JP2010208488A - Cooling system of flight vehicle - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To achieve efficient thermal control by a simple configuration and an improved degree of freedom of an attachment arrangement including design. <P>SOLUTION: An aerial 11 is arranged on an outer wall of a flight vehicle body 10, and a pressurized chamber 101 and an outside 102 of the pressurized chamber of the flight vehicle body 10 are communicated with a duct member 13. Air in the pressurized chamber 101 is flowed to the outside 102 of the pressurized chamber by using the pressure difference between the pressurized chamber 101 and the outside 102 of the pressurized chamber, the ambient temperature of the outside 102 of the pressurized chamber is cooled, a heat sink 12 thermally combined with a heat release face of the aerial 11 is blown by the air, and the aerial 11 is therefore thermally controlled. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a flying body such as an aircraft or an airship, and more particularly to a cooling system thereof.

  In general, a large number of electronic devices such as antennas and transceivers are mounted on a flying body, and the performance of the electronic devices is maintained by thermally controlling the electronic devices using a cooling device such as a blower or a heat exchanger. A cooling system has been established. By the way, in such a cooling system for an air vehicle, the amount of heat generated is increased due to the increase in the capacity of the electronic device mounted on the aircraft, while the space for mounting the electronic device on the aircraft is limited. Increasingly severe is one of the important issues in the field of flying objects.

  For example, conventionally, an antenna mounted on a flying body is mounted on the flying body, and a cooling device including a blower and a heat exchanger is assembled, and the cooling device is driven and controlled to thermally control the antenna. It has been.

  As a cooling system mounted on such a flying object, for example, an air cooling method using an air cooling device provided with a cooling fan (see, for example, Non-Patent Document 1), a heat exchanger in which a working medium is circulated and supplied is used. A liquid cooling system (for example, see Non-Patent Document 2) that thermally controls equipment is known.

  Recently, in the field of an aerial mounted on a flying object, a structure in which it is directly arranged on the outer wall of the flying object for use is being studied. Such an aerial is especially high because the outer shape of the aircraft body is constrained by the relationship with flight performance, and is made smaller and thinner. The thermal control is considered to be an important issue.

"Latest version of electronic device cooling technology practical manual" (published by Japan Technology Center) Author: DAVES. Steinberg supervision: Koichi Oshima Tadashi Matsushita "Mechanical design of electronic communication devices" (published by Morikita Publishing Co., Ltd.) Author: Masao Kubota Takayoshi Serizawa

  However, in the above cooling system of the flying body, any system must be equipped with a driving source such as a cooling fan or a heat exchanger, and the structure is complicated and large, and the weight increases. There is a problem that the degree of freedom of the mounting arrangement including the design is inferior.

  The situation of such thermal control becomes a serious problem because of the high heat generation density due to its configuration, particularly in the case of the antenna system that is arranged on the outer wall of the aircraft body that has been recently studied.

  The present invention has been made in view of the above circumstances, and has a simple configuration, can improve the degree of freedom of mounting and placement including design, and can realize high-efficiency thermal control. An object of the present invention is to provide a cooling system.

  According to the present invention, the electronic device disposed outside the pressurizing chamber of the flying body, one end portion is opened to the pressurizing chamber of the flying body, and the other end portion is disposed to be opened outside the pressurizing chamber. Using the pressure difference between the pressurizing chamber and the pressurizing chamber, the air in the pressurizing chamber is caused to flow outside the pressurizing chamber, and cooled at the ambient temperature outside the pressurizing chamber, and on the heat radiation surface side of the electronic device A cooling system for an air vehicle was configured by including an air passage for spraying to cool the electronic device.

  According to the above configuration, the air in the pressurizing chamber flows through the air path due to a pressure difference with the outside of the pressurizing chamber, flows outside the pressurizing chamber, is cooled by the ambient temperature outside the pressurizing chamber, and is blown to the heat radiation surface of the electronic device. The heat transferred from the heat generating part to the heat radiating surface of the electronic device is exhausted.

  As a result, it is possible to achieve highly efficient cooling of electronic equipment without providing a blower or other air source and a heat exchanger, and it is possible to promote downsizing and weight reduction, thereby reducing the number of components. Thus, the degree of freedom of the mounting arrangement including the design can be improved.

  As described above, according to the present invention, a cooling system for an aircraft that can improve the degree of freedom of mounting and placement including design and achieve high-efficiency thermal control with a simple configuration. Can be provided.

