A method for determining rocket launch parameters and probe orbit insertion parameters

Abstract

The application discloses a rocket launch parameter and a detector orbit injection orbit parameter determination method and device, belongs to the technical field of spacecraft orbit design, and is used for jointly and rapidly determining the rocket launch parameter and the detector orbit injection orbit parameter. In the method, the rocket inclination value range and the corresponding rocket sliding time value range are determined according to the detector orbit injection orbit inclination, the expected rocket sliding time is determined based on the detector orbit injection orbit perigee amplitude, and the expected rocket orbit injection orbit ascending node longitude is determined based on the expected rocket sliding time. The expected detector orbit injection time is determined according to the ascending node longitude difference between the rocket and the detector. The rocket launch time and the launch azimuth angle are determined according to the detector orbit injection orbit inclination, the rocket inclination value range, the expected rocket sliding time, the rocket sliding time value range and the expected detector orbit injection time, and the rocket launch parameter consistent with the detector orbit injection orbit parameter is obtained.

Description

Technical Field

[0001] This application relates to the field of spacecraft orbit design technology, and in particular to a method, apparatus, electronic equipment and storage medium for determining rocket launch parameters and probe orbit parameters. Background Technology

[0002] A probe is an unmanned spacecraft used to explore a target planet. The probe's orbital insertion trajectory is a transfer trajectory launched from Earth by a rocket to the target planet. This trajectory is typically determined based on a pre-set insertion time and target orbital parameters. During launch, the rocket's orbital insertion trajectory and the probe's orbital insertion trajectory must be aligned to ensure the probe is placed into the mission's required target orbit. Due to limitations in launch site location and the orbital parameters of the rocket's trajectory, alignment between the rocket and probe orbital insertion trajectories can only be guaranteed under specific launch times and azimuth angles. Therefore, before launching the probe, the rocket's orbital insertion trajectory and the probe's orbital insertion trajectory must be spliced ​​together to determine the launch time and azimuth angle. Thus, rapidly determining the launch time and azimuth angle by combining the rocket's trajectory and the probe's orbital insertion trajectory has become a key development area in this field. Summary of the Invention

[0003] This application provides a method, apparatus, electronic device, and storage medium for determining rocket launch parameters and probe orbital parameters, which are used to jointly and quickly determine rocket launch parameters and probe orbital parameters.

[0004] In a first aspect, embodiments of this application provide a method for determining rocket launch parameters and probe orbital parameters, comprising: acquiring the launch date of the probe and a preset probe orbital insertion time; determining the probe orbital parameters corresponding to the probe orbital insertion time based on the correspondence between the probe orbital insertion time and the probe orbital parameters, wherein the probe orbital parameters include the probe orbital inclination, the probe orbital perigee argument, and the longitude of the probe orbital ascending node; determining the rocket inclination range to which the probe orbital inclination belongs from a preset set of rocket orbital inclinations; determining the rocket glide time range corresponding to the rocket inclination range based on a preset correspondence between the rocket orbital inclination and rocket glide time; determining the rocket perigee argument range corresponding to the rocket glide time range based on a preset correspondence between the rocket orbital inclination and rocket glide time; determining the expected rocket glide time based on the rocket perigee argument range, the rocket glide time range, and the probe orbital perigee argument; and determining the rocket orbital inclination range, The predicted longitude of the ascending node of the rocket's orbit is determined by the range of values ​​for the rocket's glide time and the predicted rocket glide time. Based on the correspondence between the ascending node longitude and time, the time difference between the probe's and rocket's ascending node longitudes is determined, and it is confirmed that the time difference between the probe and rocket's ascending node longitudes meets the set targets. Based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, the predicted longitude of the rocket's orbit is determined according to the probe's orbital inclination, the range of values ​​for the rocket's inclination, and the predicted rocket glide time. The estimated rocket-satellite separation flight time is determined by the flight time and the range of values ​​for the rocket's coasting time; the rocket launch time is determined based on the estimated rocket-satellite separation flight time and the preset probe insertion time; the rocket launch azimuth is determined based on the preset correspondence between the rocket launch azimuth, the rocket insertion orbit inclination, and the rocket coasting time, according to the probe insertion orbit inclination, the range of values ​​for the rocket inclination, the estimated rocket coasting time, and the range of values ​​for the rocket coasting time; the rocket is launched according to the rocket launch time and the rocket launch azimuth.

[0005] Using this method, the first device determines the probe's orbital parameters based on the preset probe orbital insertion time, and determines the rocket launch parameters based on the correspondence between the probe's orbital parameters and multiple preset orbital parameters. The rocket is then launched based on these launch parameters, thereby improving the efficiency of determining the rocket launch parameters while ensuring that the rocket launch parameters are reasonable, and achieving joint and rapid determination of the rocket launch parameters and the probe's orbital parameters.

[0006] In one optional implementation, after determining the probe orbit parameters corresponding to the probe's orbit insertion time, the method further includes: determining whether the longitude of the ascending node of the probe's orbit meets the longitude value of the ascending node within a preset range of longitudes of the rocket's orbit; when the longitude of the ascending node of the probe's orbit does not meet the longitude value of the ascending node within the preset range of longitudes of the rocket's orbit, determining the time corresponding to the longitude of the ascending node of the probe's orbit based on the correspondence between the longitude of the ascending node and time, and adjusting the preset probe orbit insertion time according to the time.

[0007] In one optional implementation, before determining the expected rocket glide time based on the range of the rocket's perigee argument, the range of the rocket's glide time, and the perigee argument of the probe's orbital insertion, the method further includes: determining that the perigee argument of the probe's orbital insertion falls within the range of the rocket's perigee argument.

