CN112340070A - Design method of ground test system of high-stability temperature measurement and control system - Google Patents
Design method of ground test system of high-stability temperature measurement and control system Download PDFInfo
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- CN112340070A CN112340070A CN202011053254.1A CN202011053254A CN112340070A CN 112340070 A CN112340070 A CN 112340070A CN 202011053254 A CN202011053254 A CN 202011053254A CN 112340070 A CN112340070 A CN 112340070A
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
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Abstract
The invention relates to a design method of a ground test system of a high-stability temperature measurement and control system, which is used for establishing a ground detection test system aiming at the high-stability temperature measurement and control system in a satellite. The method specifically comprises three stages, namely a first stage, a temperature measurement circuit noise test: aiming at a single board or a single machine of the temperature measuring circuit, the temperature measuring noise test is carried out by matching with a standard resistor and is used for calibrating the noise level of the temperature measuring circuit; and in the second stage, testing the noise of the temperature measuring assembly: after the noise level test of the temperature measuring circuit is finished, carrying out the noise test of the temperature measuring assembly for calibrating the noise level of the whole temperature measuring system; and in the third stage, the temperature measurement and control component ground simulation test: after the first two stages of tests are completed, a temperature measurement and control component ground simulation test is carried out, and the whole noise test of a high-stability temperature measurement and control system is carried out under the simulation of a real environment. The invention realizes the ground test of the temperature measurement and control system with high stability.
Description
Technical Field
The invention belongs to the technical field of spacecraft thermal control, and relates to a design method of a ground test system of a high-stability temperature measurement and control system.
Background
The high-stability thermal control technology is based on the specific load requirement and the engineering practical application of a gravitational wave space detection technology test satellite, and aims at the problem that the existing thermal control technology is difficult to realize the frequency of 0.1mHz to 0.1Hz and 1mK/Hz1/2The novel thermal control technology is provided by the internal temperature control precision. The function of the temperature control device is to meet or exceed the temperature stability control requirement of a temperature control target through a high-precision temperature measurement technology, a multi-stage heat insulation passive thermal stability technology and a PID (proportion integration differentiation) refined temperature control algorithm so as to meet the function of testing satellite loads by a gravitational wave space detection technology.
In the satellite in-orbit process, the satellite load detection performance is affected by thermal deformation caused by temperature change, and in order to ensure the stability of the load performance, a stable temperature environment needs to be constructed, which needs to accurately measure the temperature of load equipment firstly.
The temperature measurement component, the temperature control component and the controlled object (namely the load equipment) form a high-stability temperature control system. The temperature measuring component is used for measuring temperature and comprises a temperature measuring circuit and a temperature measuring element, wherein the noise of the temperature measuring element is low in magnitude; the temperature control component is used for outputting temperature control power and controlling a controlled object to achieve a stable temperature requirement and comprises a temperature control circuit, a temperature control heating loop and a temperature control algorithm; the controlled object is typically, but not limited to, a laser interferometer and an accelerometer.
Considering the ground verification requirements of the whole temperature measurement and control system and the thermal control design, a high-stability temperature measurement and control system ground test system needs to be established for verification. If the ground test system cannot realize high-stability measurement and calibration, the feasibility of the design of the temperature measurement and control system and the thermal control system cannot be judged.
Disclosure of Invention
Based on the background, in order to detect the temperature measurement performance of the high-stability temperature measurement and control system on the ground, the invention establishes a set of design method of the ground test system of the high-stability temperature measurement and control system, which is specifically divided into three stages, namely a first stage, a temperature measurement circuit noise test: considering that the noise of a temperature measuring element in the temperature measuring component is low level, firstly, under the condition of a single temperature measuring circuit board or a single temperature measuring circuit, the temperature measuring noise is tested by matching with a standard resistor and is used for calibrating the noise level of the temperature measuring circuit; and in the second stage, testing the noise of the temperature measuring assembly: after the noise level test of the temperature measuring circuit is finished, carrying out the noise test of the temperature measuring assembly for calibrating the noise level of the whole temperature measuring system, and specifically calibrating by adopting a temperature measuring circuit single board or a single machine to be matched with a four-wire platinum resistor or a thermistor; and in the third stage, the temperature measurement and control component ground simulation test: after the first two stages of tests are completed, a temperature measurement and control component ground simulation test is carried out, and the whole noise test of a high-stability temperature measurement and control system is carried out under the simulation of a real environment.
