Method, device and equipment for formulating phase adjustment control strategy based on Newton iteration

Abstract

The present invention provides a method, device and equipment for formulating a phase adjustment control strategy based on Newton iteration, including: judging whether the phase adjustment process of the main body satellite involves a transfer orbit based on a preset phase angle to be adjusted, adjustment phase time constraint, initial orbit parameters and target orbit parameters; if so, determining an orbit generation strategy to generate the transfer orbit required for the phase adjustment process; determining the number of orbits of the main body satellite during the phase adjustment process and the actual duration required for phase adjustment based on the adjustment phase time constraint and the transfer orbit; using the Newton iteration algorithm to determine the target orbit semi-major axis corresponding to the transfer orbit based on the number of orbits and the actual duration required for phase adjustment; and determining the phase adjustment control strategy corresponding to the main body satellite according to the initial orbit parameters, target orbit parameters and the target orbit semi-major axis corresponding to the transfer orbit. The present invention realizes the minimum velocity increment under the premise of the adjustment phase time constraint, saves the fuel required for phase adjustment, and reduces the launch cost of the main body satellite.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular, to a method, device, and equipment for formulating a phase adjustment control strategy based on Newton iteration. Background Art

[0002] For constellation satellites, usually after being put into orbit, it is necessary to adjust the phase of some satellites so that they can complete the phase deployment within a certain time and be adjusted to the target orbital altitude.

[0003] Related technologies propose to design a single-loop phase adjustment transfer orbit. Under the condition of meeting the phase adjustment time constraint, the velocity increment designed to enter the target phase will be relatively large. However, in the case of the minimum velocity increment, the phase adjustment time constraint cannot be met, that is, related technologies cannot meet the dual constraints of the phase adjustment duration constraint and the most fuel-efficient consumption. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a method, device, and equipment for formulating a phase adjustment control strategy based on Newton iteration, which can minimize the velocity increment on the premise of adjusting the phase time constraint, save the fuel required for phase adjustment, and reduce the launch cost of the main satellite.

[0005] In a first aspect, an embodiment of the present invention provides a method for formulating a phase adjustment control strategy based on Newton iteration, which is characterized by including:

[0006] Obtain the initial orbital parameters corresponding to the main satellite and the target orbital parameters corresponding to the target satellite, and based on the preset phase angle to be adjusted, the phase adjustment time constraint, the initial orbital parameters, and the target orbital parameters, determine whether a transfer orbit is designed for the phase adjustment process of the main satellite; where the phase adjustment process is the process of adjusting the main satellite to the orbital altitude where the target satellite is located;

[0007] If so, determine an orbit generation strategy to generate the transfer orbit required for the phase adjustment process;

[0008] Based on the phase adjustment time constraint and the transfer orbit, determine the number of orbits the main satellite runs in the phase adjustment process and the actual duration required for phase adjustment;

[0009] Use the Newton iteration algorithm to determine the target orbital semi-major axis corresponding to the transfer orbit based on the number of orbits and the actual duration required for phase adjustment;

[0010] According to the initial orbital parameters, the target orbital parameters, and the target orbital semi-major axis corresponding to the transfer orbit, determine the phase adjustment control strategy corresponding to the main satellite.

[0011] In one embodiment, the initial orbit parameters include the semi-major axis of the body star and the phase angle of the body star, and the target orbit parameters include the semi-major axis of the target star and the phase angle of the target star;

[0012] The step of determining whether the phase adjustment process of the body star involves a transfer orbit based on a preset phase angle to be adjusted, an adjustment phase time constraint, the initial orbit parameters, and the target orbit parameters includes:

[0013] Based on the semi-major axis of the body star and the semi-major axis of the target star, determine the orbital angular velocity of the body star and the orbital angular velocity of the target star respectively;

[0014] If the orbital angular velocity of the body star is equal to the orbital acceleration of the target star, it is determined that the phase adjustment process of the body star requires a transfer orbit to be designed;

[0015] If the orbital angular velocity of the body star is not equal to the orbital acceleration of the target star, based on the phase angle to be adjusted, the semi-major axis of the body star, the phase angle of the body star, the semi-major axis of the target star, and the phase angle of the target star, determine the estimated duration required for phase adjustment in the assumed scenario without designing a transfer orbit;

[0016] If the estimated duration required for phase adjustment does not meet the adjustment phase time constraint, it is determined that the phase adjustment process of the body star requires a transfer orbit to be designed.

[0017] In one embodiment, the step of determining an orbit generation strategy to generate the transfer orbit required for the phase adjustment process includes:

[0018] Based on the phase angle to be adjusted and the adjustment phase time constraint, determine the first semi-major axis adjustment amount of the body star when using the ascending orbit phase adjustment strategy and the second semi-major axis adjustment amount of the body star when using the descending orbit phase adjustment strategy respectively;

[0019] If the first semi-major axis adjustment amount is less than the second semi-major axis adjustment amount, determine the ascending orbit phase adjustment strategy as the orbit generation strategy and set the transfer orbit required for the phase adjustment process to 1;

[0020] If the first semi-major axis adjustment amount is greater than the second semi-major axis adjustment amount, determine the descending orbit phase adjustment strategy as the orbit generation strategy and set the transfer orbit required for the phase adjustment process to -1.

[0021] In one embodiment, the step of determining the number of orbits the body star runs during the phase adjustment process and the actual duration required for phase adjustment based on the adjustment phase time constraint and the transfer orbit includes:

[0022] Determine the phase modulation compensation duration corresponding to the main body satellite based on the adjusted phase time constraint;

[0023] Determine the number of orbits of the target satellite during the phase modulation process based on the adjusted phase time constraint and the phase modulation compensation duration;

[0024] If the orbit generation strategy adopts the ascending orbit phase adjustment strategy, the number of orbits of the main body satellite during the phase modulation process is equal to the number of orbits of the target satellite; or, if the orbit generation strategy adopts the descending orbit phase adjustment strategy, the number of orbits of the main body satellite during the phase modulation process is equal to the sum of the number of orbits of the target satellite and a specified value;

[0025] And determine the actual duration required for phase modulation according to the phase modulation compensation duration and the number of orbits of the target satellite.

[0026] In one implementation manner, the step of determining the target orbit semi-major axis corresponding to the transfer orbit based on the number of orbits and the actual duration required for phase modulation by using the Newton iteration algorithm includes:

[0027] Set the semi-major axis of the main body satellite in the initial orbit parameters to the initial orbit semi-major axis corresponding to the transfer orbit, and determine the deviation orbit semi-major axis corresponding to the transfer orbit;

[0028] Substitute the initial orbit semi-major axis and the deviation orbit semi-major axis into the fitness function in the Newton iteration algorithm respectively to obtain the fitness value corresponding to the initial orbit semi-major axis and the fitness value corresponding to the deviation orbit semi-major axis, and determine the semi-major axis deviation amount based on the fitness value;

[0029] If the semi-major axis deviation amount is greater than or equal to the preset deviation amount threshold, adjust the initial orbit semi-major axis based on the semi-major axis deviation amount, and re-determine the deviation orbit semi-major axis corresponding to the transfer orbit until the re-determined semi-major axis deviation amount is less than the preset deviation amount threshold, and then determine the adjusted initial orbit semi-major axis as the target orbit semi-major axis corresponding to the transfer orbit.

