Complex task track thermal environment adaptability assessment method and system
By conducting thermal simulation analysis of deep space detection models under complex task tracks and formulating corresponding thermal environment assessment test projects, the problem of difficult to effectively assess the adaptability of deep space detection models in extreme thermal environments in the existing technology is solved, and efficient and economical thermal environment adaptability assessment is achieved.
Patent Information
- Application Number
- CN202411618544.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-13
- Publication Date
- 2025-03-07
AI Technical Summary
The prior art is difficult to effectively assess the adaptability of the extreme high temperature, extreme low temperature and hot and cold alternating environments experienced by deep space detection models under complex mission tracks.
By analyzing the environmental profile of complex task tracks, disassembly of typical orbit segments, and thermal simulation analysis is performed in combination with the model's working mode at this stage, the thermal environmental profile experienced by the satellite model product is obtained. Then formulate corresponding thermal environment assessment and testing projects, including high-temperature, low-temperature and cold-heat alternating environment adaptability assessment and testing conditions, and provide accelerated testing methods.
A comprehensive assessment of the thermal environment adaptability of deep space detection models under complex task tracks has been achieved, effectively reducing the test time and cost, and at the same time solving the product assessment problems in extremely harsh thermal environments.
Smart Images
Figure CN119578049A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of deep space exploration, and in particular to a method and system for assessing the thermal environment adaptability of a complex mission orbit. Background Art
[0002] In order to save fuel and time to reach the target orbit, deep space exploration models usually need to use celestial bodies, such as Venus, Earth, and Jupiter. Therefore, deep space exploration models may need to experience the extremely high temperature environment of Venus, the extremely low temperature environment of Jupiter or the target celestial body, and the temperature alternating environment of the target celestial body.
[0003] Deep space exploration models usually have a cabin, and the temperature environment of the single-unit products in the cabin is better due to the guarantee of thermal control measures. However, the models outside the cabin are subject to energy constraints and need to take into account both extreme high and extreme low temperatures, so the thermal control measures are limited (mainly passive thermal control), requiring them to have the ability to adapt to the extreme thermal environment of each typical orbit.
[0004] At present, most Earth orbit satellite models are mainly based on a single orbital environment, and the thermal environment assessment of model products is generally carried out in a hot and cold alternating manner. There is no precedent for interactive assessment of extremely high temperature, hot and cold alternating, and extremely low temperature environments.
[0005] Therefore, it is necessary to propose a new technical solution to improve the above technical problems. Summary of the invention
[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a method and system for assessing the thermal environment adaptability of a complex mission orbit.
[0007] According to a method for assessing the thermal environment adaptability of a complex mission track provided by the present invention, the method comprises the following steps:
[0008] Step S1: Analyze the environmental profile of the complex mission track and disassemble the typical track section that needs to be thermally simulated;
[0009] Step S2: Conduct thermal simulation analysis on each typical orbit segment identified in step S1 in combination with the model's working mode at this stage to obtain the thermal environment profile experienced by the satellite model product;
[0010] Step S3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in step S2, formulate the thermal environment assessment test items that need to be carried out for the product;
[0011] Step S4: According to the extreme high temperature and holding time of the typical track section obtained by the thermal simulation in step S2, the test conditions for high temperature environment adaptability assessment are formulated, and an accelerated test method is given;
[0012] Step S5: According to the hot-cold alternating temperature range and the number of cycles of different orbital sections obtained by the thermal simulation in step S2, formulate the test conditions for the adaptability assessment of the hot-cold alternating environment, and provide an accelerated test method;
[0013] Step S6: According to the extreme low temperature and holding time of the typical track section obtained by the thermal simulation in step S2, the test conditions for the extreme low temperature environment adaptability assessment are formulated, and the accelerated test method is given.
[0014] Preferably, step S1 comprises the following steps:
[0015] Step S1.1: According to the characteristics of the orbiting mission and the crossing mission of the deep space exploration model, identify and set the typical orbital segment of the celestial body and the typical orbital segment of the celestial body;
[0016] Step S1.2: According to the orbit design of the deep space exploration mission, identify the celestial body's leverage orbit segment, set the celestial body's leverage orbit segment with a typical thermal environment as a typical orbit segment, and identify the celestial body's leverage typical orbit segment.
