Temperature control method and system for non-uniform discontinuous space detection instrument

Abstract

The application provides a temperature control method and system for a non-uniform discontinuous space detection instrument, wherein a main temperature control heater of the space detection instrument is designed as a first type of heater and a second type of heater to obtain a heater ideal model; a mathematical heat transfer model is established based on a configuration of the space detection instrument; based on the mathematical heat transfer model, a heat transfer law and factors influencing a temperature field distribution are analyzed to obtain heat transfer characteristics and determine a temperature control target with a radial main temperature control as a core; and based on the mathematical heat transfer model and the temperature control target, a Bellman optimization algorithm is adopted to calculate optimal power density parameters according to corresponding weight parameters configured according to requirements. The application has the advantages of accurate temperature control, strong anti-interference capability, energy efficiency optimization and production efficiency improvement, and provides strong support for accurate control and stability improvement of a space telescope system temperature.

Description

Technical Field

[0001] The present invention relates to the technical field of precision temperature control for space science detectors, and more specifically, to an optimized precision temperature control method and system for non-uniform and discontinuous space detection instruments. It also relates to a corresponding computer terminal and computer-readable storage medium. Background Art

[0002] When it comes to temperature control for space science probes, especially space telescopes, existing technologies primarily combine active and passive temperature control techniques. This approach aims to leverage the strengths of both technologies to achieve higher temperature control accuracy and stability.

[0003] Passive temperature control minimizes the impact of the external environment on device temperature through materials and design. It doesn't rely on external energy sources, resulting in high reliability and low energy consumption. Active temperature control can quickly adjust temperature based on real-time changes through heating or cooling, providing flexibility and precision. The combination of these two approaches ensures reliability while effectively adapting to complex and changing spatial environments.

[0004] Commonly used passive temperature control technologies include: ① Multi-layer insulation (MLI): provides good thermal insulation for space cameras, reducing the impact of the external thermal environment on the internal temperature of the camera; ② Heat reflective coating: applies a special heat reflective coating on the camera surface to reduce solar radiation absorption and reduce heat load; ③ Heat baffle: uses heat baffles to isolate heat sources (such as heat generated by electronic equipment) from sensitive components (such as optical components) to reduce heat conduction.

[0005] Existing active temperature control technologies include: 1. Electric heating system: The key components of the space camera are heated by electric heaters to maintain them within a specific temperature range. This is especially suitable for extremely cold environments or occasions that require rapid temperature adjustment. 2. Refrigeration system: For equipment that needs to work at low temperatures, such as infrared cameras, active cooling technologies such as mechanical refrigeration or Peltier refrigeration may be used to achieve the required low-temperature working conditions.

[0006] Despite the aforementioned advantages of combined active and passive temperature control methods, existing design approaches are mostly based on uniform, continuous controlled objects. This means that when encountering specialized equipment such as non-uniform and discontinuous space exploration instruments, existing temperature control methods may not meet the precise temperature control requirements. This is because non-uniform and discontinuous controlled objects have more complex thermal characteristics and thermal response behaviors, which places higher demands on the design and implementation of temperature control systems.

[0007] Existing precision temperature control methods for space telescopes face challenges such as an inability to adapt to complex temperature control targets, difficulty in reducing temperature gradients, and susceptibility to external interference. These methods also struggle to meet the specific temperature control requirements of various scientific missions. Temperature control methods based on a combination of active and passive methods often depart from heat transfer models and fail to fully understand the laws of heat transfer. Furthermore, the granularity of temperature control methods has not yet been refined to the level of the actuator components. Furthermore, existing precision temperature control methods for space telescopes have failed to fully quantify process feasibility and balance temperature control performance with process difficulty during research, resulting in a significant gap between theoretical calculations and actual test results. These issues limit the observational performance and reliability of telescopes. Summary of the Invention

[0008] The present invention addresses the above-mentioned deficiencies in the prior art and provides a temperature control method and system for a non-uniform and discontinuous space detection instrument, as well as a corresponding computer terminal and computer-readable storage medium.

[0009] According to one aspect of the present invention, a temperature control method for a non-uniform discontinuous space detection instrument is provided, comprising:

[0010] The active temperature control heater of the space exploration instrument is designed into the first type of heater and the second type of heater, and the ideal model of the heater is obtained; wherein the first type of heater adopts a variable power density heater; and the second type of heater adopts a system conventional heater;

[0011] Based on the configuration of the space detection instrument, a mathematical heat transfer model is established;

[0012] Based on the mathematical heat transfer model, the heat transfer law and the factors affecting the temperature field distribution are analyzed to obtain the heat transfer characteristics and determine the temperature control target centered on radial active temperature control for the first type of heater;

[0013] Based on the mathematical heat transfer model and the temperature control target, the Bellman optimization algorithm is used to configure the corresponding weight parameters of the first type of heater according to the temperature control requirements to obtain the optimal power density parameters, and then the temperature of the space detection instrument is controlled.

[0014] Preferably, the mathematical heat transfer model is established based on the configuration of the space detection instrument, including:

[0015] Based on the configuration of space exploration instruments, a mathematical heat transfer model is established using the thermal network method;

[0016] The key nodes of the mathematical heat transfer model are set, including: the corresponding area N0 of the hub spoke and the lens N1 of the space exploration instrument;

[0017] Setting the boundary nodes of the mathematical heat transfer model, including: the hub spoke corresponding area boundary N2 of the space exploration instrument, the spoke corresponding area boundary N3, the lens radial boundary N4, the lens radial boundary N5, the lens lower end axial boundary N6, and the collimator N7;

[0018] According to the heat transfer relationship, the state space equations for spoke and lens temperatures are established as:

[0019]

[0020] in:

[0021] T=[T0 T1] T

[0022]

[0023]

[0024] u=[T2 T3 T4 T5 T6 T7 Q] T

[0025] Where, is the temperature change rate of the space detection instrument system, A is the parameter matrix of the space detection instrument system, B is the control matrix of the space detection instrument system, T is the temperature vector of the space detection instrument system, u is the control vector of the space detection instrument system, T0~T7 are the temperatures of different nodes of the space detection instrument system, corresponding to the numbers N0~N7, is the heat transfer factor, m and n are the node numbers, and Q is the heating power.