The invention firstly carries out the noise test of the temperature measuring circuit, then carries out the noise test of the temperature measuring component, and finally completes the ground simulation test of the temperature measuring and controlling component so as to obtain the noise chain on the whole temperature measuring and controlling chain and the noise relation of the temperature measuring and controlling chain. The method is realized by the following technical scheme:
the first step is as follows: connecting the standard resistor as a substitute temperature measuring element to a temperature measuring circuit single board or a single machine, and placing the assembly in a stable temperature testing environment;
the second step is that: operating the temperature measuring component for a sufficient time under the conditions to obtain a noise test result of the temperature measuring circuit;
the third step: a four-wire platinum resistor or other star temperature measuring elements are used as temperature measuring elements and connected to a temperature measuring circuit single board or a single machine, the temperature measuring elements are placed in a stable temperature testing environment, the stable temperature environment requires that the stability is at least one order of magnitude higher than the noise of the temperature measuring circuit, and a constant temperature water tank is generally used as the environment;
the fourth step: and operating the temperature measuring component for a sufficient time under the conditions to obtain a noise test result of the temperature measuring circuit component.
The fifth step: in the vacuum simulation chamber, external heat flow simulation equipment such as an infrared cage, a heater, a solar lamp array and the like is matched with temperature measuring elements such as a thermocouple, a thermistor, a platinum resistor and the like to form an external heat flow simulation environment; a heater is matched with temperature measuring elements such as a thermocouple, a thermistor, a platinum resistor and the like to form an in-satellite equipment heat consumption simulation environment; the vacuum test chamber can simulate the vacuum degree and the deep cooling background of a cold space and provide a space radiation environment as real as possible; in this step, the simulation of the external heat flow and the internal heat source is required to reflect the working change amplitude of the rail;
and a sixth step: and the temperature measurement component and the temperature control component are used in or outside the vacuum test chamber to carry out high-stability temperature control on the controlled object, so that a noise test result of the high-stability temperature control system is obtained.
Advantageous effects
The ground test and calibration system of the high-stability temperature measurement and control system is established, the contents and the test method of the subsequent ground test of the high-stability temperature measurement and control system of the aerospace system are determined, and the ground test of the high-stability temperature measurement and control system is realized.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Fig. 2 is a schematic structural diagram of a gravitational wave detection satellite.
FIG. 3 is a time domain curve of a single-board noise test of a high-stability temperature measurement circuit board.
FIG. 4 is a time domain plot of a noise test of a high stability temperature measurement circuit assembly.
Fig. 5 is a schematic view of the state of the vacuum simulator and the simulation capsule.
Fig. 6 is a model of a simulated capsule and internal loads.
FIG. 7 is a time domain graph of a ground simulation test of a high-stability temperature measurement and control system.
FIG. 8 is a PSD curve of a single board noise test of a high-stability temperature measurement circuit board.
FIG. 9 is a PSD curve for noise test of the high stability temperature measurement circuit assembly.
FIG. 10 is a PSD curve of a ground simulation test of a high-stability temperature measurement and control system.
Detailed Description
The invention and the implementation effect are described in detail below by referring to the drawings and the embodiment.
In the embodiment, a pilot test satellite of a gravitational wave application technology is taken as a simulation research object, the orbit height of the satellite is 630Km, the time of a descending intersection point is 10:30, and the orbit is a sun synchronous orbit, as shown in FIG. 2. The controlled objects of the satellite are a laser interferometer and an accelerometer, and the temperature control stability is required to be better than +/-50 mk. In order to realize high-stability temperature control, the temperature measuring element adopts a four-wire platinum resistor, and adopts high-stability temperature measuring and controlling equipment, specifically comprises 1 temperature measuring part and 2 temperature control PCB boards, and is finally installed in a stack assembly in a satellite.
In order to obtain the overall temperature measurement and control noise level of the temperature measurement single plate, the temperature measurement component and the high-stability temperature measurement and control system, a ground equivalent simulation test of the temperature measurement single plate, the standard resistor, the temperature measurement component (a temperature measurement device is a four-wire platinum resistor) and the overall high-stability temperature measurement and control system is respectively carried out. And analyzing the data of the result in a time domain and a frequency domain to obtain the temperature measurement and control noise under respective levels.
The following steps are given to the present embodiment:
the first step is as follows: the high-stability temperature measuring circuit board is matched with a standard resistor to be used as a measuring element for testing.
