CN114237329A - Temperature control system and control method for aircraft solar radiation test - Google Patents
Temperature control system and control method for aircraft solar radiation test Download PDFInfo
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- CN114237329A CN114237329A CN202210028317.0A CN202210028317A CN114237329A CN 114237329 A CN114237329 A CN 114237329A CN 202210028317 A CN202210028317 A CN 202210028317A CN 114237329 A CN114237329 A CN 114237329A
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- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/30—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature
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Abstract
The invention relates to the technical field of airplane testing, in particular to a temperature control system and a temperature control method for an airplane solar radiation test; the control system comprises an environment simulation system and an irradiation system; the irradiation system comprises an irradiation light source lamp array and an irradiation sensor which are positioned in the laboratory, and a control cabinet which is electrically connected with the irradiation light source lamp array and the irradiation sensor; the control method comprises the following steps: s1, calibrating irradiance of the irradiation light source lamp array; s2, calculating the heat load of the irradiation light source; s3, soaking and dehumidifying the base line; s4, starting irradiation light source daily cycle; s5, controlling the temperature; the aircraft solar radiation test temperature control system and the control method provided by the invention have the advantages of high response speed, small temperature overshoot and thermal load interference resistance, and can realize accurate control of the temperature in an aircraft solar radiation-high temperature daily cycle test.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a temperature control system and a temperature control method for an airplane solar radiation test.
Background
The climate test of the airplane in the airplane test engineering is an important ring, and the climate test is mainly used for evaluating the effectiveness of each system of the airplane under various extreme climate environmental conditions and estimating the possible risk level of the airplane; the flight test under the extreme climatic environment condition, the initial stage is finished in a climatic environment laboratory, and the environmental adaptability of the airplane is verified through high-temperature, low-temperature, damp-heat, rain, snow fall, freezing rain, ice accumulation, solar radiation and other climatic tests; the environmental adaptability is the basis for realizing the functions and performance indexes of the airplane and is related to the full-life-cycle service and task completion capability of the airplane;
different from the thermal effect generated by high temperature, the solar radiation thermal effect has directionality and generates thermal gradient, and the gradient is caused by different absorption solar spectrum energy at different positions (such as a light facing surface and a backlight surface) of equipment; when the equipment is affected by non-uniform heating, or the heating magnitude or the heating mechanism caused by solar radiation is unclear, a solar radiation test and a high-temperature storage daily cycle test are jointly carried out, the environment simulated in the laboratory is the comprehensive environment of temperature and irradiance, and the irradiance and the temperature need to be adjusted in a step-by-step matching mode according to an environment spectrum.
Compared with a small and medium-sized solar radiation laboratory with a small scale of a domestic environment simulation system, the solar radiation laboratory has the volume of 100000m3When the climate environment laboratory carries out solar radiation-high temperature daily cycle test on the whole aircraft or large-scale equipment, the circulating air volume reaches 280m3And/s, 347s completes full-space air replacement, and due to the characteristics of overlarge space and large lag of a laboratory, the irradiance of a radiation light source is not timely controlled along with different degrees of heat load interference during the adjustment of an environment spectrum, another key control parameter, namely temperature fluctuation is caused, adverse effects are caused on the solar radiation-high temperature daily cycle test of the whole airplane, and the problem of test misalignment is caused.
Therefore, a temperature control technology for an aircraft solar radiation test is needed to meet the technical requirements of an aircraft solar radiation-high temperature daily cycle test.
Disclosure of Invention
The technical problem solved by the invention is as follows: the airplane solar radiation test temperature control system and the control method thereof have the advantages of quick response, small temperature overshoot and thermal load interference resistance, and can realize accurate control of the temperature in the airplane solar radiation-high temperature daily cycle test.
