JP4715984B2 - Cooling system with cool storage function - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a system that cools in order to stably operate a high-power circuit part such as a part of an electromagnetic wave having directivity such as a radar or a laser in an aircraft or a part of an ultrahigh-speed arithmetic circuit.
[0002]
[Prior art]
For example, an electromagnetic wave transmission part in an electromagnetic wave transmission device such as a radar mounted on an aircraft to search for a victim, a wrecked ship, a suspicious ship, etc. is replaced with one composed of a number of semiconductor elements from an old transmission pipe. As a result, the direction change of the electromagnetic wave is changed from a method of changing the direction of the transmitter tube to a method of changing without 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 corresponding to each semiconductor element, a large number of semiconductor elements with a power control circuit exist in order to stabilize performance so that electromagnetic waves can be stably transmitted. It is necessary to cool the whole electromagnetic wave transmission part constituted by and maintain it within a certain set temperature range. In view of this, a method of directly cooling the electromagnetic wave transmission site by using an antifreeze solution called brine, in which water or the like is added as a main component and an additive, as a heat transfer fluid is employed. The heat transfer fluid is cooled in response to 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 to cool a high-power circuit part other than the electromagnetic wave transmitting part, for example, an ultra-high speed arithmetic circuit and an inverter circuit that controls power supply to various electronic devices during operation.
[0003]
[Problems to be solved by the invention]
In recent years, in response to a recent demand for higher performance, an aircraft is often accompanied by a signal processing device with various high-speed arithmetic processing. Furthermore, in order to improve the function, it is required to cope with the transmission of high output electromagnetic waves. For this reason, when performing the transmission of electromagnetic waves and high-speed arithmetic processing, a large amount of heat is expected from the high output circuit part including the accompanying circuit part, etc., to cool the heat transfer fluid that has absorbed the generated heat The capacity of the in-flight cooling system had to be increased.
[0004]
However, in order to increase the capacity of the in-flight cooling system, it is necessary to increase the engine bleed amount when the air cycle method is adopted as the in-flight cooling system, and to increase the refrigerant compression capacity when the vapor cycle method is adopted. In addition, it is necessary to increase power consumption. In either case, an increase in power consumption in the high-power circuit portion is not preferable because it significantly increases the load for the engine in flight. In particular, aircraft that emit directional electromagnetic waves such as radar waves to the ground or the ocean operate with the flight altitude lowered, so the temperature of the outside air that releases the pumped heat increases. In many cases, the capacity of the cooling system is required to be large, and not only the engine load increases, but also the cooling system must be large and heavy.
[0005]
[Means for Solving the Problems]
The cooling system with a cool storage function of the present invention is a cooling system that cools a high-power circuit portion in an aircraft with a heat transfer fluid cooled by a cooling means, and the heat transfer fluid flows in a circulation channel, The circulation flow path has a flow path constituted by a pipe connecting a portion from the high power circuit portion to the cooling means to a portion from the cooling means to the high output circuit portion, and accumulates cold heat. A possible cold storage material is arranged in the heat transfer fluid flow path between both ends of the pipe so as to be able to exchange heat with the heat transfer fluid, and when the heat transfer fluid is at a lower temperature than the cold storage material, the heat transfer fluid When the cool storage material is cooled and the heat transfer fluid is hotter than the cool storage material, the flow direction of the heat transfer fluid in the piping is such that the heat transfer fluid is cooled by the cool storage material. Wherein the fluid is reversed at the time a high temperature when it is cooler than the cold accumulating material. The aircraft includes a rotorcraft such as a helicopter.