[0008] In one optional implementation, determining the rocket perigee argument range corresponding to the rocket glide time range based on the preset correspondence between the rocket's perigee argument and its glide time includes: obtaining a perigee argument trajectory matrix, which is determined based on multiple sets of first rocket entry parameters, including the rocket entry trajectory inclination, rocket glide time, and rocket entry trajectory perigee argument, wherein the rocket entry trajectory corresponding to the first rocket entry parameters is connected to the probe's entry trajectory; and processing each rocket glide time in the rocket glide time range using a grid interpolation method based on the perigee argument trajectory matrix to determine the rocket perigee argument range corresponding to the rocket glide time range.

[0009] In one optional implementation, determining the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of the rocket's orbital inclination angle, the range of the rocket's glide time, and the expected rocket glide time includes: obtaining an ascending node trajectory matrix, wherein the ascending node longitude trajectory matrix is ​​determined based on multiple sets of second rocket entry parameters, the second rocket entry parameters including the rocket's orbital inclination angle, the rocket's glide time, and the longitude of the ascending node of the rocket's orbital insertion trajectory, and the rocket's orbital insertion trajectory corresponding to the second rocket entry parameters being connected to the probe's orbital insertion trajectory; and determining the expected longitude of the ascending node of the rocket's orbital insertion trajectory by processing the range of the rocket's orbital inclination angle, the range of the rocket's glide time, and the expected rocket glide time using a grid interpolation method based on the ascending node trajectory matrix.

[0010] In one optional implementation, when the time difference between the probe and the rocket's entry into orbit does not meet a set target, the method further includes: adjusting the preset probe entry time based on the time difference between the probe and the rocket's entry into orbit.

[0011] In one optional implementation, determining the rocket launch time includes: obtaining a rocket-satellite separation flight time trajectory matrix, which is determined based on multiple sets of third rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket-satellite separation flight time, wherein the rocket orbital corresponding to the third rocket orbital parameters is connected to the probe orbital; based on the rocket-satellite separation flight time trajectory matrix, a grid interpolation method is used to process the probe orbital inclination, the range of the rocket inclination, the expected rocket glide time, and the range of the rocket glide time to obtain the expected rocket-satellite separation flight time; and subtracting the expected probe orbital time from the expected rocket-satellite separation flight time to obtain the rocket launch time.

[0012] In one optional implementation, determining the rocket launch azimuth includes: obtaining a rocket launch azimuth trajectory matrix, which is determined based on multiple sets of fourth rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket launch azimuth, wherein the rocket orbital corresponding to the fourth rocket orbital parameters is connected to the probe orbital; and obtaining the rocket launch azimuth by processing the probe orbital inclination, the rocket inclination range, the expected rocket glide time, and the rocket glide time range using a grid interpolation method based on the rocket launch azimuth trajectory matrix.

[0013] Secondly, embodiments of this application provide a device for determining rocket launch parameters and probe orbital parameters, comprising:

[0014] The communication module is used to acquire the launch date and preset orbit insertion time of the probe; the processing module is used to determine the probe's orbit insertion parameters corresponding to the probe's orbit insertion time based on the correspondence between the probe's orbit insertion time and the probe's orbital parameters, the probe's orbital parameters including the probe's orbital inclination, the probe's orbital perigee argument, and the longitude of the probe's ascending node; the processing module is also used to determine the rocket inclination range to which the probe's orbital inclination belongs from a preset set of rocket orbital inclination values; the processing module is also used to determine the rocket inclination range to which the probe's orbital inclination belongs based on the preset set of rocket orbital inclination values. The processing module determines the rocket's glide time range corresponding to the rocket's inclination angle range based on the correspondence between the inclination angle and the rocket's glide time. The processing module is further configured to determine the rocket's perigee angle range corresponding to the rocket's glide time range based on a preset correspondence between the rocket's perigee angle and the rocket's glide time. The processing module is also configured to determine the expected rocket glide time based on the rocket's perigee angle range, the rocket's glide time range, and the probe's perigee angle. The processing module is also configured to determine the expected rocket glide time based on the rocket's orbital inclination angle range, the rocket's glide time range, and the orbital perigee angle of the probe. The estimated rocket glide time determines the estimated longitude of the ascending node of the rocket's orbit. The processing module is further configured to, based on the correspondence between the ascending node longitude and time, determine the orbital insertion time difference between the probe and the rocket corresponding to the ascending node longitude of the probe's orbit and the rocket's orbit, and determine if the orbital insertion time difference between the probe and the rocket meets a set target. The processing module is also configured to, based on a preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, determine the orbital insertion time of the probe, the range of values ​​for the rocket's inclination angle, the estimated rocket glide time, and the rocket glide time... The processing module determines the expected rocket-satellite separation flight time based on the expected rocket-satellite separation flight time and the preset probe insertion time. The processing module is also used to determine the rocket launch time based on the preset correspondence between the rocket launch azimuth angle, the rocket insertion orbit inclination angle, and the rocket coasting time, according to the probe insertion orbit inclination angle, the range of values ​​for the rocket inclination angle, the expected rocket coasting time, and the range of values ​​for the rocket coasting time. The processing module is further used to launch the rocket based on the rocket launch time and the rocket launch azimuth angle.

[0015] In one optional implementation, after determining the probe's orbital parameters corresponding to the probe's orbital insertion time, the processing module is specifically used to: determine whether the longitude of the probe's orbital ascending node meets the longitude value of the ascending node within a preset range of rocket orbital ascending node longitudes; when the longitude of the probe's orbital ascending node does not meet the longitude value of the ascending node within the preset range of rocket orbital ascending node longitudes, determine the time corresponding to the longitude of the probe's orbital ascending node based on the correspondence between the longitude of the ascending node and time, and adjust the preset probe orbital insertion time according to the time.