[0030] In one implementation manner, the step of determining the phase adjustment control strategy corresponding to the main body satellite according to the initial orbit parameters, the target orbit parameters and the target orbit semi-major axis corresponding to the transfer orbit includes:

[0031] Based on the initial orbit parameters, the target orbit parameters, and the semi-major axis of the target orbit corresponding to the transfer orbit, determine the orbit parameters corresponding to the initial adjustment orbit and the final adjustment orbit respectively during the phase adjustment process; wherein, the initial adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the currently occupied orbit to the transfer orbit, and the final adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the transfer orbit to the orbit where the target satellite is located;

[0032] Based on the orbit parameters corresponding to the initial adjustment orbit and the final adjustment orbit respectively, determine the multiple velocity increments involved in the phase adjustment process and the time intervals between adjacent two orbit controls, so as to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0033] In one implementation manner, the method further includes:

[0034] If the phase adjustment process of the main body satellite does not need to involve a transfer orbit, based on the initial orbit parameters and the target orbit parameters, determine the orbit parameters corresponding to the target adjustment orbit during the phase adjustment process; wherein, the target adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the currently occupied orbit to the orbit where the target satellite is located;

[0035] Based on the orbit parameters corresponding to the target adjustment orbit, determine the multiple velocity increments, the initial parking duration, and the time intervals between adjacent two orbit controls involved in the phase adjustment process, so as to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0036] In a second aspect, an apparatus for formulating a phase adjustment control strategy based on Newton iteration provided by an embodiment of the present invention includes:

[0037] A judgment module, configured to obtain the initial orbit parameters corresponding to the main body satellite and the target orbit parameters corresponding to the target satellite, and based on a preset phase angle to be adjusted, an adjustment phase time constraint, the initial orbit parameters, and the target orbit parameters, judge whether the phase adjustment process of the main body satellite involves a transfer orbit; wherein, the phase adjustment process is the process of adjusting the main body satellite to the orbit height where the target satellite is located;

[0038] A transfer orbit generation module, configured to determine an orbit generation strategy to generate the transfer orbit required for the phase adjustment process when the judgment result of the judgment module is yes;

[0039] A revolution number and duration determination module, configured to determine the number of revolutions of the main body satellite and the actual duration required for phase adjustment during the phase adjustment process based on the adjustment phase time constraint and the transfer orbit;

[0040] The semi-major axis determination module is configured to use the Newton iteration algorithm to determine the target orbit semi-major axis corresponding to the transfer orbit based on the number of operating cycles and the true duration required for phase modulation.

[0041] The strategy determination module is configured to determine the phase adjustment control strategy corresponding to the main body satellite according to the initial orbit parameters, the target orbit parameters, and the target orbit semi-major axis corresponding to the transfer orbit.

[0042] In a third aspect, an embodiment of the present invention further provides an electronic device, including a processor and a memory. The memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement any one of the methods provided in the first aspect.

[0043] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium. The computer-readable storage medium stores computer-executable instructions. When the computer-executable instructions are called and executed by a processor, the computer-executable instructions cause the processor to implement any one of the methods provided in the first aspect.

[0044] A method, device, and equipment for formulating a phase adjustment control strategy based on Newton iteration provided by an embodiment of the present invention first obtain the initial orbit parameters corresponding to the main body satellite and the target orbit parameters corresponding to the target satellite, and based on the preset phase angle to be adjusted, the adjustment phase time constraint, the initial orbit parameters, and the target orbit parameters, determine whether the phase adjustment process of the main body satellite involves a transfer orbit. The phase adjustment process is the process of adjusting the main body satellite to the orbit height where the target satellite is located; in the case where the judgment result is yes, determine an orbit generation strategy to generate the transfer orbit required for the phase adjustment process; then based on the adjustment phase time constraint and the transfer orbit, determine the number of operating cycles of the main body satellite during the phase adjustment process and the true duration required for phase adjustment; then use the Newton iteration algorithm to determine the target orbit semi-major axis corresponding to the transfer orbit based on the number of operating cycles and the true duration required for phase adjustment; finally, determine the phase adjustment control strategy corresponding to the main body satellite according to the initial orbit parameters, the target orbit parameters, and the target orbit semi-major axis corresponding to the transfer orbit. The above method constrains the adjustment phase time, and in the case where it is determined that a transfer orbit needs to be designed, designs a multi-cycle transfer orbit, uses the Newton iteration algorithm to determine the target orbit semi-major axis corresponding to the transfer orbit, and then obtains the phase adjustment control strategy, so as to minimize the velocity increment under the premise of the adjustment phase time constraint, save the fuel required for phase adjustment, and reduce the launch cost of the main body satellite.

[0045] Other features and advantages of the present invention will be described in the following specification, and part of them will become obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention are achieved and obtained by the structures specifically pointed out in the specification, the claims, and the drawings.

[0046] In order to make the above objects, features, and advantages of the present invention more obvious and understandable, the following specifically gives preferred embodiments and, in conjunction with the accompanying drawings, makes a detailed description as follows. Brief Description of the Drawings

[0047] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0048] Figure 1 It is a schematic flowchart of a method for formulating a phase adjustment control strategy based on Newton iteration provided by an embodiment of the present invention;

[0049] Figure 2 It is a schematic diagram of a phase adjustment process provided by an embodiment of the present invention;

[0050] Figure 3 It is a schematic diagram of ascending and descending orbits provided by an embodiment of the present invention;

[0051] Figure 4 It is a schematic diagram of the transition orbit adjustment time provided by an embodiment of the present invention;

[0052] Figure 5 It is an overall flowchart of a method for formulating a phase adjustment control strategy based on Newton iteration provided by an embodiment of the present invention;

[0053] Figure 6 It is a schematic structural diagram of a device for formulating a phase adjustment control strategy based on Newton iteration provided by an embodiment of the present invention;

[0054] Figure 7 It is a schematic structural diagram of an electronic device provided by an embodiment of the present invention. Detailed Embodiments

[0055] In order to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions of the present invention in conjunction with the embodiments. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0056] Currently, traditional phase modulation adjusts the phase through a single-loop transfer orbit. This method saves time but comes at the cost of a large velocity increment. Based on this, the present invention provides a method, device, and equipment for formulating a phase adjustment control strategy based on Newton iteration. By constraining the phase adjustment time and designing a multi-loop transfer orbit, the minimum velocity increment is achieved under the premise of the phase adjustment time constraint, saving the fuel required for phase adjustment and reducing the launch cost of the main body satellite.

[0057] To facilitate the understanding of this embodiment, first, a method for formulating a phase adjustment control strategy based on Newton iteration disclosed in the embodiments of the present invention will be introduced in detail. Refer to Figure 1 The schematic flowchart of a method for formulating a phase adjustment control strategy based on Newton iteration shown. This method mainly includes the following steps S102 to S110:

[0058] Step S102, obtain the initial orbit parameters corresponding to the main body satellite and the target orbit parameters corresponding to the target satellite, and based on the preset phase angle to be adjusted, phase adjustment time constraint, initial orbit parameters, and target orbit parameters, determine whether the phase adjustment process of the main body satellite involves a transfer orbit.