[0017] Preferably, in step S2, thermal simulation analysis is performed on each typical orbital segment identified in step S1 in combination with the working mode of the model at this stage to obtain the thermal environment profile experienced by the satellite model product: including extremely high temperature, extremely low temperature, typical extreme temperature duration and number of hot and cold alternations.
[0018] Preferably, in step S4, the high temperature temperature gradient is subjected to a 1:1 assessment test in sequence according to the flight order, and the temperature gradient and holding time obtained by simulation are used as the test conditions for the high temperature storage test of the product; without increasing the failure mechanism of the product, the equivalent screening stress intensity is used as the basis for the accelerated test equivalence judgment, and the high temperature storage accelerated screening calculation formula is as follows:
[0019] SS R =1-exp[-0.0017(R R +0.6) 0.6 t]
[0020] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours.
[0021] Preferably, in step S5, different orbital segments are subjected to 1:1 assessment tests in sequence according to the flight order, and the hot and cold alternating temperature ranges and the number of cycles of different orbital segments are used as the test conditions for the hot and cold alternating test of the product; the equivalent screening stress strength is used as the basis for the accelerated test equivalence judgment, and the hot and cold alternating accelerated screening calculation formula is as follows:
[0022] SS LR=1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N]
[0023] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; and e is the natural logarithm.
[0024] Preferably, step S6 performs a 1:1 assessment test on the lowest temperature section in all task sections, and uses the extreme low temperature and holding time obtained by simulation as the test conditions for the low-temperature storage test of the product; the equivalent screening stress intensity is used as the basis for the accelerated test equivalence judgment, and the low-temperature storage accelerated screening calculation formula is as follows:
[0025] SS L =1-exp[-0.0017(R L +0.6) 0.6 t]
[0026] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
[0027] The present invention also provides a complex mission orbit thermal environment adaptability assessment system, the system comprising the following modules:
[0028] Module M1: Analyze the environmental profile of complex mission orbits and disassemble typical orbital sections that require thermal simulation analysis;
[0029] Module M2: Conduct thermal simulation analysis on each typical orbit segment identified by module M1 in combination with the model’s working mode at that stage to obtain the thermal environment profile experienced by the satellite model product;
[0030] Module M3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in module M2, formulate the thermal environment assessment test items that need to be carried out for the product;
[0031] Module M4: Based on the extreme high temperature and holding time of the typical track section obtained by thermal simulation in module M2, formulate the test conditions for high temperature environment adaptability assessment and provide an accelerated test system;
[0032] Module M5: According to the hot and cold alternating temperature range and cycle times of different orbital sections obtained by thermal simulation in module M2, formulate the test conditions for the adaptability assessment of the hot and cold alternating environment, and provide an accelerated test system;
[0033] Module M6: Based on the extreme low temperature and holding time of the typical track section obtained by the thermal simulation of module M2, formulate the test conditions for the adaptability to extreme low temperature environment and provide an accelerated test system.
[0034] Preferably, the module M1 includes the following modules:
[0035] Module M1.1: Identify and set typical orbital segments for celestial bodies and typical orbital segments for celestial bodies according to the characteristics of orbital missions and traversal missions of deep space exploration models;
[0036] Module M1.2: Based on the orbit design of deep space exploration missions, identify the celestial body's leveraged orbital segments, set the celestial body's leveraged orbital segments with typical thermal environments as typical orbital segments, and identify the celestial body's leveraged typical orbital segments.
[0037] Preferably, the module M2 performs thermal simulation analysis on each typical orbital segment identified by the module M1 in combination with the working mode of the model at this stage, so as to obtain the thermal environment profile experienced by the satellite model product: including extremely high temperature, extremely low temperature, typical extreme temperature duration and number of hot and cold alternations.
