JP2009092630A - Aircraft loading type carbon dioxide continuous measuring device - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a device for measuring continuously a carbon dioxide concentration in the atmosphere in the high sky by loading it on an aircraft. <P>SOLUTION: This aircraft loading type carbon dioxide continuous measuring device 10 has a case 100 made of a honeycomb panel, and two tanks 110, 120. The tanks 110, 120 are filled with two kinds of standard gases having each verified concentration of carbon dioxide. An unillustrated carbon dioxide analyzing cell is provided in the case 100 to measure continuously the carbon dioxide concentration in the atmosphere. Each standard gas is analyzed periodically to improve measurement accuracy. The carbon dioxide analyzing cell is stored in a heat insulating device to reduce an influence of a temperature change during flight. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to an aircraft-mounted continuous carbon dioxide measurement device that is mounted on an aircraft and continuously and automatically measures the carbon dioxide concentration in the atmosphere in the high sky.

  In recent years, there is an increasing need for international environmental conservation in order to prevent deterioration of the global environment. In particular, there is an urgent need to reduce the release of carbon dioxide released into the atmosphere as a causative substance of global warming.

Observations of atmospheric components are carried out at various ground stations. However, it is desirable that large-scale global observations be performed over a long period of time using international passenger aircraft that fly at high altitude for a long time.
An object of the present invention is to provide an aircraft-mounted continuous carbon dioxide measurement device that can be mounted on a large aircraft and continuously measure the carbon dioxide concentration in the air in the high sky, and simultaneously store information such as measurement position and altitude. Is.

In order to achieve the above object, an aircraft-mounted carbon dioxide continuous measurement apparatus according to the present invention includes, as a basic means, a central panel made of a honeycomb panel and an upper panel and a lower panel whose central part is fixed to the upper and lower parts of the central panel A casing constituted by a panel, two tanks filled with two kinds of standard gases preliminarily tested for the concentration of carbon dioxide provided on one wall surface side of the central panel of the casing, The carbon dioxide analysis cell that analyzes the concentration of carbon dioxide installed on the other wall side of the center panel, the flow regulator that keeps the flow rate of gas flowing through the carbon dioxide analysis cell constant, and the pressure in the carbon dioxide analysis cell A pressure regulator that keeps constant, an electromagnetic valve that alternately supplies two types of standard gas and outside air to the carbon dioxide analysis cell, and a heat insulating device that houses the carbon dioxide analysis cell are provided.
The valve installed in the tank has a safety valve function that has a rupture plate that ruptures and escapes gas when the gas pressure in the tank exceeds a predetermined pressure. It has characteristics that satisfy the requirements of the US High Pressure Gas Law at the same time.

  According to the aircraft-mounted continuous carbon dioxide measuring apparatus of the present invention, each device is housed in a lightweight and strong casing, and the size and weight can be reduced. Also, the carbon dioxide analysis cell is insulated and the measurement accuracy is improved.

FIG. 1 shows an outline of an aircraft equipped with an aircraft-mounted carbon dioxide continuous measurement apparatus of the present invention, and FIG. 2 shows a cross section of a portion A in FIG.
A storage space 3 is prepared in the lower part of the floor member 2 of the aircraft body 1 and is equipped with, for example, a tank 5 for fresh water used in the aircraft.
The aircraft-mounted carbon dioxide continuous measurement apparatus 10 of the present invention is mounted using the space of the storage space 3. At the time of mounting, an appropriate mounting member is prepared and suspended from the floor member 2 so as to avoid interference with existing equipment and the like and not affect the airframe structure.
Since there are a plurality of models on which the aircraft-mounted carbon dioxide continuous measurement apparatus 10 is mounted, the aircraft-mounted carbon dioxide continuous measuring apparatus 10 is mounted at a position suitable for each model.

3 is a perspective view seen from one direction showing an outline of an aircraft-mounted carbon dioxide continuous measuring apparatus, FIG. 4 is a perspective view seen from the other side, and FIG. 5 is an explanatory view of a housing.
An aircraft-mounted carbon dioxide continuous measurement apparatus, indicated as a whole by reference numeral 10, has a casing 100 formed of a honeycomb panel. The housing 100 includes a central panel 102, and an upper panel 104 and a lower panel 106 whose central part is fixed to the upper and lower parts of the central panel 102.
Top panel 104 and bottom panel 106 is secured by screws _{S 1} with respect to central panel 102. Central panel 102, the openings H ₁ for attaching the measuring device or the like are prepared in advance.
On one side of the central panel 102, two tanks 110 and 120 filled with two kinds of standard gases whose carbon dioxide (CO ₂ ) concentration has been previously tested are mounted. The tanks 110 and 120 are automatically sent to a carbon dioxide analysis cell 300 described later by an electromagnetic valve 220 or the like.

