Space environment thermal test satellite temperature regulation and control method and system
By using multi-stage error interval control and anti-saturation integral PID algorithm temperature control methods in space environment thermal tests of spacecraft such as satellites, the problems of unstable and low efficiency of temperature control in traditional control methods are solved, and fast and stable temperature control is achieved.
Patent Information
- Application Number
- CN202411947526.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-27
- Publication Date
- 2025-05-16
AI Technical Summary
In the space environment thermal test of spacecraft such as satellites, traditional PID control or manual control is difficult to automatically adjust according to changes in the controlled object parameters, resulting in overshoot and oscillation in the temperature control process, low efficiency and poor consistency.
A satellite temperature regulation method for thermal test space is adopted. By setting the target temperature value and temperature change speed, automatic temperature circulation control is performed, the heat flow output is controlled using multi-stage error intervals, and the anti-saturation integral PID algorithm is activated when the target temperature is reached to achieve stable temperature control.
This method can adapt to the physical characteristics of different test products, quickly reach the target temperature without overshooting, improves the control efficiency of the test process and reduces the need for manual intervention.
Smart Images
Figure CN120010580A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of spacecraft thermal testing, and in particular to a temperature control method and system for a space environment thermal testing satellite. Background Art
[0002] The satellite space environment thermal test is an environmental adaptability and environmental reliability test. It is the most important part of space environment engineering and is used to verify the ability of products to complete specified functions under specified conditions and within a specified time. One of the main purposes of satellite thermal balance testing is to obtain temperature data of satellites under extreme high temperature and extreme low temperature conditions. The high temperature, low temperature, heating and cooling rates, and hot and cold soak cycles of thermal vacuum tests are the conditions for obtaining temperature data of satellites under high and low temperature conditions. The infrared simulation equipment and power supply system are controlled by temperature measurement and control software to simulate the external heat flow state, and the satellite temperature data is obtained through data acquisition equipment.
[0003] When satellites and other spacecraft conduct thermal balance and thermal vacuum tests of aerospace products in a vacuum and low-temperature space environment, the temperature measurement and control software usually uses traditional PID control or manual control. This method has the following problems. First, due to the differences in test products and test conditions, the characteristic parameters of the controlled objects such as the thermal load or surface characteristics of the test products are different. Conventional PID control cannot automatically adjust its own parameter values according to the changes in the parameters of the controlled objects. The control coefficients corresponding to the PID parameters of each test are also difficult to determine at one time. In addition, due to the hysteresis and nonlinearity of the temperature control system itself, the product temperature control process will have large overshoot and oscillation. This is unacceptable for satellites and other spacecraft that strictly control the product temperature range. Second, the temperature control adjustment process is long during the test, and personnel often need to intervene manually based on experience. The temperature control process is inefficient and the consistency of the temperature control results is poor. Summary of the invention
[0004] The present invention provides a temperature control method and system for a space environment thermal test satellite, which are intended to adapt to the physical characteristics of different test products and control the temperature change rate during the heating and cooling stages so that the target temperature can be reached quickly without overshoot, thereby improving the control efficiency of the test process.
[0005] The present invention provides a temperature control method for a space environment thermal test satellite, comprising the following steps: S1. Set the target temperature values of the temperature measurement points corresponding to each heating zone of the spacecraft, including the high temperature working condition temperature and the low temperature working condition temperature, and set the temperature holding time of each working condition, set the temperature change speed, and set the number of automatic cycles of the high temperature working condition and the low temperature working condition; S2. Execute automatic temperature cycle control; S3. The spacecraft controls the power output value of the heater to increase the temperature at a preset temperature change rate, determines that the temperature of the corresponding measuring point of each heating zone reaches the high temperature working temperature, and starts high temperature maintenance and timing; S4. After the timing is over, the spacecraft starts to cool down according to the preset temperature change rate by controlling the power output value of the heater, determines that the temperature of the corresponding measuring point of each heating zone reaches the low temperature working temperature, and starts low temperature maintenance and timing; S5. After the timing ends, steps S3 and S4 are repeated until the number of automatic cycles reaches the preset number of cycles.
