JP4465864B2 - Cooling system - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a cooling device for an aircraft that cools a heating element attached to the surface of an aircraft body, for example, an element of a transmission source that transmits radar electromagnetic waves or laser light.
[0002]
[Prior art]
An aircraft or the like transmits various electromagnetic waves and operates a radar or the like. In particular, recently, a fixed type radar that freely changes the direction of electromagnetic waves by controlling the phase of a large number of transmitting elements has been put into practical use, and further attempts to arrange these elements on the surface of the aircraft are planned. This eliminates the need to place the space inside the aircraft in order to equip the radar, and allows the user to freely set the location where the radar is placed, so there are advantages such as eliminating multiple radar blind spots by arranging multiple radars. Is obtained.
On the other hand, attempts have been made to reduce the seeker function of flying objects by placing laser beam sources at various locations on the aircraft. unfathomable.
[0003]
[Problems to be solved by the invention]
In order to cool such a conventional element, it is necessary to control the element temperature within a certain set range. Therefore, a cooling part with a liquid having a large heat capacity is provided, and this liquid is sent to an air conditioner to be cooled. The method was taken. This is because until now it was mainly applied to nose radar.
However, when considering radar placement at various locations on the fuselage or at the tip of the wing, the pumping capacity and piping length for flowing liquid can be used to rotate the liquid cooling line to every corner of the fuselage. This also creates a problem and places restrictions on the degree of freedom of arrangement. In addition, since the absorbed heat is cooled by in-flight air conditioning, when the capacity of the transmission source is increased, the amount of heat that must be released increases, and the air conditioning capacity needs to be improved. As a result of increasing the amount of air extracted for air conditioning, there is a problem that engine thrust is reduced.
SUMMARY OF THE INVENTION In view of the above problems, the present invention aims to reduce the size and weight of a cooling device.
[0004]
[Means for Solving the Problems]
In order to achieve the above object, a heating element disposed along the fuselage, a heat absorbing member that absorbs heat generated by the heating element, a dissipating member that dissipates heat absorbed by the heat absorbing member to the outside of the fuselage, A cooling device including a heat transfer mechanism for moving heat from the heat absorbing member to the heat dissipation member, wherein the heat dissipation member, the heat transfer mechanism, and the heat dissipation member are integrated with each other. A cooling device having a structure is provided.
Here, examples of the heating element include an electromagnetic wave transmitting element, but are not limited to this, and a member generated locally from various control / communication devices or the like is applicable.
[0005]
For example, an evaporator can be used as the heat-absorbing member, but the heat-absorbing member is not limited to this, and any member that absorbs heat may be used. Further, the dissipating member is not particularly limited as long as it forms a part of the airframe surface and exchanges heat with outside air outside the aircraft to dissipate the heat absorbed by the heat absorbing member. The heat transfer mechanism is a heat pump that draws heat from the heat-absorbing member to the heat-dissipating member.For example, in a closed system filled with the refrigerant, a compressor forcibly circulates the refrigerant. It is not limited. This heat transfer mechanism is preferably set to operate at a temperature difference of 0 to 50 ° C. between the heat radiating member and the heat absorbing member.
Further, “the heat absorbing member, the heat transfer mechanism, and the dissipating member are integrally structured” means that these members are attached as a unit to the inner wall that forms the surface of the airframe. This facilitates maintenance and inspection of the cooling device and unit replacement.
The aircraft includes any aircraft that travels at high speed, such as an aircraft.
[0006]
DETAILED DESCRIPTION OF THE INVENTION
Embodiments of the present invention will be described with reference to the drawings.
FIG. 1A is a schematic view showing the entire aircraft, FIG. 1B is an external view of the outer plate of the fuselage, and FIG. 1C is an inner view of the outer plate. In the figure, reference numeral 1 denotes an airframe, and an electromagnetic wave transmission device 3 that is a heating element and a heat exchanger (condenser) 4 that is a dissipating member are mounted on an outer plate 2 that forms part of the surface of the aircraft 1.
The heat exchanger 4 is configured such that a refrigerant pipe 6 is spirally accommodated in a case, and one surface of the heat exchanger 4 constitutes an outer plate 4. Therefore, the heat in the refrigerant pipe 6 can be directly radiated to the outside air by directly exchanging heat with the outside air of the aircraft flying at high speed.
Further, as shown in FIG. 1C, a compressor 7, an expansion valve 8, and an evaporator 9 are mounted on the inner wall of the outer plate 2, and the connection relationship among these members will be clarified with reference to FIG. The evaporator 9 is in close contact with the electromagnetic wave transmission device 3 described above. Heat generated by the electromagnetic wave transmission device 3 is absorbed by the evaporator 9.
Since the heat exchanger 4, the compressor 7, the expansion valve 8, and the evaporator 9 are all attached to the outer plate 2 by the support member 10 as an integral structure, units of these members can be exchanged. Further, the outer plate 2 is fitted by an airframe fixing screw (not shown).