[0059] Among them, the initial orbit parameters include the semi-major axis of the main body satellite and the phase angle of the main body satellite, and the target orbit parameters include the semi-major axis of the target satellite and the phase angle of the target satellite. The phase adjustment process is the process of adjusting the main body satellite to the orbital altitude where the target satellite is located.

[0060] In an example, according to the phase angle to be adjusted, initial orbit parameters, and target orbit parameters, determine the estimated duration required for phase adjustment in the assumed scenario without designing a transfer orbit. If the estimated duration required for phase adjustment is less than the phase adjustment time constraint, it means that the initial orbits of the main body satellite and the target satellite can complete the phase adjustment under the phase adjustment time constraint, and at this time, there is no need to design a transfer orbit; conversely, if the estimated duration required for phase adjustment is greater than the phase adjustment time constraint, a transfer orbit needs to be designed.

[0061] Step S104, if so, determine the orbit generation strategy to generate the transfer orbit required for the phase adjustment process.

[0062] Among them, the orbit generation strategy can be an ascending orbit phase adjustment strategy or a descending orbit phase adjustment strategy.

[0063] In an example, if a transfer orbit needs to be designed, both the ascending orbit phase adjustment strategy and the descending orbit phase adjustment strategy can complete the phase correction within the phase adjustment time constraint. The semi-major axis adjustment amounts of the ascending orbit phase adjustment strategy and the descending orbit phase adjustment strategy can be initially calculated, and the descending or ascending orbit phase adjustment can be determined according to the magnitude of the semi-major axis adjustment amount, and then the transfer orbit is generated based on the determined orbit generation strategy.

[0064] Step S106: Based on the adjusted phase time constraint and the transfer orbit, determine the number of orbits the main body satellite travels during the phase adjustment process and the actual duration required for phase adjustment.

[0065] In one example, the phase adjustment compensation duration can be determined according to the phase angle to be adjusted and the orbital angular velocity of the target satellite. Using the phase adjustment compensation duration, the adjusted phase time constraint, and the orbital angular velocity of the target satellite, determine the number of orbits the target satellite travels during the phase adjustment process. Then, based on the number of orbits the target satellite travels, determine the number of orbits the main body satellite travels and the actual duration required for phase adjustment respectively.

[0066] Step S108: Using the Newton iteration algorithm, based on the number of orbits and the actual duration required for phase adjustment, determine the semi-major axis of the target orbit corresponding to the transfer orbit.

[0067] In one example, a fitness function can be designed, and the initial semi-major axis of the orbit corresponding to the transfer orbit can be configured. Use the Newton iteration algorithm to iterate the semi-major axis of the orbit. When the iteration stop condition is met, the semi-major axis of the target orbit corresponding to the transfer orbit can be obtained. Among them, the iteration stop condition can be reaching the preset number of iterations or the deviation of the semi-major axis being less than the preset deviation threshold.

[0068] Step S110: According to the initial orbit parameters, the target orbit parameters, and the semi-major axis of the target orbit corresponding to the transfer orbit, determine the phase adjustment control strategy corresponding to the main body satellite.

[0069] Among them, the phase adjustment control strategy includes multiple (such as four times) velocity increments when designing the transfer orbit and the time interval between two adjacent orbit controls.

[0070] In one example, according to the initial orbit parameters, the target orbit parameters, and the semi-major axis of the target orbit corresponding to the transfer orbit, determine the orbit parameters corresponding to the initial adjustment orbit and the terminal adjustment orbit respectively during the phase adjustment process. Then, based on these orbit parameters, determine the four velocity increments involved in the phase adjustment process and the time interval between two adjacent orbit controls to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0071] The method for formulating a phase adjustment control strategy based on Newton iteration provided by the embodiments of the present invention restricts the adjusted phase time. When it is determined that a transfer orbit needs to be designed, a multi-orbit transfer orbit is designed. The Newton iteration algorithm is used to determine the semi-major axis of the target orbit corresponding to the transfer orbit, and then the phase adjustment control strategy is obtained. Thus, the minimum velocity increment is realized under the premise of restricting the adjusted phase time, saving the fuel required for phase adjustment and reducing the launch cost of the main body satellite.

[0072] First, an explanation of the phase adjustment process is given. Refer to Figure 2A schematic diagram of a phase modulation process is shown. Before phase modulation, the initial phase angle exists between the body satellite and the target satellite. The phase angle to be adjusted is determined and phase modulation begins. After phase modulation, the target phase angle exists between the body satellite and the target satellite.

[0073] On this basis, an embodiment of the present invention provides a specific implementation manner of a method for formulating a phase adjustment control strategy based on Newton iteration.

[0074] For the foregoing step S102, an embodiment of the present invention provides an implementation manner for determining whether the phase modulation process of the body satellite involves a transfer orbit based on a preset phase angle to be adjusted, a phase adjustment time constraint, initial orbit parameters, and target orbit parameters. See the following steps 1A to 1D:

[0075] Step 1A: Determine the orbital angular velocity of the body satellite and the orbital angular velocity of the target satellite respectively based on the semi-major axis of the body satellite and the semi-major axis of the target satellite.

[0076] In an example, the orbital angular velocity of the body satellite and the orbital angular velocity of the target satellite can be determined respectively according to the following formulas:

[0077]

[0078] Where, n T is the orbital angular velocity of the target satellite, n S is the orbital angular velocity of the body satellite, v is the gravitational constant of the earth, a T is the semi-major axis of the target satellite, a. S is the semi-major axis of the body satellite.

[0079] Step 1B: If the orbital angular velocity of the body satellite is equal to the orbital acceleration of the target satellite, it is determined that the phase modulation process of the body satellite needs to design a transfer orbit.

[0080] In an example, if the orbital angular velocity of the body satellite is equal to the orbital acceleration of the target satellite, that is, n T = n S , then t = 2·AT time ; where, t is the estimated duration required for phase modulation in the assumed scenario without designing a transfer orbit, and AT time is the phase adjustment time constraint. Since the estimated duration t required for phase modulation is greater than the phase adjustment time constraint AT time , it is necessary to design a transfer orbit.

[0081] Step 1C: If the orbital angular velocity of the body satellite is not equal to the orbital acceleration of the target satellite, determine the estimated duration required for phase modulation in the assumed scenario without designing a transfer orbit based on the phase angle to be adjusted, the semi-major axis of the body satellite, the phase angle of the body satellite, the semi-major axis of the target satellite, and the phase angle of the target satellite.

[0082] In one example, when the orbital angular velocity of the main body star is not equal to the orbital acceleration of the target star, the estimated duration required for phase adjustment in the assumed scenario without designing a transfer orbit can be determined according to the following formula:

[0083]

[0084] where t is the estimated duration required for phase adjustment in the assumed scenario without designing a transfer orbit; AT time is the phase adjustment time constraint; Δu best is the phase angle that the main body star needs to adjust, that is, the phase angle to be adjusted, with a range of [0, 2π); n T is the orbital angular velocity of the target star; n S is the orbital angular velocity of the main body star, u T is the phase angle of the target star; u S is the phase angle of the main body star.

[0085] Step 1D, if the estimated duration required for phase adjustment does not meet the phase adjustment time constraint, it is determined that a transfer orbit needs to be designed for the phase adjustment process of the main body star.

