Analysis Method and System for Complex Thermal Flow Extreme Conditions of High-Orbit Satellites

Abstract

This invention provides a method and system for analyzing complex thermal flow extreme conditions of high-orbit satellites, including: Step S1: Establishing a satellite coordinate system and calculating the solar vector and Earth vector within the regression period based on given orbital parameter data and satellite attitude mode data; Step S2: Establishing the normal vector of the analysis object and calculating the dot product A of the solar vector and Earth vector at each moment; Step S3: Calculating the angle θ between the solar vector and Earth vector. s and the shielding angle α provided by the Earth e Step S4: Determine whether the satellite is in the shadow period or the illumination period; Step S5: Statistically analyze the external heat flow characteristic parameters of each orbital analysis object and their extreme values ​​and maximum values; The external heat flow characteristic parameters include the instantaneous value F of solar radiation heat flow and the average value F of the illumination period. i‑ave and the mean orbital period F o‑ave The method provided by this invention reduces the computational load of traversing operating conditions in the simulation model, saves time, improves work efficiency, and also saves costs.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically, to a method and system for analyzing complex thermal flux extreme operating conditions of high-orbit satellites. Background Technology

[0002] A high-orbit satellite operating in a highly elliptical Molniya orbit has an apogee of approximately 38,900 km, a perigee of approximately 550 km, an inclination of 62.8–65.5°, and an orbital period of approximately 12 hours. The satellite's orbital plane rotates slowly westward (approximately 0.13 degrees per day), while the sun moves eastward by an average of 1 degree per day. The presence of the obliquity of the ecliptic further complicates the variation of the angle (illuminance angle, β angle) between the highly elliptical orbital plane and the sun, resulting in a period of approximately 320 days, with the β angle variation curves not perfectly consistent between adjacent years.

[0003] The satellite has four operating modes, and the pattern of attitude change differs in each mode. This results in variations in the external heat flow throughout the year, and even between adjacent years, with a regression period of over eight years.

[0004] Due to the influence of orbital motion, solar motion, and attitude patterns, the external heat flow on the satellite's outer surface is complex. Using traditional traversal methods to screen for extreme external heat flow conditions is labor-intensive and time-consuming.

[0005] Chinese patent document CN114757040A discloses a method and system for microsatellite thermal balance testing, comprising: after the microsatellite undergoes a normal satellite mounting process, selecting a ground space environment simulator of appropriate size to conduct a vacuum thermal balance test; using a simplified initial model of thermal analysis to conduct a first simulation analysis of the microsatellite, shielding external heat flow, and obtaining a first simulation result; comparing the test result of the vacuum thermal balance test with the first simulation result, analyzing the temperature distribution difference, and judging the deviation between the test result and the thermal design result based on the temperature distribution difference; obtaining a thermal analysis correction simplified model based on the deviation between the test result and the thermal design result; conducting a second simulation analysis of the microsatellite, reloading external heat flow for simulation analysis, and obtaining a second simulation result. However, this method cannot solve the aforementioned problems. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for analyzing complex thermal flow under extreme operating conditions of high-orbit satellites.

[0007] A method for analyzing complex heat flow extreme conditions of high-orbit satellites according to the present invention includes:

[0008] Step S1: Establish the satellite's coordinate system and calculate the solar vector within the regression period based on the given orbital parameter data and satellite attitude mode data. and Earth vector

[0009] Step S2: Establish the normal vector of the object being analyzed on the satellite surface or star-sensitive shield. Calculate each time step and The dot product A;

[0010] Step S3: Calculate the solar vector With Earth Vector The angle θ between the Sun, Earth, and Planet s and the shielding angle α provided by the Earth e By comparing the sizes of the two, it can be determined whether the satellite is in the shadow period or the illumination period.