[0007]
Next, the connection relationship of each component will be described with reference to FIG. In FIG. 2, the same components as those in FIG.
The refrigerant pipe 6 constitutes a closed system, and a refrigerant such as alternative CFC is forcibly circulated by the compressor 7. In the circulation system of the refrigerant pipe 6, an evaporator 9, a heat exchanger (condenser) 4, and an expansion valve 8 are arranged. The electromagnetic wave transmission device 3 is in close contact with the evaporator 9, and when the electromagnetic wave transmission device 3 generates heat, the heat is absorbed by the evaporator 9 and is radiated from the heat exchanger 4 to the outside. At this time, since the heat exchanger is a part of the outer plate of the fuselage flying at high speed, the heat can be directly radiated to the outside air.
[0008]
Heat from the evaporator 9 to the heat exchanger 4 is generated by forcibly circulating the refrigerant by the compressor 7 in a closed system filled with the refrigerant.
First, the refrigerant gas that has absorbed the heat from the electromagnetic wave transmission device 3 by the evaporator 9 is compressed by the compressor 7, becomes high-temperature and high-pressure superheated refrigerant gas, flows through the refrigerant pipe 6, and reaches the heat exchanger 4. Since the heat exchanger 4 is a part of the outer plate that flies at high speed, the heat exchanger 4 can directly radiate heat to the outside air. Here, the superheated refrigerant gas is subjected to heat exchange, and the refrigerant gas becomes a high-pressure condensate liquefied refrigerant, which is adiabatically expanded by the expansion valve 8 and decreases in temperature, so that it becomes a mixed refrigerant of gas and liquid and returns to the evaporator 9 where heat is generated. Is absorbed into a gaseous refrigerant gas.
Hereinafter, by repeating this cycle, the heat of the electromagnetic wave transmission device 3 can be radiated to the outside air. In addition, regarding the temperature of the evaporator 9 and the temperature of the heat exchanger 4, the compressor 7 is controlled so that a temperature difference can operate | move at 0-50 degreeC.
[0009]
In the above configuration, the outer plate 2 is traveling at a high speed, so that means for forcibly blowing and dissipating heat like a normal heat exchanger is unnecessary. Therefore, there is no need for additional equipment such as a fan for forcibly blowing air, a blower, a fan, a duct, and a bracket for fixing the heat exchanger as in a normal heat exchanger, and the space inside the fuselage is effectively used. it can. Since it is not necessary to use air conditioning for cooling the electromagnetic wave transmission device 3, the capability of air conditioning is improved.
[0010]
In the above description, the compressor 7 is used. However, a heat medium such as oil having an appropriate operation capability may be circulated from the evaporator 9 to the heat exchanger 4 by a pump without using the compressor 7. The mounting position of the heat exchanger and the electromagnetic wave transmission device 3 is not limited to the back surface of the airframe, but may be the front surface or the rear surface of the airframe.
The heat exchanger 3a may have a movable structure that also serves as an equipment maintenance door (not shown) in the pod 2, for example, in addition to the structure that is fixed to the pod 2 with the fixing screw S.
The form of the heat exchanger 4 is not limited to the tube type as described above, and even if it is a plate fin type or the like, the effect of the present invention is not affected at all.
The present invention can be applied to the entire body for high-speed traveling, and can be applied to, for example, railway vehicles and ships. Further, the heating element is not limited to the electromagnetic wave transmission device.
[0011]
【The invention's effect】
According to the present invention, it is not necessary to use air conditioning for cooling the electromagnetic wave transmission device or the like, so that it is not necessary to improve the air conditioning capability. In addition, since the cooling device is disposed near the heating element, it is not necessary to route a cooling line (for example, a coolant pipe).
Furthermore, since the electromagnetic wave transmission device and its cooling device can be assembled to the airframe as an integrated module, the assembly is easy. In addition, maintenance inspection and unit replacement are easy.
[Brief description of the drawings]
1A and 1B are diagrams in which the present invention is applied to an aircraft, in which FIG. 1A is a schematic diagram showing the entire aircraft, FIG. 1B is an external view of the outer plate of the fuselage, and FIG.
FIG. 2 is a diagram showing a connection relationship between components.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Aircraft 2 ... Outer plate 3 ... Electromagnetic wave transmission device 4 ... Heat exchanger 6 ... Refrigerant pipe 7 ... Compressor 8 ... Expansion valve 9 ... Evaporator

Claims (1)

A plurality of electromagnetic wave transmitter element arranged along an aircraft fuselage, to dissipate the heat generated by the plurality of electromagnetic wave transmitting device and the heat absorbing member that absorbs heat, it was absorbed in the heat absorbing member thermally to the body outside the aircraft A cooling device comprising a dissipating member and a heat transfer mechanism for transferring heat from the heat absorbing member to the heat dissipating member, wherein the heat dissipating member is constituted by a part of the aircraft body surface, and the heat absorbing member, heat transfer A cooling device comprising a mechanism and a dissipating member in an integral structure.

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