[0086] In one example, if the estimated duration required for phase adjustment t is greater than or equal to the phase adjustment time constraint AT time , it is determined that the phase adjustment time constraint is not met, and at this time, it is determined that a transfer orbit needs to be designed; conversely, if t < AT time , the transfer orbit flag is set to 0, indicating that there is no need to design a transfer orbit.

[0087] For the foregoing step S104, the embodiment of the present invention provides an implementation manner for determining an orbit generation strategy to generate a transfer orbit required for the phase adjustment process. The orbit generation strategy can adopt an ascending orbit phase adjustment strategy or a descending orbit phase adjustment strategy, such as Figure 3 a schematic diagram of an ascending and descending orbit as shown. Specifically, refer to the following steps 2A to 2B:

[0088] Step 2A, based on the phase angle to be adjusted and the phase adjustment time constraint, respectively determine the first semi-major axis adjustment amount of the main body star when adopting the ascending orbit phase adjustment strategy, and the second semi-major axis adjustment amount of the main body star when adopting the descending orbit phase adjustment strategy.

[0089] In one example, the first semi-major axis adjustment amount Δa of the main body star when adopting the ascending orbit phase adjustment strategy can be determined according to the following formula s :

[0090]

[0091] Δa s = |a is - a S | + |ais -a T |;

[0092] Wherein, n is is the orbital angular velocity of the body satellite when adopting the ascending orbit phase adjustment strategy, n T is the orbital angular velocity of the target satellite, Δu best is the phase angle to be adjusted, AT time is the phase adjustment time constraint, a is is the semi-major axis of the body satellite when adopting the ascending orbit phase adjustment strategy, v is the gravitational constant of the earth, Δa s is the first semi-major axis adjustment amount, a T is the semi-major axis of the target satellite, a S is the semi-major axis of the body satellite.

[0093] In one example, the second semi-major axis adjustment amount Δa of the body satellite when adopting the descending orbit phase adjustment strategy can be determined according to the following formula j :

[0094]

[0095] Δa j =|a ij -a S |+|a ij -a T |;

[0096] Wherein, n ij is the orbital angular velocity of the body satellite when adopting the descending orbit phase adjustment strategy, n T is the orbital angular velocity of the target satellite, Δu best is the phase angle to be adjusted, AT time is the phase adjustment time constraint, a ij is the semi-major axis of the body satellite when adopting the descending orbit phase adjustment strategy, μ is the gravitational constant of the earth, Δa j is the second semi-major axis adjustment amount, a T is the semi-major axis of the target satellite, a S is the semi-major axis of the body satellite.

[0097] Step 2B, determine whether to adopt the ascending orbit phase adjustment strategy or the descending orbit phase adjustment strategy to design the transfer orbit according to the magnitude of the semi-major axis adjustment amount. Specifically:

[0098] (1) If the first semi-major axis adjustment amount is less than the second semi-major axis adjustment amount, then determine the ascending orbit phase adjustment strategy as the orbit generation strategy, and set the transfer orbit required for the phase adjustment process to 1. In one example, if Δa s <Δa j , then adopt the ascending orbit phase adjustment strategy, and the transfer orbit flag = 1.

[0099] (2) If the adjustment amount of the first semi-major axis is greater than that of the second semi-major axis, the downlink adjustment phase strategy is determined as the orbit generation strategy, and the transition orbit required for the phase adjustment process is set to -1. In one example, if Δa s >Δa j , the downlink adjustment phase strategy is adopted, and the transition orbit flag = -1.

[0100] For the foregoing step S106, the embodiment of the present invention provides an implementation manner for determining the number of orbits of the main body satellite during the phase adjustment process and the actual duration required for phase adjustment based on the phase adjustment time constraint and the transition orbit. See the following steps 3A to 3D:

[0101] Step 3A: Determine the phase adjustment compensation duration corresponding to the main body satellite based on the phase adjustment time constraint.

[0102] In one example, if Δu best <π, Otherwise where time 1 is the phase adjustment compensation duration.

[0103] Step 3B: Determine the number of orbits of the target satellite during the phase adjustment process based on the phase adjustment time constraint and the phase adjustment compensation duration.

[0104] In one example, the number of orbits of the target satellite during the phase adjustment process is determined according to the following formula:

[0105]

[0106] where N T is the number of orbits of the target satellite during the phase adjustment process, AT time is the phase adjustment time constraint, time 1 is the phase adjustment compensation duration, and n T is the orbital angular velocity of the target satellite.

[0107] Step 3C: If the orbit generation strategy adopts the uplink adjustment phase strategy, the number of orbits of the main body satellite during the phase adjustment process is equal to the number of orbits of the target satellite; or, if the orbit generation strategy adopts the downlink adjustment phase strategy, the number of orbits of the main body satellite during the phase adjustment process is equal to the sum of the number of orbits of the target satellite and a specified value.

[0108] In one example, if the uplink adjustment phase strategy is adopted, the number of orbits of the main body satellite during the phase adjustment process is equal to the number of orbits of the target satellite, that is, N S = N T ; where N S is the number of orbits of the main body satellite during the phase adjustment process (including the number of orbits adjusted to the transition orbit), and N T is the number of orbits of the target satellite during the phase adjustment process.

[0109] In another example, if the descending orbit phase adjustment strategy is adopted, the number of orbits of the main body satellite during the phase adjustment process is equal to the sum of the number of orbits of the target satellite and a specified value, that is, N S = N T + 1; where N S is the number of orbits of the main body satellite during the phase adjustment process (including the number of orbits adjusted to the transfer orbit), and N T is the number of orbits of the target satellite during the phase adjustment process.

[0110] Step 3D, determine the actual duration required for phase adjustment according to the phase adjustment compensation duration and the number of orbits of the target satellite.

[0111] In one example, the actual duration required for phase adjustment is determined according to the following formula:

[0112]

[0113] where AT real is the actual duration required for phase adjustment, N T is the number of orbits of the target satellite during the phase adjustment process, time 1 is the phase adjustment compensation duration, and n T is the orbital angular velocity of the target satellite.

[0114] For the foregoing step S108, the embodiment of the present invention provides an implementation manner of using the Newton iteration algorithm to determine the target orbital semi-major axis corresponding to the transfer orbit based on the number of orbits and the actual duration required for phase adjustment. Refer to Figure 4 a schematic diagram of the transfer orbit adjustment time shown in

[0115]

[0116] where:

[0117] AT real is the phase adjustment time constraint, N S is the number of orbits of the main body satellite during the phase adjustment process, T AP is the orbital period of the transfer orbit, T AD1 is the orbital period of the initial adjustment orbit, T AD2 is the orbital period of the terminal adjustment orbit, a AT is the orbital semi-major axis corresponding to the transfer orbit, v is the gravitational constant of the earth, a T is the semi-major axis of the target satellite, and a S is the semi-major axis of the main body satellite.

[0118] Specifically, refer to the following steps 4A to step 4C:

[0119] Step 4A, set the semi-major axis of the main body star in the initial orbit parameters to the initial orbit semi-major axis corresponding to the transfer orbit, and determine the deviation orbit semi-major axis corresponding to the transfer orbit. It includes:

[0120] In one example, assign an initial value to the orbit semi-major axis of the transfer orbit, a 0 = a S ; where a 0 is the initial orbit semi-major axis, and a S is the semi-major axis of the main body star.

