distortion phenomenon of the junction bundle, which is an inherent problem of thermocouples, the air vehicle temperature measuring device manufactures a metal case, places a junction bundle in the metal case, and measures the temperature of the junction bundle using an Altidy sensor. Then, a temperature compensation device configured to compensate for the temperature distortion phenomenon can be applied. The theoretical equations described above are constructed in hardware in the following way.

That is, as shown in Figure 3, the aircraft temperature measuring apparatus equipped with a correction function according to the present invention, and a thermocouple attached to the aircraft for measuring the temperature of the aircraft; A junction part 30 connecting the electric wire part 20 and the general electric wire 40 of the thermocouple extending from the temperature measuring point 10 of the thermocouple; An Alti sensor 50 connected to the Alti sensor for conducting wire 60 and for measuring the temperature of the junction unit 30; A remote measuring unit 80 receiving the output voltage of the thermocouple and the output signal of the ALTI sensor 50 and having a transmitting function; A calculator configured to calculate a temperature of a vehicle in which a measurement error according to a temperature rise of the junction unit 30 is compensated by the received output voltage of the thermocouple and the output signal of the ALTI sensor 50; It is configured to include.

Meanwhile, a connector 70 may be further included to electrically connect the general wire 40 and the ALTI sensor wire 60 to the telemetry unit 80.

)에 정션부(30) 온도상승에 따른 전압 강하량(

)을 더한 값을 파라미터로 하는 수학식으로부터 정션부(30)의 온도상승에 따른 측정오차가 보상된 비행체의 온도(

)를 계산하도록 이루어질 수 있다. The calculation unit, the voltage measured at the end of the general wire 40 (

Voltage drop amount according to temperature rise of junction unit 30

The temperature of the vehicle (compensated for the measurement error according to the temperature rise of the junction unit 30) is calculated from the equation that adds) as a parameter (

) Can be calculated.

)은 알티디 센서에서 측정된 저항값을 파라미터로 하는 수학식(예를 들어, 수학식 4)에 의해 계산될 수 있다. In addition, as described above, the voltage drop amount according to the temperature rise of the junction unit 30 (

) May be calculated by a formula (for example, Equation 4) using the resistance value measured by the Alti sensor as a parameter.

)은, 알티디 센서(50)에서 측정된 저항값을 열전대의 전압으로 환산하기 위한 다항식 계수(

)를 포함하는 다항식 형태의 수학식(예를 들어, 수학식 4)으로 계산되고, 정션부(30)의 온도상승에 따른 측정오차가 보상된 비행체의 온도(

)는 전압을 온도로 환산하기 위한 다항식 계수(

)를 포함하는 다항식 형태의 수학식(예를 들어, 수학식 5)으로 계산될 수 있다. In addition, the voltage drop amount according to the temperature rise of the junction unit 30 (

) Is a polynomial coefficient for converting the resistance value measured by the Alti sensor 50 into the voltage of the thermocouple.

) Is calculated as a polynomial equation (for example, Equation 4), including the temperature of the flying vehicle compensated for the measurement error according to the temperature rise of the junction unit 30 (

) Is the polynomial coefficient (

It can be calculated as a polynomial equation (for example, equation 5) including).

Since the Altidy sensor 50 responds to the sudden temperature rise relatively slower than the thermocouple, it is preferable to lower the temperature rise of the junction portion 30. In addition, if there is little temperature rise of the junction 30, there will be little temperature correction error. However, when the aircraft flies so that the internal temperature reaches 100 to 300 ° C. due to the rapid temperature rise of the external gas, the temperature rise of the junction part 30 where the wire part 20 and the general electric wire 40 meet the thermocouple is met. Stopping is not easy. Therefore, it is necessary to use a metal heat absorber to suppress the temperature rise and to prevent hot air from penetrating into the junction portion 30. In addition, it is necessary to use light metals because these devices have to be applied to aircraft.

4 is a plan view of a thermocouple temperature compensation device for measuring the temperature of the aircraft according to the first embodiment of the present invention, Figure 5 is a front view of the thermocouple temperature compensation device for measuring the temperature of the vehicle according to the first embodiment of the present invention, 6 is a side view of a thermocouple temperature compensation device for measuring a vehicle temperature according to Embodiment 1 of the present invention.