The aircraft-mounted carbon dioxide continuous measuring device 10 is equipped with equipment for alternately sending these two types of standard gas and the atmosphere to the carbon dioxide measuring device, and a pump 160 that pressurizes the collected high-air atmosphere, a dryer 140, filters 150 and 152, a regulator 130, and the like are provided on the tanks 110 and 120 side.
A carbon dioxide analysis cell 300 stored in the heat insulating device 400 is installed in the casing 100 on the opposite side across the central panel 102, and flow rate regulators 170 and 172, pressure gauges 180 and 182, and a pressure controller 132. , A flow rate controller 134 and the like are provided.
As the electrical components, an input board 200, an RS232C module 210, a solenoid valve 220, an ARINC converter 230, an ARINC filter 240, a storage module 250, a data logger 260, and the like are provided.
Further, a DC converter 202 is provided on the tanks 110 and 120 side, and the direct current power supplied from the airframe side is replaced with a direct current power supply for the aircraft-mounted carbon dioxide continuous measuring device 10.
In addition, a noise filter 280 that prevents noise from entering the line is also provided.

The carbon dioxide analysis cell 300 has a cylindrical analysis chamber 320 in a casing 310.
The analysis chamber 320 has an infrared light emitting lamp 340 at one end, and an infrared light receiving element 350 is provided at the other end. An optical filter 360 is provided in front of the infrared light receiving element 350.
A gas G ₁ supply port 330 to be measured is provided near the infrared light emitting lamp 340 in the analysis chamber 320, and a gas discharge port is provided on the infrared light receiving element 350 side.

The carbon dioxide molecule CO ₂ contained in the supplied gas G ₁ absorbs infrared IR having a wavelength of 4.26 μm or the like irradiated from the infrared light emitting lamp 340. Other molecules M ₁ and M ₂ contained in the gas G ₁ do not absorb infrared IR.
Therefore, the CO ₂ concentration can be measured by measuring the amount of infrared IR received by the infrared light receiving element 350 as compared to the amount of infrared IR irradiated from the infrared light emitting lamp 340.

  The value of the carbon dioxide concentration output from the carbon dioxide analysis cell 300 is greatly influenced by the ambient temperature in addition to the carbon dioxide concentration. Therefore, as a measure not affected by changes in the ambient temperature, a heater is attached so as to keep the cell temperature constant at 50 ° C. However, the cell temperature cannot be kept constant when a sudden drop in ambient temperature occurs. Therefore, it is necessary to insulate the cell as a countermeasure when a sudden drop in ambient temperature occurs. When the ambient temperature drop occurs, the value of carbon dioxide concentration is indicated to be lower than the actual value. In addition, the rapid change cannot be compensated for by calibration with the standard gas, and the accuracy of the measured value deteriorates.

  The front cargo compartment in which the aircraft-mounted carbon dioxide continuous measurement device 10 is mounted is a place that is susceptible to a change in the outside temperature unlike the cabin, although it is pressurized and partly temperature controlled. The place where the aircraft-mounted carbon dioxide continuous measurement device 10 is attached may have a minimum temperature of about 5 ° C.

When the temperature change in the front cargo compartment equipped with the aircraft-mounted carbon dioxide continuous measurement device 10 was measured, the maximum was ± 0.6 ° C / min (-0.6 ° C / min during the rise, + 0.6 ° C during the descent) / Min).
Therefore, the standard of the temperature change is set to ± 0.6 ° C./min, the heat insulating device 400 is designed, and the carbon dioxide analysis cell 300 is covered.