[0121] In one example, set the initial semi-major axis deviation amount, ratio = flag·1000; where ratio is the semi-major axis deviation amount and flag is the transfer orbit.

[0122] In one example, calculate the deviation orbit semi-major axis corresponding to the transfer orbit: a 1 = a 0 + ratio; where a 1 is the deviation orbit semi-major axis, a 0 is the initial orbit semi-major axis, and ratio is the semi-major axis deviation amount.

[0123] Step 4B, substitute the initial orbit semi-major axis and the deviation orbit semi-major axis into the fitness function in the Newton iteration algorithm to obtain the fitness value corresponding to the initial orbit semi-major axis and the fitness value corresponding to the deviation orbit semi-major axis, and determine the semi-major axis deviation amount based on the fitness values.

[0124] In one example, substitute a 0 , a T , a S , AT real , N S into the fitness function to find the fitness value f 0 corresponding to the initial orbit semi-major axis, where substitute the value of a 0 into the a AT parameter in the fitness function to obtain the fitness value f 0 corresponding to the initial orbit semi-major axis; similarly, substitute a 1 , a T , a S , AT real , N S into the fitness function to find the fitness value f 1 corresponding to the deviation orbit semi-major axis.

[0125] Determine the slope based on the two fitness values:

[0126] Determine the semi-major axis deviation amount for this iteration based on the slope

[0127] Step 4C. If the semi-major axis deviation amount is greater than or equal to the preset deviation amount threshold, adjust the initial orbit semi-major axis based on the semi-major axis deviation amount, and re-determine the deviation orbit semi-major axis corresponding to the transfer orbit. Until the re-determined semi-major axis deviation amount is less than the preset deviation amount threshold, determine the adjusted initial orbit semi-major axis as the target orbit semi-major axis corresponding to the transfer orbit.

[0128] In one example, determine whether the semi-major axis deviation amount ratio of this iteration is less than the preset deviation amount threshold. Assume the deviation amount threshold is 0.001. If ratio < 0.001, then exit the loop, and the initial orbit semi-major axis a 0 is determined as the target orbit semi-major axis a AT corresponding to the transfer orbit, that is, a AT = a 0 ; if ratio ≥ 0.001, then adjust the initial orbit semi-major axis based on the semi-major axis deviation amount, that is, a 0 = a 0 - ratio, and according to the formula in step 4A, based on the adjusted initial orbit semi-major axis a 0 re-determine the deviation orbit semi-major axis a 1 , based on the adjusted initial orbit semi-major axis a 0 and the adjusted deviation orbit semi-major axis a 1 , execute the aforementioned step 4B again to obtain a new semi-major axis deviation amount ratio; repeat this process until ratio < 0.001 and then exit the loop, and the adjusted initial orbit semi-major axis a 0 is determined as the target orbit semi-major axis a AT corresponding to the transfer orbit, that is, a AT = a 0 .

[0129] For the aforementioned step S110, the embodiment of the present invention provides an implementation manner for determining the phase adjustment control strategy corresponding to the main body star according to the initial orbit parameters, target orbit parameters, and the target orbit semi-major axis corresponding to the transfer orbit. See the following steps 5A to 5B:

[0130] Step 5A. According to the initial orbit parameters, target orbit parameters, and the target orbit semi-major axis corresponding to the transfer orbit, determine the orbit parameters corresponding to the initial adjustment orbit and the terminal adjustment orbit respectively during the phase adjustment process.

[0131] Among them, the initial adjustment orbit is the orbit generated during the process of adjusting the main body star from the current orbit to the transfer orbit, and the final adjustment orbit is the orbit generated during the process of adjusting the main body star from the transfer orbit to the orbit of the target star. The orbit parameters include the semi-major axis of the initial adjustment orbit, the eccentricity of the initial adjustment orbit, the angular momentum of the initial adjustment orbit, the perigee velocity of the initial adjustment orbit, the apogee velocity of the initial adjustment orbit, the semi-major axis of the final adjustment orbit, the eccentricity of the final adjustment orbit, the angular momentum of the final adjustment orbit, the perigee velocity of the final adjustment orbit, and the apogee velocity of the final adjustment orbit.

[0132] In one example, the orbit parameters corresponding to the initial adjustment orbit can be calculated according to the following formula:

[0133] Semi-major axis of the initial adjustment orbit:

[0134] Eccentricity of the initial adjustment orbit:

[0135] Angular momentum of the initial adjustment orbit:

[0136] Perigee velocity of the initial adjustment orbit:

[0137] Apogee velocity of the initial adjustment orbit:

[0138] In one example, the orbit parameters corresponding to the final adjustment orbit can be calculated according to the following formula:

[0139] Semi-major axis of the final adjustment orbit:

[0140] Eccentricity of the final adjustment orbit:

[0141] Angular momentum of the final adjustment orbit:

[0142] Perigee velocity of the final adjustment orbit:

[0143] Apogee velocity of the final adjustment orbit:

[0144] Step 5B: Based on the orbit parameters corresponding to the initial adjustment orbit and the final adjustment orbit respectively, determine the multiple velocity increments involved in the phase adjustment process and the time interval between two adjacent orbit controls, so as to obtain the phase adjustment control strategy corresponding to the main body star.

[0145] In one example, if the orbit-raising phase adjustment strategy is adopted, that is, if flag = 1, the four velocity increments Δv involved in the phase adjustment process are determined according to the following formula 1 、Δv2 、Δv 3 、Δv 4 :

[0146] Δv 1 =vp AD1 -v S ;

[0147] Δv 2 =v AT -va AD1 ;

[0148] Δv 3 =va AD2 -v AT ;

[0149] Δv 4 =v T -vp AD2 ;

[0150] Among them, vp AD1 is the perigee velocity of the initial adjustment orbit, va AD1 is the apogee velocity of the initial adjustment orbit, va AD2 is the apogee velocity of the terminal adjustment orbit, vp AD2 is the perigee velocity of the terminal adjustment orbit, v T is the velocity of the target star, v S is the velocity of the main body star, v AT is the velocity of the transfer orbit.

[0151] In one example, if the orbit descent adjustment phase strategy is adopted, that is, if flag = -1, then the four velocity increments Δv 1 、Δv 2 、Δv 3 、Δv 4 :

[0152] Δv 1 =vp AD1 -v S ;

[0153] Δv 2 =v AT -va AD1 ;

[0154] Δv 3 =va AD2 -v AT ;

[0155] Δv 4 =v T -vp AD2 ;

[0156] Among them, vp AD1 is the perigee velocity of the initial adjustment orbit, va AD1 is the apogee velocity of the initial adjustment orbit, va AD2 is the apogee velocity of the terminal adjustment orbit, vp AD2 is the perigee velocity of the terminal adjustment orbit, v T is the velocity of the target star, v S is the velocity of the main body star, v AT is the velocity of the transfer orbit.

[0157] In one example, the time interval between two adjacent orbit controls can be calculated according to the following formula:

[0158] Time interval of the 1st - 2nd orbit controls:

[0159] Time interval of the 2nd - 3rd orbit controls:

[0160] Time interval of the 3rd - 4th orbit controls:

[0161] Among them, a AD1 is the semi - major axis of the initial adjustment orbit, a AT is the target orbit semi - major axis of the transfer orbit, a AD2 is the semi - major axis of the terminal adjustment orbit.

