RUGGEDIZING APPARATUS AND METHOD FOR ELECTRONIC EQUIPMENT MOUNTED ON SPACECRAFT

Abstract

A ruggedizing apparatus for electronic equipment in a spacecraft is provided that can achieve both a radiation shielding effect and a heat-dissipation effect. The ruggedizing apparatus includes: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

Claims

1. A ruggedizing apparatus for electronic equipment in a spacecraft mounted with the electronic equipment, comprising: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

2. The ruggedizing apparatus according to claim 1, wherein the forced liquid-flow generator causes the coolant and bubbles on the heat-generating electronic circuit to flow toward an inner wall of the pressure vessel, wherein the bubbles are generated by boiling of the coolant on the heat-generating electronic circuit.

3. The ruggedizing apparatus according to claim 1, wherein the forced liquid-flow generator is a contra-rotating fan causing the coolant to flow in a predetermined direction.

4. The ruggedizing apparatus according to claim 1, wherein the forced liquid-flow generator comprises: a first rotating blade unit that causes the coolant to flow in a predetermined direction; and a second rotating blade unit that causes the coolant in the predetermined direction, wherein the first rotating blade unit and the second rotating blade unit rotate in mutually opposite directions on a concentric rotation axis.

5. The ruggedizing apparatus according to claim 1, wherein the forced liquid-flow generator causes the coolant to flow toward the heat-generating electronic circuit, thereby the coolant and bubbles on the heat-generating electronic circuit to flow toward an inner wall of the pressure vessel, wherein the bubbles are generated by boiling of the coolant on the heat-generating electronic circuit.

6. A ruggedizing method for electronic equipment in a spacecraft mounted with the electronic equipment, comprising: immersing at least a heat-generating electronic circuit of the electronic equipment in a coolant of a pressure vessel that is filled with the coolant; and by a forced liquid-flow generator placed within the pressure vessel, forcedly flowing the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

7. The ruggedizing method according to claim 6, wherein by the forced liquid-flow generator, the coolant and bubbles on the heat-generating electronic circuit flow toward an inner wall of the pressure vessel, wherein the bubbles are generated by boiling of the coolant on the heat-generating electronic circuit.

8. The ruggedizing method according to claim 6, wherein the forced liquid-flow generator is a contra-rotating fan causing the coolant to flow in a predetermined direction.

9. The ruggedizing method according to claim 6, wherein by the forced liquid-flow generator, the coolant flows toward the heat-generating electronic circuit, thereby the coolant and bubbles on the heat-generating electronic circuit flow toward an inner wall of the pressure vessel, wherein the bubbles are generated by boiling of the coolant on the heat-generating electronic circuit.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0017] FIG. 1 illustrates a schematic cross-sectional view of a ruggedizing apparatus according to an exemplary embodiment of the present invention.

[0018] FIG. 2 illustrates a schematic side view partially broken away of an example of a forced-liquid flow generator in the ruggedizing apparatus according to the exemplary embodiment.

[0019] FIG. 3 illustrates a schematic plan view of the forced-liquid flow generator in the ruggedizing apparatus according to the exemplary embodiment.

[0020] FIG. 4 illustrates a schematic diagram of a man-made satellite to which an example of the ruggedizing apparatus according to the exemplary embodiment is applied.

DETAILED DESCRIPTION

<Outline of an Exemplary Embodiment>

[0021] According to an exemplary embodiment of the present invention, an immersion cooling system is employed for cooling electronic equipment in a spacecraft. More specifically, the spacecraft electronic equipment or at least heat-generating parts of the electronic equipment is immersed in a coolant and placed in a pressure vessel filled with the coolant. Accordingly, at least the space around the electronic circuitry is filled with the coolant, which provides a radiation moderation effect.

