CN111498146A - Thermal control system and method for detecting and verifying satellite by near-earth orbit gravitational wave - Google Patents
Thermal control system and method for detecting and verifying satellite by near-earth orbit gravitational wave Download PDFInfo
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Abstract
The invention provides a thermal control system and a method for a near-earth orbit gravitational wave detection verification satellite.A primary thermal control module comprises a plurality of cabin plates, and a load is surrounded at the center and sealed to form a load cabin; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources; the secondary thermal control module comprises an automatic temperature control unit, detects the temperature of the load cabin, sends the temperature of the load cabin to the thermal control main processor, and controls the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin by adopting a PID algorithm so as to form a constant temperature cage type heating area when the load cabin works; the three-level thermal control module comprises a compensation module fixed on the load, a heat insulation assembly wrapping the load and the compensation module, and a temperature measurement unit, wherein the temperature measurement unit detects the temperature of the load and sends the temperature of the load to the thermal control main processor, and the temperature of the compensation module is controlled to be adjusted by adopting a PID algorithm according to the temperature of the load, so that the temperature of the load is kept uniform at all positions during working.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a thermal control system and method for a near-earth orbit gravitational wave detection verification satellite.
Background
The invention is applied to gravitational wave detection satellites in the near-earth orbit. The detection and accurate measurement of the gravitational wave provide a brand-new important window for observing and recognizing the universe different from the electromagnetic wave, and the nature of the gravitational wave is prompted by accurately checking the Einstein generalized relativity theory, so that a plurality of new mysteries of the universe structure and the evolution process can be revealed. The gravitational wave detection plan of China is divided into three steps, and a Taiji plan is drawn up, wherein the Taiji plan I is a first technical verification star of Taiji, which is a Chinese space gravitational wave plan determined by a space science strategic leading science and technology special item of Chinese academy of sciences, and aims to carry out space experimental verification on part of key technologies in advance.
The high-precision high-stability thermal control index of the load system of 'Tai Chi I' is higher in requirement, the load subsystem mainly comprises an inter-satellite laser interference ranging system and a non-towing system, wherein the laser interference ranging system has high requirement on thermal deformation, so that the requirement that the temperature stability index of a core load is T +/-0.1K/1000 s is provided; the non-dragging system is controlled by micro-thrust, so that the pressure change of the pipeline is strict, the pressure influence caused by temperature becomes important constraint, and the system puts forward the requirement of target temperature T +/-3K/1000 s. Therefore, the highest stability index in the project of 'tai chi one' is that the temperature controlled by thermal control is at a certain specific temperature T in the process of working the load for 1000s, and the fluctuation of the temperature controlled temperature is better than 0.1K.
Therefore, a high-precision and high-stability thermal control system needs to be designed for the gravitational wave detection satellite.
Disclosure of Invention
The invention aims to provide a thermal control system and a thermal control method for a near-earth orbit gravitational wave detection verification satellite, so as to realize a high-precision and high-stability thermal control system required by the gravitational wave detection satellite.
In order to solve the technical problem, the invention provides a thermal control system for a near-earth orbit gravitational wave detection verification satellite, wherein the gravitational wave detection satellite comprises a load and a platform, and the load and the thermal control system are positioned in the platform; the thermal control system comprises:
a primary thermal control module comprising a plurality of deck plates configured to enclose the load centrally and closed to form a load compartment; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources;
a secondary thermal control module comprising an automatic temperature control unit configured to detect a temperature of the load compartment and send the temperature of the load compartment to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin, so that the load cabin forms a constant-temperature cage type heating area when in load work;
the three-level thermal control module comprises a compensation module fixed on the load, a heat insulation assembly wrapping the load and the compensation module, and a temperature measurement unit, wherein the temperature measurement unit is configured to detect the temperature of the load and send the temperature of the load to the thermal control main processor; and
and the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load so as to keep the temperature of the load uniform at all places during work.
Optionally, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the temperature of the load cabin during load operation requires that the stability is better than 0.1K/1000s, and the actually obtained temperature stability is better than 5mK/1000 s during the orbit load operation.
Optionally, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the plate material of the load compartment is a honeycomb structure plate compounded with a reinforced heat exchange coating.