According to the configuration of the present invention, when the high-power circuit portion is not activated, there is a margin of power, when the aircraft is flying at a high temperature or in a cold area, the outside of the aircraft during standby on the ground before the flight In the case where the power source can be used, the cooling means is driven to cool the heat transfer fluid without overloading the aircraft engine and without increasing the engine bleed and power consumption in the aircraft, The cold storage material can be cooled by the heat transfer fluid to accumulate cold heat. As a result, if the heat transfer fluid becomes hotter than the cold storage material due to the operation of the high-power circuit part, the heat transfer fluid is cooled by the accumulated cold heat, thereby overloading the aircraft engine. Therefore, it is possible to cool high power circuit parts such as electromagnetic wave transmitting parts. In addition, when cooling an electromagnetic wave transmission part as a high-power circuit part, if there is a possibility that countermeasures against the electromagnetic wave will be taken from the electromagnetic wave transmission target, the strong electromagnetic wave should be transmitted until it approaches the transmission target. In addition, it is common to intermittently transmit electromagnetic waves instead of continuously transmitting electromagnetic waves. In such a case, according to the present invention, cold energy is accumulated in the cold storage material while flying for movement at a sufficient altitude to increase flight efficiency, and the stored cold energy is used when electromagnetic waves are transmitted. To cool the transmitting part.
[0006]
The cooling means is preferably capable of cooling the heat transfer fluid below the melting point of the cold storage material.
As a result, the regenerator material is cooled and solidified below the melting point, and when the regenerator material melts, the heat transfer fluid can be cooled by absorbing the heat of fusion, and solidification is greater than when the regenerator material is in the liquid phase. Heat, for example, if the cold storage material is water, solidification heat of about 80 times the specific heat can be held as cold heat, and even with a small amount, all of the heat generated in the high output circuit part such as the electromagnetic wave transmission part or the like due to the cold storage substance having a large heat capacity This is preferable for an aircraft that can absorb a part and requires weight reduction.
[0007]
A cooling means for cooling the air circulating in the aircraft body with the heat transfer fluid is provided, and as a part of the circulation flow path, a first flow path for supplying the heat transfer fluid to the high-power circuit portion, an aircraft machine A second flow path for supplying the heat transfer fluid to the cooling means for circulating air in the body, and 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 It is preferable that means for changing according to a variable correlated with a temperature change of the transfer fluid is provided.
As a result, the heat transfer fluid that is cooled while the high-power circuit portion is not operating can be used effectively for cooling the air circulating in the aircraft.
[0008]
The cold storage material is preferably enclosed in a number of expandable and contractible containers, which are disposed 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, heat exchange can be performed efficiently, and the volume fluctuation of the cold storage material can be absorbed by the expansion and contraction of the container.
[0009]
It is preferable that heat exchange is possible between the RAM air introduced from the outside of the aircraft body and the refrigerant of the cooling means for the heat transfer fluid.
As a result, when the aircraft is flying at high altitude, cold energy can be efficiently stored in the cold storage material, which is suitable for actual operation.
[0010]
DETAILED DESCRIPTION OF THE INVENTION
1 and 2 show a cooling system A with a cold storage function for cooling a high-power circuit portion in a phased array radar 2 mounted on an aircraft body 1. As the radar 2, for example, a radar that generates heat exceeding 10 kW when electromagnetic waves are transmitted at full power is used. The high-power circuit part in the radar 2 is constituted by an electromagnetic wave transmission part made up of a large number of semiconductor elements with power control circuits, and has a cooling jacket 20 for cooling the electromagnetic wave transmission part 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 with the cooling jacket 20. The heat transfer fluid supplied from the cooling system A is introduced into the cooling jacket 20 through the supply port 21 and discharged through the return port 22, so that the electromagnetic wave transmission site is cooled by the heat transfer fluid. The In this embodiment, a general high-concentration ethylene glycol solution or the like is used as the heat transfer fluid.
[0011]
The cooling system A includes a cooling device 3 and a cold storage device 4, and the cooling device 3 cools the heat transfer fluid flowing through the circulation flow path 40 in the cold storage device 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 the cooling capacity of the air cycle 31. And a vapor cycle type cooling device 32 for compensating for the above.
[0012]
The air cycle type cooling device 31 cools the engine bleed air by heat exchange with RAM air introduced from outside the machine body by the first heat exchanger 311, compresses it by the centrifugal compressor 312, and compresses the RAM by the second heat exchanger 313. Cooling is again performed by heat exchange with air, and further cooling is performed by the regenerative heat exchanger 314, whereby moisture contained in the extracted engine bleed air is removed by the moisture remover 315, and then the engine bleed air is expanded by the expansion turbine 316. Get cold. A part of the obtained cold air passes through the regenerative heat exchanger 314 to cool the engine bleed air, and then is supplied to the aircraft cabin 6 and the like as duct air through the duct 317. The remaining portion of the cold air thus obtained passes through the cooler 42 of the regenerator 4 to cool the heat transfer fluid, and then 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 single in the drawing, a plurality of them are actually provided in the machine body 1.