[0011] Step S4: Based on the dot product size calculated in Step S2 and the illumination and shading conditions calculated in Step S3, statistically analyze the external heat flow characteristic parameters of each track analysis object; the external heat flow characteristic parameters include the instantaneous value F of solar radiation heat flow and the average value F of the illumination period. i-ave and the mean orbital period F o-ave The extreme values ​​and maximum values ​​of external heat flow of the analyzed object within the statistical external heat flow regression period.

[0012] Preferably, the dot product

[0013] Preferably, when the dot product A is positive, it indicates that the surface is illuminated and the solar radiation intensity is proportional to it; when the dot product A is negative, it indicates that the surface is not illuminated and takes a value of 0.

[0014] Preferably, the method for calculating the angle between the sun, stars, and the earth is as follows:

[0015]

[0016] The method for calculating the shielding angle that the Earth can provide is as follows:

[0017] α e =arcsin(R) e / (R e +H));

[0018] In the formula R e Where is the Earth's radius and H is the satellite's orbital altitude.

[0019] Preferably, when θ s >α e At that time, the satellite was in its sunlight period; when θ s ≤α e At that time, the satellite was in the Earth's shadow period.

[0020] Preferably, the instantaneous value of solar radiation heat flux F = S e ·A, where Se is the solar constant.

[0021] Preferably, the average illumination period F i-ave The average solar radiation heat flux of the analyzed object within a single orbit during the illumination period is statistically analyzed; the mean orbital period F o-ave The average value of solar radiation heat flux of the analyzed object within one orbit is statistically analyzed.

[0022]

[0023]

[0024] In the formula, F m Let m be the instantaneous value of solar radiation heat flux at time m within the illumination period of orbit one, n be the total value of the satellite within orbit one during the illumination period, and k be the total value of the satellite within orbit one at each time.

[0025] Preferably, in the satellite attitude mode, the flight and pointing direction of the satellite is not parallel to any axis or forms a fixed angle.

[0026] Preferably, the extreme values ​​and maximum / minimum values ​​include: the instantaneous value of solar radiation heat flux F and the average value of the photoperiod F. i-ave and the mean orbital period F o-ave The maximum, minimum, maximum and minimum values ​​of .

[0027] A system for analyzing complex heat flow extreme conditions of high-orbit satellites according to the present invention includes:

[0028] Module M1: Establishes the satellite's coordinate system and calculates the solar vector within the regression period based on given orbital parameter data and satellite attitude mode data. and Earth vector

[0029] Module M2: Establishes the normal vector of the analysis object on the satellite surface or star-sensitive shield. Calculate each time step and The dot product A;

[0030] Module M3: Calculates the solar vector With Earth Vector The angle θ between the Sun, Earth, and Planet s and the shielding angle α provided by the Earth e By comparing the sizes of the two, it can be determined whether the satellite is in the shadow period or the illumination period.

[0031] Module M4: Based on the dot product size calculated by Module M2 and the illumination and shading conditions calculated by Module M3, statistically analyzes the external heat flow characteristic parameters of each track analysis object; the external heat flow characteristic parameters include the instantaneous value F of solar radiation heat flow and the average value F of the illumination period.i-ave and the mean orbital period F o-ave The extreme values ​​and maximum values ​​of external heat flow of the analyzed object within the statistical external heat flow regression period.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] 1. The method provided by this invention reduces the amount of calculation required for the simulation model to traverse working conditions, saves time, improves work efficiency, and also saves costs.

[0034] 2. The extreme and maximum values ​​of external heat flux per orbit within the regression period obtained by the method provided by this invention greatly narrow the screening range of extreme external heat flux conditions. Some specific conditions can be directly used as the screening basis for extreme conditions of the analysis object, and have a wide range of applications in the field of satellite technology.

[0035] Other beneficial effects of the present invention will be explained in detail through the introduction of specific technical features and technical solutions in specific embodiments. Those skilled in the art should be able to understand the beneficial technical effects brought about by these technical features and technical solutions through the introduction of these technical features and technical solutions. Attached Figure Description

[0036] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0037] Figure 1 This is a flowchart of the method for analyzing complex heat flow extreme conditions of high-orbit satellites in an embodiment of the present invention.