Optionally, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the heat insulation gasket is made of glass fiber reinforced plastic, the heat insulation gasket is a square sheet with a side length of 15mm and a thickness of 3mm, and the heat conductivity coefficient of the heat insulation gasket is 0.40w/(m · k);
the heat insulation assembly comprises 10 layers of composite materials, wherein each layer of composite material is formed by superposing a terylene net towel and an aluminized film and superposing polyimide films on the upper surface and the lower surface of the terylene net towel, the thickness of the heat insulation assembly is smaller than 5mm, and the equivalent heat conductivity coefficient of the heat insulation assembly is 0.001.
Optionally, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the number of the deck boards is 6, and the deck boards form a hexahedron;
the heat insulation gasket is pasted on the boundary coupling surface of the load cabin, and the multilayer heat insulation assembly is coated on the outer surface of the load cabin.
Optionally, in the thermal control system for detecting and verifying a satellite by using a near-earth orbit gravitational wave, the automatic temperature control unit includes a heating wire and a temperature measuring element, wherein:
the heating wires are fixed on the inner surface of the load cabin and are covered by the reinforced heat exchange coating, the plurality of heating wires on each cabin plate are distributed in parallel, and the distance between every two heating wires is 2 cm;
the temperature measuring elements are fixed in gaps among the heating wires and are covered by the enhanced heat exchange coating, and the temperature measuring elements are uniformly distributed on all the cabin plates;
the heating wires are configured to cause the load compartment to form a constant temperature cage heating zone during load operation, and the temperature sensing element is configured to sense the temperature of the load compartment.
Optionally, in the thermal control system for the near-earth orbit gravitational wave detection verification satellite, the automatic temperature control unit further includes a temperature measurement signal processing circuit, the temperature measurement element is a temperature measurement resistor, the temperature measurement signal processing circuit includes four outgoing lines, two of the outgoing lines provide a constant voltage at two ends of the temperature measurement resistor, the other two outgoing lines provide a current flowing through the temperature measurement resistor to the temperature measurement signal processing circuit, two of the four outgoing lines form a twisted pair, and a shielding layer covers the twisted pair; the automatic temperature control unit further comprises an active heating loop, the active heating loop adopts a four-wire system, and the active heating loop comprises a fuse loop.
Optionally, in the thermal control system for detecting and verifying a satellite by using a near-earth orbit gravitational wave, the thermal control total processor includes a data acquisition unit, and the number of acquisition bits of the data acquisition unit is 32 bits;
the temperature measurement signal processing circuit provides the current of the temperature measurement resistor to the data acquisition unit, and the data acquisition unit forms a temperature measurement value according to the current of the temperature measurement resistor and sends the temperature measurement value to the thermal control main processor.
Optionally, in the thermal control system for detecting and verifying the satellite by using the near-earth orbit gravitational wave, the temperature measurement signal processing circuit is powered by an electrical connector, the electrical connector takes electricity from the satellite platform, and the electrical connector is coated by a copper foil.
The invention also provides a thermal control method for the low earth orbit gravitational wave detection verification satellite, wherein a load and thermal control system of the gravitational wave detection satellite is arranged in the platform, and the method is characterized by comprising the following steps:
enclosing the load in the center by a plurality of cabin plates of the primary thermal control module and sealing to form a load cabin; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources;
detecting the temperature of the load cabin by an automatic temperature control unit of the secondary thermal control module, and sending the temperature of the load cabin to a thermal control main processor; the thermal control main processor adopts a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin, so that a constant temperature cage type heating area is formed when the load cabin works; and
fixing a compensation module of a three-level thermal control module on the load, wrapping the load and the compensation module by adopting a multilayer heat insulation assembly of the three-level thermal control module, detecting the temperature of the load by a temperature measurement unit of the three-level thermal control module, and sending the temperature of the load to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in work.