[0006] As a further improvement of the present invention, the high temperature working condition temperature includes a thermal equilibrium high temperature working condition temperature and a thermal vacuum high temperature working condition temperature, and the low temperature working condition temperature includes a thermal equilibrium low temperature working condition temperature and a thermal vacuum low temperature working condition temperature.
[0007] As a further improvement of the present invention, the temperature measuring point corresponding to the heating zone is a temperature control point in the corresponding heating zone, or an average value of multiple temperature control points in the corresponding heating zone.
[0008] As a further improvement of the present invention, in steps S3 and S4, timing starts when all the temperature measuring points corresponding to the heating zones reach the target temperature value.
[0009] As a further improvement of the present invention, in step S2, the automatic temperature cycle control may be executed by scheduled execution or immediately.
[0010] As a further improvement of the present invention, in steps S3 and S4, the control process of controlling the power output of the heater so that the temperature value reaches the target temperature and stabilizes includes the following steps: a1. According to the target temperature value of the spacecraft in a vacuum low-temperature environment, the target temperature value between the low-temperature working condition and the high-temperature working condition is divided into multiple temperature intervals, and the initial current output value is preset for each temperature interval; multiple temperature error intervals are set in the temperature interval, and the temperature adjustment speed, temperature adjustment speed error, current adjustment step, and initial current bias are preset in each temperature error interval; a2. Start temperature sampling to monitor the current temperature values of each component of the spacecraft in a vacuum low temperature environment; a3. Set the target temperature value, and output the initial current setting value in the set temperature range; a4. Check the error range between the current temperature value and the target temperature value, set the output temperature control speed value according to the temperature error interval, calculate the current temperature control speed, if the temperature control speed is less than the temperature control speed value set in the temperature error interval, the current output value increases according to the current adjustment step length, if the current temperature control speed is greater than the temperature control speed value set in the temperature error interval, the current output value decreases according to the current adjustment step length, if the current temperature control speed is within the temperature control speed range set in the temperature error interval, the current output value remains unchanged; a5. After the current temperature changes according to the set temperature adjustment speed, jump to the next temperature error interval and repeat step a4 until the current temperature error is reduced to the error start range of PID control; a6. Start PID control, assign PID integral accumulation to the initial current setting value, and use the anti-saturation integral PID algorithm to limit the integral accumulation value to not exceed the maximum current value or the minimum current value. By judging the range of the control amount, dynamically adjust the accumulation of PID integral.
[0011] As a further improvement of the present invention, after step S5 is completed, the following step is further included: S6. The power output value of the heater is kept unchanged, and a prompt indicating that the automatic temperature cycle is completed is displayed.
[0012] The present invention also provides a temperature control system for a space environment thermal test satellite, which is used to execute the temperature control method for the space environment thermal test satellite, including a data acquisition instrument, a temperature sensor, a heater, a programmable power supply, and a heat flow measurement and control unit. The data acquisition instrument, temperature sensor, heater, programmable power supply, and heat flow measurement and control unit are all installed in the temperature control system of the test satellite of the spacecraft; the data acquisition instrument is used to collect data from the temperature sensor, the temperature sensor is used to sense the high temperature working temperature and the low temperature working temperature, the heater is used to output power according to a preset temperature change speed, the programmable power supply is used to output voltage and current to the heater, and the heat flow measurement and control unit controls the data acquisition instrument to collect temperature sensor data and controls the programmable power supply to output voltage and current data to the heater, and collects data including time, working temperature, temperature change speed, and number of cycles.