[0026] Preferably, the heat transfer law and the factors affecting the temperature field distribution are analyzed based on the mathematical heat transfer model to obtain the heat transfer characteristics and determine the temperature control target with radial active temperature control as the core for the first type of heater, including:

[0027] Based on the mathematical heat transfer model, the thermal environment is determined so that the temperature field of the lens of the space exploration instrument is stabilized in a certain area;

[0028] As the lens temperature T1 increases over time, the lens temperature T1 tends to the equilibrium point temperature T1 infinitely. * ,get:

[0029]

[0030] in, is the heat transfer factor, is the radiation heat transfer factor;

[0031] According to the physical parameters and boundary conditions of the mathematical heat transfer model, the proportional relationship between the heat transfer factors is analyzed to obtain the temperature range of the radial thermal environment of the space exploration instrument;

[0032] For the temperature control target of the first type of heater, the following differentiated designs are made based on the ambient temperature and heat transfer factor:

[0033] Assume that the temperature of all lenses should be equal, satisfying T * 1=T4=T5, then:

[0034]

[0035] According to the characteristics of lens position distribution, the spokes are divided into 54 grids;

[0036] When the space detection instrument system is stable, the equilibrium point temperature T0 of the spoke is obtained by formula (1): * for:

[0037]

[0038] in, is the heat transfer coefficient between the hub spokes and the lens of the space exploration instrument, is the heat transfer coefficient of the spoke body, is the radiation heat transfer factor between the spokes and the collimator, is the heat compensation factor;

[0039] Assume that the lens temperature T1 = T * 1, combined with formula (4), we get the expected value of thermal compensation Q * for:

[0040]

[0041] The temperature control target with radial active temperature control as the core is obtained.

[0042] Preferably, based on the mathematical heat transfer model and the temperature control target, a Bellman optimization algorithm is used to configure corresponding weight parameters for the first type of heater according to requirements to obtain the optimal power density parameters, including:

[0043] Based on the mathematical heat transfer model, the model is extended to the R lenses and the entire spoke of the space exploration instrument, and the thermal model with 2R state variables is obtained as follows:

[0044]

[0045] Set weight parameters, including mean deviation s1, maximum deviation s2, number of regions s3, and minimum region length s4;

[0046] The following steps are performed:

[0047] M1, divide the first type of heater into k regions using P partition methods, each region has a length ≥ a set length threshold, and the heat flux density of each region takes the average value of the corresponding Q* of the region;

[0048] M2, calculate the control variable u and the compensation heat Q of each lens corresponding region n ; wherein:

[0049] The length L[m] of each region is calculated as:

[0050]

[0051] In the formula, L i is the grid length of the region corresponding to the ith lens, i m is the maximum lens number in the mth region;

[0052] The total power u[m] of each region is calculated as:

[0053]

[0054] In the formula, is the heat that needs to be compensated for the grid corresponding to the ith lens;

[0055] The mth region instruction sequence Q i is calculated as:

[0056]

[0057] M3, run the heat model as shown in formula (6) to calculate the lens temperature T 1,n ;

[0058] M4, calculate the cost function sequence under P partition methods as:

[0059] J = s1e1 + s2e2 + s3k + s4 min{L[m]} (10)

[0060] In the formula, e1 is the average deviation, e2 is the maximum deviation, and k is the number of regions;

[0061] Wherein, the average deviation and the maximum deviation are:

[0062]

[0063] In the formula, T r is the target temperature, and R is the number of lenses;

[0064] M5, calculate the minimum value of the sequence as:

[0065] J minJ[k]=min{J[1],J[2],…,J[P]}

[0066] determine the sequence minimum value J min whether the gradient value in the k direction is <0:

[0067] if the gradient value is <0, then k=k+1, repeat the calculation of M1-M5;

[0068] if the gradient value is ≥0, then output the first type of heater each region length {L k} and compensation power {u k}, to obtain the optimal power density parameter.

[0069] Preferably, the R takes the value of 54.

[0070] Preferably, the length threshold takes the value of 10mm.

[0071] Preferably, the T r takes the value of 20℃.

[0072] Preferably, the method further comprises:

[0073] The space exploration instrument system is wrapped with two or more layers of thermal insulation materials, and the thermal insulation materials are used to suppress external thermal disturbance.

[0074] According to another aspect of the present application, a temperature control system for a non-uniform discontinuous space exploration instrument is provided, comprising:

[0075] a heater design module, which is used to design the active temperature control heater of the space exploration instrument into a first type of heater and a second type of heater, to obtain a heater ideal model; wherein the first type of heater adopts a variable power density heater; and the second type of heater adopts a system conventional heater;

[0076] a heat transfer model construction module, which is used to establish a mathematical heat transfer model based on the configuration of the space exploration instrument;

[0077] a temperature control target determination module, which is used to analyze the law of heat transfer and factors affecting the temperature field distribution based on the mathematical heat transfer model, to obtain heat transfer characteristics, and to determine the temperature control target of the first type of heater with the radial active temperature control as the core;

[0078] a temperature control parameter optimization module, which is used to configure the corresponding weight parameters of the first type of heater according to the temperature control requirement based on the mathematical heat transfer model and the temperature control target, to obtain the optimal power density parameter, and to further control the temperature of the space exploration instrument by using the Bellman optimization algorithm.

[0079] Preferably, the system further comprises:

[0080] The thermal disturbance suppression module is used to wrap the space detection instrument system with two or more layers of thermal insulation materials to suppress external thermal disturbance by using the thermal insulation materials.

[0081] According to a third aspect of the present application, a computer terminal is provided, comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor is configured to execute the computer program to perform the method according to any one of the preceding aspects of the present application, or to run the system according to the preceding aspects of the present application.

[0082] According to a fourth aspect of the present application, a computer readable storage medium is provided, which stores a computer program executable by a processor to perform the method according to any one of the preceding aspects of the present application, or to run the system according to the preceding aspects of the present application.