[0038] Preferably, the module M4 performs a 1:1 assessment test on the high temperature gradient in the order of flight, and uses the temperature gradient and holding time obtained by simulation as the test conditions for the high temperature storage test of the product; without increasing the failure mechanism of the product, the equivalent screening stress intensity is used as the basis for the equivalent judgment of the accelerated test, and the high temperature storage accelerated screening calculation formula is as follows:
[0039] SS R =1-exp[-0.0017(R R +0.6) 0.6 t]
[0040] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours;
[0041] The module M5 conducts 1:1 assessment tests on different orbital segments in the order of flight, and uses the hot and cold alternating temperature range and cycle number of different orbital segments as the test conditions for the hot and cold alternating test of the product; the equivalent screening stress strength is used as the basis for the equivalent judgment of the accelerated test, and the calculation formula for hot and cold alternating accelerated screening is as follows:
[0042] SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N]
[0043] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; e is the natural logarithm;
[0044] The module M6 performs a 1:1 assessment test on the lowest temperature section in all task sections, and uses the extreme low temperature and holding time obtained by simulation as the test conditions for the low-temperature storage test of the product; the equivalent screening stress intensity is used as the basis for the equivalent judgment of the accelerated test, and the calculation formula for the low-temperature storage accelerated screening is as follows:
[0045] SS L =1-exp[-0.0017(R L +0.6) 0.6 t]
[0046] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
[0047] Compared with the prior art, the present invention has the following beneficial effects:
[0048] 1. The present invention provides a comprehensive assessment method for the thermal environment of complex mission orbits; it provides a reference for the thermal test assessment of deep space exploration models; it can also be applied to other satellite models with complex orbits.
[0049] 2. The present invention can effectively reduce the test time and reduce the test cost while ensuring the effectiveness of the thermal environment assessment;
[0050] 3. The present invention solves the difficult problem of "how to conduct sufficient and effective thermal environment adaptability assessment for products that experience extremely harsh thermal environments in deep space exploration under complex mission orbital profiles", and can provide a reference for the thermal environment adaptability assessment of Jupiter exploration models and subsequent deep space exploration models. BRIEF DESCRIPTION OF THE DRAWINGS
[0051] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:
[0052] Figure 1 It is a schematic diagram of the complex mission track of the present invention;
[0053] Figure 2 This is a schematic diagram of a high temperature gradient environment for thermal simulation of a typical mission track segment of the present invention;
[0054] Figure 3 This is a schematic diagram of the conditions for the extremely high temperature storage accelerated test of the present invention;
[0055] Figure 4 This is a schematic diagram of a hot and cold alternating temperature environment for thermal simulation of a typical mission track segment of the present invention;
[0056] Figure 5 This is a schematic diagram of the hot-cold alternating accelerated test conditions of the present invention;
[0057] Figure 6 It is a schematic diagram of the process of the present invention. DETAILED DESCRIPTION
[0058] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.
[0059] Embodiment 1:
[0060] Reference Figure 6 According to a method for evaluating the thermal environment adaptability of a complex mission track provided by the present invention, the method comprises the following steps:
[0061] Step S1: Analyze the environmental profile of the complex mission track and disassemble the typical track section that needs to be thermally simulated;
[0062] Step S1.1: According to the characteristics of the orbiting mission and the crossing mission of the deep space exploration model, identify and set the typical orbital segment of the celestial body and the typical orbital segment of the celestial body;
[0063] Step S1.2: According to the orbit design of the deep space exploration mission, identify the celestial body's leverage orbit segment, set the celestial body's leverage orbit segment with a typical thermal environment as a typical orbit segment, and identify the celestial body's leverage typical orbit segment.
[0064] Step S2: Conduct thermal simulation analysis on each typical orbit segment identified in step S1 in combination with the model’s working mode at this stage to obtain the thermal environment profile experienced by the satellite model product: including extreme high temperature, extreme low temperature, typical extreme temperature duration, and number of hot and cold alternations.
[0065] Step S3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in step S2, formulate the thermal environment assessment test items that need to be carried out for the product;
[0066] Step S4: According to the extreme high temperature and holding time of the typical track section obtained by thermal simulation in step S2, formulate the test conditions for high temperature environment adaptability assessment and provide the accelerated test method; carry out 1:1 assessment test on the high temperature temperature gradient in the flight sequence, and use the temperature gradient and holding time obtained by simulation as the test conditions for the product high temperature storage test; without increasing the product failure mechanism, use the equivalent screening stress intensity as the basis for the accelerated test equivalence judgment, and the high temperature storage accelerated screening calculation formula is as follows:
[0067] SS R =1-exp[-0.0017(R R+0.6) 0.6 t]
[0068] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours.
