JP3124651U - Liquid cooling system for aircraft equipment - Google Patents

Abstract

PROBLEM TO BE SOLVED: To detect the amount of cooling liquid in a reservoir tank even if the occupied area is reduced by eliminating the structure in which an indicator or the like protrudes from the reservoir tank.
SOLUTION: A piping system mainly composed of piping 12 that is sealed from the atmosphere and circulates a cooling liquid L, and a tank body 11 that pressurizes a piston 13 with a spring 14 to pressurize the cooling liquid L to the piping system. In addition, this is a liquid cooling system for aircraft equipment that supplies and recovers the cooling liquid L to the object to be cooled, and the arithmetic circuit 16 detects the position of the piston 13 from the strain gauge 15 attached to the spring 14 and the output of the strain gauge 15. Thus, the amount of the coolant L in the tank body 11 is calculated.
[Selection] Figure 1

Description

  The present invention relates to a liquid cooling system for aircraft equipment that supplies a coolant to a device to be cooled.

  Conventionally, in a liquid cooling system for aircraft equipment, a cooling liquid is circulated through a piping system completely sealed with respect to the atmosphere, and the cooling liquid is supplied to the equipment to be cooled. A reservoir tank 50 as shown in FIG. 2 is mounted on the piping system, which has a function of always pressurizing the coolant in the piping system by pushing the piston with a spring from the rear. That is, in FIG. 2, the piston 53 is connected to the spring 54 so that the coolant L in the tank body 51 is connected to the pipe 52 so as to be able to flow in and out, and is pressurized in the direction in which the coolant L flows into the pipe 52. It is energized by. This

(1) Absorbing a change in the volume of the system due to a temperature change to prevent excess or deficiency of the coolant L in the piping system to prevent damage to the equipment (as shown in FIGS. 2a and 2b, the piston in the tank body 11). 53 moves with the volume change and the reservoir volume changes).
(2) By boosting with the force of the spring 54 inside the tank body 51, the pump suction pressure is ensured even during high altitude flight, and cavitation is prevented.

  On the other hand, even in a sealed piping system, the amount of liquid in the piping system may decrease due to evaporation, discharge, or leakage of cooling liquid due to aging, relief function, equipment failure, etc. . Therefore, as a method of detecting the amount of liquid in the tank body 51 in order to find a decrease in the amount of liquid, as shown in FIG. 2, an indicator 57 fixed to the piston 53 is projected from the tank body 51, and the position thereof is determined. The position of the piston 53 was detected by providing a linear sensor in place of the direct visual reading method or the indicator 57.

  However, the indicator or linear sensor 57 fixed to the piston 53 needs a length longer than the stroke of the piston 53 in order to read the position, and the length corresponding to the stroke protrudes from the tank body 51, and is occupied. The area was increasing.

  As described above, the present invention provides a liquid cooling system for aircraft equipment that can detect the amount of coolant in the tank body even if the occupied area is reduced by eliminating the structure in which the indicator or the like protrudes from the tank body.

  The present invention includes a piping system that is sealed from the atmosphere and circulates the cooling liquid, and a reservoir tank that pressurizes the cooling liquid to the piping system by urging the piston with a spring, and supplies the cooling liquid to the object to be cooled. In the liquid cooling system for aircraft equipment to be recovered, a strain gauge affixed to the spring, and calculating means for calculating the amount of the coolant in the reservoir tank by detecting the position of the piston from the output of the strain gauge; It is provided with.

  In the present invention, in order to detect the amount of liquid in the reservoir tank, an indicator or a linear sensor is not required, and there is no member protruding outside from the reservoir tank. Therefore, it is not necessary to secure the space area, and the apparatus can be downsized. Further, since the strain gauge is lighter than the indicator or the linear sensor, it is possible to reduce the weight.

  Hereinafter, the reservoir tank in the liquid cooling system for aircraft equipment of the present embodiment will be described with reference to FIG.

  FIG. 1 shows the structure of a reservoir tank 10 in the liquid cooling system for aircraft equipment of the present invention. In the liquid cooling system for aircraft equipment, the cooling liquid L is circulated in a piping system completely sealed to the atmosphere, and the cooling liquid L is supplied to the equipment to be cooled. A certain reservoir tank 10 is arranged.

  The reservoir tank 10 is connected to the piping 12 constituting the piping system so that the coolant L in the tank body 11 can flow in and out, and the piston 13 is always cooled by pushing the piston 13 with the spring 14 from the rear. It has a function of pressurizing the liquid L.

  Further, a strain gauge 15 is affixed to the spring 14 of the tank body 11, and an output of the strain gauge 15 corresponding to the deflection amount of the spring 14 is input to the arithmetic circuit 16. That is, since the position of the piston 13 and the amount of deflection are correlated, it is possible to specify the position of the piston 13 by the output of the strain gauge 15, and by specifying the position of the piston 13, The volume in which the coolant L is stored is specified, and the amount of the coolant L can be calculated by the arithmetic circuit 16 and notified.

  Next, the operation of the present invention will be described with reference to FIG. In the liquid cooling system for aircraft equipment of the present invention, the cooling liquid L circulates through the piping 12 of the piping system to cool the aircraft equipment parts. The volume of the cooling liquid L in the piping system increases or decreases due to expansion and contraction of the cooling liquid L in the piping system due to temperature changes.

  When the volume of the cooling liquid L in the piping system decreases, the cooling liquid L pressurized to the piston 13 pressed by the spring 14 is supplied from the tank body 11 into the piping system to prevent cavitation. Further, when the volume of the cooling liquid L in the piping system increases, the pressure in the piping system increases as the volume increases, and the cooling liquid L pushes the piston 13 and is stored in the reservoir tank body 11. This prevents the leakage of the coolant L and the failure of the equipment. Further, the increase and decrease of the volume of the coolant L accompanying the change of the atmospheric pressure during the operation of the aircraft works similarly.

  On the other hand, over time, the relief function, equipment failure, etc. may cause evaporation, discharge, or leakage of the coolant L, and the amount of liquid in the piping system may decrease. In this case, even if all the coolant L in the tank body 11 is supplied to the pipe 12, there is a concern that the liquid amount of the entire pipe system is insufficient. However, in this embodiment, the arithmetic circuit 16 detects and informs the liquid amount in the tank body 11 based on the output from the strain gauge 15, so that if the liquid amount falls below a preset reference value, the cooling liquid When L is replenished or when the decrease is significant, it also becomes an opportunity to perform maintenance assuming a device failure.

  Further, unlike the prior art, since the indicator fixed to the piston 13 protrudes from the tank body 11 and the position of the piston 13 is not detected, it is not necessary to secure an area outside the tank body 11, and in an aircraft equipped with a large number of devices. The influence on the installation of other equipment can be suppressed.

The figure which showed the reservoir tank in the liquid cooling system for aircraft apparatuses of a present Example. The figure which showed the reservoir tank in the liquid cooling system for the conventional aircraft equipment.

Explanation of symbols

11 Tank body 12 Piping 13 Piston 14 Spring 15 Strain gauge 16 Arithmetic circuit L Coolant

Claims (1)

For aircraft equipment that has a piping system that circulates cooling liquid that is sealed from the atmosphere and a reservoir tank that pressurizes the piston with a spring to pressurize the cooling liquid to the piping system, and supplies and recovers the cooling liquid to the object to be cooled The liquid cooling system includes a strain gauge affixed to the spring, and a calculation unit that calculates the amount of the coolant in the reservoir tank by detecting the position of the piston from the output of the strain gauge. Liquid cooling system for aircraft equipment.

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