JP2712559B2 - Temperature control device for spacecraft and temperature control method using the device - Google Patents

Description

The present invention relates to a temperature control device for a spacecraft and a temperature control method using the device.

[Related Art] In recent years, research and development on space shuttles such as a space shuttle have been advanced.

Since electronic devices such as humans and computers are mounted on the spacecraft, it is necessary to control the internal temperature with high accuracy.

Therefore, a conventional temperature control device for a spacecraft and a temperature control method using the device will be described with reference to FIG.

It circulates directly through a heat source 1 such as an electronic device provided inside a spacecraft (not shown) and through a heat exchanger 4 connected to a heat source 2 such as a fuel cell via an auxiliary fluid loop 3. A fluid main loop (hereinafter referred to as a chlorofluorocarbon main loop) 5 is formed.

A radiator 6, a water flash evaporator 7 and an ammonia boiler 8 are arranged in the middle of the CFC main loop 5.

The radiator 6 is a panel-shaped one that can be expanded only on a track, and the water flash evaporator 7 and the ammonia boiler 8 are provided with water generated by the heat source 2 such as a fuel cell, as shown in FIG. The evaporating chamber 12 having a pressure equal to the atmospheric pressure outside the space shuttle, which evaporates the water from the water tank 10 or the ammonia from the ammonia tank 11 so as to be replenished with the water 9, surrounds the outer periphery of the evaporating chamber 12. The water flash evaporator 7 and the ammonia boiler 8 have various structures other than the above, but have a structure in which a part of the CFC main loop 5 is disposed. It is almost the same).

 13 is a pump, 14 is a valve.

Next, a method for controlling the temperature of a spacecraft using the above-described apparatus will be described with reference to FIGS.

By operating the pump 13 to circulate the Freon main loop 5, the heat sources 1 and 2 are cooled by the Freon main loop 5.

Since the temperature of the Freon main loop 5 that has cooled the heat sources 1 and 2 rises, exhaust heat is performed using any of the radiator 6, the water flash evaporator 7, and the ammonia boiler 8, and the spacecraft a is temperature controlled. Is done.

First, in the section A passing for a while after the launch of the spacecraft a, the heat generated from the heat sources 1 and 2 is absorbed by the Freon main loop 5 due to the heat capacity of the Freon main loop 5 itself. In the section B between the time when a goes out of the atmosphere and the time when it goes into orbit, the water flash evaporator 7 is used.
The water in the water tank 10 is supplied into the evaporation chamber 12 at an extremely low pressure equal to the atmospheric pressure outside the atmosphere to evaporate the water and exhaust the heat of the CFC main loop 5 as latent heat of evaporation. Since the radiator 6 can be opened in the section C on the orbit, the heat of the Freon main loop 5 is exhausted from the radiator 6 to outer space. At the time of return of the spacecraft a, the section D outside the atmosphere uses the water flash evaporator 7 to discharge the heat of the CFC main loop 5, and the section E in the atmosphere uses the ammonia boiler 8 to switch the ammonia to the ammonia boiler 8. By supplying the ammonia to the evaporation chamber 12 of the ammonia boiler 8, ammonia having a boiling point lower than that of water and having an evaporation heat close to that of water is evaporated, and the heat of the CFC main loop 5 is exhausted as ammonia evaporation latent heat.

The amount of water supplied to the water flash evaporator 7 and the amount of ammonia supplied to the ammonia boiler 8 are adjusted so that the temperature of the CFC main loop 5 becomes constant (approximately 2 to 3 ° C.). By doing so, heat is discharged as shown in FIG. 8 showing the relationship between the amount of heat discharged from the CFC main loop 5 and time.

The hatched portions in FIG. 8 indicate the amount of heat exhausted by the actuator system (not shown) when the spacecraft a enters the atmosphere, and is not included in the amount of heat exhausted by the Freon main loop 5.

In this way, the section C on the orbit without the influence of air resistance
In the other sections B, D, and E in which the radiator 6 cannot be used, the latent heat of vaporization of water and ammonia having a boiling point lower than that of water is used. In the sections B and D outside the atmosphere, The water flash evaporator 7 was switched to the ammonia boiler 8 in the section E in the atmosphere.