The temperature stability of the resistance value of the standard resistor is +/-50 multiplied by 10-6omega/K. The test is carried out by selecting equipment in a normal pressure thermal cycle test, the normal pressure thermal cycle test is in a normal pressure environment, the temperature is circulated at high and low temperatures, the total number of the cycles is 12.5, the temperature fluctuation amplitude of a temperature balance section is +/-2K, and the resistance value fluctuation quantity corresponding to a standard resistor is +/-0.1 m omega.
The power supply current of the temperature measuring circuit is 0.1mV, and the measurement voltage fluctuation caused by +/-2K temperature change is 0.01 mu V which is far less than the minimum resolution voltage of the measuring circuit of the temperature measuring circuit, namely 3.9 mu V (corresponding to 1mK), so the influence of the standard resistor on the temperature measuring circuit can be ignored.
The second step is that: the test lasted 3.5 hours and resulted in an equilibrium period temperature profile as shown in figure 3.
The third step: the test was carried out using a high-stability temperature measuring circuit board in combination with a four-wire platinum resistor as a measuring element.
4 platinum resistor components are selected in the test process, welded on the same plug, inserted on a high-precision temperature measurement acquisition board after the temperature of a constant-temperature water tank (temperature control precision +/-1 mK) reaches a specified test temperature, and the data of an acquisition loop are recorded. This analysis was performed on the data of only the first platinum resistor.
The test environment in the test is a constant temperature water tank, and the target temperature of the constant temperature water tank in the test process is 20 ℃.
The measured temperature of the high-precision temperature measuring and controlling system is compared with the measured temperature of the constant-temperature water tank, so that the static deviation can be eliminated according to the measured value; the dynamic deviation of the water tank is +/-0.2 mK and is 1 order of magnitude higher than the temperature measurement precision of the high-stability temperature measurement and control system, so that the dynamic deviation can be ignored.
The fourth step: the test was continued for 1.5 hours, and a typical temperature profile for the equilibration period was obtained as shown in FIG. 4.
The fifth step: the high-stability temperature-measuring circuit board is matched with a four-wire platinum resistor to serve as a measuring element, and the high-stability temperature-controlling circuit board is matched with a heater to perform a ground equivalent simulation test.
The temperature control test of the high-precision temperature measurement and control system is carried out in a vacuum simulator, a cabin is vertically parked in a vacuum simulation chamber through a parking support vehicle, and a support is fixed at the bottom of a vacuum tank. The cabin is placed in a posture that the + Z axis points to the top of the vacuum tank and the + X axis points to the side gate of the vacuum tank. The cabin is built by aluminum alloy plates, and the size of the cabin is 0.76m multiplied by 0.55m multiplied by 0.3m after installation is finished.
The interior of the cabin bottom plate and the load equipment mounting plate are installed in a heat insulation way; the outer part of the test fixture support is installed in a heat insulation way, and is required to be butted with the fixture support at four corners of the bottom plate and far away from the installation position of the load equipment installation plate as far as possible; and meanwhile, a heat insulation pad (polyimide or glass fiber reinforced plastic) with the thickness not less than 30mm is required to be installed with the tool support in a heat insulation mode, a heat insulation screw sleeve is also required to be used by a fastening screw, and the outer surface of the cylindrical surface of the heat insulation pad is required to be coated with a 5-unit multi-layer heat insulation assembly. In addition, the installation position of the tool support uses a heater to track and control the temperature of the installation position of the cabin bottom plate.
The outside of all cabin plates of the cabin is subjected to temperature control by using heaters so as to simulate the temperature boundary of the cabin; sticking a black carburized polyimide film on the boundary of the cabin plate in the cabin; the cabin plates are connected by screws.
The load equipment independent radiating surface is arranged outside the cabin, the size of the load equipment independent radiating surface is 0.5m multiplied by 0.2m multiplied by 0.003m, and a heater is used for temperature control and is used for simulating the temperature level of the on-orbit independent radiating surface; one side of the heat dissipation surface, which is adhered to the heater, is required to be provided with a heat pipe, the other end of the heat pipe is connected to the load equipment mounting plate, and the other side of the heat dissipation surface is adhered to a black carburized polyimide film. As shown in fig. 5 and 6
Whether the external heat flow simulation of the boundary condition is accurate or not is crucial to the test, the real-time external heat flow reaching the surface of the satellite is simulated by the heating sheet in the test, and the external heat flow is loaded by square waves according to the temperature control time of 3 min.