[0038] Figure 2 This is a schematic diagram of a high-orbit satellite configuration and the normal unit vector of each side in an embodiment of the present invention.

[0039] Figure 3 This is a schematic diagram of the maximum external heat flow condition on the Y side of the satellite in an embodiment of the present invention.

[0040] Figure 4 This is a schematic diagram of the extreme high-temperature operating conditions of a single unit on the Y-side of the satellite in an embodiment of the present invention.

[0041] Figure 5 This is a schematic diagram of a light shield and pointing unit vector for a high-orbit satellite onboard sensor, as described in an embodiment of the present invention.

[0042] Figure 6 This is a schematic diagram of the maximum heat flux from solar radiation incident on the satellite star-sensor shield in an embodiment of the present invention. Detailed Implementation

[0043] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0044] Reference Figure 1 As shown, this invention provides a method for analyzing complex thermal flux extreme operating conditions of high-orbit satellites, including:

[0045] Step S1: Establish the satellite's coordinate system and calculate the solar vector within the regression period based on the given orbital parameter data and satellite attitude mode data. and Earth vector In satellite attitude mode, the satellite's flight and pointing direction are not parallel to any axis or form a fixed angle.

[0046] Satellites fly in high Earth orbits (H≥30000km), commonly including geostationary orbits and highly elliptical Molniya orbits. Satellites in high orbits experience low levels of Earth's albedo and infrared heat flux (<10W / m²). 2 Compared to the negligible heat flow from solar radiation, the angle between the satellite surface and the orbital plane varies with orbital altitude and Earth-Sun distance, resulting in poor repeatability of external heat flow and a long regression period.

[0047] Step S2: Establish the normal vector of the object being analyzed on the satellite surface or star-sensitive shield. Calculate each time step and The dot product A, When the dot product A is positive, it indicates that the surface is illuminated and the intensity of sunlight is proportional to it; when the dot product A is negative, it indicates that the surface is not illuminated and takes the value of 0.

[0048] Step S3: Calculate the solar vector With Earth Vector The angle θ between the Sun, Earth, and Planet s and the shielding angle α provided by the Earth e By comparing the sizes of the two, it can be determined whether the satellite is in the shadow period or the illumination period.

[0049] The method for calculating the angle between the Sun, Star, and Earth is as follows:

[0050]

[0051] The method for calculating the angle of shelter that the Earth can provide is as follows:

[0052] α e =arcsin(R) e / (Re +H));

[0053] In the formula R e Where is the Earth's radius and H is the satellite's orbital altitude.

[0054] When θ s >α e At that time, the satellite was in its sunlight period; when θ s ≤α e At that time, the satellite was in the Earth's shadow period.

[0055] Step S4: Based on the dot product size calculated in Step S2 and the illumination and shading conditions calculated in Step S3, first calculate the external heat flow characteristic parameters of each analysis object: instantaneous value of solar radiation heat flow F, mean value of illumination period F i-ave and the mean orbital period F o-ave Then, the extreme and maximum values ​​of the external heat flow of the analyzed object within the external heat flow regression period are statistically analyzed; the extreme and maximum values ​​include: the instantaneous value F of solar radiation heat flow and the mean value F of the illumination period. i-ave and the mean orbital period F o-ave The maximum, minimum, maximum and minimum values ​​of .

[0056] Wherein, the instantaneous value of solar radiation heat flux F = S e ·A, where S e The solar constant can be taken as 1322 W / m under low-temperature conditions. 2 For high-temperature operating conditions, 1414W / m can be used. 2 .