[0162] Furthermore, the embodiment of the present invention also provides an implementation manner for determining the phase adjustment control strategy corresponding to the main body star without involving the transfer orbit during the phase adjustment process of the main body star. Refer to the following steps 6A to 6B:

[0163] Step 6A, based on the initial orbit parameters and the target orbit parameters, determine the orbit parameters corresponding to the target adjustment orbit during the phase adjustment process.

[0164] Among them, the target adjustment orbit is the orbit generated during the process of the main body star adjusting from the current orbit to the orbit of the target star. The orbit parameters include the target adjustment orbit semi - major axis, the target adjustment orbit angular velocity, the target adjustment orbit eccentricity, the target adjustment orbit angular momentum, the target adjustment orbit perigee velocity, and the target adjustment orbit apogee velocity.

[0165] In one example, the orbit parameters corresponding to the target adjustment orbit during the phase adjustment process can be determined according to the following formula:

[0166] Adjustment orbit semi - major axis:

[0167] Adjustment orbit angular velocity:

[0168] Adjustment orbit eccentricity:

[0169] Adjust the orbital angular momentum:

[0170] Adjust the perigee velocity of the orbit:

[0171] Adjust the apogee velocity of the orbit:

[0172] Step 6B, based on the orbital parameters corresponding to the target adjustment orbit, determine the multiple velocity increments, the initial parking duration, and the time interval between two adjacent orbit controls involved in the phasing process, so as to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0173] In one example, if the semi-major axis of the main body satellite is smaller than that of the target satellite, that is, a S < a T , then determine the two velocity increments involved in the phasing process according to the following formula:

[0174] Δv 1 = vp AD - v S ;

[0175] Δv 2 = v T - va AD ;

[0176]

[0177] On this basis, calculate the initial parking duration according to the following formula:

[0178]

[0179] In one example, if the semi-major axis of the main body satellite is larger than that of the target satellite, that is, a S > a T , then determine the two velocity increments involved in the phasing process according to the following formula:

[0180] Δv 1 = va AD - v S ;

[0181] Δv 2 = v T - vp AD ;

[0182]

[0183] On this basis, calculate the initial parking duration according to the following formula:

[0184]

[0185] In one example, the time interval between two orbit controls is calculated according to the following formula:

[0186] Furthermore, the phase adjustment control strategy method based on Newton iteration provided by the embodiments of the present invention includes: the transition orbit uses lift-off and descent orbit judgment, the semi-major axis of the transition orbit is iteratively designed, and the phase adjustment speed increment calculation link, which can be used for the satellite to perform phase adjustment with time constraints. Specifically, refer to Figure 5 the overall flowchart of a method for formulating a phase adjustment control strategy based on Newton iteration shown in the figure. It includes: determining whether a transition orbit needs to be designed; if the judgment result is no, then calculating the 2-pulse speed increment and the orbit control time interval; if the judgment result is yes, then calculating the lift-off and descent orbit phase adjustment strategy of the transition orbit, calculating the actual duration required for phase adjustment, calculating the semi-major axis of phase adjustment by Newton iteration (i.e., the target orbit semi-major axis corresponding to the transition orbit), and calculating the 4-pulse speed increment and the orbit control time interval.

[0187] In summary, due to the adoption of the above technical solutions in the embodiments of the present invention, combining the dual constraints of phase adjustment duration constraint and minimum speed increment, designing multi-loop transition orbits, and using the Newton iteration algorithm to calculate the transition orbits, the phase adjustment problem under the phase adjustment duration constraint and minimum speed increment is solved. Phase adjustment can be achieved with the minimum speed increment within the specified time, reducing fuel consumption and saving launch costs.

[0188] Based on the foregoing embodiments, the embodiments of the present invention provide a device for formulating a phase adjustment control strategy based on Newton iteration. Refer to Figure 6 the structural schematic diagram of a device for formulating a phase adjustment control strategy based on Newton iteration shown in the figure. The device mainly includes the following parts:

[0189] A judgment module 602, configured to obtain the initial orbit parameters corresponding to the main body satellite and the target orbit parameters corresponding to the target satellite, and based on the preset phase angle to be adjusted, the phase adjustment time constraint, the initial orbit parameters, and the target orbit parameters, judge whether a transition orbit is designed in the phase adjustment process of the main body satellite; wherein, the phase adjustment process is the process of adjusting the main body satellite to the orbit height where the target satellite is located;

[0190] A transition orbit generation module 604, configured to determine an orbit generation strategy to generate the transition orbit required for the phase adjustment process when the judgment result of the judgment module is yes;

[0191] A loop number and duration determination module 606, configured to determine the number of orbits of the main body satellite during the phase adjustment process and the actual duration required for phase adjustment based on the phase adjustment time constraint and the transition orbit;

[0192] The semi-major axis determination module 608 is configured to use the Newton iteration algorithm to determine the target orbital semi-major axis corresponding to the transfer orbit based on the number of running cycles and the actual duration required for phase adjustment;

[0193] The strategy determination module 610 is configured to determine the phase adjustment control strategy corresponding to the main body satellite according to the initial orbital parameters, the target orbital parameters, and the target orbital semi-major axis corresponding to the transfer orbit.

[0194] The phase adjustment control strategy formulation device based on Newton iteration provided by the embodiments of the present invention restricts the phase adjustment time, and when it is determined that a transfer orbit needs to be designed, designs a multi-cycle transfer orbit, uses the Newton iteration algorithm to determine the target orbital semi-major axis corresponding to the transfer orbit, and then obtains the phase adjustment control strategy, so as to minimize the velocity increment on the premise of restricting the phase adjustment time, save the fuel required for phase adjustment, and reduce the launch cost of the main body satellite.

[0195] In one implementation, the initial orbital parameters include the semi-major axis of the main body satellite and the phase angle of the main body satellite, and the target orbital parameters include the semi-major axis of the target satellite and the phase angle of the target satellite; the judgment module 602 is further configured to:

[0196] Based on the semi-major axis of the main body satellite and the semi-major axis of the target satellite, determine the orbital angular velocity of the main body satellite and the orbital angular velocity of the target satellite respectively;

[0197] If the orbital angular velocity of the main body satellite is equal to the orbital acceleration of the target satellite, it is determined that a transfer orbit needs to be designed for the phase adjustment process of the main body satellite;

[0198] If the orbital angular velocity of the main body satellite is not equal to the orbital acceleration of the target satellite, based on the phase angle to be adjusted, the semi-major axis of the main body satellite, the phase angle of the main body satellite, the semi-major axis of the target satellite, and the phase angle of the target satellite, determine the estimated duration required for phase adjustment in the assumed scenario without designing a transfer orbit;

[0199] If the estimated duration required for phase adjustment does not meet the phase adjustment time constraint, it is determined that a transfer orbit needs to be designed for the phase adjustment process of the main body satellite.