[Problems to be Solved by the Invention] However, in the conventional temperature control device of the spacecraft and the temperature control method using the device, the radiator occupying more than one third of the total temperature control device of the spacecraft a is used. 6 and two separate water flash evaporators 7 and ammonia boilers 8 having substantially the same basic structure, the weight of the spacecraft a is increased, and the spacecraft a The temperature control has been complicated because water and ammonia must be switched and used depending on the atmospheric pressure.

Further, the evaporation amount of water and ammonia increases in accordance with the amount of heat exhausted from the spacecraft a, and as a result, the amount of liquid that must be loaded on the spacecraft a also increases. This has been a problem especially when the spacecraft a stays on the orbit c for a long time.

The present invention has been made in view of the above circumstances, and has as its object to provide a temperature control device for a spacecraft and a temperature control method using the device, which can reduce the weight of the spacecraft and simplify temperature control. Is what you do.

[Means for Solving the Problems] A first invention is a fluid main loop provided to circulate by receiving heat from a heat source provided inside a spacecraft.
A low-boiling liquid aqueous solution evaporator provided in the middle of the fluid main loop to evaporate any one of water and a low-boiling liquid aqueous solution in which both are mixed, and a flow rate for adjusting the amount of water A water tank with a regulating valve, a low-boiling liquid tank with a flow-regulating valve for regulating the amount of low-boiling liquid, and a low-boiling liquid aqueous solution evaporator and a water tank and interconnected between the low-boiling liquid tank; A temperature control device for a space shuttle vehicle, comprising a pipe capable of directly or mixing water from a water tank and a low-boiling liquid from a low-boiling liquid tank and supplying the water to a low-boiling liquid aqueous solution evaporator. The second invention is a low-boiling liquid loop provided to circulate by receiving heat of a heat source that generates heat at least when the spacecraft is launched,
A water tank provided in the middle of the low-boiling liquid loop; a flow control valve for mixing the low-boiling liquid in the low-boiling liquid loop into the water tank; and other heat sources provided inside the space shuttle. A low-boiling liquid aqueous solution evaporator provided for each source and evaporating any one of the water from the water tank and the low-boiling liquid aqueous solution as well as the low-boiling liquid aqueous solution obtained by mixing the two. A third aspect of the present invention relates to a temperature control device for a spacecraft, comprising a recovering device for returning steam discharged from an evaporator to a water tank, wherein the third invention evaporates a liquid to generate latent heat of the liquid. When heat is discharged from inside the spacecraft, a low-boiling liquid aqueous solution obtained by mixing water and a low-boiling liquid is used as the liquid, and the concentration of the low-boiling liquid solution is increased as the pressure outside the spacecraft becomes higher. Characterized by raising In which according to the temperature control method using the temperature control apparatus of the spacecraft to be.

[Operation] In the first invention, each heat source inside the spacecraft is cooled by circulating the fluid main loop, and the heat of the fluid main loop, which has been heated to a high temperature by cooling each heat source, is evaporated to a low boiling liquid aqueous solution. Exhaust heat in the vessel.

The low-boiling aqueous solution evaporator evaporates one of a low-boiling liquid such as water and ammonia as well as a low-boiling liquid aqueous solution obtained by mixing water and a low-boiling liquid, and uses the heat of the fluid main loop as latent heat of the evaporation. Exhaust heat.

In the second invention, the low-boiling liquid loop is circulated to cool the heat source that generates heat by operating at the time of launching the space shuttle, and the heat of the low-boiling liquid loop that is heated to a high temperature by cooling the heat source. Is absorbed in a water tank and a cooler.

Heat sources that generate heat by operating after the launch of the space shuttle are cooled by the low-boiling liquid aqueous solution evaporators provided respectively.

The low-boiling liquid aqueous solution evaporator evaporates one of water and a low-boiling liquid aqueous solution in which water and a low-boiling liquid are mixed together with the low-boiling liquid, and discharges the heat of each heat source as latent heat of the evaporation. I do.

The water vapor discharged from the low-boiling liquid aqueous solution evaporator is returned to the water tank by the recovery device and reused.

In the third invention, water and a low-boiling liquid are mixed to form a low-boiling liquid aqueous solution, and the low-boiling liquid aqueous solution is evaporated so that the concentration increases as the pressure outside the space shuttle increases, and the low-boiling liquid is evaporated. Waste heat from inside the spacecraft is used as latent heat.

[Example] Hereinafter, an example of the present invention will be described with reference to the drawings.

