JP2002310551A - Cooling system with cold storage function - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a cooling system with cold storage function in which the high output circuit part of an aircraft can be cooled without causing abrupt increase in engine bleed air or power consumption. SOLUTION: The high output circuit part 2 is cooled by heat transfer fluid being cooled by a cooling means 3. A cold storage substance which can store cold heat is placed in the channel 40 of the heat transfer fluid such that it can exchange heat with the heat transfer fluid. When the temperature of the heat transfer fluid is lower than that of the cold storage substance, the cold storage substance is cooled by the heat transfer fluid and when the temperature of the heat transfer fluid is higher than that of the cold storage substance, the heat transfer fluid is cooled by the cold storage substance.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION A system for cooling a high-power circuit part such as a radar or laser directional electromagnetic wave transmitting part or an ultra-high-speed arithmetic circuit part in an aircraft in order to operate stably when a large amount of electric power is applied. About.

[0002]

2. Description of the Related Art For example, an electromagnetic wave transmitting portion of an electromagnetic wave transmitting device such as a radar mounted on an aircraft for searching for a victim, a wreck, a suspicious ship, etc. is composed of a conventional transmitting tube and a number of semiconductor elements. The direction change of the electromagnetic wave is changed from a method of changing the direction of the transmission tube to a method of changing the direction without changing the movable part by controlling the phase of the electromagnetic wave emitted from each element. . In such a system, since a power control circuit is provided for each semiconductor element, there are a large number of semiconductor elements with a power control circuit in order to stabilize performance so that electromagnetic waves can be transmitted stably. It is necessary to cool the entirety of the electromagnetic wave transmission part constituted by the above and maintain it within a certain set temperature range. Therefore, a method of directly cooling an electromagnetic wave transmitting portion by using an antifreeze solution called brine, which is obtained by adding an additive with water or the like as a main component, is used as a heat transfer fluid. The heat transfer fluid is cooled in accordance with the temperature rise by an in-machine cooling system such as an air cycle cooling system using engine bleed air in an aircraft or a vapor cycle cooling system using a refrigerant. The heat transfer fluid is also used for cooling a high-power circuit portion other than the electromagnetic wave transmitting portion, for example, an ultra-high-speed arithmetic circuit or an inverter circuit for controlling power supply to various electronic devices during operation.

[0003]

[0005] In recent years, with the demand for higher performance in recent years, aircraft often include a signal processor or the like that performs various high-speed arithmetic processing. Further, it is required to cope with the transmission of high-output electromagnetic waves in order to improve functions. For this reason, when transmitting electromagnetic waves or performing high-speed arithmetic processing, a large amount of heat is expected from high-power circuit parts including the accompanying circuit parts, etc., and it is necessary to cool the heat transfer fluid that has absorbed the generated heat. The capacity of the in-flight cooling system had to be increased.

However, in order to increase the capacity of the in-board cooling system, it is necessary to increase the amount of engine bleed air when the in-board cooling system employs an air cycle system.
When the vapor cycle method is adopted, it is necessary to increase the power consumption in order to increase the refrigerant compression capacity. In any case, an increase in power consumption in the high-power circuit portion is not preferable because the load on the engine during flight is greatly increased. In particular, airplanes that emit directional electromagnetic waves such as radar waves on the ground or at sea are operated at a reduced flight altitude, so the temperature of the outside air at which the pumped heat is released increases. In many cases, the capacity of the cooling system must be large, and not only the engine load must be increased but also the cooling system must be large and heavy.

[0005]