[0057] Mean of photoperiod F i-ave The average value of solar radiation heat flux and the average orbital period F of the analyzed object within a single orbit during the illumination period are statistically analyzed. o-ave The average solar radiation heat flux of the analyzed object within one orbit is statistically analyzed, and:

[0058]

[0059]

[0060] In the formula, F m Let m be the instantaneous value of solar radiation heat flux at time m within the illumination period of orbit one, n be the total value of the satellite within orbit one during the illumination period, and k be the total value of the satellite within orbit one at each time.

[0061] The method described above, which obtains the extreme and maximum values ​​of external heat flux for each orbit within the regression period, significantly narrows the range of extreme operating conditions for external heat flux. Some specific operating conditions can be directly used as the basis for selecting extreme operating conditions for the analysis object. For example, the operating conditions with the maximum and minimum instantaneous values ​​of solar radiation heat flux can be used as extreme high and low temperature operating conditions for analyzing objects with small heat capacity and light-sensitive components. The operating conditions with the maximum and minimum average values ​​of solar radiation heat flux during the illumination period and the average values ​​of the orbital period can be used as extreme high and low temperature operating conditions for analyzing objects with large heat capacity single units or a certain part of a star.

[0062] The above are the basic embodiments of the present invention. The technical solution of the present invention will be further described below through two preferred embodiments.

[0063] Example 1:

[0064] This embodiment provides a case study of external heat flow analysis on the surface of a high-orbit satellite, specifically including:

[0065] Reference Figure 2 As shown, the satellite has a cubic structure and operates in a highly elliptical Molniya orbit with an apogee of approximately 38,000 km, a perigee of approximately 1,000 km, an inclination of 63°, and an orbital period of approximately 12 hours. During flight, it exhibits various attitude modes, and traditional extreme condition analysis methods, such as those for winter and summer solstices, spring and autumn equinoxes, and maximum and minimum illumination angles, are no longer applicable. Calculating the extraorbital heat flux and satellite temperature level using an ergonomic method would be extremely time-consuming.

[0066] The satellite spends a significant portion of its time in high-Earth orbit, with approximately 10% of its total flight time in low-Earth orbit. During this period, it experiences lower levels of Earth's albedo and infrared heat flux, making it suitable for the method described in this invention, as follows:

[0067] Step 1: Establish the satellite's body coordinate system. Given the orbital parameters and satellite attitude mode, calculate the vectors of the Sun and Earth in the satellite's body coordinate system during the return cycle. For example:

[0068] 0 1023 -0.58 0 -0.812 0 0 1 720 2346 -0.04 0 -0.999 0 0 1 1440 4822 -0.14 0 -0.99 0 0 1 2160 7568 -0.42 0 -0.907 0 0 1 2880 10260 -0.6 0 -0.801 0 0 1 3600 12804 -0.71 0 -0.701 0 0 1 4320 15181 -0.79 0 -0.612 0 0 1 5760 19445 -0.89 0 -0.462 0 0 1 7200 23124 -0.94 0 -0.343 0 0 1 8640 26294 -0.96 0 -0.274 0 0 1 10080 29016 -0.3 0.44 -0.85 0 0 1 11520 31335 -0.4 0.45 -0.797 0 0 1 12960 33286 -0.5 0.44 -0.745 0 0 1 14400 34896 -0.59 0.41 -0.694 0 0 1 15840 36184 -0.67 0.37 -0.645 0 0 1 17280 37164 -0.74 0.31 -0.596 0 0 1 18720 37848 -0.8 0.23 -0.548 0 0 1 20160 38243 -0.85 0.15 -0.5 0 0 1 21600 38352 -0.89 0.06 -0.451 0 0 1 23040 38177 -0.92 -0.04 -0.401 0 0 1 24480 37715 -0.93 -0.14 -0.35 0 0 1 25920 36963 -0.92 -0.24 -0.296 0 0 1 27360 35912 -0.91 -0.33 -0.24 0 0 1 28800 34551 -0.89 -0.42 -0.179 0 0 1 30240 32864 -0.86 -0.51 -0.113 0 0 1 31680 30830 -0.82 -0.58 -0.041 0 0 1 33120 28421 -0.77 -0.64 -0.041 0 0 1 34560 25599 -0.18 0 0.984 0 0 1 36000 22317 -0.08 0 0.997 0 0 1 37440 18509 0.03 0 0.999 0 0 1 38880 14097 0.09 0 0.995 0 0 1 39600 11641 0.03 0 0.9999 0 0 1 40320 9023 -0.12 0 0.993 0 0 1 41040 6286 -0.35 0 0.937 0 0 1 41760 3600 -0.67 0 0.745 0 0 1 42480 1510 -0.96 0 0.281 0 0 1 43200 1000 -0.68 0 -0.73 0 0 1