[0022] According to the exemplary embodiment, a forced liquid-flow generator is provided in the pressure vessel. The forced liquid-flow generator forces the coolant on electronic circuits to flow, preventing the dry-out phenomenon even in a space where gravity is negligible. The forced coolant flow efficiently cools the electronic circuits and dissipates its heat to the outside through the wall of the pressure vessel. In other words, by employing the immersion cooling system and forcedly flowing the coolant, both radiation shielding and immersion cooling effects can be achieved.

[0023] Exemplary embodiments of the present invention will be described in detail below with reference to the drawings. It should be noted that the components, their shapes, dimensions and dimension ratios, and arrangements described in the following embodiments are just examples for explaining the embodiments and are not intended to limit the technical scope of the invention to them.

1. Exemplary Embodiment

1.1) Structure

[0024] As illustrated in FIG. 1, a ruggedizing apparatus 100 according to an exemplary embodiment of the present invention includes a pressure vessel 101 in which electronic equipment 102 as a heat source and a forced liquid-flow generator 103 are accommodated. The pressure vessel 101 is sealed and filled with a coolant 104 such that the electronic equipment 102 and the forced liquid-flow generator 103 are immersed in their entirety.

[0025] The electronic equipment 102 is an electronic device such as a computer including semiconductor integrated circuits or at least an electronic circuit such as a processor that is the main source of heat. The electronic equipment 102 may be the overall electronic device. The electronic equipment 102 is fixed by a support mechanism 105 at approximately the center position within the pressure vessel 101. In other words, the electronic equipment 102 is surrounded by the coolant 104, which provides a moderating effect for cosmic rays and neutrons incident from any direction. The support mechanism 105 is configured so as not to impede the flow of the coolant 104 as much as possible.

[0026] The forced liquid-flow generator 103 is placed opposite the main surface of the electronic equipment 102 and is fixed by the support mechanism 105. The forced liquid-flow generator 103 has a function of forcedly flowing the coolant 104 within the pressure vessel 101. Preferably, the coolant 104 is forced to flow toward the inner wall of the pressure vessel 101.

[0027] More preferably, the forced liquid-flow generator 103 forces the coolant 104 to flow toward the electronic equipment 102, that is, in the direction shown by an arrow a1 in FIG. 1. The forced flow a1 causes the coolant 104 on the electronic equipment 102 to flow in the directions as shown by arrows b1 and b2, improving the efficiency of removing bubbles BB and the efficiency of cooling the electronic equipment 102.

[0028] The forced liquid-flow generator 103 can employ any liquid flow generation method, such as a method using a screw or underwater fan. However, if a rotating mechanism is used to generate liquid flow, its angular momentum may be a disturbance to the attitude control of a spacecraft. To avoid this, it is desirable to cancel the angular momentum by operating a pair of rotating fans rotating in opposite directions.

[0029] The coolant 104 should be an electrically insulating and thermally conductive liquid, especially containing hydrogen atoms for neutron beam moderation and shielding. For example, a liquid such as CFC substitute or polyester can be used as such coolant 104. In the present exemplary embodiment, when the temperature of the entire pressure vessel 101 is controlled below 60° C., the boiling point of the coolant 104 is about 76° C., for example.

[0030] The pressure vessel 101 is also provided with terminals (not shown) for input and output of power and signals to drive the electronic equipment 102 and the forced liquid-flow generator 103.

1.2) Cooling and Heat Dissipation

[0031] In FIG. 1, the forced liquid-flow generator 103 is driven, thereby generating the flow of coolant 104 in the direction of arrow a1 (in the vertical direction of FIG. 1). The flow of the coolant 104 is divided on the heat-generating part of the electronic equipment 102 into flows spreading over its surface as typically shown by arrows b1 and b2 (in the directions of a plane perpendicular to the arrow a1). The flows of coolant 104 in the directions of the arrows b1 and b2 convey the coolant 104 heated on the electronic equipment 102 and bubbles BB generated by the boiling of the coolant 104 on the electronic equipment 102 to the inner wall of the pressure vessel 101. In this way, the electronic equipment 102 is efficiently cooled. Since the bubbles BB move away from the electronic equipment 102, the dry-out phenomenon can be suppressed.

