CN-122009501-A - Temperature control method of aviation power device and liquid cooling heat dissipation loop thereof

CN122009501ACN 122009501 ACN122009501 ACN 122009501ACN-122009501-A

Abstract

The temperature control method comprises the steps of obtaining an inlet temperature change rate of the liquid cooling heat dissipation loop, determining that the power device is in a first working condition and determines first target thermal power when the inlet temperature change rate is positive and the absolute value of the inlet temperature change rate is larger than a first change rate threshold value, determining that the power device is in a second working condition and determines second target thermal power when the inlet temperature change rate is positive and the absolute value of the inlet temperature change rate is smaller than or equal to the first change rate threshold value, determining that the power device is in a third working condition and determines third target thermal power when the inlet temperature change rate is negative and the absolute value of the inlet temperature change rate is larger than the second change rate threshold value, determining the target rotational speed of a circulating pump of the liquid cooling heat dissipation loop based on the corresponding target thermal power, and controlling the circulating pump to operate at the target rotational speed. The heat dissipation efficiency and the operation stability of the aviation power plant are improved through the method.

Inventors

LIAN HONGKUI
Mou Kesai
NIU YANJIE
DING TING
LI XINYUAN
ZHANG YAGUANG
WANG YIZHE

Assignees

北京热数科技有限公司

Dates

Publication Date: 20260512
Application Date: 20260330

Claims (10)

1. The temperature control method of the aviation power plant is characterized in that the aviation power plant is connected in series on a liquid cooling heat dissipation loop, and the temperature control method comprises the following steps: acquiring the inlet temperature change rate of the liquid cooling heat dissipation loop; under the condition that the inlet temperature change rate is positive and the absolute value of the inlet temperature change rate is larger than a first change rate threshold value, determining that the power device is in a first working condition, and determining a corresponding first target thermal power; under the condition that the inlet temperature change rate is positive and the absolute value is smaller than or equal to a first change rate threshold value, determining that the power device is in a second working condition, and determining a corresponding second target thermal power; Under the condition that the inlet temperature change rate is negative and the absolute value is larger than a second change rate threshold, determining that the power device is in a third working condition, and determining a corresponding third target thermal power; Determining a target rotating speed of a circulating pump of the corresponding liquid cooling heat dissipation loop based on the first target heat power, the second target heat power or the third target heat power, wherein the first target heat power is larger than the second target heat power, and the second target heat power is larger than the third target heat power; and controlling a circulating pump of the liquid cooling heat dissipation loop to run at the target rotating speed, so as to realize temperature control of the aviation power device.
2. The temperature control method according to claim 1, wherein the first working condition includes a take-off working condition, and the value range of the first target thermal power is 8kw to 11kw.
3. The temperature control method according to claim 1, wherein the second working condition includes a maneuvering working condition, and the value range of the second target thermal power is 5.94kw to 6.3kw.
4. The temperature control method according to claim 1, wherein the third working condition includes a sliding working condition, and the third target thermal power has a value range of 3.5kw to 4.5kw.
5. The temperature control method according to claim 1, wherein the first change rate threshold has a value ranging from 0.1 ℃ to 0.3 ℃ per minute, and the second change rate threshold has a value ranging from 0.1 ℃ per minute to 0.2 ℃ per minute.
6. The temperature control method according to any one of claims 1 to 5, wherein the determining a target rotational speed of a circulation pump of the corresponding liquid-cooled heat-radiating circuit based on the first target thermal power, the second target thermal power, or the third target thermal power includes: Determining a target volume flow of a working medium of the corresponding liquid cooling heat dissipation loop by combining an inlet temperature and an outlet temperature of the liquid cooling heat dissipation loop based on the first target heat power, the second target heat power or the third target heat power; and determining the target rotating speed of the circulating pump based on the target volume flow of the working medium.
7. The method of claim 6, wherein the calculation formula of the target volumetric flow rate of the working fluid includes: ; Wherein V is the volume flow of the working medium, Q is the target thermal power, C p is the specific heat capacity of the working medium, ρ is the density of the working medium, T in is the inlet temperature of the liquid cooling heat dissipation loop, and T out is the outlet temperature of the liquid cooling heat dissipation loop.
8. A liquid-cooled heat-dissipating loop for an aerodynamic device for implementing the temperature control method of any one of claims 1-7, the liquid-cooled heat-dissipating loop comprising: The driving module comprises a liquid storage device, a flow sensor, a circulating pump and a pressure sensor, wherein the outlet end of the liquid storage device is communicated with the inlet end of the circulating pump, the flow sensor is arranged at the outlet end of the liquid storage device, and the pressure sensor is arranged at the outlet end of the circulating pump; The heat source module comprises a power device, wherein the power device comprises a motor and a motor controller, an inlet end of the motor is communicated with an outlet end of the circulating pump, and an outlet end of the motor is communicated with an inlet end of the motor controller; the cold source module comprises a radiator, wherein the inlet end of the radiator is communicated with the outlet end of the motor controller; the inlet end of the filter is communicated with the outlet end of the radiator, and the outlet end of the filter is communicated with the inlet end of the liquid reservoir; The adding and discharging valve is arranged between the driving module and the heat source module; Working medium flows out from the outlet end of the liquid storage device, flows back to the inlet end of the liquid storage device through the flow sensor, the circulating pump, the pressure sensor, the adding and discharging valve, the motor controller and the filter.
9. The liquid-cooled heat dissipation circuit of claim 8, further comprising a first temperature sensor and a second temperature sensor, wherein the first temperature sensor is disposed at an inlet end of the circulation pump for collecting an inlet temperature of the liquid-cooled heat dissipation circuit, and the second temperature sensor is disposed at an outlet end of the motor controller for collecting an outlet temperature of the liquid-cooled heat dissipation circuit.
10. The liquid-cooled heat dissipation circuit of claim 8, wherein the working fluid comprises a 50% glycol aqueous solution.