The wire part 20 and the general wire 40 of the thermocouple meet inside the metal case 100, and the temperature of the junction part 30 where the wires 20 and 40 meet is met by using the Altidi sensor 50. In order to be able to measure them, all of them were made into one junction bundle 130 and filled with silicone rubber to act as a dustproof agent to protect against vibration. Liquid silicone is good for filling any type of case, and when hardened, it becomes rubber and plays a good role in dust protection.

The connector 70 is installed on the outside of the metal case 100 so that the general wire may be conveniently connected to the telemetry unit 80, and the connector may be additionally installed if necessary. There is no need to newly attach the ALTI sensor 50 to the additionally installed connector 70 ', and just make a body with the junction bundle 130. For example, when the 15-pin connector is employed as the connector 70, the desub connector facilitates the connection with the telemetry unit 80, and can measure many channels (6 to 13 channels) at the same time. Do it. The thermocouple secures the length of the wire portion 20 to about 1 m to the outside of the temperature compensating device of the present invention, so that the temperature measuring point 10 can be easily attached to a gas far away.

The hardware production characteristics can be listed as follows easily.

A) The metal case 100 is made of a metal having a larger heat capacity than air to protect the junction 30 of the thermocouple from the internal air of the heated vehicle.

B) Preventing hot air from penetrating into the metal case 100 in order to slow the temperature rise rate of the junction portion 30.

C) After connecting the general wire 40 and the thermocouple wire 20 is coated with a shrink tube.

C) The Altidi sensor 50 is coated with a shrink tube to create an environment such as the junction portion 30 of the thermocouple.

D) The junction portion 30 and the ALTI sensor 50 of the thermocouple are bundled with a silicon tape or the like to make the junction bundle 130 together, and then coated with a liquid silicon such that there is no gap in the external gap.

E) In order to protect the junction unit 30 from combustion and flight vibrations, the silicon case is filled between the metal case 100 and the junction bundle 130 with a dustproof agent.

D) A connector 70 is installed in the metal case 100 to handle a large number of thermocouples in one device and for convenience of connection with the telemetry unit 80.

E) In order to process more thermocouples, an additional connector 70 'is installed. In this case, an additional ALTI sensor 50 is not required, and the wire portion 20 of the thermocouple is directly connected to the junction bundle 130.

As described above, the thermocouple temperature compensation device for measuring the temperature of the vehicle according to the present invention, a plurality of junctions 30 and the junction 30 connecting the thermocouple wire portion 20 and the general electric wire 40 Altidy sensor 50 capable of measuring the temperature of the) to make one junction bundle 130, the junction bundle 130 is a metal case 100 having a connector mounting portion and the opening for inserting the thermocouple wire portion It is characterized in that it is built.

Preferably, the junction portion 30 and the Alti sensor 50 is coated with a shrink tube. In addition, the bundle of junctions 130 may be formed by winding the junction unit 30 and the Alti sensor 50 with a silicone tape and injecting silicon into an empty gap, and the metal case 100 and the The space between the junction bundles 130 is filled with silicon.

The connector mounting portion is equipped with a connector 70 for connecting to the telemetry unit 80, the terminal of the connector 70 is connected to the general wire 40 and the wire for the Altidy sensor 60. The junction bundle 130 of the junction unit 30 and the ALTI sensor 50 is preferably located at the center of the metal case 100.

8 is a conceptual diagram of connection when the connector is additionally mounted. As can be seen in FIG. 8, the junction 30 'for the thermocouples T7 to T13 and the junction bundle 130' for which it is added are the temperatures of the junction 30 for the initial six thermocouples shown in FIG. The Altidy sensor 50 can be shared for measurement, so no additional Altidi sensor is required.

FIG. 9 corresponds to a top view of a thermocouple temperature compensation device equipped with a connector 70 'in order to process more thermocouples, and FIG. 10 corresponds to a front view thereof. As described above, there is no need for a separate ALTID sensor for the junction portion 30 'of FIG. 8 to be connected to the channels of the connector 70' to be added, so the junction portions 30 and 30 'and the ALTIDY sensor are not required. The junction bundle 130 ″ of 50 may be configured by one Altidi sensor 50 without adding an Altidi sensor separately. However, in order to accurately measure the temperature of the junctions 30 and 30 ', it is natural that a plurality of Alti sensors 50 may be provided.