FIG. 7 is a perspective view showing a component configuration of the heat insulating device 400.
Insulating device 400 includes a case 410 for housing the carbon dioxide analysis cell 300 has a support member 420 for fixing the case 410 to the mating member, it is fixed by a screw member _{F 1.} The carbon dioxide analysis board 430 is equipped with a connector 432 and the like.
The carbon dioxide analysis cell 300 is accommodated in the case 410 while being covered with four heat insulating materials 450, 452, 454, 456, and the lid 412 of the case 410 is closed.
The first heat insulating material 450 has a shape that covers the lower surface and both ends of the carbon dioxide analysis cell 300.
The second heat insulating material 452 and the third heat insulating material 454 are plate-shaped and cover the back surface and the front surface of the carbon dioxide analysis cell 300. The fourth heat insulating material 456 has a shape that covers the upper surface of the carbon dioxide analysis cell 300.
It has been confirmed by experiments that a predetermined heat insulating effect is obtained by housing the carbon dioxide analysis cell 300 in the heat insulating device 400 having the above-described structure.

Next, the tanks 110 and 120 filled with two kinds of standard gases are high-pressure gas containers (called cylinders) and must be compatible with both the Japanese high-pressure gas safety law and the US high-pressure gas law. is there.
The tanks 110 and 120 mounted on the aircraft-mounted carbon dioxide continuous measurement apparatus 10 of the present invention have performance that meets the above-described conditions.
In addition, a valve 500 that can be attached to the tops of the tanks 110 and 120 has been newly developed to comply with Japanese and US legal systems.

FIG. 8 is a cross-sectional view showing the structure of the valve 500.
The valve 500 has a valve main body 510 and is screwed to the top of the tank by a screw portion 511. The valve main body 510 has a passage 512 that communicates with the tank and a passage 514 that communicates with the lines L ₁ and L _2, and a valve seat 513 is provided between both the passages 512 and 514.
A valve body 520 that is inserted into the valve main body 510 so as to face the valve seat 513 has a packing material 524 and is in contact with the valve seat 513. A cap member 530 attached to the valve main body 510 via a screw portion 531 has an inner screw portion 534, and the screw member 550 is screwed together. The screw member 550 is rotated by the knob 540.

  The screw member 550 presses the valve body 520 through the receiving member 554. A return spring 522 is disposed outside the valve body 520, and always biases the valve body 520 in the valve opening direction. A bypass passage 516 that connects the passage 512 communicating with the tank of the valve body 510 and the outside of the valve body 510 is provided, and is covered with a cap nut member 560. The outlet of the bypass passage 516 is sealed with a rupturable plate 570.

The rupture disc 570 functions as a safety valve that ruptures and discharges gas from the passage 562 to the outside when the gas pressure in the tank rises above a predetermined value.
The pressure at which the rupturable plate 570 is broken is set based on the regulations of the Japanese High Pressure Gas Safety Law and the US High Pressure Gas Law.
Specifically, it is required that the burst pressure of the rupturable plate does not exceed 80% of the pressure resistance test pressure 23.0 MPa of the tanks 110 and 120 employed this time, and not less than 90%.
Therefore, the rated pressure was set to 18.4 MPa corresponding to 0.8 times 23.0 MPa, and a rupture plate 570 that ruptures from 16.6 MPa (18.4 MPa × 0.9) to 18.4 MPa was manufactured.

FIG. 9 is an explanatory diagram showing the operation of the aircraft-mounted carbon dioxide continuous measurement apparatus of the present invention.
In the aircraft-mounted continuous carbon dioxide measuring apparatus of the present invention, two types of standard gases are prepared in which the carbon dioxide concentration is previously verified to a known value. Then, the standard gas is allowed to flow through the carbon dioxide analysis cell at regular intervals during the measurement of the atmosphere, and carbon dioxide is measured. The entire apparatus is configured so that a highly accurate measurement value can be obtained by correcting the measured carbon dioxide concentration in the atmosphere with reference to the measured carbon dioxide concentration of the standard gas.

The aircraft-mounted carbon dioxide continuous measurement apparatus 10 of the present invention includes tanks 110 and 120 filled with two kinds of standard gases GK ₁ and GK ₂ . The first tank 110 is filled with the _first standard gas GK ₁ that has been verified to have a carbon dioxide concentration that is assumed to be higher than the upper limit value of the carbon dioxide concentration contained in the air to be measured.

This first standard gas GK ₁ is calibrated to a carbon dioxide concentration of 390 ppm, for example.
The second tank 120 is filled with the _second standard gas GK ₂ that has been verified to have a carbon dioxide concentration that is assumed to be lower than the lower limit value of the carbon dioxide concentration in the air to be measured.
The second standard gas GK ₂ is calibrated to a carbon dioxide concentration of 340 ppm, for example. At the start of measurement, the electromagnetic valve 220 first opens the first line L ₁ through which the first standard gas GK ₁ flows, and sends the first standard gas GK ₁ to the carbon dioxide analysis cell 300. This time is set to 50 seconds, for example. The carbon dioxide analysis cell 300 analyzes the first standard gas GK ₁ and records the measurement result K ₁ of the carbon dioxide concentration as 390 ppm.