[0016] In one optional implementation, before determining the expected rocket glide time based on the range of the rocket's perigee argument, the range of the rocket's glide time, and the perigee argument of the probe's orbital insertion, the processing module is further configured to: determine that the perigee argument of the probe's orbital insertion belongs to the range of the rocket's perigee argument.

[0017] In one optional implementation, determining the rocket perigee argument range corresponding to the rocket glide time range based on the preset correspondence between the rocket's perigee argument and its glide time includes: a communication module specifically used to acquire a perigee argument trajectory matrix, which is determined based on multiple sets of first rocket entry parameters, including the rocket entry trajectory inclination, rocket glide time, and rocket entry trajectory perigee argument, wherein the rocket entry trajectory corresponding to the first rocket entry parameters is connected to the probe's entry trajectory; and a processing module specifically used to process each rocket glide time in the rocket glide time range using a grid interpolation method based on the perigee argument trajectory matrix to determine the rocket perigee argument range corresponding to the rocket glide time range.

[0018] In one optional implementation, determining the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of the rocket's orbital inclination angle, the range of the rocket's glide time, and the expected rocket glide time includes: a communication module specifically used to acquire the ascending node trajectory matrix, wherein the ascending node longitude trajectory matrix is ​​determined based on multiple sets of second rocket entry parameters, the second rocket entry parameters including the rocket's orbital inclination angle, the rocket's glide time, and the longitude of the ascending node of the rocket's orbital insertion trajectory, and the rocket's orbital insertion trajectory corresponding to the second rocket entry parameters is connected to the probe's orbital insertion trajectory; and a processing module specifically used to determine the expected longitude of the ascending node of the rocket's orbital insertion trajectory by processing the range of the rocket's orbital inclination angle, the range of the rocket's glide time, and the expected rocket glide time using a grid interpolation method based on the ascending node trajectory matrix.

[0019] In one optional implementation, when the time difference between the probe and the rocket's entry into orbit does not meet the set target, the processing module is further configured to: adjust the preset probe entry into orbit time according to the time difference between the probe and the rocket's entry into orbit.

[0020] In one optional implementation, determining the rocket launch time includes: the communication module, specifically used to acquire the rocket-satellite separation flight time trajectory matrix, which is determined based on multiple sets of third rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket-satellite separation flight time, wherein the rocket orbital corresponding to the third rocket orbital parameters is connected to the probe orbital; the processing module, specifically used to, based on the rocket-satellite separation flight time trajectory matrix, use a grid interpolation method to process the probe orbital inclination, the range of the rocket inclination, the expected rocket glide time, and the range of the rocket glide time to obtain the expected rocket-satellite separation flight time; and subtracting the preset probe orbital time from the expected rocket-satellite separation flight time to obtain the rocket launch time.

[0021] In one optional implementation, determining the rocket launch azimuth includes: the communication module, specifically used to acquire the rocket launch azimuth trajectory matrix, which is determined based on multiple sets of fourth rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket launch azimuth, wherein the rocket orbital corresponding to the fourth rocket orbital parameters is connected to the probe orbital; and the processing module, specifically used to process the probe orbital inclination, the rocket inclination range, the expected rocket glide time, and the rocket glide time range based on the rocket launch azimuth trajectory matrix using a grid interpolation method to obtain the rocket launch azimuth.

[0022] Thirdly, embodiments of this application provide an electronic device, including: at least one processor, and a memory communicatively connected to the at least one processor, wherein:

[0023] The memory stores a computer program that can be executed by at least one processor, which enables the at least one processor to perform the rocket launch method described above.

[0024] Fourthly, embodiments of this application provide a storage medium in which the electronic device can execute the above-described rocket launch method when a computer program in the storage medium is executed by a processor of an electronic device.

[0025] Fifthly, embodiments of this application provide a computer program product, including a computer program that, when executed by a processor, implements the above-described rocket launch method.

[0026] The technical effects brought about by the second to fifth aspects above can be found in the description of the beneficial effects of the corresponding solutions in the first aspect above, and will not be repeated here. Attached Figure Description

[0027] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0028] Figure 1 A flowchart illustrating a method for determining rocket launch parameters and probe orbit parameters provided in this application embodiment;

[0029] Figure 2 This is a schematic diagram illustrating the determination of grid crossing point interpolation in an embodiment of this application.

[0030] Figure 3 A schematic diagram of a device for determining rocket launch parameters and probe orbit parameters provided in this application embodiment;

[0031] Figure 4 This is a schematic diagram of the hardware structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application. Unless otherwise specified, the embodiments and features in the embodiments of this application can be arbitrarily combined with each other. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be performed in a different order than that shown here.

[0033] The terms "first," "second," "third," and "fourth," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, not to describe a specific order. Furthermore, the term "comprising," and any variations thereof, is intended to cover non-exclusive protection. For example, a process, method, system, product, or device that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or devices. The term "multiple" in this application can mean at least two, for example, two, three, or more; this application does not impose limitations on its embodiments.

[0034] The data collection, dissemination, and use in this application all comply with relevant national laws and regulations.

[0035] Before introducing the determination of rocket launch parameters and probe orbit parameters provided in the embodiments of this application, the technical background of the embodiments of this application will be described in detail below for ease of understanding.

[0036] In rocket launch schemes, the correspondence between the rocket launch azimuth and the rocket's orbital inclination is usually fixed; different launch azimuths correspond to different orbital inclinations. Furthermore, the longitude of the ascending node of the rocket's orbit often differs depending on the launch azimuth, and different launch azimuths also correspond to different perigee arguments. In other words, when the rocket launch azimuth changes, both the longitude of the ascending node and the perigee argument of the probe's orbit will also change.