[0200] In one implementation, the transfer orbit generation module 604 is further configured to:

[0201] Based on the phase angle to be adjusted and the phase adjustment time constraint, determine the first semi-major axis adjustment amount of the main body satellite when adopting the ascending orbit phase adjustment strategy and the second semi-major axis adjustment amount of the main body satellite when adopting the descending orbit phase adjustment strategy respectively;

[0202] If the first semi-major axis adjustment amount is less than the second semi-major axis adjustment amount, determine the ascending orbit phase adjustment strategy as the orbit generation strategy, and set the transfer orbit required for the phase adjustment process to 1;

[0203] If the adjustment amount of the first semi-major axis is greater than that of the second semi-major axis, the descending orbit adjustment phase strategy is determined as the orbit generation strategy, and the transition orbit required for the phase adjustment process is set to -1.

[0204] In one implementation, the lap number and duration determination module 606 is further configured to:

[0205] Determine the phase adjustment compensation duration corresponding to the main body satellite based on the phase adjustment time constraint;

[0206] Determine the number of laps of the target satellite during the phase adjustment process based on the phase adjustment time constraint and the phase adjustment compensation duration;

[0207] If the orbit generation strategy adopts the ascending orbit adjustment phase strategy, the number of laps of the main body satellite during the phase adjustment process is equal to the number of laps of the target satellite; or, if the orbit generation strategy adopts the descending orbit adjustment phase strategy, the number of laps of the main body satellite during the phase adjustment process is equal to the sum of the number of laps of the target satellite and a specified value;

[0208] And determine the actual duration required for phase adjustment according to the phase adjustment compensation duration and the number of laps of the target satellite.

[0209] In one implementation, the semi-major axis determination module 608 is further configured to:

[0210] Set the semi-major axis of the main body satellite in the initial orbit parameters to the initial orbit semi-major axis corresponding to the transition orbit, and determine the deviation orbit semi-major axis corresponding to the transition orbit;

[0211] Substitute the initial orbit semi-major axis and the deviation orbit semi-major axis into the fitness function in the Newton iteration algorithm respectively to obtain the fitness value corresponding to the initial orbit semi-major axis and the fitness value corresponding to the deviation orbit semi-major axis, and determine the semi-major axis deviation amount based on the fitness value;

[0212] If the semi-major axis deviation amount is greater than or equal to the preset deviation amount threshold, adjust the initial orbit semi-major axis based on the semi-major axis deviation amount, and re-determine the deviation orbit semi-major axis corresponding to the transition orbit until the re-determined semi-major axis deviation amount is less than the preset deviation amount threshold, and set the adjusted initial orbit semi-major axis as the target orbit semi-major axis corresponding to the transition orbit.

[0213] In one implementation, the strategy determination module 610 is further configured to:

[0214] Determine the orbit parameters corresponding to the initial adjustment orbit and the end adjustment orbit respectively during the phase adjustment process according to the initial orbit parameters, the target orbit parameters and the target orbit semi-major axis corresponding to the transition orbit; wherein, the initial adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the current orbit to the transition orbit, and the end adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the transition orbit to the orbit where the target satellite is located;

[0215] Based on the orbital parameters corresponding to the initial adjustment orbit and the terminal adjustment orbit respectively, determine the multiple velocity increments involved in the phase adjustment process and the time interval between two adjacent orbit controls, so as to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0216] In one implementation, the method further includes:

[0217] If the phase adjustment process of the main body satellite does not need to involve a transfer orbit, based on the initial orbital parameters and the target orbital parameters, determine the orbital parameters corresponding to the target adjustment orbit in the phase adjustment process; wherein, the target adjustment orbit is the orbit generated during the process of the main body satellite adjusting from the current orbit to the orbit where the target satellite is located;

[0218] Based on the orbital parameters corresponding to the target adjustment orbit, determine the multiple velocity increments, the initial parking duration, and the time interval between two adjacent orbit controls involved in the phase adjustment process, so as to obtain the phase adjustment control strategy corresponding to the main body satellite.

[0219] The device provided by the embodiments of the present invention has the same implementation principle and the same technical effects as the foregoing method embodiments. For the sake of brief description, for the parts not mentioned in the device embodiments, reference may be made to the corresponding content in the foregoing method embodiments.

[0220] The embodiments of the present invention provide an electronic device. Specifically, the electronic device includes a processor and a storage device; a computer program is stored on the storage device, and when the computer program is run by the processor, it executes the method according to any one of the foregoing implementation manners.

[0221] Figure 7 FIG. is a schematic structural diagram of an electronic device provided by an embodiment of the present invention. The electronic device 100 includes: a processor 70, a memory 71, a bus 72, and a communication interface 73. The processor 70, the communication interface 73, and the memory 71 are connected through the bus 72; the processor 70 is used to execute an executable module stored in the memory 71, such as a computer program.

[0222] Among them, the memory 71 may include a high-speed random access memory (RAM, Random Access Memory), and may also include a non-volatile memory, such as at least one disk memory. Through at least one communication interface 73 (which may be wired or wireless), a communication connection between the system network element and at least one other network element is realized, and the Internet, a wide area network, a local area network, a metropolitan area network, etc. can be used.

[0223] The bus 72 may be an ISA bus, a PCI bus, an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. For the sake of convenience of representation,Figure 7 is represented only by a bidirectional arrow, but does not mean that there is only one bus or one type of bus.

[0224] Among them, the memory 71 is used to store a program. After receiving an execution instruction, the processor 70 executes the program. The method executed by the device defined by the flow process disclosed in any embodiment of the foregoing embodiments of the present invention can be applied to the processor 70 or implemented by the processor 70.

[0225] The processor 70 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the integrated logic circuit in the hardware of the processor 70 or by instructions in the form of software. The above-mentioned processor 70 may be a general-purpose processor, including a central processing unit (CPU for short), a network processor (NP for short), etc.; it may also be a digital signal processor (DSP for short), an application specific integrated circuit (ASIC for short), a field-programmable gate array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of the present invention. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present invention can be directly embodied as being executed and completed by a hardware decoding processor, or by a combination of hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory 71, and the processor 70 reads the information in the memory 71 and combines its hardware to complete the steps of the above method.

[0226] The computer program product of the readable storage medium provided by the embodiments of the present invention includes a computer-readable storage medium storing program code. The instructions included in the program code can be used to execute the method described in the foregoing method embodiments. For the specific implementation, reference can be made to the foregoing method embodiments, which will not be elaborated herein.

[0227] If the above-mentioned functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The foregoing storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs that can store program codes.

[0228] Finally, it should be noted that the above-mentioned embodiments are only specific implementation manners of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting it. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that any person skilled in the art within the technical scope disclosed by the present invention can still modify the technical solutions recorded in the foregoing embodiments or easily conceive of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes, or replacements 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 and should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A method for formulating a phase adjustment control strategy based on Newton iteration, characterized in that: include: Acquire the initial orbital parameters corresponding to the main body star and the target orbital parameters corresponding to the target star, and determine whether the phase adjustment process of the main body star designs a transition orbit based on the preset phase angle to be adjusted, the phase adjustment time constraint, the initial orbital parameters and the target orbital parameters; wherein the phase adjustment process is a process of adjusting the main body star to the orbital height of the target star; If yes, determining an orbit generation strategy to generate the transition orbit required for the phasing process; Based on the phase adjustment time constraint and the transition orbit, determining the orbit number of the main body star and the actual duration required for the phase adjustment during the phase adjustment process; Using a Newton iteration algorithm, based on the number of running circles and the real time required for the phase adjustment, determine the semi-major axis of the target orbit corresponding to the transition orbit; A phase adjustment control strategy corresponding to the main body star is determined according to the initial orbit parameters, the target orbit parameters and the target orbit semi-major axis corresponding to the transition orbit.

2. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The initial orbit parameters include the semi-major axis of the main body star and the phase angle of the main body star, and the target orbit parameters include the semi-major axis of the target star and the phase angle of the target star; The step of judging whether the phase adjustment process of the main body star is to design a transition orbit based on the preset phase angle to be adjusted, the phase adjustment time constraint, the initial orbit parameters and the target orbit parameters comprises: Determine the orbital angular velocity of the subject star and the orbital angular velocity of the target star based on the semi-major axis of the subject star and the semi-major axis of the target star; If the orbital angular velocity of the subject star is equal to the orbital acceleration of the target star, it is determined that the phase adjustment process of the subject star needs to design a transition orbit; If the orbital angular velocity of the main body star is not equal to the orbital acceleration of the target star, then based on the phase angle to be adjusted, the semi-major axis of the main body star, the phase angle of the main body star, the semi-major axis of the target star and the phase angle of the target star, determine the estimated duration required for phase adjustment under the assumed scenario of not designing a transition orbit; If the estimated duration required for the phase adjustment does not satisfy the phase adjustment time constraint, it is determined that the phase adjustment process of the main body star needs to design a transition orbit.

3. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The step of determining an orbit generation strategy to generate the transition orbit required for the phase modulation process includes: Based on the phase angle to be adjusted and the phase adjustment time constraint, respectively determine a first semi-major axis adjustment amount of the main body satellite when an orbit-raising phase adjustment strategy is adopted, and a second semi-major axis adjustment amount of the main body satellite when an orbit-lowering phase adjustment strategy is adopted; If the first semi-major axis adjustment amount is less than the second semi-major axis adjustment amount, determining the orbit raising adjustment phase strategy as the orbit generation strategy, and setting the transition orbit required for the phase adjustment process to 1; If the first semi-major axis adjustment amount is greater than the second semi-major axis adjustment amount, the orbit-dropping adjustment phase strategy is determined as the orbit generation strategy, and the transition orbit required by the phase adjustment process is set to -1.

4. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The step of determining the number of orbits of the main body star and the actual duration required for phase adjustment during the phase adjustment process based on the phase adjustment time constraint and the transition orbit includes: Based on the phase adjustment time constraint, determining the phase adjustment compensation duration corresponding to the main body star; Based on the phase adjustment time constraint and the phase adjustment compensation duration, determining the number of orbits of the target star during the phase adjustment process; If the orbit generation strategy adopts the orbit raising phase adjustment strategy, the orbit number of the main body star during the phase adjustment process is equal to the orbit number of the target star; or, if the orbit generation strategy adopts the orbit lowering phase adjustment strategy, the orbit number of the main body star during the phase adjustment process is equal to the sum of the orbit number of the target star and the specified value; And, according to the phase adjustment compensation time and the orbit number of the target star, the actual time required for the phase adjustment is determined.

5. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The step of determining the semi-major axis of the target orbit corresponding to the transition orbit based on the number of running circles and the real time required for the phase adjustment by using the Newton iteration algorithm comprises: The semi-major axis of the main body in the initial orbit parameter is set as the semi-major axis of the initial orbit corresponding to the transition orbit, and the semi-major axis of the deviation orbit corresponding to the transition orbit is determined; Substituting the initial orbit semi-major axis and the deviation orbit semi-major axis into the fitness function in the Newton iteration algorithm respectively to obtain the fitness value corresponding to the initial orbit semi-major axis and the fitness value corresponding to the deviation orbit semi-major axis, and determining the semi-major axis deviation based on the fitness value; If the semi-major axis deviation is greater than or equal to a preset deviation threshold, the semi-major axis of the initial orbit is adjusted based on the semi-major axis deviation, and the semi-major axis of the deviation orbit corresponding to the transition orbit is re-determined until the re-determined semi-major axis deviation is less than the preset deviation threshold, and the adjusted semi-major axis of the initial orbit is determined as the semi-major axis of the target orbit corresponding to the transition orbit.

6. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The step of determining the phase adjustment control strategy corresponding to the main body star according to the initial orbit parameters, the target orbit parameters and the target orbit semi-major axis corresponding to the transition orbit comprises: According to the initial orbital parameters, the target orbital parameters and the semi-major axis of the target orbit corresponding to the transition orbit, the orbital parameters corresponding to the initial adjustment orbit and the final adjustment orbit in the phase adjustment process are determined; wherein the initial adjustment orbit is the orbit generated in the process of adjusting the main body star from the current orbit to the transition orbit, and the final adjustment orbit is the orbit generated in the process of adjusting the main body star from the transition orbit to the orbit of the target star; Based on the orbital parameters corresponding to the initial adjustment orbit and the final adjustment orbit respectively, multiple velocity increments involved in the phase adjustment process and the time interval between two adjacent orbit controls are determined to obtain a phase adjustment control strategy corresponding to the main body satellite.

7. The method for formulating a phase adjustment control strategy based on Newton iteration according to claim 1, characterized in that: The method further comprises: If the phase adjustment process of the main body star does not need to involve a transition orbit, then based on the initial orbital parameters and the target orbital parameters, the orbital parameters corresponding to the target adjustment orbit in the phase adjustment process are determined; wherein the target adjustment orbit is the orbit generated in the process of adjusting the main body star from the current orbit to the orbit of the target star; Based on the orbital parameters corresponding to the target adjustment orbit, multiple velocity increments, initial parking duration, and time interval between two adjacent orbital controls involved in the phase adjustment process are determined to obtain a phase adjustment control strategy corresponding to the main body satellite.

8. A phase adjustment control strategy formulation device based on Newton iteration, characterized in that: include: A judgment module is used to obtain the initial orbital parameters corresponding to the main body star and the target orbital parameters corresponding to the target star, and judge whether the phase adjustment process of the main body star designs a transition orbit based on the preset phase angle to be adjusted, the phase adjustment time constraint, the initial orbital parameters and the target orbital parameters; wherein the phase adjustment process is a process of adjusting the main body star to the orbital height of the target star; A transition track generation module, used for determining a track generation strategy to generate a transition track required for the phase modulation process when the judgment result of the judgment module is yes; A circle number and duration determination module, used to determine the number of circles of the main body satellite and the actual duration required for the phase adjustment during the phase adjustment process based on the phase adjustment time constraint and the transition orbit; A semi-major axis determination module is used to determine the semi-major axis of the target orbit corresponding to the transition orbit based on the number of running circles and the real time required for the phase adjustment by using a Newton iteration algorithm; A strategy determination module is used to determine the phase adjustment control strategy corresponding to the main body star according to the initial orbit parameters, the target orbit parameters and the target orbit semi-major axis corresponding to the transition orbit.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer executable instructions that can be executed by the processor, and the processor executes the computer executable instructions to implement the method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer-executable instructions, and when the computer-executable instructions are called and executed by a processor, the computer-executable instructions prompt the processor to implement the method according to any one of claims 1 to 7.

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