Next, the solenoid valve 220 closes the circuit of the first line _{L 1,} opening the second line _{L 2} and supplies the second standard gas GK _2. The carbon dioxide analysis cell analyzes the second standard gas GK ₂ and records the measurement result K ₂ as 340 ppm.
When the analysis of the standard gas is completed, the solenoid valve 220 closes the circuits of the first line L ₁ and the second line L ₂ , and sends the air collected from outside the aircraft to the carbon dioxide analysis cell 300. opening the L _3.

During the third line L _3, the pump 160 or the like for pressurizing the dryer 140 and air to remove moisture collected in the air is inserted. Carbon dioxide analysis cell 300 which air is supplied, the concentration of carbon dioxide in the atmosphere continuously analyzed, records the measurement results M _1.
The continuous measurement time is, for example, 10 minutes. When this continuous measurement is completed, the aircraft-mounted carbon dioxide continuous measurement device 10 returns to the cycle of analyzing the standard gas again, and records the reference value of the carbon dioxide concentration of the standard gas.
After this standard gas measurement cycle, we return to a continuous measurement cycle of atmospheric carbon dioxide concentration.

The aircraft-mounted continuous carbon dioxide measuring apparatus 10 of the present invention can continuously measure the CO ₂ concentration in the atmosphere on the route on which the aircraft flies by repeating the above-described cycle.
The flight route and altitude data are taken into the airborne carbon dioxide continuous measurement device 10 from the ARINC bus of the aircraft via the ARINC converter 230.
According to the present invention, the carbon dioxide concentration in the atmosphere on the entire flight route of an aircraft can be continuously measured and recorded.

BRIEF DESCRIPTION OF THE DRAWINGS Explanatory drawing which shows the outline | summary of the aircraft carrying the aircraft-mounted type carbon dioxide continuous measuring apparatus of this invention. Sectional drawing of the A section of FIG. BRIEF DESCRIPTION OF THE DRAWINGS The perspective view seen from one direction which shows the outline | summary of the aircraft mounting type carbon dioxide continuous measuring apparatus of this invention. The perspective view seen from the other side which shows the outline | summary of the aircraft mounting type carbon dioxide continuous measuring apparatus of this invention. Explanatory drawing of a housing | casing. Explanatory drawing which shows the outline | summary of a carbon dioxide analysis cell. The perspective view which shows the components structure of a heat insulation apparatus. Sectional drawing which shows the structure of a valve | bulb. Explanatory drawing which shows the effect | action of the airborne carbon dioxide continuous measuring apparatus of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Aircraft 10 Airplane-mounted carbon dioxide continuous measuring apparatus 100 Housing | casing 110 1st tank 120 2nd tank 200 Input board 230 ARINC converter 300 Carbon dioxide analysis cell 400 Heat insulation apparatus 500 Valve

Claims (2)

An aircraft-mounted carbon dioxide continuous measurement device that is detachably mounted in an aircraft storage space,
A central panel made of honeycomb panel, a casing composed of an upper panel and a lower panel whose central part is fixed to the upper and lower parts of the central panel, and a concentration of carbon dioxide provided on one wall side of the central panel of the casing Two tanks filled with two kinds of standard gases that have been verified in advance, a carbon dioxide analysis cell for analyzing the concentration of carbon dioxide provided on the other wall surface of the central panel of the housing, and carbon dioxide analysis A flow regulator that keeps the flow rate of gas flowing through the cell constant, a pressure regulator that keeps the pressure inside the carbon dioxide analysis cell constant, and an electromagnetic that alternately supplies two types of standard gas and outside air to the carbon dioxide analysis cell An aircraft-mounted continuous carbon dioxide measuring device, comprising a valve and a heat insulating device that houses a carbon dioxide analysis cell.   The valve installed in the tank has a safety valve function that has a rupture disk that ruptures and escapes gas when the gas pressure in the tank exceeds a predetermined pressure. The aircraft-mounted carbon dioxide continuous measurement apparatus according to claim 1, which has characteristics satisfying the provisions of the high-pressure gas method at the same time.

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