[0069] Step 2: Establish the normal unit vector of the satellite surface (six sides) in the satellite body coordinate system. The surface facing outwards is positive. The normal unit vector of surface ABCD. The unit normal vector of surface ABB'A' is (0,0,1). The unit normal vector of plane A'B'C'D' is (-1,0,0). The unit normal vector of surface DCC'D' is (0,0,-1). The unit normal vector of plane BCC'B is (1,0,0). The unit normal vector of the surface ADD'A', which is (0, -1, 0). The value is (0,1,0).

[0070] Step 3: Calculate the dot product A of the solar vector and each side surface at each moment, which is the projection of the solar vector onto the normal vector of the side surface: Negative values ​​are taken as 0. For example:

[0071] 0 1023 0 0.58 0.812 0 0 0 720 2346 0 0.04 0.999 0 0 0 1440 4822 0 0.14 0.99 0 0 0 2160 7568 0 0.42 0.907 0 0 0 2880 10260 0 0.6 0.801 0 0 0 3600 12804 0 0.71 0.701 0 0 0 4320 15181 0 0.79 0.612 0 0 0 5760 19445 0 0.89 0.462 0 0 0 7200 23124 0 0.94 0.343 0 0 0 8640 26294 0 0.96 0.274 0 0 0 10080 29016 0 0.3 0.85 0 0 0.44 11520 31335 0 0.4 0.797 0 0 0.45 12960 33286 0 0.5 0.745 0 0 0.44 14400 34896 0 0.59 0.694 0 0 0.41 15840 36184 0 0.67 0.645 0 0 0.37 17280 37164 0 0.74 0.596 0 0 0.31 18720 37848 0 0.8 0.548 0 0 0.23 20160 38243 0 0.85 0.5 0 0 0.15 21600 38352 0 0.89 0.451 0 0 0.06 23040 38177 0 0.92 0.401 0 0.04 0 24480 37715 0 0.93 0.35 0 0.14 0 25920 36963 0 0.92 0.296 0 0.24 0 27360 35912 0 0.91 0.24 0 0.33 0 28800 34551 0 0.89 0.179 0 0.42 0 30240 32864 0 0.86 0.113 0 0.51 0 31680 30830 0 0.82 0.041 0 0.58 0 33120 28421 0 0.77 0.041 0 0.64 0 34560 25599 0.984 0.18 0 0 0 0 36000 22317 0.997 0.08 0 0 0 0 37440 18509 0.999 0 0 0.03 0 0 38880 14097 0.995 0 0 0.09 0 0 39600 11641 0.9999 0 0 0.03 0 0 40320 9023 0.993 0.12 0 0 0 0 41040 6286 0.937 0.35 0 0 0 0 41760 3600 0.745 0.67 0 0 0 0 42480 1510 0.281 0.96 0 0 0 0 43200 1000 0 0.68 0.73 0 0 0

[0072] Step 4: Calculate the angle θ between the Sun's vector and the Earth's vector. s And the angle of shelter α that the Earth can provide. e By comparing the sizes of the two, it can be determined whether the satellite is in its shadow or illumination period. For example:

[0073]

[0074]

[0075] Step 5: Based on the illumination and shadow conditions calculated in Step 3 and Step 4, statistically analyze the external heat flow characteristic parameters of each orbital side: instantaneous value of solar radiation heat flow, average value of illumination period, and average value of orbital period.