[0037] During rocket launch, the rocket typically needs to coast in a low Earth orbit (LEO) to wait for a specific time and location before being launched into the target planet's transfer orbit. This LEO is also known as the rocket parking orbit, and the time the rocket spends coasting in this orbit is referred to below as the rocket coasting time.

[0038] The perigee argument of the probe's insertion orbit varies depending on the rocket's glide time, and the longitude of the ascending node also varies. Specifically, the orbital period of the rocket's parking orbit is approximately 90 minutes, the rocket's glide time does not exceed one orbital period, the perigee argument of the rocket's insertion orbit ranges from 0° to 360°, and the longitude of the ascending node ranges from 0° to 22.5°.

[0039] In summary, both the rocket launch azimuth and the rocket's coasting time affect the longitude of the ascending node and the argument of perigee of the rocket's orbit. Therefore, the rocket's orbit can be stitched together with the target planet's transfer orbit by adjusting the rocket launch azimuth and the rocket's coasting time.

[0040] However, due to the limitations of rocket launch site locations and the orbital parameters of rocket launch trajectories, the rocket's orbital insertion can only be guaranteed to align with the probe's orbital insertion under specific launch times and azimuth angles. Therefore, before launching a probe, it is necessary to stitch the rocket's orbital insertion trajectory with the probe's orbital insertion trajectory to determine the launch time and azimuth angle. Thus, how to quickly determine the rocket's launch time and azimuth angle by combining the rocket launch trajectory and the probe's orbital insertion has become a key development point in this field.

[0041] To address the above technical issues, this application provides a method for determining rocket launch parameters and probe orbital parameters, which can be used to jointly and quickly determine rocket launch parameters and probe orbital parameters.

[0042] The method provided in this application includes: obtaining the launch date of the probe and a preset probe orbit insertion time; determining the probe orbit insertion parameters corresponding to the probe orbit insertion time based on the correspondence between the probe orbit insertion time and the probe orbit insertion parameters, including the probe orbit insertion inclination, the probe orbit insertion perigee argument, and the probe orbit insertion ascending node longitude; determining the rocket inclination range to which the probe orbit insertion inclination belongs from a preset set of rocket orbit insertion inclination values; determining the rocket glide time range corresponding to the rocket inclination range based on the preset correspondence between the rocket orbit insertion inclination and the rocket glide time; determining the rocket perigee argument range corresponding to the rocket glide time range based on the preset correspondence between the rocket orbit insertion perigee argument and the rocket glide time; determining the expected rocket glide time based on the rocket perigee argument range, the rocket glide time range, and the probe orbit insertion perigee argument; and determining the expected longitude of the rocket orbit insertion ascending node based on the rocket orbit inclination range, the rocket glide time range, and the expected rocket glide time. Based on the correspondence between the longitude of the ascending node and time, the time difference between the longitude of the ascending node of the probe's orbit and the longitude of the ascending node of the rocket's orbit is determined, and it is confirmed that the time difference between the probe and the rocket meets the set target. Based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, the estimated rocket-satellite separation flight time is determined according to the probe's orbital inclination, the range of rocket inclination values, the expected rocket coasting time, and the range of rocket coasting time values. The rocket launch time is determined based on the estimated rocket-satellite separation flight time and the preset probe orbital insertion time. Based on the preset correspondence between the rocket launch azimuth, the rocket's orbital inclination, and the rocket coasting time, the rocket launch azimuth is determined according to the probe's orbital inclination, the range of rocket inclination values, the expected rocket coasting time, and the range of rocket coasting time values. The rocket is launched according to the rocket launch time and rocket launch azimuth.

[0043] Using this method, the first device determines the probe's orbital parameters based on the preset probe orbital insertion time, and determines the rocket launch parameters based on the correspondence between the probe's orbital parameters and multiple preset orbital parameters. The rocket is then launched based on these launch parameters, thereby improving the efficiency of determining the rocket launch parameters while ensuring that the rocket launch parameters are reasonable, and achieving joint and rapid determination of the rocket launch parameters and the probe's orbital parameters.

[0044] Understandably, in this application, the probe's orbital insertion time can refer to the moment the probe enters the target planet's transfer orbit. The rocket launch time can refer to the moment the rocket is launched from the rocket launch site.

[0045] Figure 1 This is a flowchart illustrating a method for determining rocket launch parameters and probe orbit parameters according to an embodiment of this application. Taking a first device as the executing entity, the target planet as the Moon, and the probe as a lunar probe as an example, the process may include the following steps:

[0046] S101, the first device obtains the launch date of the probe and the preset probe orbit insertion time.

[0047] As an example, the preset probe orbit insertion time can be any time; that is, the preset probe orbit insertion time can be any time on the date the probe is launched.

[0048] As another example, the preset probe orbit insertion time can also be a specific time. That is, the preset probe orbit insertion time can be a specific time within the probe's launch date.

[0049] S102, the first device determines the probe's orbital parameters corresponding to the probe's orbital insertion time based on the correspondence between the probe's orbital insertion time and the probe's orbital parameters. These orbital parameters include the probe's orbital inclination angle, the perigee argument angle, and the longitude of the ascending node.

[0050] In one or more embodiments, the correspondence between the probe's orbital insertion time and its orbital parameters can be preset. Different probe orbital insertion times correspond to different probe orbital parameters.

[0051] For example, the lunar probe's orbital parameters can be the Earth-Moon transfer orbit parameters in the Geocentric J2000 coordinate system, determined by processing the probe's orbital insertion time using Earth-Moon transfer orbit design software. This application can pre-determine the corresponding probe orbital parameters based on different probe orbital insertion times using Earth-Moon transfer orbit design software, thereby obtaining the correspondence between the probe's orbital insertion time and its orbital parameters. Accordingly, the first device can determine the probe's orbital parameters corresponding to the probe's orbital insertion time based on the correspondence between the probe's orbital insertion time and its orbital parameters.