As described above, the temperature compensator of the present invention has an outer shape made of metal by the metal case 100, and can simultaneously correct six to thirteen thermocouples at a time, and the inside thereof is filled with silicon rubber to prevent vibration. It is strong.

Next, the operation of the air vehicle temperature measuring device having a correction function according to the present invention having such a configuration and the thermocouple temperature correction device for measuring the air temperature will be described.

7 is experimental data showing the actual temperature of the vehicle and the corrected vehicle measurement temperature when measured using a vehicle temperature measuring device equipped with a correction function according to the present invention and a thermocouple temperature correction device for measuring the temperature of the aircraft.

The vertical axis is temperature, the horizontal axis is time, the curve denoted by the circular separator is the actual temperature of the aircraft, the curve denoted by the square separator is the measured temperature of the compensated vehicle, and the curve indicated by the solid line is the junction temperature. It can be seen that there is little error between the actual temperature of the vehicle and the calibrated measurement temperature.

In the present invention, the Altidy sensor 50 is used for temperature correction, and unlike the high temperature external environment, the inside of the temperature correction device is designed to block the heat from the outside air so that the temperature rise of the junction 30 is slow. , The temperature of the site is measured using the Alti sensor (50).

Although the present invention has been described in connection with the above-mentioned preferred embodiment, the scope of the present invention is not limited to the embodiment, various modifications and variations will be possible. Temperature is measured to ensure structural safety of all aircraft, including guided missiles and projectiles. Especially for guided missiles and projectiles flying at high speeds, high temperature loads are an important variable. The biggest cause of this high temperature in the aircraft is aerodynamic heating. Aerodynamic heating generates very large aerodynamic heating at higher speed in proportion to density and in proportion to the third power of speed. This aerodynamic heating adds a lot of heat to the gas, which inevitably raises the temperature, which increases the structure's safety. Aerodynamic heating becomes an important variable for aircraft with higher speed, so the temperature of the structure must be measured to verify its safety.

The effects of the air vehicle temperature measuring device equipped with a correction function according to the present invention configured as described above and the thermocouple temperature correction device for measuring the air temperature are as follows.

That is, a) the rapid temperature rise of the surface temperature is 10 to 50 ° C per second, b) the maximum temperature rise of the gas surface is 200 to 700 ° C, and c) the air temperature at the junction is 100 to 300 ° C due to internal heating. In harsh environmental conditions such as combustion and flight vibrations between Hz, it is possible to precisely measure the temperature of the aircraft, and it is very small and light in size and weight to measure the temperature of aircraft with limited weight and size such as missiles and projectiles. It has a suitable effect.

In addition, in the case of solids and gases having a temperature of 500 ° C. or higher, it cannot be measured by the Altidi sensor 50 and also difficult to attach itself. Although accurate temperature measurement was difficult, the device of the present invention not only makes it possible to easily attach a weldable thermocouple to the vehicle, but also to accurately and effectively measure the temperature of the vehicle.

In addition, the FRP material of the composite combustion tube was failed every time due to the breakage of the Altidi sensor due to the bending load and the vibration of the combustion tube when measured using the Altidy sensor. It can be effectively used for temperature measurement of composites with high interstress stress.

Although the present invention has been described in connection with the above-mentioned preferred embodiments, the scope of the present invention is not limited to these embodiments, and the scope of the present invention is defined by the following claims, and equivalent scope of the present invention. It will include various modifications and variations belonging to.

Claims (10)

delete delete delete delete delete delete delete delete Connect the general wire 40 to the wire portion 20 of the thermocouple attached to the air vehicle to measure the temperature of the aircraft, and cover the connection portion of the thermocouple wire portion 20 and the general wire 40 with a shrink tube. After forming a plurality of junctions 30, one bunch of junctions 130 by enclosing the ALTI sensor 50 and the junction 30 with a shrink tube for measuring the temperature of the junction 30 ), Between the metal case 100 and the junction bundle 130 in a state in which the junction bundle 130 is embedded in the metal case 100 on which the connector 70 for convenient connection with the telemetry unit 80 is mounted. Filling the space with silicon rubber, the junction bundle is protected from vibration by the dust-proof action of the silicone rubber, characterized in that the thermocouple temperature compensation device for temperature measurement. delete

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