The technical scheme of the invention is as follows: a temperature control system for an aircraft solar radiation test comprises an environment simulation system and an irradiation system;
the irradiation system comprises an irradiation light source lamp array and an irradiation sensor which are positioned in the laboratory, and a control cabinet which is electrically connected with the irradiation light source lamp array and the irradiation sensor;
the irradiation light source lamp array comprises a plurality of groups of irradiation light sources and execution switches correspondingly connected with the irradiation light sources; the irradiation operating power of the irradiation light source can be adjusted through the control cabinet.
The invention also provides a control method of the aircraft solar radiation test temperature control system, which comprises the following steps:
s1 calibration of irradiance of irradiation light source lamp array
Under the room temperature condition of a climate laboratory, the irradiation light source lamp array, the control cabinet and the irradiation sensor are electrically connected; according to a daily cycle target spectrum of the light source irradiance, adjusting the single light source switch state and the single light source running power in an irradiation light source lamp array step by step, and establishing a single light source switch matrix and a single light source running power matrix of each light source irradiance level; irradiance non-uniformity is no greater than 10%;
s2 calculation of heat load of irradiation light source
Step S1, after the irradiation of the irradiation light source lamp array is calibrated, calculating the heat load of the irradiation light source lamp array during irradiation of each irradiance level according to the operation results of the irradiation light source lamp array executing the single light source switch matrix and the single light source operation power matrix;
s3, base line soaking and dehumidification
The method comprises the following steps that an environment simulation system of a climate laboratory adjusts the indoor temperature to be the baseline environment temperature, the whole airplane is soaked for 10-20 hours, and indoor air is dehumidified during the soaking; the baseline ambient temperature range is +21 ± 3 ℃;
s4, starting irradiation light source daily cycle
Starting the irradiation light source lamp array according to a single light source switch matrix calibrated according to the irradiance of the irradiation light source lamp array, the setting parameters of a single light source running power matrix and the setting parameters of an irradiation degree daily cycle test spectrum; wherein 24h is a cycle period of an irradiation degree daily cycle test spectrum;
s5, temperature control
Setting the target temperature per hour according to the temperature rising and falling rate requirement of the temperature spectrum; the environment simulation system calculates a temperature change value caused by heat load interference of an irradiation light source in a test area, inputs the temperature change value into temperature deviation calculation of the controller, calculates a target temperature value once per minute, offsets the temperature change value caused by the heat load interference, inputs the temperature change value into the environment simulation system, and performs heating or cooling operation.
Further, in step S2, the irradiation time is 1h for each irradiance level; adjusting irradiance and temperature in a step-by-step matching manner in the change of every 1h according to an environment spectrum; the gradient is obvious, the simulation feasibility is high, and the temperature control is convenient.
Furthermore, the environment simulation system comprises a circulating air processing section, a cold and heat carrying section, an air supply section, a solar radiation area and a feedforward-PID control system;
the circulating air treatment section comprises a circulating pipeline, a centrifugal fan, an air valve and a circulating air heat exchanger;
the feedforward-PID control system calculates the target temperature value of each minute in a room according to a formula (1), and calculates the temperature change value caused by heat load interference according to a formula (2);
wherein, TnThe indoor temperature target value at the current moment; t isiIs the initial temperature; t isfIs the final target indoor temperature; t is tcThe adjusting time from the initial temperature to the final target temperature in the room; t is tkIs the adjusted time; t isnThe feedforward-PID control system calculates the opening degrees of the secondary refrigerant liquid return valve and the bypass valve for the input of the feedforward-PID control system, and the environment simulation system automaticallyAdjusting the temperature of the secondary refrigerant at the inlet of the heat exchanger so as to change the temperature of the supplied air;
Tl＝Ql/camf (2)
wherein, TlIs a temperature change value; qlThe solar radiation light source heat load is a test area; c. CaThe specific heat capacity at the current indoor temperature; m isfIs the mass of air flowing through the circulating air heat exchanger per unit time.
The air supply temperature is fed back to the rear end of the heat exchanger of the circulating air processing section, and the quick response can be realized according to the issued target temperature, so that the closed control loop selects the air supply temperature which is closer to the regulating valve and has smaller lag time as a controlled variable, the control channel is short, the lag is small, the control is timely, and the control precision of the air supply temperature can be effectively improved.