[0032] The heated coolant 104 cools as it moves along the inner wall of the pressure vessel 101, and the bubbles BB condenses back to liquid. The cooled coolant 104 is again forced to flow toward the electronic equipment 102 by the forced liquid-flow generator 103 as shown by the arrow a1. In this way, the cooling process is repeated, allowing the electronic equipment 102 to be cooled by the forced circulation of the coolant 104.

[0033] Various heat-dissipation methods can be employed to dissipate heat from the outer surface of the pressure vessel 101. In the case where the outer surface of the pressure vessel 101 is exposed to the outer space, heat can be dissipated directly. In the case where the pressure vessel 101 is radiation-coupled to the external heat sink of the spacecraft, heat can be dissipated depending on its heat flux.

2. Generation of Forced Liquid Flow

[0034] Hereinafter, as an example of the forced liquid-flow generator 103, a contra-rotating system will be described, which includes a pair of rotating blade units that rotate in opposite directions and generate liquid flow in the same direction. The rotating blade units that generate the liquid flow are referred to as “fans” for convenience.

[0035] As illustrated in FIGS. 2 and 3, the contra-rotating fan 200 is an example of the forced liquid-flow generator 103 employed in the present exemplary embodiment. The contra-rotating fan 200 includes a first fan (first rotating blade unit) 201 and a second fan (second rotating blade unit) 202, which have the same rotation axis 203. The contra-rotating fan 200 has such a structure that the first fan 201 and the second fan 202 are stacked in the direction of the rotation axis 203. The first fan 201 and the second fan 202 have the same structure, shape and mass except that their blades have mirror-image symmetrical orientations or profiles with respect to the line A perpendicular to the rotation axis 203.

[0036] The first fan 201 has a predetermined number of blades BL1 fixed to a motor M1. The motor M1 is rotatably supported on a frame F1 by bearings BE11 and BE12. The motor M1 is driven to rotate the blades BL1 in the direction of arrow R1.

[0037] Similarly, the second fan 201 has the same number of blades BL2 as the first fan 201. The blades BL2 are fixed to a motor M2. The motor M2 is rotatably supported on a frame F2 by bearings BE21 and BE22. The motor M2 is driven to rotate the blades BL2 in the direction of arrow R2 opposite to that of the arrow R1.

[0038] The first fan 201 and the second fan 202 rotate in opposite directions as indicated by R1 and R2, and each fan produces the same liquid flow in the direction of the arrow a1. Since the first fan 201 and the second fan 202 rotate in opposite directions, their angular momentums are canceled out, allowing suppressed disturbances in spacecraft attitude control.

[0039] The first fan 201 and the second fan 202 are stacked and fixed to supports 204 on concentric axes which are both on the rotation axis 203. The supports 204 are fixed to a plate 206 such that the bottom surface (coolant outflow surface) of the second fan 202 is placed at a predetermined distance from the plate 206. On the plate 206, a circuit board 301 of the electronic equipment, a semiconductor circuit 302, and heat dissipating fins 303 are stacked in the order from bottom to top. The heat dissipating fins 303 contacts the semiconductor circuit 302 with spacers 303 being placed between the heat dissipating fins 304 and the circuit board 301. The heat dissipating fins 304 and the coolant outflow surface of the second fan 202 are opposed. The distance between the heat dissipating fins 304 and the coolant outflow surface of the second fan 202 is determined taking into account the cooling efficiency of the forced coolant flow.

[0040] The flow of coolant generated by the first fan 201 and the second fan 202 passes through the heat dissipating fins 304. Accordingly, the cooling efficiency of the semiconductor circuit 302 is improved and bubbles BB generated on the heat dissipating fins 304 are removed, which can prevent the dry-out phenomenon.

