JP2001074320A - Cooling system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a cooling system, permitting an aircraft, cooling mounted electronic instruments employing a refrigerant, to cool them even upon staying on the ground. SOLUTION: A skin condenser 5 of vapor cycle cooling system(VCS) employing a refrigerant is covered by a cooling jacket 12 and the cooling jacket 12 is fixed by mounting tension bands 21 so as to be contacted closely with the condenser 5. Cooling liquid is circulated through the cooling jacket 12 by a cooling liquid circulating/cooling device 14 to cool the skin condenser 5. Further, an altitude, a speed of a plane and an atmospheric temperature are thrown into a CPU 17 through a flying condition throwing key 24 in a control unit 23 and data from a memory device 15 are read and operated to control the cooling liquid circulating/cooling device 14 while simulation on the ground can also be effected by a feedback signal from a temperature detector 13.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling system for controlling the temperature of an electronic device mounted on an aircraft and a cabin, and more particularly to a vapor cycle cooling system that operates even when the aircraft is parked on the ground.

[0002]

2. Description of the Related Art Electronic equipment in a pod mounted on an aircraft is cooled by using a refrigerant, for example, an alternative Freon or the like, by using a compressor (compressor), a condenser (condenser), a receiver (liquid receiver), and expansion. A vapor cycle cooling system (hereinafter referred to as VC) for a refrigeration cycle comprising a valve and an evaporator (evaporator).
S). FIG. 4 shows a control block diagram in which the electronic device 11 mounted on the aircraft is cooled by VCS. When the aircraft is flying, the cold air of the outside air touches the surface of the skin condenser 5 attached to the aircraft pod outer panel 5a. The high-temperature and high-pressure vapor-state refrigerant compressed by the compressor 6 enters the skin condenser 5, takes heat from the surroundings, condenses, becomes a liquid, flows into the tank of the receiver 7, and is stored. The refrigerant from the receiver 7 is adiabatically expanded by the expansion valve 8 and becomes low pressure, enters the evaporator 9, takes heat from the surroundings, and turns into steam. The vaporized refrigerant is sucked into the compressor 6 from the cooling coil. And it is compressed to high temperature and high pressure. The cooling liquid for cooling the electronic device 11 is exchanged with heat by the evaporator 9 of the refrigeration cycle, and the cooling liquid is circulated by the circulation pump 2 to cool the electronic device 11. The same applies to cabin cooling.

[0003]

The conventional cooling system is constructed as described above. However, since the air volume is sufficient and the outside air temperature is low during the flight of the aircraft, the skin condenser mounted on the pod outer plate 5a is required. Although the skin condenser 5 is cooled, the skin condenser 5 is not sufficiently cooled when it is parked on the ground because a sufficient air volume cannot be obtained and the outside air temperature is high. Therefore, even if the high-temperature and high-pressure vapor-like refrigerant compressed by the compressor 6 enters the skin condenser 5, it cannot be condensed and becomes a liquid and is not stored in the tank of the receiver 7. Therefore, the cooling system (VC
There is a problem that S) cannot be operated. In addition, the skin condenser 5
There is a problem that it is required to cool the cooling system and perform a simulation test of a cooling system (VCS).

[0004] The present invention has been made in view of such circumstances, and when an aircraft is parked on the ground, the temperature of electronic equipment mounted on the aircraft and the temperature in the cabin is measured using a refrigerant. It is an object of the present invention to provide a cooling system capable of performing cooling control.

[0005]

To achieve the above object, a cooling system according to the present invention uses a refrigerant to cool a compressor, a skin condenser, a receiver, and the like in a pod mounted on an aircraft by using a refrigerant in electronic equipment and a cabin. In a vapor cycle cooling system that cools with a system consisting of an expansion valve and an evaporator, while the coolant circulates inside,
A cooling jacket capable of covering the surface of the skin capacitor is provided.

Further, the cooling system of the present invention has a key for inputting flight conditions, a storage device for storing temperature data on the surface of the skin condenser corresponding to the flight conditions, and an automatic readout of data in the storage device by a key input signal. A CPU for calculating the surface temperature of the skin capacitor and outputting a control signal to the cooling device, a cooling device for controlling the flow rate and temperature of the cooling liquid sent to the cooling jacket, and detecting the surface temperature of the skin capacitor and transmitting the signal. And a temperature detector that returns to the CPU.

[0007] The cooling system of the present invention is configured as described above, and when the vehicle is parked on the ground where a sufficient air volume and a low outside air temperature cannot be obtained, a cooling jacket made of a soft resin and having a cooling liquid flow path therein. Then, the surface of the VCS skin condenser is covered, the internal flow path is connected to the cooling device, and the skin condenser is cooled by the cooling jacket, so that the VCS cooling system can be normally operated while the vehicle is parked on the ground. It is possible to cool the inside of the cabin and the electronic devices mounted on the aircraft. Further, the cooling jacket of the present cooling system can simulate the surface of the skin condenser on the ground by keying in a cooling condition at the time of flight at a high altitude, instead of simply cooling the object. That is, by inputting flight conditions such as altitude, aircraft speed, and atmospheric temperature, the CPU automatically calculates the surface temperature of the skin capacitor by reading data from the storage device and calculating the surface temperature of the skin capacitor. By controlling the cooling condenser with the cooling jacket so that the temperature becomes equal to the temperature, the skin condenser is placed in a condition equivalent to high altitude flight.

