JPH06249598A - Cooling device using coolant - Google Patents

Abstract

PURPOSE:To use a coolant with good efficiency by beginning cooling when a cooled portion exceeds a predetermined temperature through discharging the coolant enclosed in a high temperature portion through a throttle set at an exit portion by opening a cover of the exit of a pipe line when the cooled portion reached a predetermined temperature. CONSTITUTION:A nozzle inner wall portion 6 executes a temperature rising by a high temperature gas of a rocket motor 7, a coolant in a space 1 is gasified and the pressure rises. By an operation and the like of a rudder operating blade 8, temperatures of a rudder blade controlling device 5a, a feedback operation portion 5b, and a rudder operating blade driving motor 5C and the like rises rapidly and, accompanied by this, when a nipped body 9 reaches a predetermined temperature, a cover 3a opens an exit 3. When the exit 3 opens, a coolant in gas in a space 1 is discharged through a throttle 3a of the exit 3. By a heat absorbing action by an adiabatic expansion of the coolant at this time, the throttle 3 is cooled. By this, the rudder blade controlling device 5a, the fied back operation part 5b, and the rudder operating blade driving motor 5C mounted on the nipped 9 can be effectively cooled.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling device using a refrigerant used for cooling electric / electronic devices mounted on a flying object.

[0002]

2. Description of the Related Art In a conventional flying object, when cooling an electric / electronic device, the electric / electronic device 14 is moved to the position shown in FIG.
As shown in (a), a high-temperature heating element (rocket motor,
The installation place is separated from the engine 15 or, as shown in FIG. 3B, outside air is taken in from the air intake 10 during flight to air-cool the electric component 13. When cooling is performed by the outside air, the flying body is provided with air intakes 10 at four places on the circumference, and the outside air enters from here when flying and the heating element 11 (in FIG. 3 (b), The exhaust gas is discharged from the rear gap 12 by passing around the jet engine exhaust nozzle) to cool the electric components 13 by air cooling.

In addition, regarding equipment such as a motor in a flying object that generates heat by itself, a wire such as a coil winding is thickened to reduce resistance and suppress heat generation when a necessary current is passed, heat capacity (case etc.) ) Is designed so that the temperature does not rise too high.

[0004]

In cooling the electric / electronic device of the flying object, when the electric / electronic device is positioned away from the heating element such as the rocket motor or the engine as described above, the normal flying It is necessary to connect a wire to the steering device located at the rearmost part of the body. Further, as described above, when cooling is performed by the outside air, when the flying body attempts to fly at supersonic speed, the temperature of the air may rise due to aerodynamic heating, resulting in insufficient cooling. Furthermore,
As described above, in devices that generate heat, such as motors, if the wire of the coil winding is thickened to reduce the resistance and suppress heat generation, or if the heat capacity is increased to prevent temperature rise, the device must be large. I have no choice.

The present invention is intended to provide a cooling device using a refrigerant capable of solving the above problems.

[0006]

A cooling device using a refrigerant according to the present invention is a space provided in a high temperature part for enclosing a refrigerant, a pipe line connecting the space and a cooling part, and a pipe provided with a throttle. It is characterized by comprising an outlet to the cooling part of the passage and a lid provided at the outlet and opening the outlet at a constant temperature.

[0007]

Since the present invention has the above-mentioned structure, when the temperature of the cooling portion reaches a constant temperature, the lid at the outlet of the pipeline opens. Since the refrigerant in the space heated in the high temperature part is vaporized and the pressure is rising, the refrigerant is discharged from the outlet where the lid is opened via the throttle of the pipeline. At this time, the adiabatic expansion absorbs heat to cool the throttle and cool the blown refrigerant itself. As described above, the cooling of the cooling portion is performed by cooling the throttle at the outlet and also cooling the blown refrigerant itself.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. As shown in FIG. 1, the flying body 20 incorporating the rocket motor 7 controls the flight path by moving the steering wings 8 attached to the outer periphery of the nozzle portion 7a of the rocket motor 7 at the rear end. It has become. In this flying object 20, altitude, acceleration, and homing information is calculated, and a steering signal is transmitted to the steering wing control device 5a provided in the nozzle portion 7a of the rocket motor 7, and the feedback calculation unit 5b of the control device 5a is transmitted. Performs feedback calculation together with the signals of the angle and angular velocity of the steering blade 8 and turns the steering blade driving motor 5c to
To control the steering angle.

The nozzle portion 7a of the rocket motor 7 forms a high temperature gas discharge nozzle of the rocket motor 7 and a space 1 in which a ring-shaped refrigerant is sealed is provided in the nozzle inner wall portion 6 which is a high temperature portion. One end of a pipeline 2 is opened in the same space 1, and at the other end of the pipeline 2, the pipeline 2, the steering blade control device 5a, its feedback calculation unit 5b, and a steering blade driving motor 5c. An outlet 3 is formed in close proximity to the electric / electronic device by means of a cylinder 9 attached to the electric / electronic device, and a throttle 3a is provided at the outlet 3.