In the thermal control system and the method for the near-earth orbit gravitational wave detection verification satellite, a load is surrounded and sealed in the center through a cabin plate of a primary thermal control module to form a load cabin, a heat insulation gasket and/or a multilayer heat insulation assembly are/is arranged inside and/or outside the load cabin to isolate the load from other heat sources, an automatic temperature control unit of a secondary thermal control module detects the temperature of the load cabin, a thermal control total processor controls the automatic temperature control unit to regulate the temperature according to the temperature of the load cabin by adopting a PID algorithm so as to enable the load cabin to form a constant temperature heating area when the load works, a temperature measurement unit of a tertiary thermal control module detects the temperature of the load, the thermal control total processor controls a compensation module to regulate the temperature according to the temperature of the load by adopting the PID algorithm so as to enable the temperature of each part of the load to be kept uniform when the load works, and the index requirement of a satellite load subsystem of a 'Taiji I' satellite is, an effective thermal control scheme is designed, and a high-precision control index of a temperature stability index +/-0.005K is realized by means of three-stage temperature control, so that reference is provided for a subsequent high-precision high-stability thermal control technology.
Drawings
FIG. 1 is a schematic diagram of a thermal control method for a low earth orbit gravitational wave detection satellite according to an embodiment of the present invention;
FIG. 2 is a schematic view of a load compartment of a thermal control system for a low earth orbit gravitational wave detection verification satellite in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of an automatic temperature control unit of a thermal control system for a low earth orbit gravitational wave detection verification satellite according to an embodiment of the present invention;
FIG. 4 is a schematic structural design diagram of a "constant temperature cage" thermal control product according to an embodiment of the present invention;
FIG. 5 is a graphical illustration of an on-track stability temperature indicator in accordance with an embodiment of the present invention;
shown in the figure: 10-a load compartment; 20-heating wires; 30-a temperature measuring element; 40-heat exchange enhancing coating (load compartment); 41-heat transfer enhancement coating (load); 50-a deck plate; 60-insulation assembly (load compartment); 61-insulation assembly (load); 62-a heat insulating spacer; 63-heaters.
Detailed Description
The thermal control system and method for detecting and verifying a satellite by using a gravitational wave in a near earth orbit according to the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The core idea of the invention is to provide a thermal control system and a method for detecting and verifying a satellite by using gravitational wave in a near-earth orbit so as to realize a high-precision and high-stability thermal control system required by the gravitational wave detection satellite.
In order to realize the idea, the invention provides a thermal control system and a method for a near-earth orbit gravitational wave detection verification satellite, wherein the gravitational wave detection satellite comprises a load and a platform, and the load and the thermal control system are positioned in the platform; the thermal control system comprises a first-level thermal control module, a second-level thermal control module, a third-level thermal control module and a thermal control main processor, wherein: the primary thermal control module comprises a plurality of deck plates configured to enclose the load centrally and closed to form a load compartment; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources; the secondary thermal control module comprises an automatic temperature control unit, and the automatic temperature control unit is configured to detect the temperature of the load compartment and send the temperature of the load compartment to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin, so that the load cabin forms a constant-temperature cage type heating area when in load work; the three-level thermal control module comprises a compensation module fixed on the load, a heat insulation assembly wrapping the load and the compensation module, and a temperature measurement unit, wherein the temperature measurement unit is configured to detect the temperature of the load and send the temperature of the load to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in work.
< example one >
The present embodiment provides a thermal control system for a low earth orbit gravitational wave detection verification satellite, as shown in fig. 1, where the gravitational wave detection satellite includes a load and a platform, and the load and the thermal control system are located inside the platform; the thermal control system comprises a first-level thermal control module, a second-level thermal control module, a third-level thermal control module and a thermal control main processor, wherein: as shown in fig. 2, the primary thermal control module comprises a plurality of deck boards 50, the deck boards 50 being configured to enclose the load centrally and closed to form a load compartment 10; as shown in fig. 4, heat insulating spacers and/or multi-layer heat insulating assemblies 60 are disposed inside and/or outside the load compartment 10 to insulate the load from other heat sources; the secondary thermal control module comprises an automatic temperature control unit configured to detect the temperature of the load compartment 10 and send the temperature of the load compartment 10 to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load compartment 10, so that the load compartment 10 forms a constant-temperature cage type heating area when the load works; the three-level thermal control module comprises a compensation module fixed on the load, a heat insulation assembly 60 wrapping the load and the compensation module, and a temperature measurement unit, wherein the temperature measurement unit is configured to detect the temperature of the load and send the temperature of the load to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in work.