[0069] Step S5: According to the hot and cold alternating temperature ranges and the number of cycles of different orbital segments obtained by the thermal simulation in step S2, formulate the hot and cold alternating environmental adaptability assessment test conditions and provide the accelerated test method; conduct 1:1 assessment tests on different orbital segments in the order of flight, and use the hot and cold alternating temperature ranges and the number of cycles of different orbital segments as the test conditions for the hot and cold alternating test of the product; without increasing the failure mechanism of the product, use the equivalent screening stress strength as the basis for the accelerated test equivalence judgment, and the hot and cold alternating accelerated screening calculation formula is as follows:
[0070] SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N]
[0071] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; e is the natural logarithm;
[0072] Step S6: According to the extreme low temperature and holding time of the typical track section obtained by thermal simulation in step S2, formulate the test conditions for extreme low temperature environment adaptability assessment and provide the accelerated test method; conduct a 1:1 assessment test on the lowest temperature section in all mission sections, and use the extreme low temperature and holding time obtained by simulation as the test conditions for the product low temperature storage test; without increasing the product failure mechanism, use the equivalent screening stress intensity as the basis for the accelerated test equivalence judgment, and the low temperature storage accelerated screening calculation formula is as follows:
[0073] SS L =1-exp[-0.0017(R L +0.6) 0.6 t]
[0074] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
[0075] The present invention also provides a complex mission track thermal environment adaptability assessment system, which can be implemented by executing the process steps of the complex mission track thermal environment adaptability assessment method, that is, those skilled in the art can understand the complex mission track thermal environment adaptability assessment method as a preferred implementation of the complex mission track thermal environment adaptability assessment system.
[0076] Embodiment 2:
[0077] The present invention also provides a complex mission orbit thermal environment adaptability assessment system, the system comprising the following modules:
[0078] Module M1: Analyze the environmental profile of complex mission orbits and disassemble typical orbital sections that require thermal simulation analysis;
[0079] Module M1.1: Identify and set typical orbital segments for celestial bodies and typical orbital segments for celestial bodies according to the characteristics of orbital missions and traversal missions of deep space exploration models;
[0080] Module M1.2: Based on the orbit design of deep space exploration missions, identify the celestial body's leveraged orbital segments, set the celestial body's leveraged orbital segments with typical thermal environments as typical orbital segments, and identify the celestial body's leveraged typical orbital segments.
[0081] Module M2: Conduct thermal simulation analysis on each typical orbital segment identified by module M1 in combination with the model’s working mode at this stage to obtain the thermal environment profile experienced by the satellite model product: including extreme high temperature, extreme low temperature, typical extreme temperature duration and number of hot and cold alternations.
[0082] Module M3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in module M2, formulate the thermal environment assessment test items that need to be carried out for the product;
[0083] Module M4: According to the extreme high temperature and holding time of the typical track section obtained by the thermal simulation of module M2, the test conditions for high temperature environment adaptability assessment are formulated, and an accelerated test system is given; the high temperature temperature gradient is subjected to a 1:1 assessment test in the order of flight, and the temperature gradient and holding time obtained by simulation are used as the test conditions for the product high temperature storage test; without increasing the product failure mechanism, the equivalent screening stress intensity is used as the basis for the accelerated test equivalence judgment, and the high temperature storage accelerated screening calculation formula is as follows:
[0084] SS R =1-exp[-0.0017(R R +0.6) 0.6 t]
[0085] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours.