[0083] Compared with the prior art, the present application has at least one of the following beneficial effects:

[0084] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the present application have the advantages of accurate temperature control, strong anti-interference ability, energy efficiency optimization and production efficiency improvement, and provide strong support for accurate control and stability improvement of the temperature of the space telescope system.

[0085] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the present application integrate model establishment, characteristic analysis and execution component design into one through an integrated technical solution, and balance the temperature control performance and process difficulty.

[0086] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the present application effectively reduce the influence of external heat on the system by adopting a multi-stage passive thermal protection strategy, and improve the thermal stability and anti-interference ability of the system.

[0087] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the present application accurately control the system temperature by adopting a double-class active temperature control heater design, and optimizes the heater design parameters by using the Bellman optimization algorithm, thereby improving the temperature control effect and energy efficiency of the system.

[0088] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the present application ensure that the manufacturing process meets the design requirements through full-link model identification, and improve the production efficiency and product quality.

[0089] The temperature control method and system for non-uniform discontinuous space detection instruments provided by the present application can be widely applied in the technical fields of space science research, semiconductor manufacturing, medical devices, and new energy batteries. In space science research, the technology can be used in devices such as space telescopes to achieve high-precision temperature control in extreme environments and improve observation performance. In semiconductor manufacturing, accurate temperature control is crucial for product quality, and the technology can be applied to semiconductor production equipment. For some temperature-sensitive medical devices, the technology can achieve precise temperature control to ensure normal operation and safety. In addition, in the research and production of new energy batteries, accurate control of battery temperature is needed to improve battery performance and lifespan.

[0090] The temperature control method and system for non-uniform discontinuous space detection instruments provided by the present application bring improvement and development opportunities to multiple fields, improving device performance, product quality, and promoting progress and development in related fields. BRIEF DESCRIPTION OF DRAWINGS

[0091] Other features, objects, and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, with reference to the following drawings:

[0092] Figure 1 The workflow diagram of the temperature control method for non-uniform discontinuous space detection instruments in a preferred embodiment of the present application.

[0093] Figure 2 The composition and heat transfer model of the X-ray focusing mirror system in a specific application example of the present application. In the figure, 1 is the hub, 2 is the heat insulation cylinder, 3 is the spoke, 4 is the outer ring, 5 is the middle shaft, and 6 is the lens.

[0094] Figure 3 The heat exchange grid division schematic diagram of the spoke area in a specific application example of the present application.

[0095] Figure 4 The first type of heater partition design optimization algorithm flowchart in a specific application example of the present application.

[0096] Figure 5 The composition module schematic diagram of the temperature control system for non-uniform discontinuous space detection instruments in a preferred embodiment of the present application. DETAILED DESCRIPTION

[0097] The embodiments of the present application are described in detail below: The present embodiments are implemented on the premise of the technical solutions of the present application, and detailed implementation methods and specific operation processes are given. It should be noted that, for ordinary skilled persons in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of protection of the present application.

[0098] In response to the lack of existing temperature control technologies that can effectively improve temperature control effects and overall performance, one embodiment of the present invention provides a temperature control method for non-uniform and discontinuous space detection instruments. This method, based on optimization control theory, achieves a temperature control accuracy of 20±1°C for the 54 focusing lenses. Compared with conventional temperature control methods, optimization control theory can provide a systematic approach to designing control strategies, comprehensively considering key factors such as performance indicators, process feasibility, and energy consumption, and combining theoretical design, simulation calculations, and process implementation for cyclic optimization. Using this method, designers can adjust various weight parameters to obtain the most optimized precision temperature control strategy and the most reasonable and feasible heater design solution.

[0099] Specifically, if Figure 1 As shown, the temperature control method for a non-uniform and discontinuous space detection instrument provided in this embodiment may include the following operations:

[0100] S1, the active temperature control heater of the space exploration instrument is designed as a first type heater and a second type heater, and the ideal heater model is obtained; wherein the first type heater adopts a variable power density heater; the second type heater adopts a system conventional heater (such as a thin film electric heater);

[0101] S2, establish a mathematical heat transfer model based on the configuration of space exploration instruments;

[0102] S3, based on the mathematical heat transfer model, analyzes the heat transfer law and the factors affecting the temperature field distribution, obtains the heat transfer characteristics, and determines the temperature control target centered on radial active temperature control for the first type of heater;

[0103] S4, based on the mathematical heat transfer model and temperature control target, adopts the Bellman optimization algorithm to configure the corresponding weight parameters of the first type of heater according to the temperature control requirements, obtains the optimal power density parameters, and then controls the temperature of the space detection instrument.

[0104] In some preferred embodiments, the above S1, establishing a mathematical heat transfer model based on the configuration of the space exploration instrument, may further include the following operations:

[0105] S11, based on the configuration of space exploration instruments, a mathematical heat transfer model is established using the thermal network method;

[0106] The key nodes of the mathematical heat transfer model are set, including the corresponding area N0 of the hub spoke and the lens N1 of the space exploration instrument;

[0107] The boundary nodes of the mathematical heat transfer model are set, including: a hub spoke corresponding area boundary N2 of a space exploration instrument, a spoke corresponding area boundary N3, a lens radial boundary N4, a lens radial boundary N5, a lens lower end axial boundary N6, and a collimator N7;

[0108] S12, according to the heat transfer relationship, a state space equation of the spoke and the lens temperature is established as:

[0109]

[0110] Wherein:

[0111] T = [T0 T1] T

[0112]

[0113]

[0114] u = [T2 T3 T4 T5 T6 T7 Q] T

[0115] In the formula is a temperature change rate of the space exploration instrument system, A is a parameter matrix of the space exploration instrument system, B is a control matrix of the space exploration instrument system, T is a temperature vector of the space exploration instrument system, u is a control vector of the space exploration instrument system, T0-T7 are temperatures of different nodes of the space exploration instrument system, and correspond to N0-N7 numbering, is a heat exchange factor, m and n are node numbers respectively, and Q is a heating power.