Specifically, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the temperature of the load cabin 10 during load operation requires that the stability is better than 0.1K/1000 seconds, and the actually obtained temperature stability during the orbital load operation is better than 5mK/1000 seconds. The material of the deck plate 50 of the load compartment 10 is a honeycomb-structured plate compounded with a reinforced heat exchange coating. The heat insulation gasket is made of glass fiber reinforced plastics, the heat insulation gasket is a square sheet with the side length of 15mm and the thickness of 3mm, and the heat conductivity coefficient of the heat insulation gasket is 0.40 w/(m.k); the heat insulation assembly comprises 10 layers of composite materials, wherein each layer of composite material is formed by superposing a terylene net towel and an aluminized film and superposing polyimide films on the upper surface and the lower surface of the terylene net towel, the thickness of the heat insulation assembly is smaller than 5mm, and the equivalent heat conductivity coefficient of the heat insulation assembly is 0.001. The number of the deck boards 50 is 6, and the deck boards 50 form a hexahedron; the heat insulating gasket is adhered to the boundary coupling surface of the load compartment 10, and the multi-layer heat insulating assembly 60 is coated on the outer surface of the load compartment 10.
As shown in fig. 3, in the thermal control system for a low earth orbit gravitational wave detection verification satellite, the automatic temperature control unit includes a heating wire 20 and a temperature measuring element 30, wherein: the heating wires 20 are fixed on the inner surface of the load compartment 10 and are covered by a heat transfer enhancement coating 40 (such as black paint), a plurality of heating wires 20 are distributed in parallel on each compartment plate 50, and the distance between every two heating wires 20 is 2 cm; the temperature measuring elements 30 are fixed in the gaps between the heating wires 20 and are covered by the reinforced heat exchange coating 40, and the temperature measuring elements 30 are uniformly arranged on each cabin plate 50; the heating wires 20 are configured to form a thermostatic cage heating zone for the load compartment 10 during load operation, and the temperature sensing elements 30 are configured to sense the temperature of the load compartment 10. The automatic temperature control unit further comprises a temperature measurement signal processing circuit, the temperature measurement element 30 is a temperature measurement resistor, the temperature measurement signal processing circuit comprises four outgoing lines, two outgoing lines provide constant voltage at two ends of the temperature measurement resistor, and the other two outgoing lines provide current flowing through the temperature measurement resistor to the temperature measurement signal processing circuit; the four outgoing lines form a twisted pair in pairs, and a shielding layer is adopted to cover the twisted pair; the automatic temperature control unit further comprises an active heating loop, the active heating loop adopts a four-wire system, and the active heating loop comprises a fuse loop.
In addition, in the thermal control system for the low earth orbit gravitational wave detection verification satellite, the thermal control total processor comprises a data acquisition unit, and the acquisition number of the data acquisition unit is 32 bits; the temperature measurement signal processing circuit provides the current of the temperature measurement resistor to the data acquisition unit, and the data acquisition unit forms a temperature measurement value according to the current of the temperature measurement resistor and sends the temperature measurement value to the thermal control main processor. The temperature measurement signal processing circuit is powered by an electric connector, the electric connector obtains electricity from the satellite platform, and the electric connector is wrapped by a copper foil.
In summary, the above embodiments have described in detail different configurations of the thermal control system for the low earth orbit gravitational wave detection verification satellite, and it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of protection of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
< example two >
The embodiment provides a thermal control method for a low earth orbit gravitational wave detection verification satellite, wherein a load of the gravitational wave detection satellite and a thermal control system are installed inside a platform; the load is surrounded in the center and closed by a plurality of deck plates 50 of the primary thermal control module to form a load compartment 10; arranging insulating spacers and/or multi-layer insulating assemblies 60 inside and/or outside the load compartment 10 to insulate the load from other heat sources; an automatic temperature control unit of the secondary thermal control module detects the temperature of the load compartment 10 and sends the temperature of the load compartment 10 to a thermal control main processor; the thermal control main processor adopts a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load compartment 10, so that a constant-temperature cage type heating area is formed when the load compartment 10 works under load; fixing a compensation module of a three-level thermal control module on the load, wrapping the load and the compensation module by adopting a multilayer heat insulation assembly 60 of the three-level thermal control module, detecting the temperature of the load by a temperature measurement unit of the three-level thermal control module, and sending the temperature of the load to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in work.