[0086] Module M5: According to the hot and cold alternating temperature range and number of cycles of different orbital segments obtained by thermal simulation of module M2, formulate the test conditions for the adaptability of the hot and cold alternating environment, and provide an accelerated test system; conduct 1:1 assessment tests on different orbital segments in the order of flight, and use the hot and cold alternating temperature range and number of cycles of different orbital segments as the test conditions for the hot and cold alternating test of the product; use the equivalent screening stress strength as the basis for the equivalent judgment of the accelerated test, and the calculation formula for hot and cold alternating accelerated screening is as follows:
[0087] SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N]
[0088] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; e is the natural logarithm;
[0089] Module M6: According to the extreme low temperature and holding time of the typical track section obtained by thermal simulation of module M2, formulate the test conditions for extreme low temperature environment adaptability assessment, and provide an accelerated test system; conduct a 1:1 assessment test on the lowest temperature section in all mission sections, and use the extreme low temperature and holding time obtained by simulation as the test conditions for the product low temperature storage test; use the equivalent screening stress intensity as the basis for the accelerated test equivalence judgment, and the low temperature storage accelerated screening calculation formula is as follows:
[0090] SS L =1-exp[-0.0017(R L +0.6) 0.6 t]
[0091] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
[0092] Embodiment 3:
[0093] The present invention provides a method for formulating the thermal environment adaptability assessment conditions for products under complex mission orbits of deep space exploration models, including: a method for formulating thermal environment adaptability assessment test items; test conditions and accelerated test methods for adaptability assessment in alternating hot and cold environments; test conditions and accelerated test methods for adaptability assessment in high temperature environments; and test conditions and accelerated test methods for adaptability assessment in extreme low temperature environments. The present invention solves the problem of "how to conduct a sufficient and effective thermal environment adaptability assessment for products that experience extremely harsh thermal environments in deep space exploration under complex mission orbit profiles", and can provide a reference for the thermal environment adaptability assessment of Jupiter exploration models and subsequent deep space exploration models.
[0094] A method for evaluating the thermal environment adaptability of a complex mission track provided by the present invention comprises the following steps:
[0095] Step 1: Analyze the environmental profile of the complex mission track and disassemble the typical track sections that need to be thermally simulated;
[0096] Step 2: Conduct thermal simulation analysis on each typical orbital segment to obtain the thermal environment profile experienced by the satellite model product: including extreme high temperature, extreme low temperature, duration of typical extreme temperature, number of hot and cold alternations, etc.
[0097] Step 3: According to the characteristics of the thermal environment profile experienced by the satellite model product, formulate the thermal environment assessment test items that the product needs to carry out: including hot and cold alternation, high temperature storage, and low temperature storage;
[0098] Step 4: Establish the test conditions for high temperature environment adaptability assessment and provide the accelerated test method;
[0099] Step 5: Establish the test conditions for adaptability to hot and cold alternating environments and provide accelerated test methods;
[0100] Step 6: Establish test conditions for extreme low temperature environment adaptability assessment and provide accelerated test methods.
[0101] Preferably, the test items may include hot and cold alternation, high temperature storage, and low temperature storage at the same time. It may not be limited to these three test items, or it may only include one or two of them, depending on the thermal environment profile. The hot and cold alternation test can be simulated one-to-one, or it can be accelerated screening. The high temperature storage test can be simulated one-to-one, or it can be accelerated screening. The low temperature storage test can be simulated one-to-one, or it can be accelerated screening.
[0102] Preferably, the thermal environments between different typical mission orbital segments are quite different: the temperature ranges may be very different, or the temperature characteristics may be completely different (for example, some typical orbits are mainly high-temperature environments, some typical orbits are mainly low-temperature environments, and some typical orbits have alternating hot and cold environments).
[0103] Preferably, depending on the product characteristics and tolerance, accelerated testing can be carried out according to the principle of equivalent screening to save testing time and cost.
[0104] Preferably, the thermal environment assessment of different typical tracks can be conducted in sections or through a comprehensive assessment using equivalent factors.
[0105] like Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, the complex mission orbit thermal environment adaptability assessment method provided by the present invention includes the following steps:
[0106] Step 1: Analyze the environmental profile of the complex mission track and disassemble the typical track sections that need to be thermally simulated;
[0107] Step 1.1: Reference Figure 1 The example mission orbit segment, according to the characteristics of the deep space exploration model orbiting mission and (or) crossing mission, identifies and sets the typical orbit segment of celestial body orbit and the typical orbit segment of crossing: Jupiter orbit segment and planetary crossing orbit segment.