And a sixth step: the test was continued for 4 days and a typical temperature profile for the equilibration period was obtained as shown in figure 7.
The seventh step: and (3) performing time domain analysis on results of each stage to obtain the noise level of the high-stability temperature measurement circuit board, the high-stability temperature measurement assembly and the high-stability temperature measurement and control system in the time domain, as shown in table 1.
TABLE 1
Eighth step: the results of each stage are subjected to fourier transform, and the noise level of the high-stability temperature measurement circuit board, the high-stability temperature measurement component and the high-stability temperature measurement and control system in the frequency domain is obtained according to the power spectral density definition of the invention, as shown in fig. 8 to 10.
The above description is only an example of the present invention, and is not intended to limit the present invention; other equivalent variations and modifications within the scope of the features of the present invention, which are obvious to those skilled in the art, are also included within the scope of the present invention.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (8)
1. A design method of a ground test system of a high-stability temperature measurement and control system is used for designing the ground test system for realizing the noise test of a satellite temperature measurement and control system in a gravitational wave space detection technology test, the high-stability temperature measurement and control system comprises a temperature measurement component, a temperature control component and a controlled object, and is characterized in that data analysis is required to be carried out under the condition of a large sample, and the design method comprises the following steps:
the first stage, the noise test of the temperature measuring circuit is used for calibrating the noise level of the temperature measuring circuit;
and in the second stage, testing the noise of the temperature measuring assembly: after the noise level test of the temperature measuring circuit is finished, the temperature measuring circuit and the temperature measuring element are combined into a temperature measuring assembly, and the noise test of the temperature measuring assembly is carried out for calibrating the noise level of the whole temperature measuring system;
and in the third stage, the temperature measurement and control component ground simulation test: and after the first two stages of tests are finished, carrying out a temperature measurement and control component ground simulation test for carrying out the whole noise test of a high-stability temperature measurement and control system under a simulated real environment.
2. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 1, wherein the first stage is as follows:
step 1.1: building a temperature measuring circuit single board or a measuring circuit of a single machine state combined standard resistor, and building a stable temperature testing environment;
step 1.2: and acquiring temperature time domain data with the standard resistor as a temperature measuring element, and acquiring a noise test result of the temperature measuring circuit.
3. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 2, wherein the test environment in step 1.1 is a stand-alone thermal vacuum test environment.
4. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 1, wherein the second stage is as follows:
step 2.1: a temperature measuring circuit single board or a measuring circuit of a satellite temperature measuring element in a single state is built, temperature measuring precision calibration of a temperature measuring component is carried out in a constant temperature water tank, and the temperature control precision of the constant temperature water tank is required to be at least one order of magnitude higher than the temperature measuring precision of a measured object;
step 2.2: and acquiring temperature time domain data of the temperature measurement component, thereby acquiring temperature measurement precision calibration and noise test results of the temperature measurement component.
5. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 4, wherein the satellite temperature measurement element in the step 2.1 is a four-wire platinum resistor or a thermistor.
6. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 1, wherein the third stage is as follows:
step 3.1: building an outer heat flow simulation environment and an inner heat source simulation environment in a vacuum test room, and building a ground equivalent simulation test environment, wherein the outer heat flow simulation environment is used for simulating transient change of heat flow outside an on-orbit, and the inner heat source simulation environment is used for simulating an in-satellite energy environment and reflecting work transient change of on-orbit equipment;
step 3.2: the temperature measuring component and the temperature control component are used in or outside the vacuum test chamber to carry out high-stability temperature control on the controlled object so as to obtain temperature time domain data of the ground test of the high-stability temperature measurement and control system, and further obtain a noise test result of the ground test of the high-stability temperature measurement and control system.
7. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 6, characterized in that: 3.1, the external heat flow simulation environment is formed by matching external heat flow simulation equipment with a temperature measuring element; the internal heat source simulation environment is formed by matching a simulation heat source with a temperature measuring element.
8. The design method of the ground test system of the high-stability temperature measurement and control system according to claim 1, wherein the large sample conditions are as follows: greater than a minimum number of samples, wherein the minimum number of samples is defined as follows:
nmin＝Tperiod×fs
wherein T isperiodThe satellite working cycle is the orbit cycle for the sun synchronous orbit; f. ofsSampling frequency for temperature measurement component and requirement fs≥1。
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