Further, the temperature spectrum range in the step S5 is 30-50 ℃; the irradiation condition under the high-temperature weather condition can be simulated in the range, so that the capability of the whole aircraft for resisting the solar radiation heat effect can be accurately verified.
Further, in the step S5, the temperature rise and fall rate is required to be 1-3 ℃/h; the temperature regulation capacity of the climate laboratory can reach 6 ℃/h, the temperature rise and drop rate is required to be 1-3 ℃/h and is smaller than that of the climate environment laboratory, so that the overshoot of temperature control needs to be reduced in the control process, and the target temperature value is gradually approached.
Further, in step S5, a specific method of performing temperature control includes:
the centrifugal fan drives indoor air and dry air processed by the fresh air system to circulate, and the dry air is sucked by the air return port and the fresh air valve and enters the circulating air processing section; the cold-carrying heat-carrying section cools or heats the secondary refrigerant by cooling water or steam, then the secondary refrigerant enters the heat exchanger to exchange heat with air flowing through the circulating air treatment section, the air temperature of the treatment section is treated by adjusting a bypass valve and a liquid return valve of the heat exchanger to change the temperature of the secondary refrigerant at the inlet of the heat exchanger, and the air treated by the cold-carrying heat-carrying section passes through the air supply section and is sent into a climate laboratory by a swirl air inlet; the method can quickly respond and has small overshoot; the capability of the whole aircraft of resisting the solar radiation heat effect can be effectively verified.
Further, in the step S5, the primary cycle of the coolant is switched to the steam plate switch during the temperature rise, and the feedforward-PID control system is based on the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; heating from 32 ℃ to 49 ℃; according to the temperature rising and falling rate requirement of the environment spectrum, the target temperature is converted into a stepped temperature rising curve, and the target temperature value is calculated once per minute and is used as the input of the controller, so that the environment simulation system can respond quickly, and the control precision of the temperature is effectively improved.
Further, in the step S5, the primary circulation of the coolant is switched to the chilled water plate during cooling, and the feedforward-PID control system is based on the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; cooling from 37 ℃ to 32 ℃; the response speed of the environment simulation system is improved, and the control precision of the temperature is effectively improved.
Further, the irradiation intensity of the light source irradiation degree in the daily cycle target spectrum is 0-1120W/m2(ii) a When the irradiation intensity is zero, the night condition is simulated, and the irradiation intensity is 1120W/m2Time, is the maximum irradiation intensity during the day; so as to realize accurate simulation of natural irradiation intensity and improve the true simulation degree of the whole aircraft radiation test.
The invention has the beneficial effects that: the invention provides a temperature control system and a temperature control method for an airplane solar radiation test, which adjust the single light source switch state and the single light source running power in an irradiation light source lamp array step by step according to a daily cycle target spectrum of light source irradiance, and establish a single light source switch matrix and a single light source running power matrix of each light source irradiance level; reducing non-uniformity of irradiance; the temperature change value caused by the heat load is obtained by calculating the heat load generated by the radiation light source, the target temperature value is calculated once per minute by the environment simulation system, and the temperature change value caused by the heat load interference is counteracted, so that the environment simulation system has quick response, small temperature overshoot and thermal load interference resistance, and the accurate control of the temperature and irradiance in the whole aircraft solar radiation test is realized.
Drawings
FIG. 1 is a flow chart of an aircraft solar radiation test temperature control method of the present invention;
FIG. 2 is a light source irradiance daily cycle target spectrum of example 2 of the present invention;
FIG. 3 is a schematic diagram of an environmental simulation process of an aircraft solar radiation-high temperature daily cycle test according to embodiment 2 of the present invention.
Detailed Description
Example 1
A temperature control system for an aircraft solar radiation test comprises an environment simulation system and an irradiation system;
the irradiation system comprises an irradiation light source lamp array and an irradiation sensor which are positioned in the laboratory, and a control cabinet which is electrically connected with the irradiation light source lamp array and the irradiation sensor;
the irradiation light source lamp array comprises a plurality of groups of irradiation light sources and execution switches correspondingly connected with the irradiation light sources; the irradiation operating power of the irradiation light source can be adjusted through the control cabinet.