[0116] In some preferred embodiments, the above S2, based on the mathematical heat transfer model, analyzes the law of heat transfer and the factors affecting the temperature field distribution, obtains the heat transfer characteristics, determines the temperature control target of the radial active temperature control for the first type of heater, and can further include the following operations:

[0117] S21, based on the mathematical heat transfer model, the heat environment is determined, so that the lens temperature field of the space exploration instrument is stabilized in a certain region;

[0118] S22, with the increase of time, the lens temperature T1 is increased, so that the lens temperature T1 tends to an equilibrium point temperature T1 * , obtain:

[0119]

[0120] Wherein, is a heat conduction heat exchange factor, is a radiation heat exchange factor;

[0121] S23, according to the physical parameters and boundary conditions of the mathematical heat transfer model, the proportional relationship between the heat transfer factors is analyzed, and the temperature range of the radial thermal environment of the space exploration instrument is obtained;

[0122] S24, for the temperature control target of the first type of heater, the environmental temperature and the heat transfer factor are used for differential design as follows:

[0123] Suppose the temperatures of all lenses are equal, satisfying T * 1=T4=T5, then:

[0124]

[0125] According to the characteristics of the lens position distribution, the spokes are divided into 54 grids;

[0126] When the space exploration instrument system is stable, the balance point temperature T0 of the spoke is obtained through formula (1) * :

[0127]

[0128] Wherein, is the heat conduction and heat transfer factor between the hub spoke and the lens of the space exploration instrument, is the spoke body heat conduction and heat transfer factor, is the radiation heat transfer factor between the spoke and the collimator, is the heat compensation factor;

[0129] Suppose the lens temperature T1=T * 1, combined with formula (4), the heat compensation expectation value Q * is obtained:

[0130]

[0131] The temperature control target with radial active temperature control as the core is obtained.

[0132] In some preferred embodiments, S3 above, based on the mathematical heat transfer model and the temperature control target, the Bellman optimization algorithm is used to configure the corresponding weight parameters of the first type of heater according to the requirements, and the optimal power density parameters are obtained, which can further include the following operations:

[0133] S31, based on the mathematical heat transfer model, the model is extended to R lenses and the whole spoke of the space exploration instrument, and the heat model with 2R state variables is obtained as:

[0134]

[0135] S32, set the weight parameters, including: mean deviation s1, maximum deviation s2, number of regions s3 and minimum length of region s4;

[0136] S33, performing the following steps:

[0137] M1, using P partition methods to divide the first type of heater into k regions, each region length ≥ set length threshold, and the heat flux density of each region takes the average of the corresponding Q* of the region;

[0138] M2, calculating the control variable u and the compensation heat Q of each lens corresponding region n ; wherein:

[0139] The length L[m] of each region is calculated as:

[0140]

[0141] In the formula, l i is the grid length of the region corresponding to the ith lens, i m is the maximum lens number in the mth region;

[0142] The total power u[m] of each region is calculated as:

[0143]

[0144] In the formula, is the heat that needs to be compensated for the grid corresponding to the ith lens;

[0145] The mth region instruction sequence Q i is calculated as:

[0146]

[0147] M3, running the heat model as shown in formula (6) to calculate the lens temperature T 1,n ;

[0148] M4, calculating the cost function sequence under P partition methods as:

[0149] J = s1e1 + s2e2 + s3k + s4 min{L[m]} (10)

[0150] In the formula, e1 is the average deviation, e2 is the maximum deviation, and k is the number of regions;

[0151] Wherein, the average deviation and the maximum deviation are:

[0152]

[0153] In the formula, T r is the target temperature, and R is the number of lenses;

[0154] M5, calculating the minimum value of the sequence as:

[0155] J min =min{J[1],J[2],…,J[P]}

[0156] S34, determine the minimum value J of the sequence min Is the gradient value in the k direction less than 0?

[0157] If the gradient value is less than 0, then k=k+1 and repeat the calculation of M1 to M5;

[0158] If the gradient value is ≥ 0, the length of each area of ​​the first type heater {L k} and compensation power {u k}, and obtain the optimal power density parameters.

[0159] The above algorithm flow chart is as follows Figure 3 shown.

[0160] In some preferred embodiments, the above 31, R takes a value of 54.

[0161] In some preferred embodiments, the length threshold of M1 is 10 mm.

[0162] In some preferred embodiments, the above M4, T r The value is 20℃.

[0163] In some preferred embodiments, the method provided in the above embodiment of the present invention may further include the following operations:

[0164] The space detection instrument system is wrapped with two or more layers of thermal insulation materials, which are used to suppress external thermal disturbances.

[0165] The temperature control method for non-uniform and discontinuous space detection instruments provided by the above-mentioned embodiment of the present invention closely combines model establishment, characteristic analysis and execution component design, aiming to strike a balance between temperature control performance and manufacturing process difficulty; a multi-level passive thermal protection strategy can be adopted, that is, the focusing mirror system is wrapped with two or more layers of thermal insulation material to effectively suppress external thermal disturbances to build a stable thermal environment; the active temperature control heaters are divided into two categories, which can achieve precise control of radial boundary temperature and radial temperature gradient; in view of the non-uniform and discontinuous characteristics of the system, the first type of heater adopts a variable power density heater design; the Bellman optimization algorithm is used to carry out detailed calculation and analysis of the physical parameters of the first type of heater; by quantifying the feasibility of the execution component manufacturing process, the full-link model identification from the mathematical heat transfer model to the execution component is realized.

[0166] The technical solution provided by the above embodiment of the present invention is further described in detail below with reference to a specific application example and the accompanying drawings.