[0052] Understandably, the specific implementation method of obtaining the probe's orbital parameters using Earth-Moon transfer orbit design software is existing technology, and this application will not provide a specific explanation.

[0053] Optionally, the Earth-Moon transfer orbit parameters may include the semi-major axis, eccentricity, inclination, perigee argument, and ascending node longitude. In the geocentric J2000 coordinate system, the semi-major axis can be represented as a. I The eccentricity can be expressed as e I The tilt angle can be expressed as i I The longitude of the ascending node can be expressed as Ω. I The argument of perigee can be expressed as ω I .

[0054] Furthermore, the orbital parameters of the geocentric J2000 coordinate system can be converted to the orbital parameters of the geocentric instantaneous inertial coordinate system. In the geocentric instantaneous inertial coordinate system, the semi-major axis can be represented as a. e The eccentricity can be expressed as e e The tilt angle can be expressed as i e The longitude of the ascending node can be expressed as Ω. e The argument of perigee can be expressed as ω e .

[0055] Optionally, the first device can use Earth-Moon transfer orbit design software to process the probe's orbit insertion time to obtain the corresponding probe orbit insertion parameters. For example, if the pre-stored correspondence between probe orbit insertion times and probe orbit insertion parameters does not include a preset probe orbit insertion time, the first device can use Earth-Moon transfer orbit design software to process that probe orbit insertion time to obtain the corresponding probe orbit insertion parameters.

[0056] In one or more embodiments, after determining the probe orbit parameters corresponding to the probe's orbit insertion time, the first device can also determine whether the longitude of the ascending node of the probe's orbit meets the preset longitude value of the ascending node within the range of the rocket's orbital ascending node longitude.

[0057] The longitude values ​​of the ascending node within the preset range of the rocket's ascending node longitude can be determined based on the maximum and minimum values ​​of the ascending node longitude in the ascending node longitude trajectory matrix. The ascending node longitude trajectory matrix can be determined based on multiple sets of secondary rocket entry parameters. These secondary rocket entry parameters may include the rocket's orbital inclination, rocket glide time, and the longitude of the ascending node. Furthermore, the rocket's orbit corresponding to these secondary rocket entry parameters is aligned with the probe's orbital trajectory.

[0058] The longitude trajectory matrix of the ascending node satisfies:

[0059]

[0060] Among them, the orbital inclination of the rocket can be represented by i. i The rocket's glide time can be expressed as Δt pj The longitude of the ascending node of the rocket's orbit can be expressed as Ω. i The longitude ballistic matrix of the ascending node can be represented as Ω.

[0061] Optionally, the longitude of the ascending node can be determined based on the maximum and minimum values ​​of the longitude of the ascending node in the longitude trajectory matrix.

[0062] In one or more embodiments, when the longitude of the ascending node of the probe's orbit does not meet the preset range of ascending node longitude values ​​for rocket orbits, it indicates that the probe's orbit insertion time corresponding to that longitude does not meet operational requirements. Therefore, this probe orbit insertion time can be excluded, and the first device can re-acquire the probe orbit insertion time. That is, when the longitude of the ascending node of the probe's orbit does not meet the preset range of ascending node longitude values ​​for rocket orbits, step S101 is re-executed.

[0063] Optionally, when the longitude of the ascending node of the probe's orbit does not meet the preset range of ascending node longitude values ​​for rocket orbits, the first device can determine the time corresponding to the longitude of the ascending node of the probe's orbit based on the correspondence between the longitude of the ascending node and time, and adjust the preset probe orbit insertion time according to the time.

[0064] For example, the longitude of the ascending node of the probe's orbit can be expressed as Ω. e The maximum value of the longitude of the ascending node within the preset range of the longitude of the rocket's ascending node can be expressed as Ω. max The minimum value of the longitude of the ascending node within the preset range of the longitude of the rocket's ascending node can be expressed as Ω. min The probe's orbital insertion time can be expressed as t I Then the probe's orbital insertion time satisfies:

[0065] tI =t I +Δt;

[0066] Δt=(Ω e -Ω m )×240;

[0067]

[0068] Here, Δt can be represented as the adjustment time, and 240 can be represented as the number of seconds required for the Earth to rotate 1°.

[0069] Understandably, when the probe's orbital insertion time cannot meet the requirements, the time corresponding to the longitude of the ascending node of the probe's orbit can be determined based on the correspondence between the longitude of the ascending node and time. The preset probe orbital insertion time can then be adjusted according to the time, thereby improving the accuracy of obtaining a probe orbital insertion time that meets the requirements.

[0070] S103, the first device determines the range of rocket inclination angles to which the probe's orbital inclination angle belongs from a preset set of rocket orbital inclination angles.

[0071] In one or more embodiments, the set of rocket orbit inclination angles can be obtained by discretizing the range of values ​​for the rocket orbit inclination angles according to actual operational needs. For example, if the range of values ​​for the set of rocket orbit inclination angles is 20° to 30°, the set of rocket orbit inclination angles can be obtained by discretizing this range according to operational needs as [20°, 24°, 28.7°, 30°].

[0072] The first device can determine the range of rocket inclination angle values ​​that satisfy the probe's orbital inclination angle from the set of rocket orbital inclination angles. For example, if the set of rocket orbital inclination angles can be [20°, 24°, 28.7°, 30°], and the probe's orbital inclination angle can be represented as 21°, then the range of rocket inclination angle values ​​is [20°, 24°].