[0013]
The vapor cycle type cooling device 32 is cooled by a capacitor 323 through heat exchange with the RAM air through heat exchange with the RAM air by being compressed by a compressor 322 driven by an electric motor 321, and then expanded. The pressure is reduced by the valve 324, evaporated by the evaporator 325, and returned to the compressor 322 to complete the cycle. As the refrigerant, HFC134a having no ozone depletion effect is suitable. In the evaporator 325, the heat transfer fluid flowing in the circulation flow path 40 of the regenerator 4 is cooled by the cooling ability exhibited by taking away the ambient heat when the refrigerant evaporates. You may make it remove the heat | fever which generate | occur | produces in an apparatus by directly cooling the air circulating in a body with the cooling capability. In addition, although the capacitor | condenser 323 is single in illustration, you may make it provide with two or more in the body 1. FIG.
[0014]
The cold storage device 4 pumps the heat transfer fluid by the main pump 41. As a result, the heat transfer fluid is cooled in the evaporator 325 and the cooler 42 as described above. The cooled heat transfer fluid is introduced into the in-machine cooler 44 disposed in the airframe 1 and the cooling jacket 20 of the radar 2 through the pipes a and b by the main distribution valve 43 provided in the circulation flow path 40. To be distributed. The heat transfer fluid introduced into the in-machine cooler 44 is returned to the suction side of the main pump 41 after cooling the air circulating in the body. 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 transmission portion of the radar 2. A plurality of in-machine coolers 44 may be provided.
[0015]
A cold storage material capable of accumulating cold heat is disposed so as to be able to exchange heat with a heat transfer fluid flowing in the circulation flow path 40. In this 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 by piping to a reservoir pump 451. 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 internal cooler 44 and the supply port 21 of the cooling jacket 20 via the lines c and d. Connected. Accordingly, when the heat transfer fluid is at a lower 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 than the cold storage material, the heat transfer fluid is cooled by the cold storage material.
[0016]
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 cold storage material is not limited to water, but may be any material that can accumulate cold heat. Other than water, formic acid, acetic acid, p-xylene, glycerin, and others have a melting point between -5 ° C and + 25 ° C. It is preferable to employ a substance mainly composed of a substance having a stable molecular structure. The capsule-like 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 when the volume of the pure water is frozen and changes, for example, polytetrafluoroethylene (PTFE). It is made. A pair of mesh plates 73 are attached in the main body 71 so as to hold the capsule containers 72. In addition, although the container 72 is partially omitted in the drawing, the container 72 is filled so as to substantially fill between the mesh plates 73. A guide cylinder 74 is provided at the center of the main body 71, and pipes 75 and 76 for connection to the circulation flow path 40 are introduced into the guide cylinder 74. The inside of the guide cylinder 74 is connected to one end side by a partition plate 74a. The other end side of the connecting pipe 75 is arranged on one end side with respect to the partition plate 74a, and the other end of the connecting pipe 76 is arranged on the other end side with respect to the partition plate 74a. The The heat transfer fluid stirring blade 77 in the main body 71 is driven to rotate by a motor 78. An air bag 79 that absorbs the volume variation 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. A change in volume caused by a change in temperature of the fluid can be absorbed. Thereby, the capsule-like container 72 is arranged 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 drawing and the cold storage material. At this time, the cold storage material is sealed in a large number of capsule containers 72, so that the contact area between the cold storage material and the heat transfer fluid is increased to efficiently perform heat exchange, and the volume variation of the cold storage material is encapsulated. It can be absorbed by the expansion and contraction of the container 72. Note that a container other than the spherical capsule-like container 72, for example, a tubular or plate-like container may be used as the container for enclosing the cold storage material.