[0041] The coolant 104 flows toward the heat spreader fins 304 in the direction shown by the arrow a1, which can obtain a higher cooling effect. However, the coolant flow direction is not limited to the arrow a1. For example, the coolant 104 can be made to flow in the opposite direction of arrow a1 (upward in FIG. 2) to remove the coolant and bubbles on the heat dissipating fins 304.

3. Example of Application

[0042] The ruggedizing apparatus 100 as described above can be applied to the ruggedizing of semiconductor circuits included in the electronic equipment mounted in the body of a man-made satellite. For example, a plurality of pieces of electronic equipment 102 are immersed in the coolant 104 of the pressure vessel 101, and each electronic equipment 102 is mounted with the forced liquid-flow generator 103, which can achieve both cooling and radiation shielding. Hereinafter, there will be described an example such that the contra-rotating fan 200 shown in FIGS. 2 and 3 is applied to the cooling of the semiconductor circuits 302.

[0043] As illustrated in FIG. 4, the ruggedizing apparatus 100 is installed inside a satellite body 400. For heat dissipation, the pressure vessel 101 is radiation-coupled to a radiation plate 40 provided on the outer surface of the satellite body 400. Inside the pressure vessel 101, the circuit board 301 is immersed in the coolant 104 and mounted with semiconductor circuits 302a and 302b, on which contra-rotating fans 200a and 200b are mounted, respectively. The semiconductor circuits 302a and 302b and the contra-rotating fans 200a and 200b are connected to a recovery apparatus 402, through which power is supplied and signal are transmitted and received.

[0044] The heat-generating semiconductor circuits 302a and 302b may be separate integrated circuits or a redundant system on the same integrated circuit. For example, if satellite control needs to be performed without interruption, a redundant system may be employed such that the semiconductor circuit 302a is used for a working circuit and the semiconductor circuit 302b is used for a reserved circuit. Normally, the working semiconductor circuit 302a and contra-rotating fan 200a are in operation while the reserved semiconductor circuit 302b and contra-rotating fan 200b are on standby.

[0045] Upon the occurrence of a failure or the like in a working system, the recovery apparatus 402 switches circuit operation from the working system to a reserved system. Accordingly, the semiconductor circuit 302b can continue the same control as the semiconductor circuit 302a and the contra-rotating fan 200b rotates to cool the semiconductor circuit 302b. In this way, in case a malfunction occurs in one of the semiconductor circuits, the same operation can continue in the other, enabling non-stop control that maintains the satellite's functions and improving reliability of the satellite.

4. Advantageous Effects

[0046] As mentioned above, according to the exemplary embodiment of the invention, at least the heat-generating semiconductor circuit 302 of electronic equipment is placed within the pressure vessel 101 filled with the coolant 104. Accordingly, the at least the heat-generating semiconductor circuit 302 is immersed in the coolant 104, ensuring that at least the space around the semiconductor circuit 302 is filled with the coolant, thereby obtaining the radiation moderating effect. In addition, the contra-rotating fan 200 forces the coolant on the heat-dissipating fins 3 04 to flow, thereby efficiently cooling the semiconductor circuit 302 and preventing the dry-out phenomenon.

[0047] In other words, the ruggedizing apparatus 100 according to the exemplary embodiment can achieve both the radiation shielding effect and the immersion cooling effect by immersing the semiconductor circuit 302, which can become highly heated, in the coolant 104, and forcing the coolant 104 to flow in the pressure vessel 101. This allows electronic equipment to operate in the outer space and control the satellite while maintaining its performance.

[0048] The present invention is applicable to a ruggedizing apparatus for use in a spacecraft such as a man-made satellite mounted with semiconductor integrated circuits that require cooling.

[0049] The present invention is not limited to the exemplary embodiments described above but can be modified in various ways without departing from the spirit or essential characteristics of the present invention.