The environment simulation system comprises a circulating air processing section, a fresh air handling unit, a cold and heat carrying section, an air supply section, a solar radiation area and a feedforward-PID control system; the air outlet of the air supply section is provided with a rotational flow air port;
the circulating air treatment section comprises a circulating pipeline, a centrifugal fan, an air valve and a circulating air heat exchanger;
the circulating air heat exchanger comprises a steam plate exchanger, a cooling water plate exchanger, a bypass valve and a liquid return valve;
it should be noted that, the irradiation light source, the circulating pipeline, the irradiation sensor, the centrifugal fan, the air valve, the circulating air heat exchanger, the air supply section, the cold and heat carrying section, the steam plate exchanger, and the cooling water plate exchanger are all prior art products, and the specific product types can be selected by those skilled in the art according to needs.
Example 2
As shown in fig. 1, the control method of the aircraft solar radiation test temperature control system according to embodiment 1 includes the steps of:
s1 calibration of irradiance of irradiation light source lamp array
Under the room temperature condition of a climate laboratory, the irradiation light source lamp array, the control cabinet and the irradiation sensor are electrically connected; according to a daily cycle target spectrum of the light source irradiance, adjusting the single light source switch state and the single light source running power in an irradiation light source lamp array step by step, and establishing a single light source switch matrix and a single light source running power matrix of each light source irradiance level; irradiance non-uniformity is 7%;
s2 calculation of heat load of irradiation light source
Step S1, after the irradiation of the irradiation light source lamp array is calibrated, calculating the heat load of the irradiation light source lamp array during irradiation of each irradiance level according to the operation results of the irradiation light source lamp array executing the single light source switch matrix and the single light source operation power matrix; the irradiation time of each irradiance level is 1 h;
s3, base line soaking and dehumidification
The environmental simulation system of the climate laboratory adjusts the indoor temperature to the baseline environmental temperature, and the whole aircraft is soaked for 11 hours, and indoor air is dehumidified during the soaking; the baseline ambient temperature range is +18 ℃;
s4, starting irradiation light source daily cycle
Starting the irradiation light source lamp array according to a single light source switch matrix calibrated according to the irradiance of the irradiation light source lamp array, the setting parameters of a single light source running power matrix and the setting parameters of an irradiation degree daily cycle test spectrum; wherein 24h is a cycle period of an irradiation degree daily cycle test spectrum;
s5, temperature control
Setting the target temperature per hour according to the temperature rising and falling rate requirement of the temperature spectrum; the environment simulation system calculates a temperature change value caused by the heat load interference of the irradiation light source in the test area, inputs the temperature change value into the temperature deviation calculation of the controller, calculates a target temperature value once per minute, and inputs the target temperature value into the environment simulation system after offsetting the temperature change value caused by the heat load interference;
then the environment simulation system carries out heating or cooling operation:
the centrifugal fan drives indoor air and dry air processed by the fresh air system to circulate, and the dry air is sucked by the air return port and the fresh air valve and enters the circulating air processing section; the cold-carrying heat-carrying section cools or heats the secondary refrigerant by cooling water or steam, then the secondary refrigerant enters the heat exchanger to exchange heat with air flowing through the circulating air treatment section, the air temperature of the treatment section is treated by adjusting a bypass valve and a liquid return valve of the heat exchanger to change the temperature of the secondary refrigerant at the inlet of the heat exchanger, and the air treated by the cold-carrying heat-carrying section passes through the air supply section and is sent into a climate laboratory by a swirl air inlet;
when the temperature is raised, the primary circulation of the secondary refrigerant is switched into steam plate exchange, and the feedforward-PID control system switches the secondary refrigerant into the steam plate exchange according to the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; heating from 32 ℃ to 49 ℃;
when the temperature is reduced, the primary circulation of the secondary refrigerant is switched into cooling water plate switching, and the feedforward-PID control system switches according to the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; the temperature is reduced from 37 ℃ to 32 ℃.