At the tip of the outlet 3, the outlet 3 is provided when the temperature is low.
A lid 4 is attached that closes the container and opens the outlet 3 when a certain temperature is reached. As the lid 4, a low-melting metal (solder, wood metal, etc.) or resin that melts at a constant temperature to open the outlet 3 or resin can be used, and the outlet 3 that is deformed and closed when the temperature exceeds a certain temperature is used. It is also possible to use a shape memory alloy that releases the.

The space 1 for accommodating the refrigerant is shown in FIG.
Use a cylinder 1a as shown in (a), a cylinder 1b provided with a liquid pool 1b 'as shown in FIG. 2 (b), or a spiral pipe line 1c as shown in FIG. 2 (c). You can

Reference numeral 21 in FIG. 1 denotes a clearance provided in the rear portion of the flying body 9 for discharging the refrigerant.

In the present embodiment, the hot gas of the rocket motor 7 causes the temperature of the inner wall 6 of the nozzle to rise, whereby the refrigerant in the space 1 is vaporized and the pressure rises. The temperature of electric / electronic devices or electric components such as the steering blade control device 5a, the feedback calculation unit 5b thereof, or the steering blade driving motor 5c is increased by the operation of the steering blade 7, and the temperature of the body 9 is accompanied with this. When reaches a constant temperature, the lid 4 opens the outlet 3.

In this way, when the outlet 3 is opened, the refrigerant gas in the space 1, which is heated by the nozzle inner wall portion 6 and vaporized to increase the pressure, is discharged through the throttle 3a of the outlet 3. . At this time, the throttle 3a is cooled by the endothermic action of the adiabatic expansion of the refrigerant.

When the refrigerant itself blown out as described above is cooled and a part thereof is liquefied, this refrigerant is blown to the body 9 and the liquefied refrigerant is vaporized by the heat of the body 9. Is cooled by the heat of vaporization. As a result, it is possible to effectively cool the steering wing control device 5a attached to the shoe 9, the feedback calculation unit 5b thereof, and the steering wing drive motor 5c.

The refrigerant gas cooled as described above is discharged to the outside through the gap 21 at the rear portion of the flying body.

In this embodiment, since the effective cooling can be performed by the refrigerant as described above, the conventional temperature conditions are not met, so that the equipment is installed away from the nozzle portion 7a of the rocket motor 7 which is a high temperature portion. The steering blade control device or the like that has been used can be installed in the vicinity of the steering blade 8, and the size and weight of the flying object can be reduced.

If the space 1 is filled with the pressurized refrigerant, the amount of the refrigerant ejected when the lid 4 of the outlet 3 is opened can be increased to enhance the cooling effect.

Although the above embodiment relates to a cooling device for a flying object, the present invention can be widely applied as a cooling device for equipment used for a short time and having a high temperature portion.

[0020]

According to the present invention, the refrigerant enclosed in the high temperature part is
When the cooling part reaches a constant temperature, the lid of the outlet of the pipeline is opened and the gas is discharged through a throttle provided in the outlet, whereby cooling can be started when the cooling part exceeds a constant temperature. , The refrigerant can be used efficiently.

Further, the device is only the space in which the refrigerant is sealed, the pipe line, the throttle and the lid, and is simple and there is almost no increase in weight due to this.

Further, by the refrigerant discharged from the outlet,
Not only cooling in the throttle by adiabatic expansion, but also cooling by the heat of vaporization when the liquefied refrigerant vaporizes again,
The cooling effect increases.

[Brief description of drawings]

1 shows an embodiment of the present invention, FIG. 1 (a) is a sectional view thereof, and FIG. 1 (b) is an enlarged view of a portion A of FIG. 1 (a).

2 (a), 2 (b), and 2 (c) are explanatory views showing an example of a space in which the refrigerant of the above embodiment is sealed.

3A and 3B show a conventional cooling method for a flying object, FIG. 3A is a sectional view thereof, and FIG. 3B is an enlarged view of a portion B of FIG. 3A.

[Explanation of symbols]

 1 Space in which a pipe is enclosed 2 Pipe 3 Outlet 3a Aperture 4 Lid 5a Steering wing control device 5b Feedback calculation unit 5c Steering wing drive motor 6 Nozzle inner wall 7 Rocket motor 8 Steering wing 9 Flying body 20 Flying body

Claims (1)

[Claims] 1. A space provided in a high temperature part in which a refrigerant is sealed,
Refrigerant characterized by comprising a pipeline connecting the space and the cooling portion, an outlet to the cooling portion of the pipeline provided with a throttle, and a lid provided at the outlet for opening the outlet at a constant temperature. Cooling device using.