[0167] The temperature control method involved in this specific application example establishes a mathematical heat transfer model for the non-uniform and discontinuous characteristics of complex X-ray space telescope configurations. This model thoroughly investigates the heat transfer characteristics in the focusing mirror and establishes a design scheme centered on radial active temperature control. To achieve precise thermal field control, two types of active temperature-controlled heaters were designed, and ideal models for each heater were successfully constructed. Addressing the difficulty of identifying a precise temperature control model, the development difficulty of the first type of heater was quantified, and an optimal temperature control method for non-uniform and discontinuous X-ray telescopes was proposed. This method balances temperature control performance with process difficulty. Based on the Bellman optimization algorithm, the physical parameters of the first type of heater were calculated and analyzed. By appropriately setting the weighting parameters (mean deviation, maximum deviation, number of regions, and minimum region length), an optimal temperature control strategy was obtained. This specific application example integrates model development, characteristic analysis, and actuator design for a precise temperature control method for complex space telescope configurations, providing technical support for future space science detectors with high-temperature requirements.

[0168] The temperature control method specifically includes the following steps:

[0169] 1. Construct a mathematical heat transfer model

[0170] The X-ray telescope adopts the traditional nested grazing incidence focusing telescope configuration, and the detector PNCCD is used as the focal plane detector to read the X-ray photons. The focusing lens group is the key component of the X-ray telescope optical transmission, which is composed of 54 layers of lenses nested layer by layer. Figure 2 As shown, the upper half of each lens layer is a paraboloid of rotation, while the lower half is a hyperboloid of rotation. Each lens layer is glued to the slots of the spider-shaped hub spokes with epoxy glue, and the outermost layer of the lens is covered with an insulating lens barrel to protect and maintain temperature.

[0171] The lenses are made of nickel-plated gold and are 300 mm long, including a 150 mm parabolic section and a 150 mm hyperbolic section. The 54 lenses require extremely high temperature uniformity and stability, with a specified temperature range of 20 ± 1°C. The diameter, thickness, and contact heat transfer coefficient of each lens are non-uniform and discontinuous. This design feature leads to complex heat transfer paths between the lenses and the environment, as well as between the lenses themselves, posing a significant challenge to precise temperature control.

[0172] The thermal environment of the focusing lens assembly is complex, consisting of two components: the axial and radial components. The axial thermal environment includes the temperatures of the collimator, anti-contamination cylinder, and filter wheel, while the radial thermal environment includes the hub and insulation cylinder. The focusing lens assembly itself does not contain any heat sources. To achieve precise temperature control of non-uniform and discontinuous X-ray focusing lenses, the design of a feasible and efficient thermal control system is crucial. Based on passive temperature control, this paper proposes the following active temperature control strategy:

[0173] 1) Adjust the temperature of the focusing mirror hub spoke, so that the temperature of each lens is evenly distributed around 20℃;

[0174] 2) Regulate the temperature of the radial heat radiation environment insulation cylinder, and reduce the temperature gradient of each lens itself.

[0175] A mathematical heat transfer model is established by using a heat network method, as shown in the following formula: Figure 1 The entire system is axisymmetric, and a minimum unit (1 / 16) is taken to establish a heat analysis model, wherein the key nodes include N0 (a corresponding area of the spoke) and N1 (a lens); the boundary nodes include N2 (a corresponding area boundary of the spoke), N3 (a corresponding area boundary of the spoke), N4 (a radial boundary of the lens), N5 (a radial boundary of the lens), N6 (an axial boundary of the lower end of the lens), and N7 (a collimator). According to the heat transfer relationship, the state space equation of the spoke and the lens temperature is as follows:

[0176]

[0177] Wherein:

[0178] T = [T0 T1] T

[0179]

[0180]

[0181] u = [T2 T3 T4 T5 T6 T7 Q] T

[0182] 2. Analyze the heat transfer characteristics of the system

[0183] Based on the mathematical heat transfer model, the law of heat transfer in the system and the factors affecting the temperature field distribution are analyzed. Through the analysis of the heat transfer factor and the research on the heat transfer characteristics of the system, the present application provides reliable support for the precise temperature control method. When the heat environment is determined, the lens temperature field will be stabilized in a certain area. With the increase of time, the lens temperature T1 will tend to the equilibrium point temperature T * 1, and the calculation formula is as follows:

[0184]

[0185] Wherein, is a heat conduction heat transfer factor, is a radiation heat transfer factor.

[0186] According to the system physical parameters and boundary conditions, the proportional relationship between the heat transfer factors can be analyzed. Taking the focusing mirror researched in the application as an example, the temperature range of the radial thermal environment is 10-30℃, wherein the radial thermal environment of the No. 1 mirror is the temperature of the heat insulation cylinder, the temperature of the No. 2 mirror, the radial thermal environment of the No. 2-53 mirror is the temperature of the adjacent mirror, and the radial thermal environment of the No. 54 mirror is the temperature of the No. 53 mirror and the central axis. The temperature range of the thermal environment of the collimator at the upper end of the mirror in the axial direction is -30-20℃; the temperature range of the thermal environment at the lower end of the mirror in the axial direction is 0-15℃, and the temperature control target T * 1 of the focusing mirror is 20℃.

[0187] The temperature control target of the first type of heater needs to be designed differently based on the environmental temperature and the heat transfer factor.

[0188] In an ideal state, the temperatures of all the mirrors should be equal, satisfying T * 1=T4=T5.

[0189]

[0190] In an ideal state (Perfect state), according to the characteristics of the distribution of the mirror positions, the spokes are divided into 54 grids, as shown in FIG. 1, for further analysis. Figure 3

[0191] When the system is stable, the equilibrium point temperature calculation formula of the spoke can be obtained from formula (1) as follows:

[0192]

[0193] wherein, is the heat conduction heat transfer factor between the spoke and the mirror, is the heat conduction heat transfer factor of the spoke body, is the radiation heat transfer factor between the spoke and the collimator, is the heat compensation factor.

[0194] In an ideal state, the mirror temperature T1=T * 1, and the expected value Q * of the heat compensation can be obtained by combining formula (4) as follows:

[0195]

[0196] Due to the complexity of the configuration, as the mirror position changes, Q * ​The change of the temperature often presents a highly nonlinear characteristic, and even the required heat compensation amount in some regions is less than 0, which brings great challenges to the design of the first type of spoke heater. Therefore, in the design of the first type of spoke heater, multiple factors such as process feasibility and energy consumption need to be considered, and theoretical analysis and actual process are combined for multi-dimensional consideration to find the optimal design scheme.