[0076]

[0077] Step 6: Statistically analyze the instantaneous values, average values ​​of solar radiation heat flow, average values ​​of the illumination period, and average values ​​of the orbital period for each side of each orbital surface within the regression period.

[0078] Through the above filtering steps, the 1.31 million rows of satellite external heat flux data can be reduced to more than 7,000 orbits of external heat flux data. Furthermore, by statistically analyzing the maximum and minimum values ​​of the external heat flux characteristic parameters on each side of each orbit, the data can be further reduced to approximately 23 rows of external heat flux data. Combined with the satellite configuration, simulation modeling calculations can quickly obtain the satellite's extreme operating conditions under certain circumstances.

[0079] For example, refer to Figure 3 and Figure 4 As shown, a simulation model was established to calculate and obtain the single-unit temperature data under these maximum operating conditions, thereby further obtaining the external heat flow of the single unit under extreme high-temperature operating conditions on the satellite-Y side.

[0080] Under certain specific conditions, the operating condition that yields the maximum external heat flow of the object being analyzed can be directly taken as the extreme operating condition.

[0081] Example 2:

[0082] This embodiment provides a case study for analyzing the maximum heat flux of incident solar radiation on the star sensor shield of a high-orbit satellite, specifically including:

[0083] Reference Figure 5 As shown, to obtain the maximum heat flux from incident solar radiation through the sunshade, the steps are as follows:

[0084] Step 1: Establish the satellite's body coordinate system. Given the orbital parameters and satellite attitude mode, calculate the vectors of the Sun and Earth in the satellite's body coordinate system during the return cycle. For example:

[0085]

[0086]

[0087] Step 2: Establish the normal unit vector of the star sensor shield in the satellite's body coordinate system. For example: the pointing unit vector of star-sensitive shield ST1 The pointing unit vector of the star-sensitive shield ST2 is (0.98, -0.14, -0.16). The pointing unit vector of the star-sensitive shield ST3 is (0.57, 0.82, -0.09). The values ​​are (0.62, 0.28, -0.74).

[0088] Step 3: Calculate the dot product A of the solar vector and the star-sensor shading vector at each moment, taking 0 for negative values. For example:

[0089]

[0090]

[0091] The fourth step is to calculate the angle θ between the Sun's vector and the Earth's vector. s And the angle of shelter α that the Earth can provide. e By comparing the sizes of the two, it can be determined whether the satellite is in its shadow or illumination period. For example:

[0092]

[0093]

[0094] Step 5: Based on the illumination and shadow conditions calculated in Steps 3 and 4, calculate the instantaneous value of solar radiation heat flux for each star-sensor shield.

[0095] 1 Instantaneous value maximum 0.117152 0.262436 0.717775 ...

[0096] Step 6: Calculate the maximum instantaneous value of solar radiation heat flux outside the star-sensor shield for each orbit within the regression period.

[0097] Reference Figure 6As shown, the maximum value represents the maximum heat flux from solar radiation incident on the star-sensor shield.

[0098] The optical components of the star sensor are sensitive to sunlight. The smaller the angle between the star sensor and the star sensor's sunshade, the greater the solar radiation heat flux entering the star sensor's light inlet. Therefore, the maximum instantaneous value can be defined as the operating condition with the maximum solar radiation heat flux entering the star sensor's sunshade. Based on the initially selected external heat flux condition, a corresponding simulation model can be established to determine whether the optical components inside the star sensor's sunshade are exposed to sunlight.

[0099] The present invention also provides a system for analyzing complex heat flow extreme conditions of high-orbit satellites. The system can be implemented by executing the process steps of the method for analyzing complex heat flow extreme conditions of high-orbit satellites. That is, those skilled in the art can understand the method for analyzing complex heat flow extreme conditions of high-orbit satellites as a preferred embodiment of the system for analyzing complex heat flow extreme conditions of high-orbit satellites.