[0013] The beneficial effects of the present invention are as follows: the temperature control method of the present invention is suitable for temperature control of different thermal capacity test products. When the temperature change speed is greater than or less than the preset temperature change speed, the output heat flow value can be automatically adjusted to control the temperature change speed within the preset threshold range. The temperature control method has adjustable heating and cooling rates; by presetting the temperature adjustment process and the number of cycles, automatic switching control of the temperature cycle is realized, thereby reducing the degree of frequent manual temperature control intervention by test personnel. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the automatic temperature cycle program of the temperature control method of the present invention; Figure 2 A schematic diagram of a temperature control variation curve of the temperature control method of the present invention; Figure 3 It is a control algorithm flow chart of the temperature control method of the present invention; Figure 4 A table showing the correspondence between each temperature range and the initial current output value in the present invention; Figure 5 A corresponding table of temperature adjustment speed, temperature adjustment speed error, current adjustment step length, and initial current bias is preset in each temperature error interval for the present invention. DETAILED DESCRIPTION
[0015] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.
[0016] In order to realize the function of automatic control and adjustment of spacecraft temperature in thermal balance and thermal vacuum test, the present invention proposes a temperature control method and system, which has the advantages of preset control process, adjustable control rate, automatic conversion of control mode, etc., and can be applied to temperature control of different satellite products, and has strong adaptability to control objects.
[0017] Specifically, Figure 1 As shown, a temperature control method for a space environment thermal test satellite of the present invention comprises the following steps: S1. Set the target temperature values of the temperature measurement points corresponding to each heating zone of the spacecraft, including the high temperature working condition temperature and the low temperature working condition temperature, and set the temperature holding time of each working condition, set the temperature change speed, and set the number of automatic cycles of the high temperature working condition and the low temperature working condition.
[0018] The high temperature working condition temperature includes the thermal equilibrium high temperature working condition temperature and the thermal vacuum high temperature working condition temperature, and the low temperature working condition temperature includes the thermal equilibrium low temperature working condition temperature and the thermal vacuum low temperature working condition temperature.
[0019] The temperature measuring point corresponding to the heating zone is a temperature control point in the corresponding heating zone, or an average value of multiple temperature control points in the corresponding heating zone.
[0020] S2. Execute automatic temperature cycle control.
[0021] The execution modes of automatic temperature cycle control include scheduled execution or immediate execution.
[0022] S3. The spacecraft controls the power output value of the heater, increases the temperature at a preset temperature change rate, determines that the temperature of the corresponding measuring point in each heating zone reaches the high-temperature operating temperature, and starts high-temperature maintenance and timing.
[0023] S4. After the timing is over, the spacecraft starts to cool down according to the preset temperature change rate by controlling the power output value of the heater, determines that the temperature of the corresponding measuring point of each heating zone reaches the low-temperature operating temperature, and starts low-temperature maintenance and timing.
[0024] The timing starts when all the corresponding temperature measuring points in each heating zone reach the target temperature value.
[0025] S5. After the timing ends, steps S3 and S4 are repeated until the number of automatic cycles reaches the preset number of cycles.
[0026] S6. Keep the power output value of the heater unchanged and indicate that the automatic temperature cycle has ended.
[0027] like Figure 2 and Figure 3 As shown, in steps S3 and S4, the power output of the heater is controlled so that the temperature value reaches the target temperature and stabilizes. A staged control method is adopted. In temperature control stage 0, the current assignment is initialized. In temperature control stage 1, the current parameter is fuzzy controlled. In control stage 2, PID control is started. The control process includes the following steps: Start temperature control stage 0: a1. According to the target temperature value of the spacecraft in a vacuum low temperature environment, the target temperature value of the low temperature working condition to the high temperature working condition is divided into a temperature interval of 10°C every -100°C~+100°C, and the initial current output value is preset for each temperature interval, such as Figure 4 As shown; eighteen temperature error intervals are set in the temperature interval, and the absolute value of the error interval range gradually decreases from 30℃ to 0.2℃. In each temperature error interval, the temperature adjustment speed, temperature adjustment speed error, current adjustment step, and initial current bias are preset, such as Figure 5 shown.
[0028] a2. Start temperature sampling and monitor the current temperature value T of each component of the spacecraft in a vacuum low temperature environment now .
[0029] a3. Set the target temperature value, and output the initial current setting value in the set temperature range; determine the current temperature value T now In the temperature range, select the appropriate initial current setting value I set ; According to the target temperature value T set , calculate the current target temperature difference delta T now =T set -T now , determine the temperature error area where the current target temperature difference is located, and select the appropriate initial current setting value I set The current bias setting value delta I set The initial setting value of output current is I set =Iset +delta I set .