[0197] 3. Obtaining an optimal temperature control method

[0198] 3.1 Method principle

[0199] The Bellman optimization algorithm adopted by the present application is a classical dynamic programming method for solving optimal control problems. The algorithm was proposed by mathematician Richard Bellman in the mid-20th century and is widely used in various fields such as control theory, operations research, economics, etc.

[0200] The core idea of the Bellman optimization algorithm is to decompose a complex optimization problem into a series of sub-problems and solve these sub-problems step by step to obtain the overall optimal solution. The basic principle can be summarized as follows:

[0201] 1) Optimal substructure property: The Bellman optimization algorithm utilizes the property of optimal substructure, which means that a sub-problem of an optimal solution is still an optimal solution. Through this property, the algorithm can decompose the original problem into sub-problems and solve these sub-problems step by step to obtain the optimal solution of the original problem.

[0202] 2) Recursive relationship: In the Bellman optimization algorithm, a value function or state value function is usually defined to represent the optimal value at each state. By recursively updating these value functions, the optimal solution can be gradually calculated. The recursive relationship usually includes the Bellman equation, which describes the relationship between the current state value and the future state value.

[0203] 3) Iterative solution: The Bellman optimization algorithm usually uses an iterative method to solve the optimal value function. In each iteration, the estimated value of the value function is updated according to the recursive relationship until it converges to the optimal solution. Such an iterative process can guarantee that the algorithm converges to the global optimal solution.

[0204] 3.2 Specific steps

[0205] The optimization algorithm steps for the first type of heater region division strategy are as follows:

[0206] 1) Establish a system heat transfer model. Taking the X-ray telescope studied in the present application as an example, equation (1) is extended to 54 mirror pieces and the whole spoke. At this time, the system has 108 state variables, and the state equation is represented as follows:

[0207]

[0208] 2) Set the weight parameter mean deviation, maximum deviation, the number of regions and the minimum length of the region corresponding value: s1, s2, s3, s4;

[0209] 3) Divide the whole heater into k regions, each region length ≥10mm, a total of P methods, the heat flux density of each region takes the mean value of the corresponding Q* of this region;

[0210] 4) Calculate the control variable u, the compensation heat Q of each lens corresponding region n ;

[0211] The calculation formula of the length of each region is as follows:

[0212]

[0213] The calculation formula of the total power of each region is as follows:

[0214]

[0215] The calculation formula of the m region instruction sequence is as follows:

[0216]

[0217] 5) Run the heat model - formula (6), calculate the lens temperature T 1,n ;

[0218] 6) Calculate the cost function sequence under P kinds of division methods:

[0219] J = s1e1 + s2e2 + s3k + s4 min{L[m]} (10)

[0220] The calculation formula of the average deviation and the maximum deviation is as follows:

[0221]

[0222] 7) Calculate the sequence minimum value J min = min{J[1], J[2], …, J[P]};

[0223] 8) Judge whether the gradient value of J min in the k direction is <0: if the degree value <0, then k = k + 1, repeat steps 3-7; if the degree value ≥0, output the first type of heater region length{L k}, compensation power{u k};

[0224] 9) The program ends.

[0225] The above algorithm flow chart is shown in Figure 4 .

[0226] As can be seen from the above specific application cases, the temperature control method for the non-uniform discontinuous X-ray space telescope provided by the above embodiments of the present application realizes optimal precise temperature control, has obvious advantages compared with the prior art, and is fully suitable for the precise temperature control requirements of space telescopes with complex configurations, and specifically embodies the following aspects:

[0227] 1) Integration of model establishment, characteristic analysis, and execution component design:

[0228] Firstly, the model establishment, characteristic analysis, and execution component design are integrated, and by comprehensively considering the factors of these three aspects, the balance between the temperature control performance and the process difficulty is realized. Specifically, in view of the temperature control requirements of the space telescope under extreme environments, by precise model establishment and characteristic analysis, combined with reasonable execution component design, the stability and reliability of the entire system are ensured.

[0229] 2) Multi-level passive thermal protection strategy:

[0230] In order to build a stable thermal environment, the present application adopts a multi-level passive thermal protection strategy. By setting multiple layers of thermal protection structures in the system, the influence of external heat on the system is effectively reduced, the thermal stability and anti-interference ability of the system are improved, and the normal operation of the telescope under various working environments is ensured.

[0231] 3) Design of dual-class active temperature control heater:

[0232] The active temperature control heater is divided into two classes to realize precise regulation of the radial boundary temperature and the radial temperature gradient. Among them, the first class of heater adopts a variable power density heater design, which is aimed at the non-uniform discontinuous characteristics of the system, and realizes accurate regulation of the system temperature; the second class of heater is designed according to the system requirements, so that the system can flexibly control the temperature under different conditions.

[0233] 4) Application of Bellman optimization algorithm:

[0234] Based on the Bellman optimization algorithm, the physical parameters of the first class of heater are calculated and analyzed. Through this optimization algorithm, the design parameters of the heater can be better optimized, the temperature control effect and energy efficiency of the system can be improved, and the stability and reliability of the system under various complex environments can be ensured.

[0235] 5) Full-link model identification:

[0236] The feasibility of the execution component manufacturing process is quantified, and full-link model identification from the mathematical heat transfer model to the execution component is realized. Through detailed analysis and optimization of the entire manufacturing process, it is ensured that each link of the system meets the design requirements, and the production efficiency and product quality are maximized.

[0237] An embodiment of the present application provides a temperature control system for a non-uniform discontinuous space detection instrument.

[0238] Specifically, as shown in the figure, the temperature control system for the non-uniform discontinuous space detection instrument provided by the embodiment can include the following modules: Figure 5

[0239] A heater design module, which is used for designing active temperature control heaters of the space detection instrument into first-type heaters and second-type heaters to obtain a heater ideal model; wherein the first-type heaters adopt variable power density heaters; and the second-type heaters adopt system conventional heaters.