The feedforward-PID control system calculates the target temperature value of each minute in a room according to a formula (1), and calculates the temperature change value caused by heat load interference according to a formula (2);
wherein, TnThe indoor temperature target value at the current moment; t isiIs the initial temperature; t isfIs the final target indoor temperature; t is tcThe adjusting time from the initial temperature to the final target temperature in the room; t is tkIs the adjusted time; t isnThe feedforward-PID control system calculates the opening degrees of a secondary refrigerant liquid return valve and a bypass valve for the input of the feedforward-PID control system, and the environment simulation system automatically adjusts the temperature of the secondary refrigerant at the inlet of the heat exchanger so as to change the air supply temperature; t isl＝Ql/camf (2)
Wherein, TlIs a temperature change value; qlThe solar radiation light source heat load is a test area; c. CaThe specific heat capacity at the current indoor temperature; m isfIs the mass of air flowing through the circulating air heat exchanger per unit time.
The temperature spectrum range is 30-50 ℃.
The temperature rising and falling speed is required to be 1 ℃/h.
The irradiation intensity in the daily cycle target spectrum of the light source irradiation degree is 0-1120W/m2。
Example 3
The control method of the aircraft solar radiation test temperature control system according to embodiment 1, comprising the steps of:
s1 calibration of irradiance of irradiation light source lamp array
Under the room temperature condition of a climate laboratory, firstly, hoisting an irradiation light source lamp array, and electrically connecting the irradiation light source lamp array, a control cabinet and an irradiation sensor; and the lamp array of the irradiation light source is preliminarily debugged; according to a daily cycle target spectrum of the light source irradiance, adjusting the single light source switch state and the single light source running power in an irradiation light source lamp array step by step, and establishing a single light source switch matrix and a single light source running power matrix of each light source irradiance level; irradiance non-uniformity of 5%;
s2 calculation of heat load of irradiation light source
Step S1, after the irradiation of the irradiation light source lamp array is calibrated, calculating the heat load of the irradiation light source lamp array during irradiation of each irradiance level according to the operation results of the irradiation light source lamp array executing the single light source switch matrix and the single light source operation power matrix; the irradiation time of each irradiance level is 0.5 h;
s3, base line soaking and dehumidification
The environmental simulation system of the climate laboratory adjusts the indoor temperature to the baseline environmental temperature, and the whole aircraft is soaked for 18 hours, and indoor air is dehumidified during the soaking; the baseline ambient temperature range is +24 ℃;
s4, starting irradiation light source daily cycle
Starting the irradiation light source lamp array according to a single light source switch matrix calibrated according to the irradiance of the irradiation light source lamp array, the setting parameters of a single light source running power matrix and the setting parameters of an irradiation degree daily cycle test spectrum; wherein 24h is a cycle period of an irradiation degree daily cycle test spectrum;
s5, temperature control
Setting the target temperature per hour according to the temperature rising and falling rate requirement of the temperature spectrum; the environment simulation system calculates a temperature change value caused by the heat load interference of the irradiation light source in the test area, inputs the temperature change value into the temperature deviation calculation of the controller, calculates a target temperature value once per minute, and inputs the target temperature value into the environment simulation system after offsetting the temperature change value caused by the heat load interference;
then the environment simulation system carries out heating or cooling operation:
the centrifugal fan drives indoor air and dry air processed by the fresh air system to circulate, and the dry air is sucked by the air return port and the fresh air valve and enters the circulating air processing section; the cold-carrying heat-carrying section cools or heats the secondary refrigerant by cooling water or steam, then the secondary refrigerant enters the heat exchanger to exchange heat with air flowing through the circulating air treatment section, the air temperature of the treatment section is treated by adjusting a bypass valve and a liquid return valve of the heat exchanger to change the temperature of the secondary refrigerant at the inlet of the heat exchanger, and the air treated by the cold-carrying heat-carrying section passes through the air supply section and is sent into a climate laboratory by a swirl air inlet;
when the temperature is raised, the primary circulation of the secondary refrigerant is switched into steam plate exchange, and the feedforward-PID control system switches the secondary refrigerant into the steam plate exchange according to the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; heating from 32 ℃ to 49 ℃;
when the temperature is reduced, the primary circulation of the secondary refrigerant is switched into cooling water plate switching, and the feedforward-PID control system switches according to the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; the temperature is reduced from 37 ℃ to 32 ℃.