[0030] Start temperature control phase 1: a4. Check the error range between the current temperature value and the target temperature value, and set the output temperature adjustment speed value according to the temperature error range; according to the current target temperature difference delta T now The temperature error range is set according to the temperature error range. set Control; calculate the current temperature adjustment speed VT now =T now -T old , T old Indicates the temperature value collected in the last cycle.
[0031] If the temperature control speed is less than the temperature control speed value set in the temperature error interval, the current output value increases according to the current adjustment step. If the current temperature control speed is greater than the temperature control speed value set in the temperature error interval, the current output value decreases according to the current adjustment step. If the current temperature control speed is within the temperature control speed range set in the temperature error interval, the current output value remains unchanged.
[0032] Based on the current temperature control speed VT now Set the temperature control speed VT set The deviation is adjusted, and the current output value is set to the initial current setting value I set , when VT now <VT set -delta VT set When set Increase, I set =I set +delta I set ; When VT now >VT set +delta VT set When set Reduce, I set =I set -delta I set ; When VT set -delta VT set <VT now <VT set +deltaVT set When the temperature adjustment speed is appropriate set Remain unchanged. delta VT set Indicates the set temperature adjustment speed difference, delta I set Indicates the current regulation step value.
[0033] a5. After the current temperature changes according to the set temperature adjustment speed, jump to the next temperature error interval and repeat step a4 until the current temperature error is reduced to the error start range of PID control.
[0034] When the current target temperature difference is within the error range of the startup PID control, -0.5℃<delta T now <+0.5℃, start control stage 2: a6. Start PID control, and assign PID integral accumulation to the initial current setting value I set , through the anti-saturation integral PID algorithm, the integral accumulation value is limited to not exceed the maximum current value I max Or minimum current value I min By judging the range of the controlled quantity, the accumulation of PID integral is adjusted dynamically, thereby improving the control stability and control accuracy.
[0035] The present invention also provides a temperature control system for a space environment thermal test satellite, which is used to execute a temperature control method for a space environment thermal test satellite, including a data acquisition instrument, a temperature sensor, a heater, a programmable power supply, and a heat flow measurement and control unit. The data acquisition instrument, the temperature sensor, the heater, the programmable power supply, and the heat flow measurement and control unit are all installed in the temperature control system of the test satellite of the spacecraft; the data acquisition instrument is used to collect data from the temperature sensor, the temperature sensor is used to sense the high-temperature working temperature and the low-temperature working temperature, the heater is used to output power according to a preset temperature change speed, the programmable power supply is used to output voltage and current to the heater, and the heat flow measurement and control unit controls the data acquisition instrument to collect temperature sensor data and controls the programmable power supply to output voltage and current data to the heater, and collects data including time, working temperature, temperature change speed, and number of cycles.
[0036] The space environment thermal test satellite temperature control method of the present invention has the following advantages: (1) The temperature control method of the present invention is suitable for temperature control of different heat capacity test products. When the temperature change speed is greater than or less than the preset temperature change speed, the output heat flow value can be automatically adjusted to control the temperature change speed within the preset threshold range. The temperature control method has a setting temperature rise and fall rate.
[0037] (2) The temperature control method of the present invention controls the heat flow output by a multi-level error interval. After the product temperature reaches the error range of the target temperature value, the anti-saturation integral PID algorithm is started to reduce temperature overshoot and oscillation, thereby improving the temperature control stability.
[0038] (3) The temperature control method of the present invention presets the temperature control process and the number of cycles to achieve automatic switching control of the temperature cycle, thereby reducing the degree of frequent manual temperature control intervention by test personnel.
[0039] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the scope of protection of the present invention.