[0008]

DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of a cooling system according to the present invention will be described with reference to FIG. FIG. 1 shows a perspective view of the cooling system of the present invention. This cooling system is connected to a vapor cycle cooling system (VCS) using a refrigerant having a skin condenser 5, a cooling jacket 12 provided with a mounting tension band 21 for covering the skin condenser 5, and the cooling jacket 12. Coolant circulation / cooling device 1 for circulating coolant through the cooled coolant passage 22
4, a flight condition input key 24 for keying in flight conditions such as altitude 18, aircraft speed 19, and atmospheric temperature 20; and a storage device 15 for storing temperature data on the surface of the skin condenser 5 for flight conditions. The data in the storage device 15 is read out by the key input signal, the surface temperature of the skin condenser 5 is automatically calculated, and the CPU 17 that outputs a control signal to the coolant circulation / cooling device 14 and the surface temperature of the skin condenser 5 are detected. , And a temperature detector 13 that feeds back the signal to the CPU. The cooling liquid circulation / cooling device 14 is composed of a cooling device 3 for cooling the cooling liquid filled in a pipe of the cooling liquid flow path 22 in the circulation loop A, and a circulation pump 1 for circulating the cooling liquid. I have. The cooling jacket 12 is provided with a cooling liquid flow path inside, is a mat-shaped cooling jacket made of a soft resin, the outside is covered with a heat insulating agent, and the inside is made of a sheet of a material having good heat conductivity. It can be closely covered with the surface of the capacitor 5. A mounting tension band 21 is provided to improve the degree of adhesion. Cooling channels 22 for flowing the coolant inside are provided at both ends of the cooling jacket 12.
Are connected. Water may be used as the cooling liquid, but an antifreeze such as ethylene glycol is preferred.

FIG. 2 shows a cooling system diagram of the present apparatus. The cooling system of the present cooling system includes a circulation loop A in which the cooling liquid cooled by the cooling liquid circulation / cooling device 14 circulates through the cooling jacket 12, a circulation loop B using the VCS refrigerant, and a VCS loop.
Of the electronic device 1 with the coolant indirectly through the evaporator 9
And a circulation loop C for cooling the cooling water. In the cooling cycle A of the cooling cycle, a cooling liquid, for example, a cooling liquid such as ethylene glycol filled in a pipe of the cooling liquid flow path 22 is cooled by the cooling device 3, passed through the valve 4 by the circulation pump 1, It is introduced into the cooling jacket 12 covered by the skin condenser 5. Then, the cooling liquid exchanges heat with the coolant of the VCS to remove heat, and is again introduced into the cooling device 3 by the circulation pump 1. That is, the circulation loop A transfers heat from the cooling jacket 12 to the skin condenser 5 of the VCS. The circulation loop B of the cooling cycle is a vapor cycle cooling system using a refrigerant, for example, an alternative Freon, in which high-temperature and high-pressure vapor-like refrigerant compressed by the compressor 6 enters the skin condenser 5 and is circulated through the skin condenser 5. The heat is removed from the surroundings of the cooling liquid of A and condensed, and becomes a liquid and flows into the tank of the receiver 7 and is stored. The refrigerant from the receiver 7 is adiabatically expanded by the expansion valve 8 to have a low pressure, enters the evaporator 9 and removes heat from the surroundings to become steam. The vaporized refrigerant is sucked into the compressor 6 from the cooling coil. And it is compressed to high temperature and high pressure. In the circulation loop C of the cooling cycle, the cooling liquid cooled by the evaporator 9 of the VCS passes through the valve 10 to cool the electronic device 11. Then, the cooling liquid is again introduced into the evaporator 9 by the circulation pump 2.

The cooling system further comprises a mechanism for automatically calculating the surface temperature of the skin condenser 5 by keying in the conditions at the time of flight at a high altitude. It can be cooled and simulated on the ground. The mechanism of the control unit 23 includes an advanced flight condition input key 24 such as an altitude 18, a speed 19, and an atmospheric temperature 20, a storage device 15 for storing temperature data on the skin condenser surface with respect to the flight condition, and a key input signal. CPU 17 which reads out data from storage device 15 to automatically calculate the surface temperature of skin capacitor 5 and calculates and outputs a control signal to coolant circulation / cooling device 14
A cooling liquid circulation / cooling device 14 for controlling the flow rate and temperature of the cooling liquid sent to the cooling jacket 12, and a temperature detector 13 for detecting the surface temperature of the skin condenser 5 and returning the signal to the CPU 17. I have. As shown in FIG. 1, a control unit 23 is stored in the upper part of the case of the coolant circulation / cooling device 14, and a flight condition input key 24
(18, 19, 20) are provided, and a CPU 17 as an arithmetic unit and a storage device 15 are provided therein. Further, a temperature detector 13 is provided inside the cooling jacket 12.