[0240] A heat transfer model construction module, which is used for establishing a mathematical heat transfer model based on a configuration of the space detection instrument.

[0241] A temperature control target determination module, which is used for analyzing a heat transfer law and factors influencing a temperature field distribution based on the mathematical heat transfer model, obtaining heat transfer characteristics, and determining a temperature control target for the first-type heaters with radial active temperature control as a core.

[0242] A temperature control parameter optimization module, which is used for configuring corresponding weight parameters of the first-type heaters according to temperature control requirements, obtaining optimal power density parameters, and then performing temperature control on the space detection instrument based on the mathematical heat transfer model and the temperature control target by using a Bellman optimization algorithm.

[0243] In some preferred embodiments, the system provided by the above embodiment can further include the following modules:

[0244] A thermal disturbance suppression module, which is used for wrapping the space detection instrument system with two or more layers of thermal insulation materials to suppress external thermal disturbances by using the thermal insulation materials.

[0245] It should be noted that the steps in the method provided by the present application can be realized by using corresponding modules, devices, units and the like in the system, and those skilled in the art can refer to the technical solutions of the method to realize the composition of the system, that is, the embodiments in the method can be understood as preferred examples of constructing the system, and details are not described herein.

[0246] An embodiment of the present application provides a computer terminal, which includes a memory, a processor, and a computer program stored in the memory and capable of running on the processor, and the processor can be used to execute the method of any one of the above embodiments of the present application or run the system of any one of the above embodiments of the present application when executing the computer program.

[0247] ​Optionally, a memory is configured to store a program; the memory can include volatile memory (e.g., random-access memory (RAM), such as static random-access memory (SRAM), Double Data Rate Synchronous Dynamic Random Access Memory (DDR SDRAM), etc.), and / or non-volatile memory (e.g., flash memory). The memory is configured to store computer programs (e.g., application programs, functional modules, etc. for implementing the above-described methods), computer instructions, etc. The computer programs, computer instructions, etc. described above can be stored in one or more memories in a partitioned manner. Furthermore, the computer programs, computer instructions, data, etc. described above can be invoked by the processor.

[0248] The computer programs, computer instructions, etc. described above can be stored in one or more memories in a partitioned manner. Furthermore, the computer programs, computer instructions, data, etc. described above can be invoked by the processor.

[0249] The processor is configured to execute the computer programs stored in the memory, so as to implement the various steps in the methods or the various modules of the system according to the above-described embodiments. For details, reference can be made to the related descriptions in the above method and system embodiments.

[0250] The processor and the memory can be independent structures, or can be integrated into an integrated structure. When the processor and the memory are independent structures, the memory and the processor can be coupled and connected through a bus.

[0251] An embodiment of the present application provides a computer readable storage medium, which stores a computer program. The computer program is configured to be executed by a processor to implement the method according to any one of the above-mentioned embodiments of the present application, or to run the system according to any one of the above-mentioned embodiments of the present application.

[0252] The temperature control method and system for the non-uniform discontinuous space detection instrument provided by the above embodiments of the present application have the advantages of precise temperature control, strong anti-interference capability, energy efficiency optimization, and production efficiency improvement, and provide strong support for precise control and stability improvement of the temperature of a space telescope system. The model establishment, characteristic analysis, and execution component design are integrated through an integrated technical solution, and the balance between the temperature control performance and the process difficulty is achieved. The multi-stage passive thermal protection strategy effectively reduces the influence of external heat on the system and improves the thermal stability and anti-interference capability of the system. The double-class active temperature control heater is designed to accurately control the system temperature, the Bellman optimization algorithm is applied to optimize the heater design parameters, and the temperature control effect and energy efficiency of the system are improved. The full-link model identification ensures that the manufacturing process meets the design requirements, and the production efficiency and product quality are improved. The comprehensive application of these innovative technologies has wide application prospects in the fields of space science research, semiconductor manufacturing, medical devices, and new energy batteries. In space science research, the technology can be used in space telescopes and other equipment to achieve high-precision temperature control in extreme environments and improve observation performance. In semiconductor manufacturing, precise temperature control is crucial for product quality, and the technology can be applied to semiconductor production equipment. For some temperature-sensitive medical devices, the technology can achieve precise temperature control to ensure normal operation and safety. In addition, in the research and production of new energy batteries, precise control of battery temperature is needed to improve battery performance and lifespan. In summary, the innovative technology of the present application brings improvement and development opportunities to multiple fields, improves equipment performance and product quality, and promotes the progress and development of related fields.

[0253] The matters not described in the above embodiments of the present application are all known technologies in the art.

[0254] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and various modifications or changes can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application.