The feedforward-PID control system calculates the target temperature value of each minute in a room according to a formula (1), and calculates the temperature change value caused by heat load interference according to a formula (2);
wherein, TnThe indoor temperature target value at the current moment; t isiIs the initial temperature; t isfIs the final target indoor temperature; t is tcThe adjusting time from the initial temperature to the final target temperature in the room; t is tkIs the adjusted time; t isnThe feedforward-PID control system calculates the opening degrees of a secondary refrigerant liquid return valve and a bypass valve for the input of the feedforward-PID control system, and the environment simulation system automatically adjusts the temperature of the secondary refrigerant at the inlet of the heat exchanger so as to change the air supply temperature;
Tl＝Ql/camf (2)
wherein, TlIs a temperature change value; qlThe solar radiation light source heat load is a test area; c. CaThe specific heat capacity at the current indoor temperature; m isfIs the mass of air flowing through the circulating air heat exchanger per unit time.
The temperature spectrum range is 30-50 ℃.
The temperature rising and falling speed is required to be 3 ℃/h.
The irradiation intensity in the daily cycle target spectrum of the light source irradiation degree is 0-1120W/m2。
Claims (10)
1. A temperature control system for an aircraft solar radiation test is characterized by comprising an environment simulation system and an irradiation system;
the irradiation system comprises an irradiation light source lamp array and an irradiation sensor which are positioned in the laboratory, and a control cabinet which is electrically connected with the irradiation light source lamp array and the irradiation sensor;
the irradiation light source lamp array comprises a plurality of groups of irradiation light sources and execution switches correspondingly connected with the irradiation light sources; the irradiation operating power of the irradiation light source can be adjusted through the control cabinet.
2. The method for controlling the aircraft solar radiation test temperature control system according to claim 1, characterized by comprising the following steps:
s1 calibration of irradiance of irradiation light source lamp array
Under the room temperature condition of a climate laboratory, the irradiation light source lamp array, the control cabinet and the irradiation sensor are electrically connected; according to a daily cycle target spectrum of the light source irradiance, adjusting the single light source switch state and the single light source running power in an irradiation light source lamp array step by step, and establishing a single light source switch matrix and a single light source running power matrix of each light source irradiance level; irradiance non-uniformity is no greater than 10%;
s2 calculation of heat load of irradiation light source
Step S1, after the irradiation of the irradiation light source lamp array is calibrated, calculating the heat load of the irradiation light source lamp array during irradiation of each irradiance level according to the operation results of the irradiation light source lamp array executing the single light source switch matrix and the single light source operation power matrix;
s3, base line soaking and dehumidification
The method comprises the following steps that an environment simulation system of a climate laboratory adjusts the indoor temperature to be the baseline environment temperature, the whole airplane is soaked for 10-20 hours, and indoor air is dehumidified during the soaking; the baseline ambient temperature range is +21 ± 3 ℃;
s4, starting irradiation light source daily cycle
Starting the irradiation light source lamp array according to a single light source switch matrix calibrated according to the irradiance of the irradiation light source lamp array, the setting parameters of a single light source running power matrix and the setting parameters of an irradiation degree daily cycle test spectrum; wherein 24h is a cycle period of an irradiation degree daily cycle test spectrum;
s5, temperature control
Setting the target temperature per hour according to the temperature rising and falling rate requirement of the temperature spectrum; the environment simulation system calculates a temperature change value caused by heat load interference of an irradiation light source in a test area, inputs the temperature change value into temperature deviation calculation of the controller, calculates a target temperature value once per minute, offsets the temperature change value caused by the heat load interference, inputs the temperature change value into the environment simulation system, and performs heating or cooling operation.