In the thermal control system and method for the near-earth orbit gravitational wave detection verification satellite provided by the invention, a load (namely a load body) is surrounded and sealed in the center through a cabin plate 50 of a primary thermal control module to form a load cabin 10, a heat insulation gasket and/or a multi-layer heat insulation assembly 60 is/are arranged inside and/or outside the load cabin 10 to isolate the load from other heat sources, an automatic temperature control unit of a secondary thermal control module detects the temperature of the load cabin 10, a thermal control total processor controls the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin 10 by adopting a PID algorithm so as to enable the load cabin 10 to form a constant temperature cage type heating area when the load works, a temperature measurement unit of a third thermal control module detects the temperature of the load, the thermal control total processor controls a compensation module to adjust the temperature according to the temperature of the load by adopting the PID algorithm so as to enable the temperature of all parts of the load to be kept, the index requirements of the satellite load subsystem of 'Tai Chi I' are met, an effective thermal control scheme is designed, a high-precision control index with a temperature stability index of +/-0.005K is achieved through a three-stage temperature control means, and reference is provided for a subsequent high-precision high-stability thermal control technology.
Aiming at the high index requirement of the load, the thermal control is based on the design concept of a constant temperature cage, and a three-level temperature control method is adopted to control the load temperature within the mk-level high stability index range.
Because the heat capacity of the load is large and the temperature index is high, the thermal control adopts a multi-stage temperature control method, such as a three-stage temperature control method with one-stage, two-stage and three-stage compensation as shown in fig. 1. Considering that the load is a core unit for completing the satellite mission, the "primary temperature control" method adopted by the thermal control is to arrange the load unit inside the satellite at the initial stage of the satellite layout, seal the load unit by 6 deck boards 50, and reduce the external thermal interference to the minimum by an effective heat insulation (multi-layer heat insulation assembly 60) means. In order to ensure that the load works at a certain T temperature value, the thermal control adopts 'secondary temperature control' active heating compensation temperature control.
During the operation of the rail, 6 cabin plates 50 are subjected to active PID closed-loop temperature control, as shown in FIG. 2, a constant-temperature cage type heating area is formed when the closed cabin works under load, so that the space environment of the load single machine is controlled in an environment of 0.1K; and finally, three-level temperature control is carried out, namely passive and automatic temperature control of the load body is carried out, on one hand, the load body is subjected to active heating compensation design through thermal control, on the other hand, the multilayer heat insulation assembly 60 is coated, so that the influence of the external environment on the load body is reduced, and the stability of the working temperature of the load is ensured to be within 0.1K through two temperature control means. For example, fig. 1 is a technical guide diagram of three-stage temperature control of the thermal control scheme.
In the design of the scheme of the invention, the temperature control object is the last stage of three-stage temperature control, and as shown in fig. 4, the cross-sectional view of the temperature control object in the satellite layout in the designed on-orbit working state is shown. The contact boundary of the core load is a heat insulation gasket 61, the load body (i.e. load) is a small interval surrounding the periphery of the core load, the visible interface of the core load and the load body is thermal radiation, the inner surface of the load body is a reinforced heat exchange coating 41, the outer surface of the load body is a multi-layer heat insulation assembly 61, and a heat insulation gasket 62 is adopted between the load bodies and exchanges heat with other parts of the satellite for thermal radiation.
From the thermal model state of the core load, a steady state energy conservation equilibrium equation is established as follows.
Q0＝cmΔT(1)
Q0＝Q1+Q2+Q3(2)
In formula (1), Q0 represents the energy change of the core load; c represents the specific heat capacity of the controlled object, and the change of the thermal property of the load material in the project in the working temperature interval can be basically ignored and considered as a constant; m represents the mass of a controlled object, is the inherent property of a material, is consistent with the temperature characteristic of heat capacity, can be ignored and is considered as a constant; Δ T represents a temperature change. The temperature change is therefore dependent on the energy change absorbed by the core load body.