A cooling system with a cold storage function according to the present invention is a cooling system for cooling a high-power circuit portion of an aircraft by a heat transfer fluid cooled by a cooling means. Is disposed in the heat transfer fluid flow path so as to be able to exchange heat with the heat transfer fluid,
When the heat transfer fluid is colder than the cold storage material, the heat transfer fluid cools the cold storage material, and when the heat transfer fluid is hotter than the cold storage material, the heat transfer fluid is cooled by the cold storage material. It is characterized by being performed. The aircraft includes a rotary wing aircraft such as a helicopter. According to the configuration of the present invention, when there is enough power because the high-power circuit part is not operating, when the aircraft is flying in a high altitude or cold region, or when the aircraft is in standby on the ground before the flight, In the case where the power source of the aircraft can be used, the cooling means is driven to cool the heat transfer fluid without overloading the engine of the aircraft, without bleeding the engine or increasing the power consumption of the aircraft, The heat transfer fluid cools the regenerator material to accumulate cold heat. As a result, when the heat transfer fluid becomes higher than the cold storage material due to the operation of the high-power circuit portion, the heat transfer fluid is cooled by the accumulated cold heat, thereby imposing an excessive load on the aircraft engine. It is possible to cool a high-power circuit portion such as an electromagnetic wave transmission portion without the need. In addition, when cooling the electromagnetic wave transmitting part as a high-power circuit part, if there is a possibility that countermeasures against the electromagnetic wave may be taken from the target of electromagnetic wave transmission, strong electromagnetic waves should be transmitted almost until approaching the target. In general, electromagnetic waves are transmitted intermittently instead of continuously. In such a case, according to the present invention, the cold energy is accumulated in the cold accumulating material while flying for movement at an altitude sufficient to increase the flight efficiency, and the accumulated cold energy is used when transmitting the electromagnetic wave. To cool the transmitting part.

Preferably, the cooling means is capable of cooling the heat transfer fluid to a temperature lower than the melting point of the cold storage material. Thereby, the regenerator material is cooled to the melting point or less and solidified,
The heat transfer fluid can be cooled by absorbing the heat of fusion when the regenerator material melts, and the heat of solidification is greater than when the regenerator material is in the liquid phase.
Aircraft that can hold 80 times the heat of solidification as cold heat, and can absorb all or part of the heat generated in high-power circuit parts such as electromagnetic wave transmission parts by a cold storage substance with a large heat capacity even in a small amount, requiring aircraft to be lightweight It is preferable for

The heat transfer fluid is caused to flow in a circulation passage, and cooling means for cooling the air circulating in the aircraft body by the heat transfer fluid is provided. A first flow path for supplying the heat transfer fluid to the circuit portion and a second flow path for supplying the heat transfer fluid to the cooling means for the air circulating in the aircraft body are provided, and the heat transfer fluid in the first flow path is provided. Preferably, means is provided for changing the ratio of the flow rate to the flow rate of the heat transfer fluid in the second flow path in accordance with a variable that correlates to a change in temperature of the heat transfer fluid. Thus, the heat transfer fluid cooled while the high-power circuit portion is not operating can be effectively used for cooling the air circulating in the machine.

Preferably, the regenerator material is enclosed in a number of expandable and contractible containers, which are arranged in the flow path of the heat transfer fluid. Accordingly, the contact area between the cold storage material and the heat transfer fluid can be increased to efficiently perform heat exchange, and the volume fluctuation of the cold storage material can be absorbed by expansion and contraction of the container.

A RAM introduced from outside the body of the aircraft
It is preferable that heat can be exchanged between the air and the refrigerant of the cooling means of the heat transfer fluid. Thereby, when the aircraft is flying at high altitude, the cold heat can be efficiently accumulated in the cold storage material, which is suitable for actual operation.

[0010]

1 and 2 show a cooling system A with a cool storage function for cooling a high-power circuit part in a phased array radar 2 mounted on an airframe 1 of an aircraft. As the radar 2, one that generates heat exceeding 10 kW, for example, when transmitting electromagnetic waves at full power is used. The high-power circuit portion of the radar 2 is constituted by an electromagnetic wave transmitting portion composed of a large number of semiconductor elements with a power control circuit, and has a cooling jacket 20 for cooling the electromagnetic wave transmitting portion with a heat transfer fluid. For example, a heat sink is attached to each element constituting the electromagnetic wave transmitting portion, and each heat sink is covered by the cooling jacket 20. The heat transfer fluid supplied from the cooling system A is supplied to the cooling jacket 2.
When the electromagnetic wave transmitting portion is introduced through the supply port 21 and discharged through the return port 22, the electromagnetic wave transmitting portion is cooled by the heat transfer fluid. In the present embodiment, a general high-concentration ethylene glycol solution or the like is used as the heat transfer fluid.