[0073] The orbital inclination angle of the probe can be expressed as i e The minimum value of the rocket tilt angle range can be expressed as i i The maximum value of the rocket tilt angle can be expressed as i. i+1 Then the range of values ​​for the probe's orbital inclination angle and the rocket's inclination angle satisfies:

[0074] i i ≤i e <i i+1 .

[0075] S104, the first device determines the range of rocket glide time corresponding to the range of rocket inclination angle values ​​based on the preset correspondence between the rocket orbital inclination angle and the rocket glide time.

[0076] Based on existing technology, it is known that different rocket launch azimuth angles and different rocket coasting times both affect the longitude of the ascending node and the argument of perigee of the rocket's orbital insertion. Therefore, multiple combinations of rocket launch azimuth angles and rocket coasting times can be determined based on the rocket launch principle. Furthermore, the correspondence between rocket launch azimuth angles and rocket orbital inclination is often fixed, so a correspondence between rocket orbital inclination and rocket coasting time can be constructed based on multiple combinations of rocket launch azimuth angles and rocket coasting times.

[0077] Accordingly, the first device can determine the range of rocket glide time values ​​corresponding to the range of rocket inclination angle values ​​based on the correspondence between the rocket's orbital inclination angle and the rocket's glide time.

[0078] Optionally, when the relationship between the rocket's orbital inclination and its coasting time does not include the rocket's orbital inclination within the range of its inclination values, the rocket's coasting time corresponding to that orbital inclination can be determined based on the rocket's launch principle.

[0079] Understandably, the method for establishing the correspondence between the rocket's orbital inclination and its glide time is existing technology, and this application does not limit it.

[0080] S105, the first device determines the range of rocket perigee angle values ​​corresponding to the range of rocket glide time values ​​based on the preset correspondence between the rocket's perigee angle and the rocket's glide time.

[0081] In one or more embodiments, the correspondence between the perigee argument of the rocket's orbital insertion and the rocket's glide time can be obtained from the perigee argument trajectory matrix corresponding to the rocket's orbital insertion and glide time. The perigee argument trajectory matrix can be constructed based on multiple sets of first rocket orbital insertion parameters. These first rocket orbital insertion parameters may include the rocket's orbital inclination, rocket glide time, and rocket orbital perigee argument. Furthermore, the rocket orbital corresponding to the first rocket orbital insertion parameters is aligned with the probe's orbital insertion.

[0082] Optionally, the perigee argument trajectory matrix satisfies:

[0083]

[0084] The orbital inclination of the rocket can be expressed as i. i The rocket's glide time can be expressed as Δt pj The argument of perigee of the rocket's orbit can be expressed as ω. i The perigee argument ballistic matrix can be represented as ω.

[0085] Furthermore, the first device can use a grid interpolation method to process each rocket glide time within the range of rocket glide time values ​​based on the perigee argument trajectory matrix, thereby determining the range of rocket perigee argument values ​​corresponding to the range of rocket glide time values.

[0086] The grid interpolation method is described in detail below:

[0087] The independent variable can be represented as:

[0088] x i , i∈[1,...,m];

[0089] y j j∈[1,...,n];

[0090] The dependent variable can be expressed as:

[0091]

[0092] The grid matrix can then be represented as:

[0093]

[0094] in, The matrix values ​​are known.

[0095] The value of the crossing point can be determined by using the values ​​of the four grid points surrounding the crossing point. Figure 2 This is a schematic diagram for determining the interpolation value of grid crossing points. The specific method for determining the value of the crossing points can be found in this schematic diagram.

[0096] When the independent variable is represented as: x∈[x i x i+1 ]hour,

[0097] The normalized independent variable can be expressed as:

[0098] When the independent variable is represented as: y∈[y j y j+1 ]hour,

[0099] The normalized independent variable can be expressed as:

[0100] Calculate the four coefficients:

[0101] w1 = (1-Δx)(1-Δy);

[0102] w2 = Δx(1-Δy);

[0103] w3 = (1-Δx)Δy;

[0104] w4 = ΔxΔy;

[0105] The grid interpolation result is: z x，y =w1z i，j +w2z i，j+1 +w3z i+1，j +w4z i+1，j+1 .

[0106] S106. The first device determines the expected rocket glide time based on the range of the rocket's perigee argument, the range of the rocket's glide time, and the perigee argument of the probe's orbital insertion.

[0107] In one or more embodiments, the first device can determine the expected rocket glide time in the following manner:

[0108] The perigee angle of the probe's orbit can be expressed as ω. e The minimum value of the rocket's perigee argument can be expressed as ω. i The maximum value of the rocket's perigee argument can be expressed as ω. i+1 The minimum value of the rocket's glide time can be expressed as Δt. pj The minimum value of the rocket's glide time can be expressed as Δt. pj+1 The expected rocket glide time can be expressed as Δt. p Then, the range of values ​​for the perigee angle of the probe's orbit, the range of values ​​for the rocket's perigee angle, the range of values ​​for the rocket's glide time, and the expected rocket glide time satisfy the following:

[0109]

[0110] In one or more embodiments, before determining the expected rocket glide time, the first device may also determine whether the perigee angle of the probe's orbital insertion meets the range of rocket perigee angle values. When the perigee angle of the probe's orbital insertion meets the range of rocket perigee angle values, the first device determines the expected rocket glide time based on the range of rocket perigee angle values, the range of rocket glide time values, and the perigee angle of the probe's orbital insertion. When the perigee angle of the probe's orbital insertion does not meet the range of rocket perigee angle values, the first device may re-acquire the probe's launch date and the preset probe insertion time according to preset rules. That is, the first device re-executes step S101.

[0111] S107, the first device determines the expected longitude of the ascending node of the rocket's orbital insertion based on the range of rocket orbital inclination angle, the range of rocket coasting time, and the expected rocket coasting time.