[0108] Step 1.2: According to the orbit design of deep space exploration mission, identify the celestial body's leverage orbit segment, and set the celestial body's leverage orbit segment with typical thermal environment as the typical orbit segment, refer to Figure 1 For example, identify the typical orbital segments of celestial bodies using leverage: Venus's orbital segment and Jupiter's orbital segment.
[0109] Step 2: Conduct thermal simulation analysis on each typical orbit segment identified in step 1 in combination with the model’s working mode at this stage to obtain the thermal environment profile experienced by the satellite model product: including extreme high temperature, extreme low temperature, typical extreme temperature duration, number of hot and cold alternations, etc. Figure 2 Example of Venus's high temperature gradient temperature and duration, Figure 4 The results of two typical orbital thermal simulations are as follows: the full temperature range and number of cycles experienced by the product in the orbital section;
[0110] Step 3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in step 2, formulate the thermal environment assessment test items that the product needs to carry out. Figure 1 The thermal test assessment items of the complex mission deep space exploration model include hot and cold alternation, high temperature storage, and low temperature storage. The test assessment sequence is high temperature storage, hot and cold alternation, and low temperature storage.
[0111] Step 4: The extreme high temperature and holding time of the typical track section obtained by thermal simulation in step 2 are as follows: Figure 2 As shown, the high temperature temperature gradient is tested in 1:1 according to the flight sequence, and the temperature gradient and holding time obtained by simulation are used as the test conditions for the high temperature storage test of the product. Without increasing the failure mechanism of the product, the corresponding storage time can be reduced by increasing the high temperature and conducting accelerated tests. Taking the equivalent screening stress intensity as the basis for the equivalence judgment of the accelerated test, the high temperature storage accelerated screening calculation formula is as follows:
[0112] SS R =1-exp[-0.0017(R R +0.6) 0.6 t]
[0113] Where R Ris the difference between high temperature and room temperature (room temperature is generally 25°C); t is the duration of high temperature storage, in hours.
[0114] Figure 3 This is a schematic diagram of the high-temperature storage accelerated test conditions. Different storage temperature combinations correspond to different holding times. If further acceleration is required, the test temperature can be further increased, and the equivalent high-temperature holding time can be calculated according to the high-temperature storage accelerated screening calculation formula.
[0115] Step 5: The hot and cold alternating temperature range and cycle times of different orbital segments obtained by thermal simulation in step 2 are as follows: Figure 4 As shown, different orbital segments are subjected to 1:1 assessment tests in the order of flight, and the hot and cold alternating temperature range and number of cycles of different orbital segments are used as the test conditions for the hot and cold alternating test of the product. Without increasing the failure mechanism of the product, the hot and cold alternating temperature range can be widened to reduce the corresponding number of test cycles and carry out accelerated tests. The equivalent screening stress strength is used as the basis for the equivalence judgment of the accelerated test, and the calculation formula for hot and cold alternating accelerated screening is as follows:
[0116] SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N]
[0117] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; and e is the natural logarithm.
[0118] Figure 5 The schematic diagram of the hot-cold alternating accelerated test conditions is shown in Figure 2. Figure 4 The hot and cold alternating temperature range of the middle orbital section 1 is extended to be consistent with that of orbital section 2. After acceleration, the original 11 cycles of hot and cold alternation in orbital section 1 are reduced to 9 cycles, and the total number of cycles is 34. If further acceleration is required, the hot and cold alternating test temperature range can be further extended, and the equivalent number of cycles can be calculated according to the hot and cold alternating accelerated screening calculation formula.
[0119] Step 6: Based on the extreme low temperature and holding time of the typical track section obtained from the thermal simulation in step 2, conduct a 1:1 assessment test on the lowest temperature section in all mission sections, and use the extreme low temperature and holding time obtained from the simulation as the test conditions for the low-temperature storage test of the product. Without increasing the failure mechanism of the product, the corresponding storage time can be reduced by lowering the test temperature and conducting accelerated tests. Using the equivalent screening stress intensity as the basis for the equivalence judgment of the accelerated test, the calculation formula for the low-temperature storage accelerated screening is as follows:
[0120] SS L =1-exp[-0.0017(RL +0.6) 0.6 t]
[0121] Where R L It is the difference between room temperature and low temperature (room temperature is generally 25°C); t is the duration of low temperature storage, in hours.