FIGS. 1 to 3 show an embodiment of the present invention.
Parts denoted by the same reference numerals as those in the drawings represent the same items.

A pipe 15 for sending water from the water tank 10 and a pipe 16 for sending a low boiling point liquid such as ammonia from the ammonia tank 11 are merged to form a merged pipe 17. It is connected to an aqueous ammonia solution evaporator 18 provided in the middle of the loop 5.

Flow control valves 19 and 20 are provided in pipes 15 and 16 for sending water and ammonia, respectively, and a temperature sensor 21 is provided on the inlet side of the ammonia aqueous solution evaporator 18 of the CFC main loop 5.

There is provided a subtractor 26 for inputting the detected temperature 22 of the temperature sensor 21 and the set temperature 24 from the temperature setter 23 to obtain a temperature difference 25 between the two.

The temperature difference 25 from the subtractor 26 and the air pressure 28 outside the spacecraft a detected by the pressure sensor 27 are input to the flow control valve.
An arithmetic and control unit 31 for sending commands 29 and 30 to 19 and 20 is provided.

 Next, the operation will be described.

The Freon main loop 5 itself operates in the same manner as that shown in FIG.

In the present invention, the temperature control of the spacecraft a is performed using the ammonia aqueous solution evaporator 18 in all the sections B, D, and E in FIG.

That is, the air pressure 28 outside the space shuttle a is detected by the pressure sensor 27 and the detected air pressure 28 is input to the arithmetic and control unit 31.

Then, the arithmetic and control unit 31 firstly waters, ammonia,
From the mixed ammonia aqueous solution, a liquid having a predetermined boiling point at the detected atmospheric pressure of 28 (the concentration of the aqueous ammonia solution) is determined.

As the above-mentioned predetermined temperature, a temperature (for example, −30 ° C.) that is most convenient for maintaining the CFC main loop 5 at a constant temperature (for example, 2 to 3 ° C.) is selected in advance.

Next, the arithmetic and control unit 31 derives the obtained enthalpy of the liquid, obtains the enthalpy difference between the enthalpy and the enthalpy of the liquid when the liquid evaporates, and obtains the CFC main loop from the temperature sensor 21 obtained by the subtractor 26. 5 detected temperature 22 and set temperature 24 input to temperature setting device 23
Is multiplied by the amount of Freon and the specific gravity to obtain the amount of heat exhausted from the Freon main loop 5, and the amount of necessary heat is obtained by dividing the amount of heat exhausted by the enthalpy.

Finally, the arithmetic and control unit 31 adjusts the flow rates of water and ammonia by sending commands 29 and 30 to the flow control valves 19 and 20 based on the obtained liquid amounts.

Therefore, in the section B at the time of the launch of the space shuttle a, the liquid discharged from the ammonia aqueous solution evaporator 18 becomes water as the pressure decreases due to the elevation of the space shuttle a, and in the sections D and E at the time of return, The liquid discharged from the ammonia aqueous solution evaporator 18 changes from water to a thin aqueous ammonia solution as the pressure rises due to a decrease in altitude of the space shuttle a, gradually increases the concentration of the aqueous ammonia solution, and finally becomes ammonia.

As described above, since the ammonia aqueous solution evaporator 18 performs the function of also evaporating water and ammonia, the weight of the spacecraft a can be reduced.

In addition, since water and ammonia are used as an aqueous ammonia solution and the concentration of the aqueous ammonia solution is changed according to the atmospheric pressure, high temperature controllability is obtained.

Next, the method of obtaining the enthalpy difference of water, ammonia, or an aqueous ammonia solution obtained by mixing both will be described in detail with reference to FIG.

At this time, the temperature of the water in the water tank 10 and the ammonia in the ammonia tank 11 was set to 0 ° C., and the pressure outside the space shuttle a was set to 0.
Assuming 1 ata, the predetermined boiling point is -30 ° C.

FIG. 2 is a During diagram showing the relationship between the concentration of an aqueous ammonia solution and enthalpy, which is generally known.

A line a indicating the enthalpy of the liquid having a boiling point of -30 ° C. on the During diagram and a line indicating the enthalpy of the liquid at the atmospheric pressure 28 outside the spacecraft a (4 evaporation lines of 0.1ata) Find the intersection c. The concentration (36%) at the intersection C is (the concentration of) the liquid to be obtained.