Description

Temperature control method of aviation power device and liquid cooling heat dissipation loop thereof Technical Field The disclosure relates to the technical field of aviation thermal control, in particular to a temperature control method of an aviation power device and a liquid cooling heat dissipation loop thereof. Background In an aviation scene, the stable operation of an aviation power plant directly determines the flight safety, and the temperature control is a key precondition for guaranteeing the long-term reliable operation of the aviation power plant. Aviation power device, like motor, motor controller etc. can continuously produce the heat in the course of working, if the heat can't in time dispel, can lead to part performance decay, life-span to shorten, causes the potential safety hazard even. At present, the heat dissipation and temperature control of the aviation power device mainly depend on an air cooling or traditional liquid cooling scheme, wherein a traditional air cooling heat dissipation system consists of a heat dissipation fan, heat dissipation fins and a flow guide air duct, the heat dissipation efficiency is limited, the heat dissipation device cannot adapt to the heating fluctuation demand of the aviation power device, the traditional liquid cooling heat dissipation scheme mostly adopts fixed rotation speed control, and the heat dissipation capacity is not matched with the actual heating demand of the aviation power device, so that the parts are overheated or the energy consumption is too high. Disclosure of Invention The temperature control method and the liquid cooling heat dissipation loop of the aviation power device are provided aiming at the problems existing in the prior art, the problem that the heat dissipation capacity of the existing air cooling or traditional liquid cooling scheme is not matched with the actual heating requirement can be solved, and the heat dissipation efficiency and the operation stability of the aviation power device are improved. In order to achieve the above purpose, the technical scheme adopted in the present disclosure is as follows: According to the temperature control method of the aviation power device, the aviation power device is connected in series to a liquid cooling heat dissipation loop, the temperature control method comprises the steps of obtaining an inlet temperature change rate of the liquid cooling heat dissipation loop, determining that the power device is in a first working condition and determines corresponding first target heat power under the condition that the inlet temperature change rate is positive and the absolute value of the inlet temperature change rate is larger than a first change rate threshold value, determining that the power device is in a second working condition and determines corresponding second target heat power under the condition that the inlet temperature change rate is positive and the absolute value of the inlet temperature change rate is smaller than or equal to the first change rate threshold value, determining that the power device is in a third working condition and determines corresponding third target heat power under the condition that the inlet temperature change rate is negative and the absolute value of the inlet temperature change rate is larger than the second change rate threshold value, and determining the target rotating speed of a circulating pump of the corresponding liquid cooling heat dissipation loop based on the first target heat power, the second target heat power or the third target heat power, wherein the first target heat power is larger than the second target heat power and the second target heat power is larger than the third target heat power, and controlling the circulating pump of the liquid cooling heat dissipation loop to operate according to the target heat dissipation loop. In one possible implementation, the first working condition includes a take-off working condition, and the value range of the first target thermal power is 8 kW-11 kW. In one possible implementation, the second working condition includes a motorized working condition, and the second target thermal power has a value in a range of 5.94kw to 6.3kw. In one possible implementation, the third working condition includes a sliding working condition, and the third target thermal power has a value ranging from 3.5kw to 4.5kw. In one possible implementation, the first rate of change threshold is in the range of 0.1-0.3 ℃ per minute and the second rate of change threshold is in the range of 0.1-0.2 ℃ per minute. In one possible implementation, the target rotational speed of the circulating pump of the corresponding liquid cooling heat dissipation loop is determined based on the first target thermal power, the second target thermal power or the third target thermal power, and the target rotational speed of the circulating pump is determined based on the target thermal power, the second target thermal power or the