[0122] Preferably, the test items may include hot and cold alternation, high temperature storage, and low temperature storage at the same time. It may not be limited to these three test items, but may only include one or two of them, depending on the thermal environment profile corresponding to the product.
[0123] Preferably, the thermal environments between different typical mission orbital segments are quite different: the temperature ranges may be very different, or the temperature characteristics may be completely different (for example, some typical orbits are mainly high-temperature environments, some typical orbits are mainly low-temperature environments, and some typical orbits have alternating hot and cold environments).
[0124] Preferably, depending on the product characteristics and tolerance, accelerated testing can be carried out according to the principle of equivalent screening to save testing time and cost.
[0125] Preferably, the thermal environment assessment of different typical tracks can be conducted in sections or through a comprehensive assessment using equivalent factors.
[0126] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1 and Embodiment 2.
[0127] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.
Claims
1. A method for assessing the adaptability of a complex mission orbit to a thermal environment, characterized in that: The method comprises the following steps: Step S1: Analyze the environmental profile of the complex mission track and disassemble the typical track section that needs to be thermally simulated; Step S2: Conduct thermal simulation analysis on each typical orbit segment identified in step S1 in combination with the model's working mode at this stage to obtain the thermal environment profile experienced by the satellite model product; Step S3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in step S2, formulate the thermal environment assessment test items that need to be carried out for the product; Step S4: According to the extreme high temperature and holding time of the typical track section obtained by the thermal simulation in step S2, the test conditions for high temperature environment adaptability assessment are formulated, and an accelerated test method is given; Step S5: According to the hot-cold alternating temperature range and the number of cycles of different orbital sections obtained by the thermal simulation in step S2, formulate the test conditions for the adaptability assessment of the hot-cold alternating environment, and provide an accelerated test method; Step S6: According to the extreme low temperature and holding time of the typical track section obtained by the thermal simulation in step S2, the test conditions for the extreme low temperature environment adaptability assessment are formulated, and the accelerated test method is given.
2. The method for assessing the thermal environment adaptability of complex mission orbits according to claim 1 is characterized in that: The step S1 comprises the following steps: Step S1.1: According to the characteristics of the orbiting mission and the crossing mission of the deep space exploration model, identify and set the typical orbital segment of the celestial body and the typical orbital segment of the celestial body; Step S1.2: According to the orbit design of the deep space exploration mission, identify the celestial body's leverage orbit segment, set the celestial body's leverage orbit segment with a typical thermal environment as a typical orbit segment, and identify the celestial body's leverage typical orbit segment.
3. The method for assessing the thermal environment adaptability of complex mission orbits according to claim 1 is characterized in that: In step S2, thermal simulation analysis is performed on each typical orbit segment identified in step S1 in combination with the working mode of the model at this stage to obtain the thermal environment profile experienced by the satellite model product: including extreme high temperature, extreme low temperature, typical extreme temperature duration and number of hot and cold alternations.
4. The method for evaluating the thermal environment adaptability of complex mission tracks according to claim 1 is characterized in that: In step S4, the high temperature temperature gradient is subjected to a 1:1 assessment test in sequence according to the flight order, and the temperature gradient and holding time obtained by simulation are used as the test conditions for the high temperature storage test of the product; without increasing the failure mechanism of the product, the equivalent screening stress intensity is used as the basis for the equivalent judgment of the accelerated test, and the high temperature storage accelerated screening calculation formula is as follows: SS R =1-exp[-0.0017(R R +0.6) 0.6 t] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours.
5. The method for assessing the thermal environment adaptability of complex mission orbits according to claim 1 is characterized in that: In step S5, different orbital segments are subjected to 1:1 assessment tests in sequence according to the flight order, and the hot and cold alternating temperature range and the number of cycles of different orbital segments are used as the test conditions of the hot and cold alternating test of the product; the equivalent screening stress strength is used as the basis for the accelerated test equivalence judgment, and the hot and cold alternating accelerated screening calculation formula is as follows: SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; and e is the natural logarithm.