Claims
1. A method for controlling the temperature of a space environment thermal test satellite, characterized in that: The following steps are involved: S1. Set the target temperature values of the temperature measurement points corresponding to each heating zone of the spacecraft, including the high temperature working condition temperature and the low temperature working condition temperature, and set the temperature holding time of each working condition, set the temperature change speed, and set the number of automatic cycles of the high temperature working condition and the low temperature working condition; S2. Execute automatic temperature cycle control; S3. The spacecraft controls the power output value of the heater to increase the temperature at a preset temperature change rate, determines that the temperature of the corresponding measuring point of each heating zone reaches the high temperature working temperature, and starts high temperature maintenance and timing; S4. After the timing is over, the spacecraft starts to cool down according to the preset temperature change rate by controlling the power output value of the heater, determines that the temperature of the corresponding measuring point of each heating zone reaches the low temperature working temperature, and starts low temperature maintenance and timing; S5. After the timing ends, steps S3 and S4 are repeated until the number of automatic cycles reaches the preset number of cycles.
2. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: The high temperature working condition temperature includes the thermal equilibrium high temperature working condition temperature and the thermal vacuum high temperature working condition temperature, and the low temperature working condition temperature includes the thermal equilibrium low temperature working condition temperature and the thermal vacuum low temperature working condition temperature.
3. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: The temperature measurement point corresponding to the heating zone is a temperature control point in the corresponding heating zone, or an average value of multiple temperature control points in the corresponding heating zone.
4. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: In the steps S3 and S4, the timing starts when all the temperature measuring points corresponding to the heating zones reach the target temperature value.
5. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: In step S2, the automatic temperature cycle control may be executed by scheduled timing or immediately.
6. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: In the steps S3 and S4, the control process of controlling the power output of the heater so that the temperature value reaches the target temperature and stabilizes includes the following steps: a1. According to the target temperature value of the spacecraft in a vacuum low-temperature environment, the target temperature value between the low-temperature working condition and the high-temperature working condition is divided into multiple temperature intervals, and the initial current output value is preset for each temperature interval; multiple temperature error intervals are set in the temperature interval, and the temperature adjustment speed, temperature adjustment speed error, current adjustment step, and initial current bias are preset in each temperature error interval; a2. Start temperature sampling to monitor the current temperature values of each component of the spacecraft in a vacuum low temperature environment; a3. Set the target temperature value, and output the initial current setting value in the set temperature range; a4. Check the error range between the current temperature value and the target temperature value, set the output temperature control speed value according to the temperature error interval, calculate the current temperature control speed, if the temperature control speed is less than the temperature control speed value set in the temperature error interval, the current output value increases according to the current adjustment step length, if the current temperature control speed is greater than the temperature control speed value set in the temperature error interval, the current output value decreases according to the current adjustment step length, if the current temperature control speed is within the temperature control speed range set in the temperature error interval, the current output value remains unchanged; a5. After the current temperature changes according to the set temperature adjustment speed, jump to the next temperature error interval and repeat step a4 until the current temperature error is reduced to the error start range of PID control; a6. Start PID control, assign PID integral accumulation to the initial current setting value, and use the anti-saturation integral PID algorithm to limit the integral accumulation value to not exceed the maximum current value or the minimum current value. By judging the range of the control amount, dynamically adjust the accumulation of PID integral.
7. The temperature control method for a space environment thermal test satellite according to claim 1, characterized in that: After step S5 is completed, the following steps are also included: S6. Keep the power output value of the heater unchanged and indicate that the automatic temperature cycle has ended.
8. A space environment thermal test satellite temperature control system, used to execute the space environment thermal test satellite temperature control method according to any one of claims 1 to 7, characterized in that: It includes a data acquisition instrument, a temperature sensor, a heater, a programmable power supply, and a heat flow measurement and control unit, which are all installed in the temperature control system of the test satellite of the spacecraft; the data acquisition instrument is used to collect data from the temperature sensor, the temperature sensor is used to sense the high-temperature working temperature and the low-temperature working temperature, the heater is used to output power according to a preset temperature change speed, the programmable power supply is used to output voltage and current to the heater, and the heat flow measurement and control unit controls the data acquisition instrument to collect temperature sensor data, controls the programmable power supply to output voltage and current data to the heater, and collects data including time, working temperature, temperature change speed, and number of cycles.