FIG. 3 is a diagram showing the relationship between the aqueous ammonia solution and the atmospheric pressure outside the spacecraft a when the boiling point is -30 ° C.

FIG. 3 shows that the concentration of the aqueous ammonia solution should be increased as the atmospheric pressure increases.

On the other hand, a line indicating the enthalpy of ammonia water at 0 ° C. on the During diagram is connected to the point of 100% of water (e) and the point of 100% of ammonia so that water at 0 ° C.
The enthalpy of the aqueous ammonia solution mixed with ammonia at ℃ is determined (line g).

Next, from the enthalpy of the point 36% concentration obtained as described above of the line indicating the enthalpy of the gas at the pressure (0.1ata) outside the spacecraft a (0.1ata), Concentration of the line that indicates the enthalpy of the aqueous ammonia solution obtained by mixing 0 ° C water and 0 ° C ammonia
The enthalpy difference is calculated by subtracting the enthalpy of the percentage point.

 FIG. 4 shows another embodiment of the present invention.

Before launch, it passes through a regenerator 33, which is connected to a ground-based refrigerator 32 to form ice inside, and a water tank 10 with a heat exchanger, and a heat source 34, which also operates at launch to generate heat. Thus, an ammonia loop 35 for circulating ammonia from the ammonia tank 11 is formed.

The ammonia loop 35 is connected to a line 37 having a flow control valve 36.
In addition, the inside of the regenerator 33 is communicated with the inside of the water tank 10 with the heat exchanger through the conduit 38 while communicating with the outlet of the water tank 10.

A small ammonia aqueous solution evaporator 18 is connected to each of the heat sources 1 and 2 operating on the orbit after the launch via the auxiliary fluid loop 3, and an ammonia loop 35 is passed through a pipe 39 connected inside the water tank 11. After passing through the heat generating source 34, it branches and is connected to each ammonia aqueous solution evaporator 18.

A conduit 40 for guiding the vapor generated by the aqueous ammonia solution evaporator 18 to the outside of the spacecraft is branched, and a collecting device 43 including a receiving portion 41 and a heater portion 42 is provided on one side. Connect to tank 10.

In addition, 45, 46, 47 are flow control valves 36, 48,
It is a command to 49.

In this embodiment, the regenerator 33 is launched before the launch of the spacecraft a.
Is connected to a refrigeration unit 32 on the ground, and ice is made and stored inside the regenerator 33.

After the launch, the ammonia loop 35 is operated, and the heat generated by the heat source 34 operating during the launch is absorbed by the ice in the regenerator 34 and the water in the water tank 10 to control the temperature. The temperature control by the regenerator 33 and the water tank 10 is performed up to the sections A and B until the spacecraft a reaches the orbit.

In section C on the orbit, the water formed by melting the ice inside the regenerator 33 and the water in the water tank 10 are supplied to the ammonia aqueous solution evaporators 18 of the heat sources 1 and 2 which generate heat by use. Thus, the temperature control using the latent heat of evaporation of water is performed for each of the heat sources 1 and 2.

At this time, the water vapor evaporated and discharged to the outside of the spacecraft a is collected by the receiving portion 41 of the recovery device 43, heated and liquefied by the heater portion 42 (the water vapor freezes when discharged on orbit). Ice particles) and returned to the water tank 10 again. As a result, the long-term stay of the spacecraft a in orbit becomes possible.

In sections D and E at the time of return, the ammonia supplied in the ammonia loop 35 and the ammonia tank 11 is appropriately mixed with the water from the water tank 10 so that the liquid supplied to the ammonia aqueous solution evaporator 18 is converted from the water into the aqueous ammonia solution. And then to ammonia.

In addition, the temperature control device of the spacecraft of the present invention and the temperature control method using the device are not limited to only the above-described embodiment, and the low boiling point liquid is not limited to ammonia,
Of course, various changes can be made without departing from the spirit of the present invention.

[Effects of the Invention] As described above, according to the temperature control device for a spacecraft and the temperature control method using the device of the present invention, the following various excellent effects can be obtained.

Since the low boiling point liquid aqueous solution evaporator is provided, the water flash evaporator and the ammonia boiler are not required, and the space shuttle can be reduced in weight.

Since the low-boiling liquid aqueous solution evaporator changes the concentration of the low-boiling liquid aqueous solution to evaporate, the temperature inside the space shuttle can be easily and accurately controlled.

