A star sensor aberration compensation method

Abstract

This invention relates to the field of optical skewing compensation technology, and particularly to a method for optical skewing compensation of a star sensor. The method includes: acquiring at least three sets of Earth's center-of-mass velocities injected from the ground that are closest to the current time at a set time, to calculate the Earth's center-of-mass velocity at the current time; wherein the Earth's center-of-mass velocity is the Earth's center-of-mass velocity corresponding to the set time in the J2000 coordinate system, periodically injected according to an astronomical almanac; calculating the satellite velocity at the current time based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein the GPS measurement period is longer than the update period of the optical skewing compensation amount; and calculating the optical skewing compensation amount at the current time based on the Earth's center-of-mass velocity and the satellite velocity. This solution not only improves the accuracy of the Earth's center-of-mass velocity, enabling the optical skewing compensation amount calculation to meet the optical skewing compensation requirements of sub-arcsecond star sensors, but also avoids significantly consuming onboard processor storage resources.

Description

Technical Field

[0001] This invention relates to the field of optical aberration compensation technology, and in particular to a method for optical aberration compensation of a star sensor. Background Technology

[0002] Star sensor skewing aberration compensation requires the Earth's center of mass velocity. Traditional star sensor skewing aberration compensation methods use the Earth's fixed velocity in the heliocentric ecliptic inertial frame, i.e., [0, -29.8, 0] km / s, which fails to reflect the annual variation of the Earth's orbital velocity, resulting in significant real-time errors. Furthermore, the fixed velocity needs to be converted from the heliocentric ecliptic inertial frame to the geocentric equatorial inertial frame (i.e., the J2000 coordinate system). This conversion requires the Earth's center of mass position, which in turn requires parameters such as the Earth's orbital argument around the Sun. Since the calculation of these parameters is not very precise, the total error introduced by these two factors can reach hundreds of meters per second, which is completely unacceptable for the skewing aberration compensation requirements of subarcsecond star sensors.

[0003] Therefore, a new method for compensating for optical aberration in star sensors is urgently needed. Summary of the Invention

[0004] To address the problem that traditional star sensor optical aberration compensation methods have poor accuracy and cannot meet the attitude determination requirements of sub-arcsecond star sensors, this invention provides a star sensor optical aberration compensation method.

[0005] In a first aspect, embodiments of the present invention provide a method for compensating for optical aberration in a star sensor, comprising:

[0006] Obtain at least three sets of Earth's center of mass velocities injected from the ground that are closest to the current time at a set time, in order to calculate the Earth's center of mass velocity at the current time; wherein, the Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system according to the periodic injection of the astronomical calendar.

[0007] The satellite velocity at the current moment is calculated based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein the GPS measurement period is longer than the update period of the optical aberration compensation.

[0008] Calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity.

[0009] Secondly, embodiments of the present invention also provide a star sensor optical aberration compensation device, comprising:

[0010] The first calculation unit is used to obtain at least three sets of Earth's center of mass velocities injected from the ground that are closest to the set time and the current time, so as to calculate the Earth's center of mass velocity at the current time; wherein, the Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system according to the periodic injection of the astronomical calendar.

[0011] The second calculation unit is used to calculate the satellite velocity at the current moment based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein the GPS measurement period is greater than the update period of the optical aberration compensation.

[0012] The calculation unit is used to calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity at the current moment.

[0013] This invention provides a method for compensating for skewing aberration in a star sensor. It can calculate the Earth's center of mass velocity at each moment based on the highest known accuracy of the Earth's center of mass velocity input from the ground (i.e., the Earth's center of mass velocity published in the astronomical almanac). Since the update cycle for the skewing aberration compensation is short, using ground-injected Earth's center of mass velocity for every moment would consume a large amount of storage resources from the satellite's onboard processor. Therefore, this solution not only improves the accuracy of the Earth's center of mass velocity, enabling the calculation accuracy of the skewing aberration compensation to meet the skewing aberration compensation requirements of sub-arcsecond star sensors, but also avoids consuming a large amount of storage resources from the onboard processor. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a flowchart of a star sensor optical aberration compensation method provided in an embodiment of the present invention;

[0016] Figure 2 It is the deviation of the Earth's center of mass velocity calculated using a fixed velocity.

[0017] Figure 3 This is an embodiment of the present invention providing the Earth's center of mass velocity deviation calculated using an interpolation method;

[0018] Figure 4 This is an example of the effect of star sensor orientation determination using the method of the present invention, provided in an embodiment of the present invention;

[0019] Figure 5 This is a hardware architecture diagram of a computing device provided in an embodiment of the present invention;

[0020] Figure 6 This is a structural diagram of a star sensor optical aberration compensation device provided in an embodiment of the present invention. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0022] As mentioned earlier, traditional star sensor optical aberration compensation methods use a fixed Earth mass center velocity and require coordinate system transformation. This transformation introduces numerous inaccurate parameters, such as the Earth's orbital argument around the Sun. Therefore, due to the inaccuracy of the Earth mass center velocity, traditional star sensor optical aberration compensation methods cannot meet the optical aberration compensation requirements of subarcsecond star sensors.

[0023] To address the aforementioned technical issues, the inventors considered periodically injecting the Earth's center of mass velocity in the J2000 coordinate system based on an astronomical almanac. Since the error in the Earth's center of mass velocity published by the astronomical almanac can reach hundreds of meters per second, and the Earth's center of mass velocity for the next few years has already been predicted, compared to the traditional method using a fixed velocity, this not only avoids the errors caused by using a fixed velocity but also avoids the errors introduced by coordinate system transformation, thus significantly improving the calculation accuracy of the Earth's center of mass velocity. Furthermore, the update cycle of the difference compensation is relatively short. If the Earth's center of mass velocity at every moment were injected from the ground, it would occupy a large amount of onboard storage space, without utilizing onboard computation. Therefore, the inventors considered calculating the Earth's center of mass velocity at each moment based on at least three sets of Earth's center of mass velocities injected from the ground that are closest to the set time and the current time. In summary, this solution not only improves the accuracy of the Earth's center of mass velocity, enabling the calculation accuracy of the optical aberration compensation to meet the optical aberration compensation requirements of sub-arcsecond star sensors, but also does not consume a large amount of onboard processor storage resources.

[0024] The specific implementation of the above concept is described below.

[0025] Please refer to Figure 1 This invention provides a method for compensating for optical line aberration in a star sensor, the method comprising:

[0026] Step 100: Obtain at least three sets of Earth's center of mass velocities injected from the ground that are closest to the set time and the current time, so as to calculate the Earth's center of mass velocity at the current time; wherein, the Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system according to the periodic injection of the astronomical calendar.

[0027] Step 102: Calculate the current satellite velocity based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein, the GPS measurement period is longer than the update period of the optical aberration compensation.

[0028] Step 104: Calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity.

[0029] In this embodiment of the invention, the Earth's center of mass velocity at each moment can be calculated based on the highest known precision Earth's center of mass velocity input from the ground (i.e., the Earth's center of mass velocity published in the astronomical almanac). Since the update cycle of the optical aberration compensation is short, if the Earth's center of mass velocity at each moment is injected from the ground, it will occupy a large amount of storage resources of the satellite's onboard processor. Therefore, this solution can not only improve the accuracy of the Earth's center of mass velocity to meet the optical aberration compensation requirements of the sub-arcsecond star sensor, but also avoid occupying a large amount of storage resources of the onboard processor.

[0030] For step 100:

[0031] In some implementations, step 100 may include:

[0032] Obtain at least three sets of Earth's center-of-mass velocities injected from the ground that are closest to the current time at a set time;

[0033] If at least three sets are obtained, the interpolation method is used to calculate the Earth's center of mass velocity at the current moment based on the three sets of Earth's center of mass velocities and the set time corresponding to each set of Earth's center of mass velocities.

[0034] If fewer than three sets are obtained, the Earth's center-of-mass velocity closest to the current moment is taken as the Earth's center-of-mass velocity at the current moment.

[0035] In this embodiment, when using interpolation to estimate the Earth's center of mass velocity at the current moment, at least three known Earth's center of mass velocities at other times are required. In order to improve the estimation accuracy of the Earth's center of mass velocity at the current moment, it is necessary to obtain at least three sets of Earth's center of mass velocities injected from the ground at the set time that are closest to the current time.

[0036] In some implementations, a set of Earth's center of mass velocities is injected into the ground each day, and the set time corresponding to the injected set of Earth's center of mass velocities on that day is 0:00 of the next day.

[0037] In this embodiment, due to the short update cycle of the optical aberration compensation (8 times per second), it is evident that injecting the Earth's center of mass velocity at every moment from the ground would result in an extremely large quantity. Therefore, one set of Earth's center of mass velocities can be injected daily. Furthermore, if the Earth's center of mass velocity at midnight of the current day is injected, the three sets of Earth's center of mass velocities obtained from the ground injection would only be those from midnight the day before yesterday, midnight yesterday, and midnight today. Therefore, using interpolation to calculate the Earth's center of mass velocity for each subsequent moment of the day would be extrapolation prediction with low accuracy. Therefore, the set time corresponding to the set of Earth's center of mass velocities injected that day can be midnight of the next day. Then, using interpolation to calculate the Earth's center of mass velocity for each subsequent moment of the day, the set times corresponding to the three known sets of Earth's center of mass velocities can cover every moment of the day, resulting in higher accuracy. If calculating the Earth's center of mass velocities for the previous two days on the satellite, and only one or two sets of Earth's center of mass velocities are injected from the ground, making it impossible to obtain three sets, then the set of Earth's center of mass velocities closest to the current moment is taken as the Earth's center of mass velocity for the current moment.

[0038] It should be noted that each set of Earth's center-of-mass velocity data represents three-dimensional data at a single moment, V. earth =[V earthx V earthy V earthz ] T , where x, y and z are the three coordinate axes of the J2000 coordinate system.

[0039] It is understandable that the ground can inject three days' worth of Earth's center of mass velocity each time, with the set times corresponding to the three days' worth of Earth's center of mass velocity being yesterday's 00:00, today's 00:00, and tomorrow's 00:00 respectively. The injection cycle can be determined according to the situation, and the number of sets of Earth's center of mass velocity injected each time can also be determined according to the situation. The set time can also be 12 o'clock or other time points.

[0040] In this embodiment of the invention, the interpolation method is Lagrange interpolation. Linear interpolation can also be used, but Lagrange interpolation calculates the Earth's center of mass velocity at the current moment with low computational complexity and high efficiency. Since the rate of change of satellite and Earth's flight velocity is relatively low, Lagrange interpolation can obtain highly accurate calculation results.

[0041] Regarding step 102:

[0042] In some implementations, step 102 may include:

[0043] Obtain at least three sets of satellite velocities in the J2000 coordinate system that are closest to the current time at the corresponding time;

[0044] If at least three sets are obtained, the satellite velocity at the current moment is extrapolated using interpolation based on the three sets of satellite velocities and the corresponding time of each set of satellite velocities.

[0045] If fewer than three sets are obtained, the satellite velocity closest to the current moment is taken as the satellite velocity at the current moment.

[0046] In this embodiment, the GPS measurement cycle is generally once per second, which is longer than the optical aberration compensation update of 8 times per second. Therefore, interpolation is required to calculate the satellite velocities needed for the remaining 7 updates based on the satellite velocities in the J2000 coordinate system of the previous three seconds. Since GPS is a real-time measurement, the three sets of satellite velocities in the J2000 coordinate system obtained from GPS measurements can only be data from the previous two seconds, the previous second, and the current second. Therefore, using interpolation to calculate the satellite velocity at each moment of the current second is extrapolation prediction.

[0047] It should be noted that the velocity data for each satellite group is three-dimensional data at a single moment, V sat =[V satx V saty V satz ] T , where x, y and z are the three coordinate axes of the J2000 coordinate system.

[0048] It's understandable; GPS can take a measurement once per second or multiple times per second.

[0049] In this embodiment of the invention, the interpolation method is Lagrange interpolation. Linear interpolation can also be used, but Lagrange interpolation calculates the satellite velocity at the current moment with less computation and higher efficiency. Since the rate of change of satellite and Earth's flight velocity is relatively low, Lagrange interpolation can obtain highly accurate calculation results.

[0050] Regarding step 104:

[0051] In some implementations, step 104 may include:

[0052] Calculate the total velocity of the satellite in the J2000 coordinate system based on the current velocity of the Earth's center of mass and the satellite's velocity.

[0053] Based on the satellite's total velocity in the J2000 coordinate system, the optical aberration compensation amount at the current moment is calculated. In this embodiment of the invention, the optical aberration compensation amount at the current moment is estimated using the following formula:

[0054] v = V earth +V sat

[0055]

[0056] In the formula, v is the total velocity of the satellite in the J2000 coordinate system, and V earthLet V be the velocity of Earth's center of mass at the current moment. sat γ represents the current satellite velocity, c represents the speed of light, and γ represents the current optical aberration compensation.

[0057] Next, the results of the traditional method and the method provided in this embodiment of the invention will be compared. Taking the calculation of the Earth's center-of-mass velocity as an example, assuming a fixed velocity of [0, -29.8, 0] km / s in the heliocentric ecliptic inertial frame is used for calculation, the deviation in the traditional calculation of the Earth's three-dimensional revolution velocity under a fixed velocity is as follows: Figure 2 As shown, the deviation in the velocity of the Earth's center of mass is quite large. And in comparison... Figure 3 The simulation results of the interpolation method in the embodiment of the present invention shown show that the real-time Earth's center of mass velocity obtained by Lagrange interpolation using the three sets of Earth velocities given by the astronomical almanac, compared with the astronomical almanac data, has an error of less than 5E-5 km / s, which is far less than the error caused by the traditional method. Figure 4 The simulation results of attitude determination using the optical aberration compensation amount calculated by the method of this invention can effectively eliminate the attitude determination error caused by optical aberration, and its accuracy has met the attitude determination requirements of sub-arcsecond star sensors.

[0058] like Figure 5 , Figure 6 As shown, this embodiment of the invention provides a star sensor optical aberration compensation device. The device embodiment can be implemented through software, hardware, or a combination of both. From a hardware perspective, as... Figure 5 The diagram shown is a hardware architecture diagram of a computing device housing a star sensor optical line difference compensation device according to an embodiment of the present invention. (Except for...) Figure 5 In addition to the processor, memory, network interface, and non-volatile memory shown, the computing device in the embodiment may also include other hardware, such as a forwarding chip responsible for processing packets. Taking software implementation as an example, such as... Figure 6 As shown, as a logical device, it is formed by the CPU of its computing device reading the corresponding computer program from the non-volatile memory into memory and running it. This embodiment provides a star sensor optical aberration compensation device, including:

[0059] The first calculation unit 601 is used to obtain at least three sets of Earth's center of mass velocities injected from the ground that are closest to the set time and the current time, so as to calculate the Earth's center of mass velocity at the current time; wherein, the Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system according to the periodic injection of the astronomical calendar.

[0060] The second calculation unit 602 is used to calculate the satellite velocity at the current moment based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein, the GPS measurement period is longer than the update period of the optical aberration compensation.

[0061] The calculation unit 603 is used to calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity at the current moment.

[0062] In one embodiment of the present invention, the first calculation unit 601 is used to perform:

[0063] Obtain at least three sets of Earth's center-of-mass velocities injected from the ground that are closest to the current time at a set time;

[0064] If at least three sets are obtained, the interpolation method is used to calculate the Earth's center of mass velocity at the current moment based on the three sets of Earth's center of mass velocities and the set time corresponding to each set of Earth's center of mass velocities.

[0065] If fewer than three sets are obtained, the Earth's center-of-mass velocity closest to the current moment is taken as the Earth's center-of-mass velocity at the current moment.

[0066] In one embodiment of the present invention, a set of Earth's center of mass velocities is injected into the ground every day in the first calculation unit 601, and the set time corresponding to the set of Earth's center of mass velocities injected on that day is 0:00 on the next day.

[0067] In one embodiment of the present invention, the second calculation unit 602 is used to perform:

[0068] Obtain at least three sets of satellite velocities in the J2000 coordinate system that are closest to the current time at the corresponding time;

[0069] If at least three sets are obtained, the satellite velocity at the current moment is extrapolated using interpolation based on the three sets of satellite velocities and the corresponding time of each set of satellite velocities.

[0070] If fewer than three sets are obtained, the satellite velocity closest to the current moment is taken as the satellite velocity at the current moment.

[0071] In one embodiment of the present invention, the computing unit 603 is used to perform:

[0072] Calculate the total velocity of the satellite in the J2000 coordinate system based on the current velocity of the Earth's center of mass and the satellite's velocity.

[0073] Calculate the optical aberration compensation amount at the current moment based on the total velocity of the satellite in the J2000 coordinate system.

[0074] In one embodiment of the present invention, the optical aberration compensation amount at the current moment in the calculation unit 603 is estimated by the following formula:

[0075] v = V earth +V sat

[0076]

[0077] In the formula, v is the total velocity of the satellite in the J2000 coordinate system, and V earth Let V be the velocity of Earth's center of mass at the current moment. sat γ represents the current satellite velocity, c represents the speed of light, and γ represents the current optical aberration compensation.

[0078] In one embodiment of the present invention, the interpolation method in the first calculation unit 601 and the second calculation unit 602 is the Lagrange interpolation method.

[0079] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on a star sensor optical aberration compensation device. In other embodiments of the present invention, a star sensor optical aberration compensation device may include more or fewer component units than illustrated, or combine certain component units, or split certain component units, or arrange different component units. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0080] The information interaction and execution process between the various units in the above-mentioned device are based on the same concept as the method embodiment of the present invention, and the specific details can be found in the description of the method embodiment of the present invention, and will not be repeated here.

[0081] This invention also provides a computing device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements a star sensor optical aberration compensation method according to any embodiment of this invention.

[0082] This invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, causes the processor to perform a star sensor optical aberration compensation method according to any embodiment of this invention.

[0083] Specifically, a system or apparatus equipped with a storage medium may be provided, on which software program code implementing the functions of any of the embodiments described above is stored, and the computer (or CPU or MPU) of the system or apparatus may read and execute the program code stored in the storage medium.

[0084] In this case, the program code read from the storage medium can itself implement the function of any of the above embodiments, and therefore the program code and the storage medium storing the program code constitute part of the present invention.

[0085] Examples of storage media used to provide program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, program code can be downloaded from a server computer via a communication network.

[0086] Furthermore, it should be clear that not only can the program code read by the computer be executed, but also the operating system or other components operating on the computer can be instructed based on the program code to perform some or all of the actual operations, thereby realizing the function of any of the embodiments described above.

[0087] Furthermore, it is understood that the program code read from the storage medium is written to the memory set in the expansion board inserted into the computer or to the memory set in the expansion module connected to the computer. Then, based on the instructions of the program code, the CPU or other components installed on the expansion board or expansion module execute some and all of the actual operations, thereby realizing the function of any of the above embodiments.

[0088] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0089] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media that can store program code, such as ROM, RAM, magnetic disk, or optical disk.

[0090] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for aberration compensation of a star sensor, characterized in that, include: The Earth's center of mass velocity is obtained from at least three ground-injected velocities that are closest to the current time at a set time, in order to calculate the Earth's center of mass velocity at the current time without consuming a large amount of storage resources of the onboard processor. The Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system, which is periodically injected according to the astronomical calendar. The satellite velocity at the current moment is calculated based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein the GPS measurement period is longer than the update period of the optical aberration compensation. Calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity at the current moment; The step of obtaining at least three sets of Earth's center-of-mass velocities injected from the ground that are closest to the current time at a set time, in order to calculate the Earth's center-of-mass velocity at the current time, includes: Obtain at least three sets of Earth's center-of-mass velocities injected from the ground that are closest to the current time at a set time; If at least three sets are obtained, the interpolation method is used to calculate the Earth's center of mass velocity at the current moment based on the three sets of Earth's center of mass velocities and the set time corresponding to each set of Earth's center of mass velocities. If less than three sets are obtained, the Earth's center of mass velocity closest to the current moment is taken as the Earth's center of mass velocity at the current moment. A set of Earth's center of mass velocities is injected into the ground every day, and the set time corresponding to the set of Earth's center of mass velocities injected on that day is 0:00 on the next day; The calculation of the current satellite velocity based on the satellite velocity measured in the J2000 coordinate system using GPS includes: Obtain at least three sets of satellite velocities in the J2000 coordinate system that are closest to the current time at the corresponding time; If at least three sets are obtained, the satellite velocity at the current moment is extrapolated using interpolation based on the three sets of satellite velocities and the corresponding time of each set of satellite velocities. If fewer than three sets are obtained, the satellite velocity closest to the current moment is taken as the satellite velocity at the current moment.

2. The method of claim 1, wherein, The calculation of the aberration compensation amount at the current moment, based on the Earth's center-of-mass velocity and the satellite velocity, includes: Based on the Earth's center of mass velocity and the satellite velocity at the current moment, calculate the satellite's total velocity in the J2000 coordinate system; Based on the total velocity of the satellite in the J2000 coordinate system, calculate the optical aberration compensation amount at the current moment.

3. The method according to claim 2, characterized in that, The optical aberration compensation amount at the current moment is estimated using the following formula: In the formula, The total velocity of the satellite in the J2000 coordinate system. Let the velocity of the Earth's center of mass at the current moment be [the velocity of the Earth's center of mass]. The satellite velocity at the current moment, At the speed of light, This represents the optical aberration compensation amount at the current moment.

4. The method according to claim 1, characterized in that, The interpolation method is the Lagrange interpolation method.

5. A star sensor optical aberration compensation device, used to implement the method as described in any one of claims 1-4, characterized in that, include: The first calculation unit is used to obtain at least three sets of Earth's center of mass velocities injected from the ground that are closest to the set time and the current time, so as to calculate the Earth's center of mass velocity at the current time; wherein, the Earth's center of mass velocity is the Earth's center of mass velocity corresponding to the set time in the J2000 coordinate system according to the periodic injection of the astronomical calendar. The second calculation unit is used to calculate the satellite velocity at the current moment based on the satellite velocity measured by GPS in the J2000 coordinate system; wherein the GPS measurement period is greater than the update period of the optical aberration compensation. The calculation unit is used to calculate the optical aberration compensation amount at the current moment based on the Earth's center of mass velocity and the satellite velocity at the current moment.

6. A computing device comprising a memory and a processor, wherein the memory stores a computer program, and the processor, when executing the computer program, implements the method as described in any one of claims 1-4.

7. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the method of any one of claims 1-4.

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