[0112] In one or more embodiments, the first device can use a grid interpolation method to process the range of rocket orbit inclination angle, the range of rocket glide time, and the expected rocket glide time based on the ascending node longitude trajectory matrix to obtain the expected longitude of the ascending node of the rocket's orbital insertion trajectory.

[0113] The specific application of the grid interpolation method can be found in the previous description, and will not be repeated here.

[0114] S108, the first device determines the orbit insertion time difference between the probe and the rocket based on the correspondence between the longitude of the ascending node and time, and determines that the orbit insertion time difference between the probe and the rocket meets the set target.

[0115] The first device can determine the time difference between the probe's and rocket's orbital insertion points, corresponding to the longitude of the ascending node and the longitude of the rocket's orbital insertion points, based on the correspondence between the longitude of the ascending node and time. Here, the longitude of the rocket's orbital insertion point can be represented as Ω1, the longitude of the probe's orbital insertion point can be represented as Ω2, and the time difference between the probe and rocket's orbital insertion points can be represented as Δt1. Then, the longitude of the probe's orbital insertion point, the longitude of the rocket's orbital insertion point, and the time difference between the probe and rocket's orbital insertion points satisfy the following:

[0116] Δt1=(Ω1-Ω2)*240.

[0117] 240 can be represented as the number of seconds required for the Earth to rotate 1°.

[0118] Furthermore, the first device can determine whether the time difference between the probe and the rocket's orbital insertion meets the set target. If the time difference between the probe and the rocket's orbital insertion meets the set target, the remaining steps are executed.

[0119] Optionally, when the time difference between the probe and the rocket's orbital insertion does not meet the set target, the first device can adjust the preset probe orbital insertion time based on the time difference, and re-acquire the probe's orbital parameters based on the adjusted preset probe orbital insertion time. In other words, when the time difference between the probe and the rocket's orbital insertion does not meet the set target, the first device can adjust the preset probe orbital insertion time based on the time difference, use the adjusted preset probe orbital insertion time as the new preset probe orbital insertion time, and re-execute steps S101 to S108.

[0120] Understandably, when the preset time difference between the probe and the rocket's orbital insertion does not meet the set target, it indicates that the probe's orbital insertion time cannot meet operational requirements. Therefore, the probe's orbital insertion time can be excluded, and the first device can reacquire the probe's orbital insertion time accordingly.

[0121] For example, the rule for verifying whether the time difference between the probe and the rocket's entry into orbit meets the set target can be that if the time difference between the probe and the rocket's entry into orbit is greater than the set target, it means that the probe's entry into orbit cannot meet the requirements, and steps S101 to S108 need to be re-executed; if the time difference between the probe and the rocket's entry into orbit is less than the set target, it means that the probe's entry into orbit can meet the requirements, and the remaining steps can continue to be executed.

[0122] Optionally, when the time difference between the probe and the rocket's orbital insertion does not meet the set target, the first device can adjust the probe's orbital insertion time based on this time difference. The probe's orbital insertion time can be expressed as t. I The time difference between the probe's entry into orbit and the rocket's entry into orbit can be expressed as Δt1. Then, the probe's entry into orbit and the time difference between the probe's entry into orbit and the rocket's entry into orbit satisfy the following:

[0123] t I =t I +Δt1.

[0124] S109, the first device determines the expected rocket-satellite separation flight time based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, according to the probe's orbital inclination, the range of rocket inclination values, the expected rocket coasting time, and the range of rocket coasting time values.

[0125] In one or more embodiments, the first device can acquire the rocket-satellite separation flight time trajectory matrix. This matrix is ​​determined based on multiple sets of third rocket orbital parameters, including the rocket's orbital inclination, rocket glide time, and rocket-satellite separation flight time. The rocket's orbital trajectory corresponding to these parameters is aligned with the probe's orbital trajectory.

[0126] For example, the orbital inclination of a rocket can be represented by i. i The rocket's glide time can be expressed as Δt pj The rocket-satellite separation flight time can be expressed as Δt. fii The trajectory matrix of the rocket-satellite separation flight time can be expressed as Δt f Then the rocket-satellite separation flight time trajectory matrix, rocket orbital inclination, rocket glide time, and rocket-satellite separation flight time satisfy the following:

[0127]

[0128] The first device can use a grid interpolation method to process the probe's orbital inclination, the range of rocket inclination angles, the expected rocket coasting time, and the range of rocket coasting time values, based on the rocket-satellite separation flight time trajectory matrix, to obtain the expected rocket-satellite separation flight time.

[0129] The specific application of the grid interpolation method can be found in the previous description, and will not be repeated here.

[0130] S110, the first device determines the rocket launch time based on the expected rocket-satellite separation flight time and the preset probe orbit insertion time.

[0131] In one or more embodiments, the first device can obtain the rocket launch time by subtracting the preset probe orbit insertion time from the expected rocket-satellite separation flight time.

[0132] For example, the probe's orbital insertion time can be expressed as t I The rocket launch time can be represented as t0, and the rocket-satellite separation flight time can be represented as Δt. f Then the probe's orbital insertion time, the rocket's launch time, and the rocket-satellite separation flight time satisfy the following:

[0133] t0 = t I -Δt f

[0134] S111, the first device determines the rocket launch azimuth angle based on the preset correspondence between the rocket launch azimuth angle, the rocket orbital inclination angle, and the rocket coasting time, according to the probe orbital inclination angle, the range of rocket inclination angle values, the expected rocket coasting time, and the range of rocket coasting time values.

[0135] In one or more embodiments, the first device can acquire the rocket launch azimuth trajectory matrix. The rocket launch azimuth trajectory matrix is ​​determined based on multiple sets of fourth rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket launch azimuth. The rocket orbital corresponding to the fourth rocket orbital parameters is aligned with the probe orbital.