In the formula (2), Q1 represents an internal heat source of the core load; q2 represents the conductive heat exchange of the core load with the load mass; q3 represents the radiative exchange of the core load with the load body. As can be seen from the equation, if the Q0 variation is required to be minimal, only the sum of the variations of Q1, Q2 and Q3 is required to be minimal.
In the thermal control method of the gravitational wave detection satellite, Q1 is 0, Q2 is an adjustable design term, and Q3 is a variable term. To minimize the variation in Q2, the present invention employs a low thermal conductivity thermal spacer to reduce the effects of heat leakage due to "thermal conduction". Q3 is the maximum heat flow fluctuation term to which the core load is subjected, and the fluctuation source is the load fluctuation generated by the active heater during temperature control, which affects the thermal fluctuation of the core load in the form of infrared radiation. In order to reduce the fluctuation of the part, the thermal control adopts the means that on one hand, the load fluctuation of the heater 63 is arranged on the outer surface of the load body, and then the two-stage transmission of longitudinal thermal resistance is carried out, so that the small fluctuation of the load body at a certain temperature is ensured, and on the other hand, the interior of the load body is covered by the reinforced heat exchange coating 41 (black paint or high-emission coating) so as to achieve the homogenization of the temperature field in the load body, and further achieve the minimization of the infrared radiation fluctuation of the whole core load.
Analysis shows that the more uniform the temperature field inside the load body is, the better the temperature stability of the core load is, and the smaller the temperature fluctuation of the load body is, the better the temperature stability of the core load is, so that the two stabilities are well controlled, and the high-precision temperature control can be achieved.
In order to realize high-precision and high-stability temperature indexes, the invention carries out principle and technical level evaluation on the thermal control scheme, and in the scheme realization process, on one hand, the selection of the thermal control product is strictly screened and applied, on the other hand, the thermal implementation of the thermal control product is strictly restricted, and simultaneously, the temperature controller is adopted to carry out temperature data acquisition and temperature control on the thermal control product. Three key (temperature measurement, thermal implementation of a multi-stage temperature control scheme, temperature control) techniques are described below.
Firstly, the temperature measuring technology is adopted, and the temperature measuring resistor is a temperature measuring element 30 which is taken as a core and represents the accuracy and the stability of temperature indexes. In the project, PT1000 is adopted for thermal control, the temperature precision of the product can reach one thousandth, and before the product is used, strict secondary screening calibration is carried out, so that high-precision and high-stability indexes of the star-containing product are guaranteed. When the product is assembled, a four-wire system is adopted, external electromagnetic interference is reduced through a shielded twisted pair, and analog quantity signals are transmitted. In the assembly process, the electric connector is shielded by adopting a copper foil, so that the anti-electromagnetic interference capability is improved; the number of acquisition bits of the data acquisition system is 32 bits to achieve a high resolution index.
Secondly, the three-level temperature control scheme is one of the key technologies for realizing high-precision temperature control. The control strategy of thermal control is three-level temperature control, wherein the object of the first-level temperature control is 'load compartment 10', the control mode of the part is that a passive means is combined with an active means, firstly, the thermal fluctuation of the star is blocked outside the multilayer by a heat insulation gasket and a multilayer heat insulation assembly 60 product, and then, the load compartment 10 plate is controlled to fluctuate within T +/-0.1 k by active heating; the object of the secondary temperature control is also a load cabin 10, and the control mode of the part is a pure passive mode, on one hand, the load cabin 10 is insulated from the core load, on the other hand, the black paint is subjected to high-intensity heat exchange to homogenize the temperature in the load cabin 10, so that the heat flow obtained by the core load is homogenized and stabilized; the object of three-level temperature control is core load, a method combining a passive means and an active means is adopted, thermal isolation is carried out through a multilayer thermal insulation assembly 61, the tiny infrared heat flow fluctuation generated by a load body is further weakened, the heat flow change reaching a core load body is minimized, and the temperature control stability index is better than +/-0.1 k by adopting active PID thermal control.