The cooling system A includes a cooling device 3 and a regenerator 4, and the cooling device 3 cools the heat transfer fluid flowing through the circulation flow passage 40 in the regenerator 4. The cooling device 3 also serves as an air conditioner for the internal space of the airframe 1 that cools the air circulating in the airframe, and functions as an air cycle type cooling device 31 that functions by extracting air from the engine 5 of the aircraft.
And a vapor cycle type cooling device 32 for supplementing the cooling capacity of the air cycle 31.

The air cycle type cooling device 31 cools the engine bleed air by heat exchange with RAM air introduced from outside the body in the first heat exchanger 311, compresses the extracted air by the centrifugal compressor 312, and cools the second heat exchanger. At 313, cooling is performed again by heat exchange with the RAM air, and further cooled at the regenerative heat exchanger 314, whereby the condensed water of the engine bleed air is removed by the water remover 315. To obtain cold air. A part of the obtained cool air is supplied to the regenerative heat exchanger 314.
The engine bleed air is cooled by passing through the air passage, and then supplied to the cabin 6 or the like of the aircraft via the duct 317 as air circulating in the machine. The remainder of the obtained cool air passes through the cooler 42 of the cool storage device 4 to cool the heat transfer fluid,
Thereafter, the air is supplied to the cabin 6 and the like as in-machine air.
Although the first heat exchanger 311 and the second heat exchanger 313 are illustrated as a single unit in the drawing, a plurality of units are actually provided on the body 1.

The vapor cycle type cooling device 32 stores a high-temperature, high-pressure refrigerant compressed by a compressor 322 driven by an electric motor 321 into a RAM.
The heat is exchanged with the air to radiate heat in the condenser 323 to be cooled and liquefied, and the pressure is reduced by the expansion valve 324, evaporated by the evaporator 325, and returned to the compressor 322 again to complete the cycle. The refrigerant is H, which has no ozone destruction effect.
FC134a or the like is suitable. The evaporator 325
In the above, the heat transfer fluid flowing through the circulation flow passage 40 of the regenerator 4 is cooled by the cooling ability exerted by the refrigerant taking away the surrounding heat during the evaporation. The heat generated in the machine may be removed by directly cooling the air circulating in the machine by the cooling capacity. Although the single condenser 323 is shown in the figure, a plurality of condensers 323 may be provided on the body 1.

The regenerator 4 sends a heat transfer fluid under pressure by a main pump 41. Thereby, the heat transfer fluid is cooled in the evaporator 325 and the cooler 42 as described above. The cooled heat transfer fluid is supplied to the circulation channel 4
By the main distribution valve 43 provided in the main body 0, the air is distributed to the in-machine cooler 44 arranged in the machine body 1 and the cooling jacket 20 of the radar 2 so as to be introduced through the pipes a and b. The heat transfer fluid introduced into the in-machine cooler 44 cools the circulating air in the machine and returns to the suction side of the main pump 41. Further, the heat transfer fluid introduced into the cooling jacket 20 is returned to the suction side of the main pump 41 after cooling the electromagnetic wave transmitting portion of the radar 2. The in-machine cooler 44 may be plural.

A regenerative substance capable of accumulating cold heat is disposed so as to be able to exchange heat with a heat transfer fluid flowing in the circulation channel 40. In the present embodiment, a cold storage reservoir tank 7 filled with a heat transfer fluid is connected between the main pump 41 and the evaporator 325 by piping, and the cold storage reservoir tank 7 is connected to a reservoir pump 451 by piping. Is connected to the main distribution valve 43 and the sub distribution valve 453 via a switching valve 452, and the sub distribution valve 453 is connected to the in-machine cooler 44 and the supply port 21 of the cooling jacket 20 via pipes c and d. Connected. Thus, when the heat transfer fluid is lower in temperature than the cold storage material, the cold storage material is cooled by the heat transfer fluid, and when the heat transfer fluid is higher temperature than the cold storage material, the heat transfer fluid is cooled by the cold storage material.