[0017]
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 machine body 1. In addition, a temperature sensor 51 that detects the temperature of the circulating air in the body as a variable that correlates with the temperature change of the heat transfer fluid is connected to the control device 50. 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 operate according to a signal output from the control device 50 according to the temperature detected by the temperature sensor 51. By the 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 passes the reservoir pump 451 through the circulation flow path. It is possible to selectively switch between the state connected to 40 and the state connected to the sub distribution valve 453, and the distribution ratio of the heat transfer fluid by the main distribution valve 43 and the sub distribution valve 453 can be changed.
[0018]
When an aircraft having the above configuration is flying at high altitude or in a cold region, the temperature of RAM air introduced from the outside of the fuselage to the first heat exchanger 311, the second heat exchanger 313, and the condenser 323 is low. In addition, the amount of water vapor contained in the bleed air compressed by the outside air in the engine is small, and there is no heat generation due to the condensation of the water vapor during cooling, so the temperature of the engine bleed air that is a refrigerant in the air cycle cooling device 31 is sufficiently low before expansion, Even if the refrigerant in the vapor cycle cooling device 32 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 is equal to or lower than the melting point of pure water that is 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 body is lowered according to the temperature of the heat transfer fluid. When the temperature of the circulating air in the body detected by the temperature sensor 51 is equal to or lower than a preset temperature, the control device 50 causes the heat transfer fluid to flow through the switching valve 452 and the reservoir pump 451 in the circulation flow path 40 to store the cold storage reservoir tank. 7, the reservoir pump 451 and the switching valve 452 are actuated. As a result, in the cold storage reservoir tank 7, water that is a cold storage material is solidified and cold energy is stored. In addition, when the temperature of the circulating air in the body has increased, the control device 50 changes the discharge amount of the main pump 41 according to the temperature detected by the temperature sensor 51 or the distribution ratio of the heat transfer fluid by the distribution valve 43. Is changed, the ratio of the heat transfer fluid flow rate passing through the cold storage reservoir tank 7 and the heat transfer fluid flow rate passing through the in-machine cooler 44 is changed, and the temperature of the circulating air in the machine body is maintained at an appropriate value. That is, as a part of the circulation flow path 40, a pipe b for supplying heat transfer fluid from the main distribution valve 43 to the cooling jacket 20 and a pipe d for supplying heat transfer fluid from the sub distribution valve 453 to the cooling jacket 20 are configured. A second flow comprising a first flow path, a pipe a for supplying heat transfer fluid from the main distribution valve 43 to the in-machine cooler 44, and a pipe c for supplying heat transfer fluid from the sub distribution valve 453 to the in-machine cooler 44. When the detected temperature of the circulating air in the body, which is a variable correlated with the temperature change of the heat transfer fluid, rises, the controller 50 sets the flow rate of the heat transfer fluid in the first flow path. When the ratio to the flow rate of the heat transfer fluid in the two flow paths is decreased and the detected temperature of the circulating air in the aircraft 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 depends on a variable correlated with the temperature change of the heat transfer fluid other than the temperature of the circulating air in the body. It may be changed. For example, the variable correlated with the temperature change of the heat transfer fluid is used as the amount of power input to the high output circuit portion, and the discharge amount of the main pump 41 is changed according to whether the power input to the high output circuit portion is on or off. By changing the distribution ratio of the heat transfer fluid by the distribution 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 input 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 decreased, and when the power input is off Increases the ratio.
[0019]
When the aircraft having the above configuration transmits electromagnetic waves from the radar 2 at a low altitude, the temperature at the electromagnetic wave transmitting portion rises, so that the air cycle cooling device 31 and the vapor cycle cooling device 32 function. However, the temperature of the heat transfer fluid exiting the cooler 42 is higher than the melting point of pure water, which is a cold storage material. In this case, the temperature of the air circulating in the body also increases according to the temperature of the heat transfer fluid. When the temperature of the circulating air in the body detected by the temperature sensor 51 exceeds the set temperature, the controller 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. Thereafter, the reservoir pump 451 and the switching valve 452 are operated so as to reach the sub-distribution valve 453. As a result, the heat transfer fluid is cooled by the cold heat accumulated in the cold storage material in the cold storage reservoir tank 7. Further, the control device 50 changes the distribution ratio of the heat transfer fluid by the distribution valves 43 and 453 in accordance with the temperature detected by the temperature sensor 51, so that the flow rate of the heat transfer fluid passing through the cold storage reservoir tank 7 and the in-machine cooler 44. The ratio of the flow rate of the heat transfer fluid passing through the vehicle is changed, and the temperature of the circulating air in the aircraft is maintained at an appropriate value. That is, when the detected temperature of the circulating air in the body rises, the control device 50 decreases the ratio of the flow rate of the heat transfer fluid in the first channel to the flow rate of the heat transfer fluid in the second channel, When the detection temperature decreases, the ratio is increased.