Finally, another technique for realizing precise thermal control is to adopt a single temperature controller to collect and control thermal control products. The single temperature controller is mainly used for solving the influence of load fluctuation of the whole satellite on thermal control acquisition and control. The acquisition precision (0.001k), the system stability index (+ -0.1 k) and the temperature control frequency (2s/60 paths) in the product development control of the single temperature controller. The temperature measuring circuit of the single temperature controller adopts a four-wire constant current source type temperature acquisition, and the method is more stable and accurate compared with the conventional two-wire system. Because the PID control method is simple and easy to implement, good in stability and high in reliability, as long as the control parameters are properly selected, the static deviation can be eliminated, the overshoot is less, and the temperature control with high precision and high stability can be realized, the PID control is adopted in the control mode of the heater in the project, the control algorithm is in a position mode, and the effect is more stable and tends to a target value compared with an incremental control algorithm.
The satellite of Tai Ji I is launched and lifted off in 2019, 8, 31 and month, the load is started up continuously, the temperature field of the whole satellite gradually enters a stable state, the thermal control mode enters the precise control mode continuously according to the planning of an experimental task, and the thermal control is carried out on the temperature field in the process of the precise control mode. Table 1 shows the on-track temperature control stability index results.
TABLE 1 on-orbit temperature control stability index results
From the results statistically obtained in table 1, it can be seen that:
1) because the temperature fields in all directions are greatly influenced by the fluctuation of a heat source in the satellite, the stability index of the Y direction (the sun facing direction and the sun back direction) without the heat source and with stable heat flow can reach +/-0.05K under the condition of active temperature control.
2) When the stability index of the load body is superior to 0.3K, the index requirement of high-precision control of 0.1K of the core load can be met.
3) In the in-orbit test process, the load is only subjected to passive radiation and temperature control by a heat insulation means, and the high stability index of +/-0.005K can be achieved. The results of the high stable temperature control obtained in-track are shown in FIG. 5.
Although the high-precision temperature control technology of 'Tai Chi I' can reach the stability index of +/-0.005K at present, the uK-level index from 'Tai Chi II' still has a great promotion space. According to the index rechecking of the thermal control product and the research on the single-machine performance of the temperature controller in the development process, the invention finds that the attack of the fine control requirement of higher index is started from the following aspects: a temperature measuring resistor with excellent stability is excavated; the resolution of a single temperature controller is improved, and the influence of noise on components is reduced; the optimization of the temperature measuring circuit can consider adopting better bridge circuit for acquisition; the simulation calculation simulation technology is improved, and PID parameters are accurately identified.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A thermal control system for a low earth orbit gravitational wave detection verification satellite, said gravitational wave detection satellite comprising a load and a platform, said load and said thermal control system being located inside said platform, said thermal control system comprising:
a primary thermal control module comprising a plurality of deck plates configured to enclose the load centrally and closed to form a load compartment; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources;
a secondary thermal control module comprising an automatic temperature control unit configured to detect a temperature of the load compartment and send the temperature of the load compartment to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin, so that the load cabin forms a constant-temperature cage type heating area when in load work;
the three-level thermal control module comprises a compensation module fixed on the load, a heat insulation assembly wrapping the load and the compensation module, and a temperature measurement unit, wherein the temperature measurement unit is configured to detect the temperature of the load and send the temperature of the load to the thermal control main processor; and the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in all places during work.
2. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 1, wherein said load compartment temperature requirement stability is better than 0.1K/1000 seconds during load operation, and actual achievement of temperature stability better than 5mK/1000 seconds during in orbit load operation.
3. The thermal control system for the low earth orbit gravitational wave detection verification satellite of claim 1, wherein the deck plate material of the load compartment is a honeycomb-structured plate compounded with a reinforced heat exchange coating.
4. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 1, wherein the material of the thermal insulation gasket is glass fiber reinforced plastic, the thermal insulation gasket is a square with a side length of 15mm and a thin sheet with a thickness of 3mm, and the thermal conductivity of the thermal insulation gasket is 0.40 w/(m-k);
the heat insulation assembly comprises 10 layers of composite materials, wherein each layer of composite material is formed by superposing a terylene net towel and an aluminized film and superposing polyimide films on the upper surface and the lower surface of the terylene net towel, the thickness of the heat insulation assembly is smaller than 5mm, and the equivalent heat conductivity coefficient of the heat insulation assembly is 0.001.
5. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 1, wherein the number of said deck boards is 6, said deck boards forming a hexahedron;
the heat insulation gasket is pasted on the boundary coupling surface of the load cabin, and the multilayer heat insulation assembly is coated on the outer surface of the load cabin.
6. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 5, wherein said automatic temperature control unit comprises a heating wire and a temperature measuring element, wherein:
the heating wires are fixed on the inner surface of the load cabin and are covered by the reinforced heat exchange coating, the plurality of heating wires on each cabin plate are distributed in parallel, and the distance between every two heating wires is 2 cm;
the temperature measuring elements are fixed in gaps among the heating wires and are covered by the enhanced heat exchange coating, and the temperature measuring elements are uniformly distributed on all the cabin plates;
the heating wires are configured to cause the load compartment to form a constant temperature cage heating zone during load operation, and the temperature sensing element is configured to sense the temperature of the load compartment.
7. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 6, wherein the automatic temperature control unit further comprises a temperature measurement signal processing circuit, the temperature measurement element is a temperature measurement resistor, the temperature measurement signal processing circuit comprises four outgoing lines, two outgoing lines provide a constant voltage at two ends of the temperature measurement resistor, the other two outgoing lines provide a current flowing through the temperature measurement resistor to the temperature measurement signal processing circuit, two of the four outgoing lines form a twisted pair, and a shielding layer covers the twisted pair; the automatic temperature control unit further comprises an active heating loop, the active heating loop adopts a four-wire system, and the active heating loop comprises a fuse loop.
8. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 7, wherein said thermal control total processor comprises a data acquisition unit, said data acquisition unit having a number of acquisition bits of 32 bits;
the temperature measurement signal processing circuit provides the current of the temperature measurement resistor to the data acquisition unit, and the data acquisition unit forms a temperature measurement value according to the current of the temperature measurement resistor and sends the temperature measurement value to the thermal control main processor.
9. The thermal control system for a low earth orbit gravitational wave detection verification satellite of claim 7, wherein the temperature measurement signal processing circuit is powered by an electrical connector, the electrical connector takes power from the satellite platform, and the electrical connector is wrapped with copper foil.
10. A thermal control method for a low earth orbit gravitational wave detection verification satellite, wherein a load and thermal control system of the gravitational wave detection satellite is installed inside the platform, the method comprising:
enclosing the load in the center by a plurality of cabin plates of the primary thermal control module and sealing to form a load cabin; arranging insulating gaskets and/or multi-layer insulating assemblies inside and/or outside the load compartment to insulate the load from other heat sources;
detecting the temperature of the load cabin by an automatic temperature control unit of the secondary thermal control module, and sending the temperature of the load cabin to a thermal control main processor; the thermal control main processor adopts a PID algorithm to control the automatic temperature control unit to adjust the temperature according to the temperature of the load cabin, so that a constant temperature cage type heating area is formed when the load cabin works; and
fixing a compensation module of a three-level thermal control module on the load, wrapping the load and the compensation module by adopting a multilayer heat insulation assembly of the three-level thermal control module, detecting the temperature of the load by a temperature measurement unit of the three-level thermal control module, and sending the temperature of the load to the thermal control main processor; the thermal control main processor is configured to adopt a PID algorithm to control the compensation module to adjust the temperature according to the temperature of the load, so that the temperature of the load is kept uniform in work.
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| CN111959830A (en) * | 2020-08-24 | 2020-11-20 | 中国科学院微小卫星创新研究院 | Thermal control system and method for satellite high-precision optical load mounting platform |
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| CN111959830A (en) * | 2020-08-24 | 2020-11-20 | 中国科学院微小卫星创新研究院 | Thermal control system and method for satellite high-precision optical load mounting platform |
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| CN112257191A (en) * | 2020-12-23 | 2021-01-22 | 中国人民解放军国防科技大学 | Load platform integrated microsatellite thermal control subsystem optimization method and system |
| CN113631014A (en) * | 2021-07-06 | 2021-11-09 | 北京自动化控制设备研究所 | Thermal examination device and system for high-power servo controller |
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