As shown in FIG. 3, a main body 71 of the cold storage reservoir tank 7 is filled with a large number of spherical capsule containers 72 filled with pure water as a cold storage material from a capsule port 71a. The regenerative substance is not limited to water, but may be any substance capable of accumulating cold heat. In addition to water, formic acid, acetic acid, p-xylene, glycerin, and other materials are used.
It is preferable to employ a substance having a melting point between-25 ° C and a substance having a stable molecular structure as a main component. The capsule-shaped container 72 is made of a polymer material that does not allow water molecules to permeate and does not break due to expansion and contraction even if the volume changes due to freezing of pure water, for example, polytetrafluoroethylene (PTFE). It is made. Those capsule-shaped containers 7
A pair of mesh plates 73 are mounted inside the main body 71 so as to hold the two. Although the container 72 is partially omitted in the drawing, it is filled so as to substantially fill the space between the mesh plates 73. A guide tube 74 is provided at the center of the main body 71, and connection pipes 75 and 76 for connecting to the circulation channel 40 are introduced into the guide tube 74. The inside of the guide tube 74 is connected to one end by a partition plate 74a. The leading end of one connecting pipe 75 is arranged at one end side of the partition plate 74a, and the leading end of the other connecting pipe 76 is partitioned by the partition plate 7a.
It is arranged on the other end side than 4a. The stirring blade 77 of the heat transfer fluid in the main body 71 is driven to rotate by the motor 78. Airbag 79 that absorbs the volume fluctuation of the cold storage material
Is disposed in the main body 71, and the inside of the airbag 79 communicates with the outside of the main body 71 through a pipe 79a so that a change in volume due to solidification of the cold storage material and a change in volume due to a change in temperature of the heat transfer fluid can be absorbed. It has become. As a result, the capsule-shaped container 72 is disposed in the flow path of the heat transfer fluid, and heat exchange is performed between the heat transfer fluid flowing in the direction indicated by the arrow A or B in the figure and the cold storage material. At this time, since the regenerator material is sealed in a large number of capsule-shaped containers 72, the contact area between the regenerator material and the heat transfer fluid is increased so that heat exchange is performed efficiently. It can be absorbed by the expansion and contraction of the container 72. In addition, a container other than the spherical capsule-like container 72, for example, a tubular or plate-like container may be used as a container for enclosing the regenerative substance.

As shown in FIG. 4, the motor 321, the main pump 41, the reservoir pump 451, the switching valve 452, the main distribution valve 43, and the sub distribution valve 453 are connected to a control device 50 mounted on the body 1. You. Further, a temperature sensor 51 for detecting the temperature of the air circulating in the machine as a variable correlated to the temperature change of the heat transfer fluid is connected to the control device 50. Its temperature sensor 51
The motor 321, the main pump 41, the reservoir pump 451, the switching valve 452, the main distribution valve 4 according to a signal output from the control device 50 according to the detected temperature of
3, and the sub-distribution valve 453 is activated. By this operation, the compression capacity of the compressor 322 can be changed, the discharge amount of the main pump 41 can be changed, the discharge direction of the reservoir pump 451 can be changed, and the switching valve 452 connects the reservoir pump 451 to the circulation flow path. 40 and a state connected to the sub-distribution valve 453.
3. The distribution ratio of the heat transfer fluid by the sub distribution valve 453 can be changed.