It should be noted that while the temperature detected by the temperature sensor 51 exceeds the set temperature but the transmission of the electromagnetic wave from the radar 2 is stopped, the heat generation at the electromagnetic wave transmission site is eliminated and the power consumption can be afforded. In this case, the controller 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 in-machine cooler in the in-machine cooler 44 may be increased.
[0020]
According to the above configuration, without applying an excessive load on the engine 5 of the aircraft, the cooling device 3 is driven to cool the heat transfer fluid, and the cold transfer material can be cooled by the heat transfer fluid to accumulate cold heat. As a result, when the heat transfer fluid becomes hotter than the cold storage material due to the transmission of electromagnetic waves, the heat transfer fluid is cooled by the accumulated cold heat, so that the electromagnetic waves are not overloaded on the aircraft engine 5. The transmission part can be cooled. In addition, the cool storage material is cooled to below the melting point and solidified, and the heat transfer fluid can be cooled by absorbing the heat of fusion when the cool storage material melts. It can absorb all or part of the generated heat, and is preferable for aircraft that require weight reduction. Further, the heat transfer fluid that is cooled while the electromagnetic wave transmitting part is not transmitting the electromagnetic wave can be effectively used for cooling the circulating air in the body. Furthermore, since heat exchange is possible between the RAM air introduced from the outside of the airframe 1 and the refrigerant of the cooling device 3, cold energy can be efficiently accumulated in the cold storage material when the aircraft is flying at high altitude.
[0021]
A cold storage reservoir tank 8 according to a modification of FIG. 5 is used in place of the cold storage reservoir tank 7, and a flow path through which a heat transfer fluid having a structure not mixed with the cold storage material 82 flows in a main body 81 enclosing the cold storage material 82. May be provided. That is, in the cold storage reservoir tank 8, a cold storage material 82 such as pure water is sealed in the main body 81, and a heat transfer fluid channel 83 is provided so as to be immersed in the cold storage material 82. 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 with the main body 81. The heat transfer fluid flow path 83 is configured 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 peripheral position. The other end openings 83 ″ are connected to each other and to the circulation flow path 40. As a result, heat exchange is performed between the heat transfer fluid flowing in the direction indicated by the arrow C or D in the figure and the cold storage material. Is called.
[0022]
The present invention is not limited to the above embodiments and modifications.
For example, in the above embodiment, in the flow path of the heat transfer fluid, the cooler 42 that is the cooling unit by the air cycle type cooling device 31 and the evaporator 325 that is the cooling unit by the vapor cycle type cooling device 32 are arranged in series. A part of the flow path of the heat transfer fluid may be branched to form a pair of parallel flow paths, and the cooler 42 may be disposed in one of the parallel flow paths and the evaporator 325 may be disposed in the other. Alternatively, the heat transfer fluid may be cooled by only one of the air cycle type cooling device 31 and the vapor cycle type cooling device 32. Alternatively, in the above embodiment, the cooling device 3 that uses the aircraft engine 5 as a power source and exchanges heat between the RAM air introduced from the outside of the aircraft and the refrigerant is used. The heat transfer fluid may be cooled by another cooling means, for example, by operating the cooling system with an external power source or air source when the aircraft is on the ground, thereby cooling the heat transfer fluid before the flight to a cold storage material. Cold heat may be accumulated. In the above embodiment, the in-machine cooler 44 is provided to cool the circulating air in the body by the heat transfer fluid together with the cooling devices 31 and 32, so that the cooling devices 31 and 32 are miniaturized. Only the transmitting part may be cooled. Further, the object to be cooled by the cooling system with a cold storage function of the present invention is not limited to the electromagnetic wave transmission part in the radar 2, and other directivities such as the interference wave transmission part in the interference radio wave transmission apparatus and the laser transmission part in the laser apparatus, for example. Other high power circuit parts such as an electromagnetic wave transmission part, a high-speed arithmetic circuit part for analyzing a radar signal, a power supply circuit part for supplying radar power may be cooled by a heat transfer fluid.