3. The aircraft solar radiation test temperature control method as claimed in claim 2, wherein in the step S2, the irradiation time is 1h for each irradiance level.
4. The aircraft solar radiation test temperature control method according to claim 2, wherein the environment simulation system comprises a circulating air processing section, a cold and heat carrying section, an air supply section, a solar radiation area and a feedforward-PID control system;
the circulating air treatment section comprises a circulating pipeline, a centrifugal fan, an air valve and a circulating air heat exchanger;
the feedforward-PID control system calculates the target temperature value of each minute in a room according to a formula (1), and calculates the temperature change value caused by heat load interference according to a formula (2);
wherein, TnThe indoor temperature target value at the current moment; t isiIs the initial temperature; t isfIs the final target indoor temperature; t is tcThe adjusting time from the initial temperature to the final target temperature in the room; t is tkIs the adjusted time; t isnThe feedforward-PID control system calculates the opening degrees of a secondary refrigerant liquid return valve and a bypass valve for the input of the feedforward-PID control system, and the environment simulation system automatically adjusts the temperature of the secondary refrigerant at the inlet of the heat exchanger so as to change the air supply temperature;
Tl＝Ql/camf (2)
wherein, TlIs a temperature change value; qlThe solar radiation light source heat load is a test area; c. CaThe specific heat capacity at the current indoor temperature; m isfIs the mass of air flowing through the circulating air heat exchanger per unit time.
5. The aircraft solar radiation test temperature control method according to claim 4, wherein the temperature spectrum in the step S5 is in a range of 30-50 ℃.
6. The aircraft solar radiation test temperature control method as claimed in claim 4, wherein the temperature rise and fall rate in the step S5 is required to be 1-3 ℃/h.
7. The aircraft solar radiation test temperature control method as claimed in claim 4, wherein the step S5 is a specific method for controlling the temperature:
the centrifugal fan drives indoor air and dry air processed by the fresh air system to circulate, and the dry air is sucked by the air return port and the fresh air valve and enters the circulating air processing section; the cold-carrying heat-carrying section cools or heats the secondary refrigerant by cooling water or steam, then the secondary refrigerant enters the heat exchanger to exchange heat with air flowing through the circulating air treatment section, the air temperature of the treatment section is treated by adjusting a bypass valve and a liquid return valve of the heat exchanger to change the temperature of the secondary refrigerant at the inlet of the heat exchanger, and the air treated by the cold-carrying heat-carrying section passes through the air supply section and is sent into a climate laboratory by a swirl air inlet.
8. The aircraft solar radiation test temperature control method as claimed in claim 7, wherein in step S5, the primary circulation of the coolant is switched to steam plate exchange during heating, and the feedforward-PID control system is based on the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; the temperature is raised from 32 ℃ to 49 ℃.
9. The aircraft solar radiation test temperature control method as claimed in claim 7, wherein in step S5, the primary circulation of coolant is switched to cooling water plate exchange during cooling, and the feedforward-PID control system is based on the input TnThe calculation result automatically adjusts the opening degrees of a bypass valve and a liquid return valve of the heat exchanger in the secondary circulation; the temperature is reduced from 37 ℃ to 32 ℃.
10. The aircraft solar radiation test temperature control method as claimed in claim 1, wherein the irradiation intensity in the light source irradiation degree daily cycle target spectrum is 0-1120W/m2。
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| CN114706295A (en) * | 2022-06-07 | 2022-07-05 | 中国飞机强度研究所 | Method for controlling fast time-varying thermal load in thermal test for testing strength of aerospace plane |
| CN114879781A (en) * | 2022-06-23 | 2022-08-09 | 中国联合网络通信集团有限公司 | Temperature control method, device and storage medium |
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