When the aircraft having the above configuration is flying at high altitude or in a cold region, the temperature of the RAM air introduced into the first heat exchanger 311, the second heat exchanger 313, and the condenser 323 from the outside of the airframe. Is low, and since the steam extracted from the compressed air outside the engine contains a small amount of water vapor and does not generate heat due to condensation of the water vapor during cooling, the temperature of the engine extracted air, which is the refrigerant in the air cycle cooling device 31, is sufficiently low before expansion. And a vapor cycle cooling device 32
Even if the refrigerant in the above is hardly compressed, the temperature becomes sufficiently low before expansion. Thereby, the cooling device 3 can cool the heat transfer fluid below the melting point of the cold storage material, and the temperature of the heat transfer fluid that has exited the cooler 42 becomes equal to or lower than the melting point of pure water as the cold storage material, for example, −10 ° C. It is also possible to: In this case, the temperature of the air circulating in the machine also decreases according to the temperature of the heat transfer fluid. When the temperature of the circulating air in the machine detected by the temperature sensor 51 is equal to or lower than a predetermined set temperature,
The control device 50 operates the reservoir pump 451 and the switching valve 452 so that the heat transfer fluid reaches the cold storage reservoir tank 7 via the switching valve 452 and the reservoir pump 451 in the circulation flow path 40. As a result, water as a cold storage substance solidifies in the cold storage reservoir tank 7, and cool heat is stored. When the temperature of the air circulating in the machine rises, the control device 50 changes the discharge amount of the main pump 41 according to the temperature detected by the temperature sensor 51, or controls the distribution ratio of the heat transfer fluid by the distribution valve 43. Is changed, the ratio of the flow rate of the heat transfer fluid passing through the cold storage reservoir tank 7 to the flow rate of the heat transfer fluid passing through the in-machine cooler 44 is changed, and the temperature of the air circulating in the machine is maintained at an appropriate value.
That is, as a part of the circulation flow path 40, a pipe b for supplying a heat transfer fluid from the main distribution valve 43 to the cooling jacket 20 and a pipe d for supplying a heat transfer fluid from the sub distribution valve 453 to the cooling jacket 20 are provided. First
A flow path, a pipe a for supplying a heat transfer fluid from the main distribution valve 43 to the internal cooler 44, and a sub distribution valve 453;
And a second flow path composed of a pipe c for supplying a heat transfer fluid to the in-machine cooler 44 from the control device 5
0 is a ratio of the flow rate of the heat transfer fluid in the first flow path to the flow rate of the heat transfer fluid in the second flow path when the detected temperature of the circulating air in the machine is increased, which is a variable correlated with the temperature change of the heat transfer fluid. When the detected temperature of the circulating air in the machine is lowered, the ratio is increased. The ratio of the flow rate of the heat transfer fluid in the first flow path to the flow rate of the heat transfer fluid in the second flow path is determined according to a variable other than the temperature of the air circulating in the machine, which correlates with a temperature change of the heat transfer fluid. May be changed. For example,
A variable correlated with the temperature change of the heat transfer fluid is defined as the amount of power input to the high-power circuit portion, and the discharge amount of the main pump 41 is changed or distributed according to the on / off of the power input to the high-output circuit portion. By changing the distribution ratio of the heat transfer fluid by the valve 43, the ratio of the flow rate of the heat transfer fluid in the first flow path to the flow rate of the heat transfer fluid in the second flow path is changed. That is, when the power supply to the high-power circuit portion is on, the ratio of the flow rate of the heat transfer fluid in the first flow path to the flow rate of the heat transfer fluid in the second flow path is reduced, and when the power supply is off. Increases the ratio.

When the aircraft having the above configuration transmits electromagnetic waves from the radar 2 at a low altitude, the temperature at the electromagnetic wave transmission site increases, so that the air cycle cooling device 31 and the vapor cycle cooling device 32 are connected. It works,
The temperature of the heat transfer fluid that has exited the cooler 42 is higher than the melting point of pure water that is a cold storage material. In this case, the temperature of the air circulating in the machine also increases according to the temperature of the heat transfer fluid. When the temperature of the air circulating in the machine detected by the temperature sensor 51 exceeds the set temperature, the control device 50 causes the heat transfer fluid to reach the switching valve 452 via the cold storage reservoir tank 7 and the reservoir pump 451 in the circulation flow path 40. The reservoir pump 451 so as to reach the sub distribution valve 453 after
And the switching valve 452 are operated. As a result, the heat transfer fluid is cooled by the cold stored in the cold storage material in the cold storage reservoir tank 7. The control device 50 also controls the distribution valves 43, 4 and 4 according to the temperature detected by the temperature sensor 51.
By changing the distribution ratio of the heat transfer fluid by 53, the ratio of the flow rate of the heat transfer fluid passing through the cold storage reservoir tank 7 to the flow rate of the heat transfer fluid passing through the in-machine cooler 44 is changed, and the temperature of the air circulating in the machine is changed. Is kept at the appropriate value. That is, when the detected temperature of the circulating air in the machine rises, the control device 50 reduces the ratio of the flow rate of the heat transfer fluid in the first flow path to the flow rate of the heat transfer fluid in the second flow path, and reduces When the detected temperature decreases, the ratio increases. While the temperature detected by the temperature sensor 51 exceeds the above set temperature, while the transmission of the electromagnetic wave from the radar 2 is stopped, no heat is generated at the electromagnetic wave transmitting portion, so that there is a margin for power consumption. In this case, the control device 50 stops the reservoir pump 451 to stop the flow of the heat transfer fluid passing through the cold storage reservoir tank 7, and increases the compression capacity of the compressor 322 driven by the motor 321 to increase the vapor cycle type cooling device. The cooling capacity of the air conditioner 32 may be increased, and the cooling capacity of the air circulating in the machine in the in-machine cooler 44 may be increased.