It is sectional drawing shown in order to demonstrate the structure of the cooling system of the aircraft which concerns on one embodiment of this invention. It is the perspective view which showed the state which attached and arrange | positioned the antenna of FIG. 1 to the outer wall of a flying body. It is the perspective view which showed the state which has arrange | positioned the heat sink on the inner wall side of the aircraft main body of FIG. It is the perspective view which showed the state which attached the duct member so that the heat sink might be covered on the inner wall side of the aircraft main body of the antenna of FIG.

  Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

  FIG. 1 shows a flying body cooling system according to an embodiment of the present invention. A flying body 10 is composed of a pressurized chamber outside 102 partitioned by a pressurized chamber 101 and a partition wall 103 on which a crew member rides. It is configured.

  Among these, the pressurized chamber 101 maintains a comfortable environment in which, for example, the room temperature is maintained at about 20 ° C. and the atmospheric pressure is maintained at about 0.6 atm in the flight state of the flying body 10. The other pressurization chamber outside 102 accommodates and arranges various equipments and the like, in the flight state of the aircraft body 10, unlike the pressurization chamber 101, for example, the temperature is approximately −54 ° C., which is substantially the same as the external environment. Becomes an environment of about 0.1 atm.

  On the outer wall of the flying body 10, an aerial wire 11, which is an electronic device, is installed corresponding to, for example, the outside of the pressurizing chamber 102 (see FIG. 2). Not electrically connected to internal equipment. The aerial line 11 is formed in a thin outer wall shape so as not to affect the flight of the flying vehicle body 10, and is used for detecting a target in a desired radar space, for example, in the flight state.

  The aerial wire 11 is provided with, for example, a heat radiating surface on the back side, and this heat radiating surface is disposed, for example, thermally connected to the outer wall of the flying body 10. Then, as shown in FIG. 3, a heat sink 12 is thermally coupled and attached to the inner wall of the aircraft body 10 to which the heat radiation surface of the antenna 11 is thermally coupled. Thereby, the heat sink 12 is thermally coupled to the heat radiating surface of the antenna 11 with the wall surface of the flying body 10 interposed therebetween.

  In the heat sink 12, for example, a plurality of pin-shaped radiating fins 121 are erected in series and parallel with a predetermined interval (see FIG. 3), and the heat of the antenna 11 is radiated to the plurality of radiating fins 121. Through the wall surface of the aircraft body 10. The heat sink 12 is not limited to the one having the pin-shaped heat dissipating fins 121, and can be configured by using various other shapes.

  And this heat sink 12 is accommodated and arrange | positioned in this duct member 13 so that it may be comprised by the intermediate part of the duct member 13 which comprises an air path, as shown in FIG. One end of the duct member 13 is opened so as to be evacuated outside the pressurizing chamber 102 and opened so that air can be discharged. One end of the duct member 13 is inserted into the pressurizing chamber 101 through the partition wall 103 (FIG. 1). The pressure chamber 101 is opened so as to be able to take in air and is opened so as to be able to enter and exit. Thereby, in the flight state of the airframe body 10, the duct member 13 causes the air in the pressurizing chamber 101 to flow out in the direction of the pressurizing chamber 102 due to the pressure difference between the pressurizing chamber 101 and the pressurizing chamber outside 102. Exhaust from the other end to the pressurized chamber 102.

  That is, during the flight, the airframe body 10 has a pressure difference between the pressurized chamber 101 and the pressurized chamber 102, such as an atmospheric pressure of the pressurized chamber 101, for example, 0.6 atm, and an atmospheric pressure of the pressurized chamber 102, for example, 0.1 atm. Due to the pressure difference, the air in the pressurizing chamber 101 flows through the duct member 13 toward the heat sink 12 at a predetermined flow rate. At this time, the air flowing in the duct member 13 is cooled by the temperature of the pressurizing chamber 101, for example, from 20 ° C. to the temperature of the pressurizing chamber outside 102, for example, −54 ° C., and sprayed to the radiating fins 121 of the heat sink 12. And is discharged from one end of the duct member 13 to the outside of the pressurizing chamber 102.