6. The complex mission orbit thermal environment adaptability assessment method according to claim 1 is characterized in that: The step S6 performs a 1:1 assessment test on the lowest temperature section in all task sections, and uses the extreme low temperature and holding time obtained by simulation as the test conditions for the product low temperature storage test; Taking the equivalent screening stress intensity as the basis for judging the equivalence of the accelerated test, the calculation formula for low-temperature storage accelerated screening is as follows: SS L =1-exp[-0.0017(R L +0.6) 0.6 t] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
7. A complex mission orbit thermal environment adaptability assessment system, characterized in that: The system includes the following modules: Module M1: Analyze the environmental profile of complex mission orbits and disassemble typical orbital sections that require thermal simulation analysis; Module M2: Conduct thermal simulation analysis on each typical orbit segment identified by module M1 in combination with the model’s working mode at that stage to obtain the thermal environment profile experienced by the satellite model product; Module M3: According to the characteristics of the thermal environment profile experienced by the satellite model product identified in module M2, formulate the thermal environment assessment test items that need to be carried out for the product; Module M4: Based on the extreme high temperature and holding time of the typical track section obtained by thermal simulation in module M2, formulate the test conditions for high temperature environment adaptability assessment and provide an accelerated test system; Module M5: According to the hot and cold alternating temperature range and cycle times of different orbital sections obtained by thermal simulation in module M2, formulate the test conditions for the adaptability assessment of the hot and cold alternating environment, and provide an accelerated test system; Module M6: Based on the extreme low temperature and holding time of the typical track section obtained by the thermal simulation of module M2, formulate the test conditions for the adaptability to extreme low temperature environment and provide an accelerated test system.
8. The complex mission orbit thermal environment adaptability assessment system according to claim 7 is characterized in that: The module M1 includes the following modules: Module M1.1: Identify and set typical orbital segments for celestial bodies and typical orbital segments for celestial bodies according to the characteristics of orbital missions and traversal missions of deep space exploration models; Module M1.2: Based on the orbit design of deep space exploration missions, identify the celestial body's leveraged orbital segments, set the celestial body's leveraged orbital segments with typical thermal environments as typical orbital segments, and identify the celestial body's leveraged typical orbital segments.
9. The complex mission orbit thermal environment adaptability assessment system according to claim 7 is characterized in that: The module M2 performs thermal simulation analysis on each typical orbit segment identified by the module M1 in combination with the model's working mode at this stage, and obtains the thermal environment profile experienced by the satellite model product: including extremely high temperature, extremely low temperature, typical extreme temperature duration and number of hot and cold alternations.
10. The complex mission orbit thermal environment adaptability assessment system according to claim 7, characterized in that: The module M4 conducts a 1:1 assessment test on the high temperature gradient in the order of flight, and uses the temperature gradient and holding time obtained by simulation as the test conditions for the high temperature storage test of the product; without increasing the failure mechanism of the product, the equivalent screening stress intensity is used as the basis for the equivalent judgment of the accelerated test, and the high temperature storage accelerated screening calculation formula is as follows: SS R =1-exp[-0.0017(R R +0.6) 0.6 t] Where R R is the difference between high temperature and room temperature; t is the duration of high temperature storage, in hours; The module M5 conducts 1:1 assessment tests on different orbital segments in the order of flight, and uses the hot and cold alternating temperature range and cycle number of different orbital segments as the test conditions for the hot and cold alternating test of the product; the equivalent screening stress strength is used as the basis for the equivalent judgment of the accelerated test, and the calculation formula for hot and cold alternating accelerated screening is as follows: SS LR =1-exp[-0.0017(R+0.6) 0.6 (Ln(e+V)) 3 N] Where R is the temperature range in degrees Celsius; V is the temperature change rate in degrees Celsius per minute; N is the number of hot and cold alternations; e is the natural logarithm; The module M6 performs a 1:1 assessment test on the lowest temperature section among all task sections, and uses the extreme low temperature and holding time obtained by simulation as the test conditions for the product low temperature storage test; Taking the equivalent screening stress intensity as the basis for judging the equivalence of the accelerated test, the calculation formula for low-temperature storage accelerated screening is as follows: SS L =1-exp[-0.0017(R L +0.6) 0.6 t] Where R L is the difference between room temperature and low temperature; t is the duration of low temperature storage, in hours.
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