Claims

1. A temperature control method for a non-uniform discontinuous space detection instrument, characterized in that: include: The active temperature control heater of the space exploration instrument is designed into the first type of heater and the second type of heater, and the ideal model of the heater is obtained; wherein the first type of heater adopts a variable power density heater; and the second type of heater adopts a system conventional heater; Based on the configuration of the space detection instrument, a mathematical heat transfer model is established; Based on the mathematical heat transfer model, the heat transfer law and the factors affecting the temperature field distribution are analyzed to obtain the heat transfer characteristics and determine the temperature control target centered on radial active temperature control for the first type of heater; Based on the mathematical heat transfer model and the temperature control target, a Bellman optimization algorithm is used to configure corresponding weight parameters of the first type of heater according to the temperature control requirements to obtain the optimal power density parameters, thereby controlling the temperature of the space exploration instrument; The mathematical heat transfer model is established based on the configuration of the space detection instrument, including: Based on the configuration of space exploration instruments, a mathematical heat transfer model is established using the thermal network method; The key nodes of the mathematical heat transfer model are set, including: the corresponding area N0 of the hub spoke and the lens N1 of the space exploration instrument; Setting the boundary nodes of the mathematical heat transfer model, including: the hub spoke corresponding area boundary N2 of the space exploration instrument, the spoke corresponding area boundary N3, the lens radial boundary N4, the lens radial boundary N5, the lens lower end axial boundary N6 and the collimator N7; According to the heat transfer relationship, the state space equations for spoke and lens temperatures are established as: in: T=[T0 T1] T u=[T2 T3 T4 T5 T6 T7 Q] T Where, is the temperature change rate of the space detection instrument system, A is the parameter matrix of the space detection instrument system, B is the control matrix of the space detection instrument system, T is the temperature vector of the space detection instrument system, u is the control vector of the space detection instrument system, T0~T7 are the temperatures of different nodes of the space detection instrument system, corresponding to the numbers N0~N7, is the heat transfer factor, m and n are the node numbers, and Q is the heating power; Based on the mathematical heat transfer model and the temperature control target, the Bellman optimization algorithm is used to configure the corresponding weight parameters of the first type of heater according to the requirements to obtain the optimal power density parameters, including: Based on the mathematical heat transfer model, the model is extended to the R lenses and the entire spoke of the space exploration instrument, and the thermal model with 2R state variables is obtained as follows: Set weight parameters, including mean deviation s1, maximum deviation s2, number of regions s3, and minimum region length s4; Perform the following steps: M1, using P division methods, divide the first type of heater into k regions, each region length ≥ the set length threshold, and the heat flux density of each region takes the average value of Q* corresponding to the region; M2, calculate the control variable u and the compensation heat Q of the corresponding area of ​​each lens n ;in: Calculate the length of each area L[m] as: Where, L i is the length of the regional grid corresponding to the i-th lens, i m is the maximum lens number in the mth area; Calculate the total power u[m] of each area as: Where, is the amount of heat that needs to be compensated for the regional grid corresponding to the i-th lens; Calculate the instruction sequence Q in region m i for: M3 runs the thermal model shown in equation (6) to calculate the lens temperature T 1,n ; M4, calculates the cost function sequence under P partitioning methods as follows: J=s1e1+s2e2+s3k+s4min{L[m]} (10) Where, e1 is the average deviation, e2 is the maximum deviation, and k is the number of divided regions; Among them, the average deviation and the maximum deviation are: Where, T r is the target temperature, R is the number of lenses; M5, calculate the minimum value of the sequence: I min =min{J[1],J[2],…,J[P]} Determine the minimum value J of the sequence min Is the gradient value in the k direction less than 0? If the gradient value is less than 0, then k=k+1 and repeat the calculation of M1 to M5; If the gradient value is ≥ 0, the length of each area of ​​the first type heater {L k } and compensation power {u k }, and obtain the optimal power density parameters.

2. The temperature control method for a non-uniform and discontinuous space detection instrument according to claim 1, characterized in that: Based on the mathematical heat transfer model, the heat transfer law and the factors affecting the temperature field distribution are analyzed to obtain the heat transfer characteristics and determine the temperature control target with radial active temperature control as the core for the first type of heater, including: Based on the mathematical heat transfer model, the thermal environment is determined so that the temperature field of the lens of the space exploration instrument is stabilized in a certain area; As the lens temperature T1 increases over time, the lens temperature T1 tends to the equilibrium point temperature T1 infinitely. * ,get: in, is the heat transfer factor, is the radiation heat transfer factor; According to the physical parameters and boundary conditions of the mathematical heat transfer model, the proportional relationship between the heat transfer factors is analyzed to obtain the temperature range of the radial thermal environment of the space exploration instrument; For the temperature control target of the first type of heater, the following differentiated designs are made based on the ambient temperature and heat transfer factor: Assume that the temperature of all lenses should be equal, satisfying T * 1=T4=T5, then: According to the characteristics of lens position distribution, the spokes are divided into 54 grids; When the space detection instrument system is stable, the equilibrium point temperature T0 of the spoke is obtained by formula (1): * for: in, is the heat transfer coefficient between the hub spokes and the lens of the space exploration instrument, is the heat transfer coefficient of the spoke body, is the radiation heat transfer factor between the spokes and the collimator, is the heat compensation factor; Assume that the lens temperature T1 = T * 1, combined with formula (4), we get the expected value of thermal compensation Q * for: The temperature control target with radial active temperature control as the core is obtained.

3. The temperature control method for a non-uniform and discontinuous space detection instrument according to claim 1, characterized in that: Also includes any one or more of the following: -The R value is 54; -The length threshold is 10 mm; -The T r The value is 20℃.

4. The temperature control method for a non-uniform discontinuous X-ray telescope according to any one of claims 1 to 3, characterized in that: Also includes: The space detection instrument system is wrapped with two or more layers of thermal insulation materials, and the thermal insulation materials are used to suppress external thermal disturbances.

5. A temperature control system for a non-uniform discontinuous space detection instrument, used to implement the temperature control method according to claim 1, characterized in that: include: A heater design module is used to design the active temperature-controlled heater of a space exploration instrument into a first-type heater and a second-type heater, thereby obtaining an ideal heater model. The first-type heater adopts a variable power density heater, while the second-type heater adopts a conventional system heater. A heat transfer model building module, which builds a mathematical heat transfer model based on the configuration of the space detection instrument; a temperature control target determination module, which analyzes the heat transfer law and factors affecting the temperature field distribution based on the mathematical heat transfer model, obtains heat transfer characteristics, and determines the temperature control target centered on radial active temperature control for the first type of heater; A temperature control parameter optimization module, based on the mathematical heat transfer model and the temperature control target, adopts the Bellman optimization algorithm to configure the corresponding weight parameters of the first type of heater according to the temperature control requirements, obtains the optimal power density parameters, and then controls the temperature of the space probe.

6. The temperature control system for non-uniform and discontinuous space detection instruments according to claim 5, characterized in that: Also includes: A thermal disturbance suppression module uses two or more layers of thermal insulation materials to wrap the space detection instrument system, and uses the thermal insulation materials to suppress external thermal disturbances.

7. A computer terminal comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When executing the computer program, the processor can be used to perform the method according to any one of claims 1 to 3, or run the system according to claim 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, it can be used to perform the method according to any one of claims 1 to 3, or to run the system according to claim 5.

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