According to the above configuration, the cooling device 3 is driven to cool the heat transfer fluid without applying an excessive load to the aircraft engine 5, and the regenerator material is cooled by the heat transfer fluid to accumulate cold heat. it can. Thereby, when the heat transfer fluid becomes higher in temperature than the cold storage material due to the transmission of the electromagnetic wave, the heat transfer fluid is cooled by the accumulated cold heat, so that the electromagnetic wave can be applied without applying an excessive load to the engine 5 of the aircraft. The transmitting part can be cooled. In addition, the regenerator material is cooled to the melting point or lower to solidify it, and the heat transfer fluid can be cooled by absorbing the heat of fusion when the regenerator material melts. This is preferable for an aircraft that can absorb all or a part of the generated heat and requires light weight. Further, the heat transfer fluid cooled while the electromagnetic transmission portion is not transmitting the electromagnetic wave can be effectively used for cooling the circulating air in the machine. Further, since heat can be exchanged between the RAM air introduced from outside the airframe 1 and the refrigerant of the cooling device 3,
When the aircraft is flying at high altitude, cold energy can be efficiently accumulated in the cold storage material.

Instead of the cold storage reservoir tank 7, a cold storage reservoir tank 8 according to a modification of FIG.
In the main body 81 in which the heat transfer fluid is not mixed with the cold storage substance 82, a flow path through which the heat transfer fluid flows may be provided. That is, in the cold storage reservoir tank 8, the main body 81
A cold storage material 82 such as pure water is sealed in the cold storage material 82.
A heat transfer fluid channel 83 is provided so as to be immersed therein. FIG. 5 shows a state in which the upper portion of the main body 81 is omitted, and the heat transfer fluid channel 83 is covered by the main body 81. The heat transfer fluid flow path 83 is formed by stacking a plurality of spiral pipes 83a, and one end openings 83 'at the center positions of the pipes 83a are connected to each other and connected to the circulation flow path 40, and the outer circumferential position is set. Are connected to each other and to the circulation channel 40. Thereby, heat exchange is performed between the heat transfer fluid flowing in the direction indicated by the arrow C or D in the drawing and the regenerator material. Will be

The present invention is not limited to the above embodiment and modified examples. For example, in the above embodiment, in the flow path of the heat transfer fluid, the cooler 42, which is a cooling unit of the air cycle cooling device 31, and the evaporator 325, which is a cooling unit of the vapor cycle cooling device 32, are arranged in series. A part of the flow path of the heat transfer fluid may be branched into a pair of parallel flow paths, and the cooler 42 may be disposed on one side of the parallel flow path and the evaporator 325 may be disposed on the other side. Alternatively, the heat transfer fluid may be cooled by only one of the air cycle cooling device 31 and the vapor cycle cooling device 32. Alternatively, in the above embodiment, the cooling device 3 that uses the engine 5 of the aircraft as a power source and performs heat exchange between the RAM air and the refrigerant introduced from outside the fuselage is used. The heat transfer fluid may be cooled by another cooling means, for example, by activating the cooling system with an external power supply or an air source when the aircraft is on the ground, thereby cooling the heat transfer fluid before flight to a regenerator material. Cold heat may be accumulated. In the above-described embodiment, the cooling devices 31 and 32 are miniaturized by providing the in-machine cooler 44 and cooling the circulating air in the machine by the heat transfer fluid together with the cooling devices 31 and 32. Only the transmitting part may be cooled. The object to be cooled by the cooling system with a regenerative storage function of the present invention is not limited to the electromagnetic wave transmitting part in the radar 2, but may be another directivity such as a jamming radio wave transmitting part in a jamming radio wave transmitting device or a laser transmitting part in a laser device. Other high-power circuit parts such as an electromagnetic wave transmission part, a high-speed operation circuit part for analyzing radar signals, and a power supply circuit part for supplying radar power may be cooled by a heat transfer fluid. In addition, gas is used as a heat transfer fluid,
Further, the heat transfer fluid may be discharged to the outside of the airframe after the cooling of the electromagnetic wave transmission unit without being circulated. In the above embodiment, the cooling means for the heat transfer fluid also serves as the cooling means for the air circulating in the machine.However, the heat transfer fluid may be cooled by a dedicated cooling means.In this case, the cooling means is stopped during transmission of the electromagnetic wave. May be operated while not transmitting electromagnetic waves.