[0100] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for analyzing complex heat flow extreme conditions of high-orbit satellites, characterized in that, include: Step S1: Establish the satellite's coordinate system and calculate the solar vector within the regression period based on the given orbital parameter data and satellite attitude mode data. and Earth vector Step S2: Establish the normal vector of the object being analyzed on the satellite surface or star-sensitive shield. Calculate each time step and The dot product A; Step S3: Calculate the solar vector With Earth Vector The angle θ between the Sun, Earth, and Planet s and the shielding angle α provided by the Earth e By comparing the sizes of the two, it can be determined whether the satellite is in the shadow period or the illumination period. Step S4: According to the dot product size calculated in step S2 and the lighting shadow condition calculated in step S3, the external heat flow characteristic parameters of the analysis object of each track are counted; the external heat flow characteristic parameters include the instantaneous value of solar radiation heat flow F, the periodic mean value of light F i-ave and the track periodic mean value F o-ave ; The extreme value and the extreme value of the external heat flow of the analysis object in the regression period are counted.

2. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, The dot product 3. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, When the dot product A is positive, it indicates that the surface is illuminated and the intensity of sunlight is proportional to it; when the dot product A is negative, it indicates that the surface is not illuminated and takes the value of 0.

4. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, The method for calculating the angle between the sun, stars, and the earth is as follows: The method for calculating the shielding angle that the Earth can provide is as follows: α e =arcsin(R e / (R e +H)); In the formula R e Where is the Earth's radius and H is the satellite's orbital altitude.

5. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, When θ s >α e At that time, the satellite was in its sunlight period; when θ s ≤α e At that time, the satellite was in the Earth's shadow period.

6. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, The instantaneous value of solar radiation heat flux F = S e ·A, where S e is the solar constant.

7. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, The average value of the illumination period F i-ave The average solar radiation heat flux of the analyzed object within a single orbit during the illumination period is statistically analyzed; the mean orbital period F o-ave The average value of solar radiation heat flux of the analyzed object within one orbit is statistically analyzed. In the formula, F m Let m be the instantaneous value of solar radiation heat flux at time m within the illumination period of orbit one, n be the total value of the satellite within orbit one during the illumination period, and k be the total value of the satellite within orbit one at each time.

8. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, In the satellite attitude mode, the satellite's flight and pointing direction are not parallel to any axis or form a fixed angle.

9. The method for analyzing complex heat flow extreme conditions of high-orbit satellites according to claim 1, characterized in that, The extreme values ​​and maximum / minimum values ​​include: the instantaneous value of solar radiation heat flux F and the average value of the photoperiod F. i-ave and the mean orbital period F o-ave The maximum, minimum, maximum and minimum values ​​of .

10. A system for analyzing complex heat flow under extreme operating conditions of high-orbit satellites, characterized in that, include: Module M1: Establishes the satellite's coordinate system and calculates the solar vector within the regression period based on given orbital parameter data and satellite attitude mode data. and Earth vector Module M2: Establishes the normal vector of the analysis object on the satellite surface or star-sensitive shield. Calculate each time step and The dot product A; Module M3: Calculates the solar vector With Earth Vector The angle θ between the Sun, Earth, and Planet s and the shielding angle α provided by the Earth e By comparing the sizes of the two, it can be determined whether the satellite is in the shadow period or the illumination period. Module M4: Based on the dot product size calculated by Module M2 and the illumination and shading conditions calculated by Module M3, statistically analyzes the external heat flow characteristic parameters of each track analysis object; the external heat flow characteristic parameters include the instantaneous value F of solar radiation heat flow and the average value F of the illumination period. i-ave and the mean orbital period F o-ave The extreme values ​​and maximum values ​​of external heat flow of the analyzed object within the statistical external heat flow regression period.

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