Next, the operation will be described with reference to FIGS. First, the cooling jacket 12 is covered over the skin capacitor 5 and tightly fixed with the mounting tension band 21. Next, the user selects the altitude 18 key of the flight condition input key 24 and inputs the altitude by ten keys. Next, the operator selects the 19 speed key and inputs the flight speed with the ten keys. Next, the user selects the ambient temperature 20 key and enters the numeric keypad assuming the atmospheric temperature of the sky above the flight based on past data. With these key inputs, the CPU 17 reads the corresponding data from the storage device 15. From the data, the CPU calculates the coolant flow rate and coolant temperature in the coolant circulation / cooling device 14,
Command operating conditions. With this signal, the cooling device 3 of the coolant circulation / cooling device 14 and the circulation pump 1 operate.
The coolant circulates through the coolant channel 22 to the cooling jacket 12. On the other hand, the temperature detector 13 detects the surface temperature of the heat-exchanged skin capacitor 5,
The CPU 17 receives the signal, and sends a corrected signal to the coolant circulation / cooling device 14 again to maintain the surface temperature of the skin condenser 5 corresponding to a predetermined flight condition. The cooling jacket 12 of the present cooling system does not simply cool the skin condenser 5 but simulates cooling conditions during flight at a high altitude on the ground.
That is, the surface temperature of the skin condenser 5 is calculated from the flight conditions (altitude, aircraft speed, and atmospheric temperature), and the surface of the skin condenser 5 is controlled by the cooling jacket 12 so as to be equal to the temperature.
Is equivalent to a high altitude flight.

In the above embodiment, the cooling jacket 12
However, the structure in which the passage for circulating the cooling liquid is provided in the inside has been described.
It may have a structure that comes into contact with the surface. For example, a structure may be used in which a packing capable of maintaining airtightness is provided inside the cooling jacket 12 and cooling water flows through a groove formed between the packing and the surface of the skin capacitor 5.

[0013]

The cooling system of the present invention is configured as described above. When the aircraft is parked on the ground, the cooling jacket covers the surface of the VCS skin condenser, and is connected to the cooling device to connect the skin condenser. Since the air conditioner is cooled, the cooling system using the refrigerant can be operated while the vehicle is parked on the ground to cool the electronic devices and the cabin mounted on the aircraft. In addition, by inputting flight conditions such as altitude, aircraft speed, and atmospheric temperature, the surface temperature of the skin condenser is automatically calculated, and the temperature of the skin condenser surface is set to a condition equivalent to high altitude flight. As described above, the cooling jacket can be controlled, and the surface of the skin capacitor can be simulated on the ground.

[Brief description of the drawings]

FIG. 1 is a diagram showing one embodiment of a cooling system of the present invention.

FIG. 2 is a diagram showing a cooling circuit using the cooling system of the present invention.

FIG. 3 is a diagram illustrating setting of a cooling temperature of the cooling system of the present invention.

FIG. 4 is a diagram showing a cooling circuit of a conventional cooling system.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Circulating pump 2 ... Circulating pump 3 ... Cooling device 4 ... Valve 5 ... Skin condenser 5a ... Pod outer plate 6 ... Compressor 7 ... Receiver 8 ... Expansion valve 9 ... Evaporator 10 ... Valve 11 ... Electronic equipment 12 ... Cooling jacket 13 ... Temperature detector 14 ... Cooling liquid circulation / cooling device 15 ... Storage device 17 ... CPU 18 ... Altitude 19 ... Machine speed 20 ... Ambient temperature 21 ... Mounting tension band 22 ... Cooling fluid channel 23 ... Control unit 24 ... Flight condition input Key

Claims (2)

[Claims] 1. A vapor cycle cooling system for cooling an electronic device and a cabin in a pod mounted on an aircraft with a system including a compressor, a skin condenser, a receiver, an expansion valve, and an evaporator using a refrigerant. A cooling system comprising: a cooling jacket that circulates a liquid and covers a surface of the skin condenser. 2. A key for inputting flight conditions, a storage device for storing temperature data on the surface of the skin capacitor with respect to the flight conditions, and data of the storage device are read out by a key input signal to automatically determine the surface temperature of the skin capacitor. A CPU that calculates and outputs a control signal to the cooling device; a cooling device that controls the flow rate and temperature of the cooling liquid sent to the cooling jacket; and a temperature detector that detects the surface temperature of the skin capacitor and returns the signal to the CPU. The cooling system according to claim 1, further comprising: