Satellite engine thrust calibration method and device, electronic equipment and storage medium

Abstract

The present application relates to a kind of on-orbit engine thrust calibration method, device, electronic equipment and storage medium.The method comprises: obtaining the theoretical output of current time on-orbit engine and the real orbit change result of current time orbit change;Theoretical output includes theoretical thrust and theoretical specific impulse, and real orbit change result includes real semi-major axis and real orbit inclination;According to theoretical output, the theoretical orbit change result of current time orbit change is calculated, and theoretical orbit change result includes theoretical semi-major axis and theoretical orbit inclination;Based on the deviation of real orbit change result and theoretical orbit change result, theoretical output is cyclically corrected until the final correction value of theoretical output is obtained;Deviation includes the semi-major axis deviation between theoretical semi-major axis and real semi-major axis, and the inclination deviation between theoretical orbit inclination and real orbit inclination;The final correction value of theoretical output is used as the thrust calibration result of current time on-orbit engine orbit change.This scheme can independently calibrate the thrust of on-orbit engine, and the accuracy of calibration result is higher.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a thrust calibration method, apparatus, electronic equipment, and storage medium for an onboard engine. Background Technology

[0002] GEO satellites typically use engines (such as the 490N engine) for orbit changes, and these changes are usually performed in multiple batches. For each orbit change, the engine provides thrust to the satellite, enabling it to achieve the desired orbital maneuver. In other words, the accuracy of the thrust is crucial for ensuring the effectiveness of the orbit changes; therefore, the engine thrust needs to be calibrated. However, current technologies cannot accurately perform autonomous calibration of onboard engine thrust, thus affecting orbit control performance.

[0003] Therefore, there is an urgent need for a thrust calibration method, device, electronic equipment, and storage medium for on-board engines to solve the above-mentioned technical problems. Summary of the Invention

[0004] This invention provides a method, apparatus, electronic device, and storage medium for calibrating the thrust of an onboard engine, which can autonomously calibrate the thrust of the onboard engine with high accuracy.

[0005] In a first aspect, embodiments of the present invention provide a thrust calibration method for an on-board engine, comprising:

[0006] Obtain the theoretical output of the onboard engine and the actual orbit change result for the current orbit change; the theoretical output includes theoretical thrust and theoretical specific impulse, and the actual orbit change result includes actual semi-major axis and actual orbit inclination.

[0007] The theoretical orbit change result for the current orbit change is calculated based on the theoretical output, and the theoretical orbit change result includes the theoretical semi-major axis and the theoretical orbit inclination.

[0008] The theoretical output is iteratively corrected based on the deviation between the actual orbit change result and the theoretical orbit change result until the final corrected value of the theoretical output is obtained; the deviation includes the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbit inclination and the actual orbit inclination.

[0009] The final corrected value of the theoretical output is used as the thrust calibration result of the onboard engine for the current orbit change.

[0010] Secondly, embodiments of the present invention also provide a thrust calibration device for an on-board engine, comprising:

[0011] The acquisition unit is used to acquire the theoretical output of the onboard engine for the current orbit change and the actual orbit change result for the current orbit change; the theoretical output includes theoretical thrust and theoretical specific impulse, and the actual orbit change result includes the actual semi-major axis and the actual orbit inclination.

[0012] The calculation unit is used to calculate the theoretical orbit change result of the current orbit change based on the theoretical output, the theoretical orbit change result including the theoretical semi-major axis and the theoretical orbit inclination angle;

[0013] The correction unit is used to cyclically correct the theoretical output based on the deviation between the actual orbit change result and the theoretical orbit change result until the final corrected value of the theoretical output is obtained; the deviation includes the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbit inclination angle and the actual orbit inclination angle.

[0014] The determination unit is used to take the final corrected value of the theoretical output as the thrust calibration result of the on-board engine for the current orbit change.

[0015] Thirdly, embodiments of the present invention also provide an electronic device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, it implements the method described in any embodiment of this specification.

[0016] Fourthly, embodiments of the present invention also provide a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the methods described in any embodiment of this specification.

[0017] This invention provides a method, apparatus, electronic device, and storage medium for calibrating the thrust of an onboard engine. First, thrust and specific impulse are used as output variables, while the semi-major axis and orbital inclination are used as the orbital change results. The deviation between the actual and theoretical orbital change results is used as a constraint. Then, a differential correction method is used to continuously adjust the theoretical output, with the convergence of the constraint as the objective. Through continuous iterative calculations, the final corrected value of the theoretical output can be obtained. This final corrected value can be considered the actual output of the onboard engine in the current orbital change, and this actual output can characterize the engine's true operating state. Therefore, using this final corrected value of the theoretical output as the thrust calibration result can accurately determine whether the engine is abnormal and provide a reference for the next orbital change. Thus, this scheme can autonomously calibrate the thrust of an onboard engine with high accuracy. Attached Figure Description

[0018] 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.

[0019] Figure 1 This is a schematic diagram of the thrust calibration method for an on-board engine provided in an embodiment of the present invention;

[0020] Figure 2 This is a hardware architecture diagram of an electronic device provided in an embodiment of the present invention;

[0021] Figure 3 This is a structural diagram of a thrust calibration device for an onboard engine provided in an embodiment of the present invention. Detailed Implementation

[0022] 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.

[0023] Please refer to Figure 1 This invention provides a method for calibrating the thrust of an onboard engine, the method comprising:

[0024] Step 100: Obtain the theoretical output of the onboard engine for the current orbit change and the actual orbit change result for the current orbit change; the theoretical output includes theoretical thrust and theoretical specific impulse, and the actual orbit change result includes the actual semi-major axis and the actual orbit inclination.

[0025] Step 102: Calculate the theoretical orbit change result for the current orbit change based on the theoretical output. The theoretical orbit change result includes the theoretical semi-major axis and the theoretical orbit inclination.

[0026] Step 104: Based on the deviation between the actual orbit change result and the theoretical orbit change result, the theoretical output is iteratively corrected until the final corrected value of the theoretical output is obtained; the deviation includes the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbit inclination and the actual orbit inclination.

[0027] Step 106: Use the final corrected value of the theoretical output as the thrust calibration result of the onboard engine for the current orbit change.

[0028] In this embodiment, thrust and specific impulse are first used as output variables, while semi-major axis and orbital inclination are used as the orbital change results. The deviation between the actual and theoretical orbital change results is used as a constraint. Then, a differential correction method is used to continuously adjust the theoretical output, with the convergence of the constraint as the objective. Through continuous iterative calculations, the final corrected value of the theoretical output can be obtained. This final corrected value can be considered as the actual output of the onboard engine in the current orbital change, and this actual output can characterize the engine's true operating state. Therefore, using this final corrected value of the theoretical output as the thrust calibration result can accurately determine whether the engine is abnormal and provide a reference for the next orbital change. Thus, this scheme can autonomously calibrate the thrust of the onboard engine with high accuracy.

[0029] The following description Figure 1 The execution method for each step is shown.

[0030] First, for step 100, obtain the theoretical output of the onboard engine for the current orbit change and the actual orbit change result for the current orbit change.

[0031] In this step, the theoretical output includes theoretical thrust and theoretical specific impulse, while the actual trajectory change results include the actual semi-major axis and the actual trajectory inclination. Thrust and specific impulse are used as adjustment variables P = [F Isp]. T The semi-major axis and orbital inclination are used as the objective variables Q = [a Incl]. T The relationship between the two can be expressed as Q = f(P). Where F is the thrust, Isp is the specific impulse, a is the semi-major axis, and Incl is the track inclination angle.

[0032] In step 102, the theoretical orbit change result for the current orbit change is calculated based on the theoretical output, including:

[0033] Based on the theoretical thrust and the theoretical specific impulse, the theoretical position vector and theoretical velocity vector of the satellite are calculated according to the orbital dynamics equations; wherein, the velocity vector is the first derivative of the position vector;

[0034] Based on the theoretical position vector and the theoretical velocity vector, the theoretical orbit change result for the current orbit change is calculated using the six-root transformation method.

[0035] In this step, the orbital dynamics equations are:

[0036]

[0037] In the formula, r is the satellite's position vector relative to the Earth; r = |r|; μ is the Earth's gravitational constant; m is the satellite's mass, and the value of m is related to the satellite's initial mass, the number of orbital maneuvers, the ignition time of each maneuver, and the specific impulse. f is the gravitational acceleration at the Earth's center;nse For the non-spherical perturbation force of the Earth; f main f is the thrust output by the engine. other The perturbation force includes atmospheric drag and solar radiation pressure, and t is time.

[0038] For step 104, the theoretical output is iteratively corrected based on the deviation between the actual trajectory change result and the theoretical trajectory change result until the final corrected value of the theoretical output is obtained, including:

[0039] S1, determine whether the current deviation between the actual trajectory change result and the current theoretical trajectory change result is not greater than a set threshold. If yes, then use the current theoretical output as the final correction value of the theoretical output; otherwise, execute S2.

[0040] S2, given a perturbation matrix for the current theoretical output, calculate the state transition matrix corresponding to the current theoretical output based on the perturbation matrix; calculate the current correction amount for the current theoretical output based on the state transition matrix and the current deviation; use the sum of the current theoretical output and the current correction amount as the new theoretical output, and execute S3;

[0041] S3, calculate the new theoretical trajectory change result based on the new theoretical output, and calculate the new deviation between the new theoretical trajectory change result and the actual trajectory change result; take the new theoretical trajectory change result as the current theoretical trajectory change result, and take the new deviation as the current deviation, and return to execute S1;

[0042] Repeat steps S1 to S3 until the calculated deviation is not greater than the set threshold.

[0043] In some implementations, the set threshold includes a semi-major axis threshold and a tilt angle threshold;

[0044] The step of determining whether the current deviation between the actual orbit change result and the current theoretical orbit change result is not greater than a set threshold includes:

[0045] Determine whether the semi-major axis deviation between the actual semi-major axis and the current theoretical semi-major axis is not greater than the semi-major axis threshold; and determine whether the tilt angle deviation between the actual tilt angle and the current theoretical tilt angle is not greater than the tilt angle threshold.

[0046] In this embodiment, the current deviation is determined to be no greater than the set threshold only when the deviation of the semi-major axis between the actual semi-major axis and the current theoretical semi-major axis is no greater than the semi-major axis threshold, and the deviation of the tilt angle between the actual tilt angle and the current theoretical tilt angle is no greater than the tilt angle threshold.

[0047] Furthermore, the formula for calculating the deviation ΔQ between the theoretical orbit change result and the actual orbit change result is as follows:

[0048] ΔQ=QQ*

[0049] The formula for calculating the state transition matrix Φ is:

[0050]

[0051] ε = [ε1 ε2]

[0052] The formula for calculating the theoretical output correction ΔP is:

[0053] ΔP=Φ -1 ΔQ

[0054] The new theoretical output calculation formula is as follows:

[0055] P n+1 =P n +ΔP

[0056] In the formula, Q represents the theoretical trajectory change result, Q = [a Incl] T , where a is the theoretical semi-major axis and Incl is the theoretical orbital inclination angle; Q * For the actual orbital change result, Q * =[a * Incl * ] T a * For the true semi-major axis, Incl * Where is the actual orbital inclination; P is the theoretical output of the engine, P = [F Isp] T F represents thrust, Isp represents specific impulse; n and n+1 are subscripts, representing the nth and n+1th iterations respectively; ε is the perturbation matrix, ε1 is the thrust perturbation value; ε2 is the specific impulse perturbation value; f() is a function.

[0057] The above formula can be used to complete the relevant calculations for the iterative process.

[0058] Finally, for step 106, the final corrected value of the theoretical output is used as the thrust calibration result of the onboard engine for the current orbit change.

[0059] The final corrected value of the theoretical output can be considered as the actual output of the on-board engine, which can characterize the actual working state of the engine and provide a reference for the next orbit change.

[0060] It should be noted that the semi-major axis threshold, tilt angle threshold, thrust perturbation value, and specific impulse perturbation value are all determined according to the user's requirements for calibration accuracy, and this application does not impose specific limitations. Furthermore, the calibration method of this application is applicable to the 490N engine, and of course, it is also applicable to other engines with the same trajectory-changing principle as the 490N engine.

[0061] like Figure 2 , Figure 3 As shown, this embodiment of the invention provides a thrust calibration device for an on-board engine. The device embodiment can be implemented through software, hardware, or a combination of both. From a hardware perspective, as... Figure 2 The diagram shown is a hardware architecture diagram of an electronic device for a thrust calibration device of a satellite engine provided in an embodiment of the present invention. Except for... Figure 2 In addition to the processor, memory, network interface, and non-volatile memory shown, the electronic 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 3 As shown, a device in a logical sense is formed by the CPU of the electronic device in which it is located reading the corresponding computer program from the non-volatile memory into the memory for execution.

[0062] This embodiment provides a thrust calibration device for an on-board engine, comprising:

[0063] The acquisition unit 300 is used to acquire the theoretical output of the on-board engine for the current orbit change and the actual orbit change result for the current orbit change; the theoretical output includes theoretical thrust and theoretical specific impulse, and the actual orbit change result includes the actual semi-major axis and the actual orbit inclination.

[0064] The calculation unit 302 is used to calculate the theoretical orbit change result of the current orbit change based on the theoretical output, wherein the theoretical orbit change result includes the theoretical semi-major axis and the theoretical orbit inclination angle;

[0065] The correction unit 304 is used to cyclically correct the theoretical output based on the deviation between the actual orbit change result and the theoretical orbit change result until the final corrected value of the theoretical output is obtained; the deviation includes the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbit inclination angle and the actual orbit inclination angle.

[0066] The determination unit 306 is used to take the final corrected value of the theoretical output as the thrust calibration result of the current orbit change of the on-board engine.

[0067] In some implementations, the computing unit 302 is used to perform the following operations:

[0068] Based on the theoretical thrust and the theoretical specific impulse, the theoretical position vector and theoretical velocity vector of the satellite are calculated according to the orbital dynamics equations.

[0069] Based on the theoretical position vector and the theoretical velocity vector, the theoretical orbit change result for the current orbit change is calculated using the six-root transformation method.

[0070] In some implementations, the orbital dynamics equations are:

[0071]

[0072] In the formula, r is the satellite's position vector relative to the Earth; r = |r|; μ is the Earth's gravitational constant; m is the satellite's mass, and the value of m is related to the satellite's initial mass, the number of orbital maneuvers, the ignition time of each maneuver, and the specific impulse. f is the gravitational acceleration at the Earth's center; nse For the non-spherical perturbation force of the Earth; f main f is the thrust output by the engine. other The perturbation force includes atmospheric drag and solar radiation pressure, and t is time.

[0073] In some implementations, the correction unit 304 is used to perform the following operations:

[0074] S1, determine whether the current deviation between the actual trajectory change result and the current theoretical trajectory change result is not greater than a set threshold. If yes, then use the current theoretical output as the final correction value of the theoretical output; otherwise, execute S2.

[0075] S2, given a perturbation matrix for the current theoretical output, calculate the state transition matrix corresponding to the current theoretical output based on the perturbation matrix; calculate the current correction amount for the current theoretical output based on the state transition matrix and the current deviation; use the sum of the current theoretical output and the current correction amount as the new theoretical output, and execute S3;

[0076] S3, calculate the new theoretical trajectory change result based on the new theoretical output, and calculate the new deviation between the new theoretical trajectory change result and the actual trajectory change result; take the new theoretical trajectory change result as the current theoretical trajectory change result, and take the new deviation as the current deviation, and return to execute S1;

[0077] Repeat steps S1 to S3 until the calculated deviation is not greater than the set threshold.

[0078] In some implementations, the set threshold includes a semi-major axis threshold and a tilt angle threshold;

[0079] The step of determining whether the current deviation between the actual orbit change result and the current theoretical orbit change result is not greater than a set threshold includes:

[0080] Determine whether the semi-major axis deviation between the actual semi-major axis and the current theoretical semi-major axis is not greater than the semi-major axis threshold; and determine whether the tilt angle deviation between the actual tilt angle and the current theoretical tilt angle is not greater than the tilt angle threshold.

[0081] Specifically, the formula for calculating the deviation ΔQ between the theoretical orbit change result and the actual orbit change result is as follows:

[0082] ΔQ=QQ*

[0083] The formula for calculating the state transition matrix Φ is:

[0084]

[0085] ε = [ε1 ε2]

[0086] The formula for calculating the theoretical output correction ΔP is:

[0087] ΔP=Φ -1 ΔQ

[0088] The new theoretical output calculation formula is as follows:

[0089] P n+1 =P n +ΔP

[0090] In the formula, Q represents the theoretical trajectory change result, Q = [a Incl] T , where a is the theoretical semi-major axis and Incl is the theoretical orbital inclination angle; Q * For the actual orbital change result, Q * =[a * Incl * ] T a * For the true semi-major axis, Incl * Where is the actual orbital inclination; P is the theoretical output of the engine, P = [F Isp] T F represents thrust, Isp represents specific impulse; n and n+1 are subscripts, representing the nth and n+1th iterations respectively; ε is the perturbation matrix, ε1 is the thrust perturbation value; ε2 is the specific impulse perturbation value; f() is a function.

[0091] In addition, the engine is a 490N engine.

[0092] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on a thrust calibration device for an on-board engine. In other embodiments of the present invention, a thrust calibration device for an on-board engine may include more or fewer components than illustrated, or combine some components, or split some components, or have different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0093] The information interaction and execution process between the modules 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.

[0094] This invention also provides an electronic device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements a thrust calibration method for an on-board engine according to any embodiment of this invention.

[0095] 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 thrust calibration method for an on-board engine according to any embodiment of this invention.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0102] 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 calibrating the thrust of an onboard engine, characterized in that, include: Obtain the theoretical output of the onboard engine and the actual orbit change result for the current orbit change; The theoretical outputs include theoretical thrust and theoretical specific impulse, and the actual orbit change results include actual semi-major axis and actual orbit inclination. The theoretical orbit change result for the current orbit change is calculated based on the theoretical output, and the theoretical orbit change result includes the theoretical semi-major axis and the theoretical orbit inclination. The theoretical output is iteratively corrected based on the deviation between the actual trajectory change result and the theoretical trajectory change result until the final corrected value of the theoretical output is obtained. The deviations include the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbital inclination and the actual orbital inclination. The final corrected value of the theoretical output is used as the thrust calibration result of the on-board engine for the current orbit change; The calculation of the theoretical orbit change result for the current orbit change based on the theoretical output includes: Based on the theoretical thrust and the theoretical specific impulse, the theoretical position vector and theoretical velocity vector of the satellite are calculated according to the orbital dynamics equations. Based on the theoretical position vector and the theoretical velocity vector, the theoretical orbit change result for the current orbit change is calculated using the six-root transformation method; The process of iteratively correcting the theoretical output based on the deviation between the actual orbit change result and the theoretical orbit change result until the final corrected value of the theoretical output is obtained includes: S1, determine whether the current deviation between the actual orbit change result and the current theoretical orbit change result is not greater than a set threshold. If yes, then use the current theoretical output as the final correction value of the theoretical output; otherwise, execute S2. S2, given a perturbation matrix for the current theoretical output, calculate the state transition matrix corresponding to the current theoretical output based on the perturbation matrix; calculate the current correction amount for the current theoretical output based on the state transition matrix and the current deviation; use the sum of the current theoretical output and the current correction amount as the new theoretical output, and execute S3; S3, calculate the new theoretical trajectory change result based on the new theoretical output, and calculate the new deviation between the new theoretical trajectory change result and the actual trajectory change result; take the new theoretical trajectory change result as the current theoretical trajectory change result, and take the new deviation as the current deviation, and return to execute S1; Repeat steps S1 to S3 until the calculated deviation is not greater than the set threshold. The set thresholds include the semi-major axis threshold and the tilt angle threshold; The step of determining whether the current deviation between the actual orbit change result and the current theoretical orbit change result is not greater than a set threshold includes: Determine whether the semi-major axis deviation between the actual semi-major axis and the current theoretical semi-major axis is not greater than the semi-major axis threshold; and determine whether the inclination angle deviation between the actual orbital inclination angle and the current theoretical orbital inclination angle is not greater than the inclination angle threshold; Deviation between theoretical and actual orbit change results The calculation formula is: State transition matrix The calculation formula is: Correction amount of theoretical output The calculation formula is: The new theoretical output calculation formula is as follows: In the formula, For theoretical orbital change results, , For the theoretical semi-major axis, This is the theoretical orbital inclination angle; For the actual orbit change result, , For the true semi-major axis, This represents the actual orbital inclination angle; This is the theoretical output of the engine. F is the thrust. is the specific impulse; n and n+1 are subscripts, representing the nth and n+1th iterations, respectively; Let be the perturbation matrix. This represents the thrust perturbation value. is the specific impulse perturbation value; f() is a function.

2. The thrust calibration method according to claim 1, characterized in that, The orbital dynamics equations are as follows: In the formula, This is the satellite's position vector relative to the Earth; ; is the Earth's gravitational constant; m is the satellite's mass, and the value of m is related to the satellite's initial mass, the number of orbital maneuvers, the ignition time of each maneuver, and the specific impulse. This refers to the gravitational acceleration at the Earth's center. The perturbation force is the non-spherical shape of the Earth; The thrust output by the engine. The perturbation force includes atmospheric drag and solar radiation pressure, and t is time.

3. The thrust calibration method according to claim 1, characterized in that, The engine is a 490N engine.

4. A thrust calibration device for an on-board engine, characterized in that, For implementing the method as described in any one of claims 1-3, the method includes: The acquisition unit is used to acquire the theoretical output of the onboard engine for the current orbit change and the actual orbit change result for the current orbit change; the theoretical output includes theoretical thrust and theoretical specific impulse, and the actual orbit change result includes the actual semi-major axis and the actual orbit inclination. The calculation unit is used to calculate the theoretical orbit change result of the current orbit change based on the theoretical output, the theoretical orbit change result including the theoretical semi-major axis and the theoretical orbit inclination angle; The correction unit is used to cyclically correct the theoretical output based on the deviation between the actual orbit change result and the theoretical orbit change result until the final corrected value of the theoretical output is obtained; the deviation includes the semi-major axis deviation between the theoretical semi-major axis and the actual semi-major axis, and the inclination deviation between the theoretical orbit inclination angle and the actual orbit inclination angle. The determination unit is used to take the final corrected value of the theoretical output as the thrust calibration result of the on-board engine for the current orbit change.

5. 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 1-3.

6. 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 1-3.

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