  In the above configuration, when the aerial wire 11 is driven and the flying vehicle body 10 flies, the aerial wire 11 generates heat, and the heat is transferred from the heat radiation surface to the heat sink 12 through the wall surface of the flying vehicle body 10. The

  At the same time, the duct member 13 has a pressure difference between the pressurizing chamber 101 and the pressurizing chamber outside 102 as described above, so that the air in the pressurizing chamber 101 flows at a predetermined flow rate in the heat sink direction. It is discharged outside the pressure chamber 102. This air is cooled by the very cool outside air outside the pressurizing chamber 102 around the duct member 13 until it flows inside the duct member 13 and is discharged from the pressurizing chamber 102, and then blown to the heat sink 12. Attached. Thereby, the heat from the aerial wire 11 transferred to the heat radiation fins 121 of the heat sink 12 is efficiently exhausted to the outside of the pressurizing chamber 102, and the aerial wire 11 is thermally controlled to a desired temperature.

  As described above, in the cooling system for the flying body, the aerial line 11 is arranged on the outer wall of the flying body 10, and the pressurized chamber 101 and the pressurized chamber outside 102 of the flying body 10 are communicated with each other via the duct member 13. The air in the pressurizing chamber 101 flows into the pressurizing chamber 102 using the pressure difference between the pressurizing chamber 101 and the pressurizing chamber 102, and is cooled at the ambient temperature of the pressurizing chamber 102. It was configured to perform thermal control of the antenna 11 by spraying on the heat sink 12 thermally coupled to the heat radiating surface.

  According to this, air in the pressurizing chamber 101 flows through the duct member 13 due to a pressure difference between the pressurizing chamber 101 and the pressurizing chamber 102 and flows to the pressurizing chamber 102, and is applied in the middle of the flow. After being cooled by the cold ambient temperature outside the pressure chamber 102, the air is blown to the radiating fins 121 of the heat sink 12, and the thermal control of the antenna 10 is performed. Thereby, without providing an air source such as a blower and a cooling source such as a heat exchanger, high-efficiency heat control of the antenna 11 can be realized, and it is possible to promote a reduction in size and weight. Can be reduced, and the degree of freedom of the mounting arrangement including the design can be improved.

  In the above-described embodiment, the heat sink 12 is provided on the inner wall of the aircraft body 10 where the heat radiation surface of the aerial wire 11 is thermally coupled, and is configured to be thermally controlled. However, the present invention is not limited to this. In addition, it is also possible to configure such that the heat control is performed by directly blowing air to the inner wall of the aircraft body 10 in which the heat dissipation surface of the antenna 11 is thermally coupled without providing the heat sink 12. Similarly, an effective effect is expected.

  In the above-described embodiment, the case where the present invention is applied to the aerial wire 11 disposed on the outer wall of the aircraft body 10 has been described. However, the present invention is not limited to this. The present invention can be applied to a cooling structure for various electronic devices such as transceivers, and similarly effective effects are expected.

  Therefore, the present invention is not limited to the above-described embodiment, and various modifications can be made without departing from the scope of the invention at the stage of implementation. Further, the above embodiments include inventions at various stages, and various inventions can be extracted by appropriately combining a plurality of disclosed constituent elements.

  For example, even if some constituent requirements are deleted from all the constituent requirements shown in the embodiment, the problem described in the column of the problem to be solved by the invention can be solved, and the effect described in the effect of the invention can be obtained. In such a case, a configuration in which this configuration requirement is deleted can be extracted as an invention.

  DESCRIPTION OF SYMBOLS 10 ... Aircraft body, 101 ... Pressurization chamber, 102 ... Outside pressurization chamber, 103 ... Partition, 11 ... Aerial wire, 12 Heat sink, 121 ... Radiation fin, 13 ... Duct member

Claims (4)

Electronic devices arranged outside the pressurized chamber of the aircraft body;
One end portion is opened to the pressurizing chamber of the flying body, and the other end portion is opened to the outside of the pressurizing chamber, and the pressurizing chamber is utilized using a pressure difference between the pressurizing chamber and the pressurizing chamber. Air flow outside the pressurizing chamber, cooled at an ambient temperature outside the pressurizing chamber, and blown to the heat radiation surface side of the electronic device to cool the electronic device;
An aircraft cooling system comprising:   3. The flying body cooling system according to claim 1, wherein a heat sink is thermally coupled to the heat radiation surface of the electronic device.   2. The flight according to claim 1, wherein the electronic device is an aerial wire that is disposed on an outer wall of the aircraft body and has a heat radiation surface that is thermally coupled to the outer wall of the aircraft body on a rear surface. Body cooling system.   4. The aircraft cooling system according to claim 3, wherein a heat sink that is thermally coupled to a heat radiation surface of the antenna is provided on an inner wall of the aircraft body.

Images