Further, the gas may be used as a heat transfer fluid, and further, the heat transfer fluid may be discharged outside the airframe after cooling the electromagnetic wave transmission unit without circulating the heat transfer fluid.
In the above embodiment, the cooling means for the heat transfer fluid also serves as the cooling means for the circulating air in the aircraft. However, the heat transfer fluid may be cooled by a dedicated cooling means. In this case, the cooling means is stopped during electromagnetic wave transmission. It may be operated while not transmitting electromagnetic waves.
[0023]
【The invention's effect】
According to the present invention, in an aircraft having a high-power circuit part, it is practically possible to cool the high-power circuit part without a sudden increase in engine bleed or power consumption, resulting in a rapid increase in engine load. This eliminates the need for a cooling system that is larger than necessary, and can efficiently store cold energy during high-flying flights, thus reducing the amount of energy consumed for heat dissipation and reducing the amount of fuel consumed. A cooling system with functions can be provided.
[Brief description of the drawings]
FIG. 1 is a configuration explanatory diagram of a cooling system with a cold storage function according to an embodiment of the present invention.
FIG. 2 is a perspective view of a main part of a cooling system with a cold storage function according to an embodiment of the present invention.
FIG. 3 is a cross-sectional view of a cold storage reservoir tank in a cooling system with a cold storage function according to an embodiment of the present invention.
FIG. 4 is a diagram showing a control configuration in a cooling system with a cold storage function according to an 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 modification of the embodiment of the present invention.
[Explanation of symbols]
2 Radar
3 Cooling device
40 Circulation channel
40a 1st flow path
40b Second flow path
41 Main pump
44 In-flight cooler
451 reservoir pump
452 switching valve
453 Sub-distribution valve
50 Control device
51 Temperature sensor
72 containers
82 Cold storage material

Claims (5)

In a cooling system for cooling a high power circuit portion in an aircraft with a heat transfer fluid cooled by a cooling means,
The heat transfer fluid is supposed to flow in the circulation channel,
The circulation flow path has a flow path constituted by a pipe that connects a portion that reaches the cooling means from the high output circuit portion to a portion that reaches the high output circuit portion from the cooling means,
A cold storage material capable of storing cold heat is disposed in the heat transfer fluid flow path between both ends of the pipe so as to be capable of exchanging heat with the heat transfer fluid,
When the heat transfer fluid is cooler than the cool storage material, the cool storage material is cooled by the heat transfer fluid, and when the heat transfer fluid is hotter than the cool storage material, the heat transfer fluid is cooled by the cool storage material. As described above, the flow direction of the heat transfer fluid in the piping is reversed between when the heat transfer fluid is at a lower temperature than the cold storage material and when the heat transfer fluid is at a higher temperature. . The cooling system with a cool storage function according to claim 1, wherein the cooling means is capable of cooling the heat transfer fluid below a melting point of the cool storage material. Cooling means for cooling the aircraft circulating air by the heat transfer fluid is provided,
As a part of the circulation flow path, a first flow path for supplying a heat transfer fluid to the high-power circuit portion and a second flow path for supplying the heat transfer fluid to a cooling means for circulating air in the aircraft body are provided. And
A means is provided for changing 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 in accordance with a variable correlated with the temperature change of the heat transfer fluid. The cooling system with a cool storage function according to 1 or 2. The cooling system with a cold storage function according to any one of claims 1 to 3, wherein the cold storage material is enclosed in a number of extendable containers, and the containers are arranged in a flow path of the heat transfer fluid. The cooling system with a cool storage function according to any one of claims 1 to 4, wherein heat exchange is possible between RAM air introduced from outside the aircraft body and a refrigerant of a cooling means for heat transfer fluid.

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