By providing a low-boiling liquid loop and a low-boiling liquid aqueous solution evaporator, the liquid main loop and radiator become unnecessary,
Further, the spacecraft can be significantly reduced in weight.

By recovering the vapor evaporated by the low boiling liquid aqueous solution evaporator, the amount of liquid that must be loaded into the space shuttle is small, and the space shuttle having a large total heat dissipation can be significantly reduced in weight.

[Brief description of the drawings]

FIG. 1 is a system diagram of one embodiment of the present invention, FIG. 2 is a During diagram showing the relationship between the concentration of an aqueous ammonia solution and enthalpy, and FIG. 3 is an aqueous ammonia solution and a space flight when the boiling point is −30 ° C. FIG. 4 is a system diagram of another embodiment of the present invention, FIG. 5 is a system diagram of a conventional example, and FIG. 6 is a water flash evaporator of FIG. FIG. 7 is a flight process diagram of the spacecraft, and FIG. 8 is a diagram showing the relationship between the amount of heat exhausted from the CFC main loop and time. In the figure, 1, 2, and 34 are heat sources, 4 is a heat exchanger, 5 is a fluid main loop (Freon main loop), 10 is a water tank, 11 is an ammonia tank, 18 is an ammonia aqueous solution evaporator, 19, 20, 36,48,49
Denotes a flow control valve, 28 denotes an air pressure outside the spacecraft, 35 denotes an ammonia loop, and a denotes a spacecraft.

 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor Toshikazu Yano 1 Shin-Nakahara-cho, Isogo-ku, Yokohama-shi, Kanagawa Prefecture Inside the Technical Research Institute of Ishikawajima-Harima Heavy Industries Co., Ltd. (72) Inventor Junichi Ochiai Shin-Nakahara-cho, Isogo-ku, Yokohama-shi, Kanagawa No. 1 Ishikawajima-Harima Heavy Industries, Ltd. Technical Research Institute (72) Inventor Koichi Chiba 1-6-2, Marunouchi, Chiyoda-ku, Tokyo Ishikawajima-Harima Heavy Industries, Ltd. Annex Building (56) References JP-A-1-132499 (JP, A) JP-A-1-132500 (JP, A) JP-A-1-145300 (JP, A) JP-A-63-201968 (JP, U)

Claims (4)

(57) [Claims] 1. A fluid main loop provided to circulate by receiving heat from a heat source provided inside a spacecraft, and a fluid main loop provided in the middle of the fluid main loop, which includes water and a low boiling point liquid. , A low-boiling liquid aqueous solution evaporator for evaporating any one of the low-boiling liquid aqueous solutions, a water tank provided with a flow control valve for adjusting the amount of water, and a flow rate for adjusting the amount of the low boiling liquid A low-boiling liquid tank equipped with a regulating valve is interconnected between the low-boiling liquid aqueous solution evaporator and the water tank and the low-boiling liquid tank to directly or directly transfer water from the water tank and low-boiling liquid from the low-boiling liquid tank. A temperature control device for a spacecraft, wherein the temperature control device comprises a pipeline that can be fed to a low boiling liquid aqueous solution evaporator while being mixed. 2. A low-boiling liquid loop provided to circulate by receiving heat from a heat source that generates heat at least when the spacecraft is launched, a water tank provided in the middle of the low-boiling liquid loop, A flow control valve for mixing the low-boiling liquid in the low-boiling liquid loop into the water tank, and a water-controlling valve provided for each of the other heat sources provided inside the spacecraft, A low-boiling liquid aqueous solution evaporator for evaporating any one of the low-boiling liquid aqueous solutions obtained by mixing the two in a liquid and a low-boiling liquid aqueous solution evaporator. 3. The temperature control device for a spacecraft according to claim 2, further comprising a recovering device for recovering the steam discharged from the aqueous solution of the low boiling point liquid and returning it to the water tank. 4. When the liquid is evaporated to discharge heat from inside the spacecraft as latent heat of vaporization of the liquid, an aqueous solution of a low-boiling liquid obtained by mixing water and a low-boiling liquid is used as the liquid. A temperature control method using a temperature control device of a space shuttle, wherein the concentration of the low-boiling liquid aqueous solution is increased as the external atmospheric pressure increases.