[0023]

According to the present invention, in an aircraft having a high-power circuit portion, it is practically possible to cool the high-power circuit portion without bleeding the engine or abruptly increasing power consumption. Prevents a sudden increase in load, eliminates the need for an excessively large cooling system, and allows efficient cold storage during high altitude flight, reducing the amount of energy consumed for heat dissipation and reducing fuel consumption. And a cooling system with a cool storage function that is effective for

[Brief description of the drawings]

FIG. 1 is a configuration diagram of a cooling system with a cool storage function according to an embodiment of the present invention.

FIG. 2 is a perspective view of a main part of the cooling system with a cool storage function according to the embodiment of the present invention.

FIG. 3 is a cross-sectional view of a cold storage reservoir tank in the cooling system with a cold storage function according to the embodiment of the present invention.

FIG. 4 is a diagram showing a control configuration in a cooling system with a cool storage function according to the embodiment of the present invention.

FIG. 5 is a perspective view of a cold storage reservoir tank in a cooling system with a cold storage function according to a modified example of the embodiment of the present invention.

[Explanation of symbols]

 2 Radar 3 Cooling device 40 Circulating flow path 40a First flow path 40b Second flow path 41 Main pump 44 In-machine cooler 451 Reservoir pump 452 Switching valve 453 Sub-distribution valve 50 Control device 51 Temperature sensor 72 Container 82 Cold storage material

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) H05K 7/20 H05K 7/20 Q F term (Reference) 3L044 AA04 BA02 CA13 DB02 DC03 3L045 AA03 BA10 CA02 DA02 FA02 5E322 DB06 DB07 DB11 EA11 FA01 FA03

Claims (5)

[Claims] In a cooling system for cooling a high-power circuit portion of an aircraft by a heat transfer fluid cooled by cooling means, a cold storage material capable of accumulating cold heat includes a heat transfer fluid and a heat transfer fluid in a flow path of the heat transfer fluid. It is arranged so that heat exchange is possible, and when the heat transfer fluid is colder than the cold storage material, the cold storage material is cooled by the heat transfer fluid, and when the heat transfer fluid is hotter than the cold storage material, the cold storage material A cooling system with a cold storage function, wherein a heat transfer fluid is cooled by a substance. 2. The cooling system with a cool storage function according to claim 1, wherein said cooling means is capable of cooling said heat transfer fluid to a temperature lower than a melting point of said cool storage material. 3. The heat transfer fluid flows in a circulation flow path, and cooling means for cooling the air circulating in the aircraft body by the heat transfer fluid is provided. A first flow path for supplying the heat transfer fluid to the high-power circuit portion and a second flow path for supplying the heat transfer fluid to the cooling means for the air circulating in the aircraft body are provided, and the heat transfer in the first flow path is provided. 3. The cool storage function according to claim 1, further comprising means for changing a ratio of a flow rate of the fluid to a flow rate of the heat transfer fluid in the second flow path in accordance with a variable correlated with a temperature change of the heat transfer fluid. With cooling system. 4. The regenerative substance according to claim 1, wherein the regenerator material is enclosed in a plurality of expandable and contractible containers, and the containers are arranged in the flow path of the heat transfer fluid. Cooling system. 5. A RAM which is introduced from outside the body of the aircraft.
The cooling system with a cool storage function according to any one of claims 1 to 4, wherein heat can be exchanged between air and a refrigerant of a cooling means of the heat transfer fluid.