[0136] For example, the rocket launch azimuth trajectory matrix, rocket orbital inclination, rocket glide time, and rocket launch azimuth satisfy the following:

[0137]

[0138] The orbital inclination of the rocket can be expressed as i. i The rocket's glide time can be expressed as Δt pj The rocket launch azimuth angle can be expressed as A. ii The trajectory matrix of the rocket launch azimuth angle can be represented as A.

[0139] The first device can obtain the rocket launch azimuth angle by processing the probe's orbital inclination angle, the range of rocket inclination angle values, the expected rocket coasting time, and the range of rocket coasting time values ​​based on the rocket launch azimuth trajectory matrix using a grid interpolation method.

[0140] The specific application of the grid interpolation method can be found in the previous description, and will not be repeated here.

[0141] Understandably, this application does not limit the order in which the steps of obtaining the rocket launch time and obtaining the rocket launch azimuth are performed. That is, in this application, the step of obtaining the rocket launch time can be performed first, followed by the step of obtaining the rocket launch azimuth. Alternatively, the step of obtaining the rocket launch azimuth can be performed first, followed by the step of obtaining the rocket launch time. Alternatively, the steps of obtaining the rocket launch azimuth and obtaining the rocket launch time can be performed simultaneously.

[0142] S112, the first device launches the rocket based on the rocket launch time and rocket launch azimuth angle.

[0143] In one or more embodiments, this application may also include control equipment for controlling rocket launch.

[0144] Optionally, the control device and the first device can be integrated or exist as a single entity, or the first device can include the control device, such as a device or module within the first device. The first device and the control device can be connected via an internal bus. In this case, the first device can directly invoke the control device to launch the rocket based on the rocket launch time and azimuth angle.

[0145] Optionally, the control device can be considered as a device independent of the first device, or a component within an independent device. The first device and the control device can be connected via a wired and / or wireless interface. The control device can send instructions to the first device via the wired and / or wireless interface to acquire the probe's orbital parameters. Correspondingly, after receiving this instruction, the first device sends the corresponding rocket launch time and launch azimuth to the control device via the wired and / or wireless interface. The control device can then launch the rocket based on the launch time and launch azimuth.

[0146] The method provided in this application will be described below using data from Example 1. Example 1 uses different probe orbital inclination angles (20.0°, 24.35°, and 28.7°) and glide times (300, 1200, 2100, 2800, 3600, 4500, and 5400) to obtain the rocket probe orbital parameters.

[0147] The specific details of Example 1 are as follows:

[0148] Table 1 is a rocket ascension node longitude trajectory matrix provided in the embodiments of this application.

[0149] 300 1200 2100 2800 3600 4500 5400 20.0 7.6 -0.3 -5.2 -3.7 -8.8 -16.2 -15.0 24.35 -20.8 -26.1 -29.7 -31.7 -35.9 -40.4 -42.6 28.7 -31.7 -36.4 -40.1 -42.6 -46.6 -50.7 -53.6

[0150] Tables 1 and 2 are ballistic matrices for the perigee angle of a rocket provided in the embodiments of this application.

[0151] 300 1200 2100 2800 3600 4500 5400 20.0 168.0 234.3 296.9 343.0 35.2 99.6 157.0 24.35 194.7 258.6 319.9 9.4 60.7 122.3 182.9 28.7 206.8 274.2 329.8 19.8 70.9 132.0 193.3

[0152] Tables 2 and 3 are a rocket-satellite separation flight time trajectory matrix provided in the embodiments of this application.

[0153] 300 1200 2100 2800 3600 4500 5400 20.0 1742.9 2640.1 3539.8 4290.9 5043.0 5944.2 6842.4 24.35 1744.7 2641.9 3541.5 4292.7 5044.8 5945.8 6844.1 28.7 1748.2 2651.6 3547.0 4298.2 5050.8 5951.3 6849.5

[0154] Tables 3 and 4 are a rocket launch azimuth trajectory matrix provided in the embodiments of this application.

[0155] 300 1200 2100 2800 3600 4500 5400 20.0 92.0 93.7 93.8 93.4 93.1 94.1 92.3 24.0 103.9 104.6 104.1 104.3 104.5 104.3 103.8 28.7 105.0 105.0 105.0 105.0 105.0 105.0 105.0

[0156] Table 4

[0157] The perigee altitude of the Earth-Moon transfer orbit is 200 kilometers, and the lunar perigee of the Earth-Moon transfer orbit is 200 kilometers.

[0158] When the inclination angle is 20°, the parameters of the Earth-Moon transfer orbit are:

[0159] The orbital insertion time is: 2029-05-17T00:37:47;

[0160] The semi-major axis is 258,305.757 kilometers;

[0161] The eccentricity rate is: 0.97426;

[0162] The tilt angle is 19.835°;

[0163] The longitude of the ascending node is -35.984°.

[0164] The perigee argument is 233.986°.

[0165] The true nearest angle is 0.000°.

[0166] The results of iterative calculations based on the above parameters are shown in Table 5 below.

[0167]

[0168] Table 5

[0169] Among them, t I Indicates the moment of insertion into the Earth-Moon transfer orbit of the probe, i eω represents the inclination angle of the probe's Earth-Moon transfer orbit. e Ω represents the perigee angle of the probe's Earth-Moon transfer orbit. e Ω represents the longitude of the ascending node of the probe's Earth-Moon transfer orbit, Ω represents the longitude of the ascending node of the rocket's insertion orbit, and Δt represents the longitude of the probe's ascending node. p Δt represents the time the rocket spends coasting in its parking orbit, and Δt represents the adjustment in orbit insertion time caused by the difference in longitude between the two ascending nodes. f The rocket's separation flight time is represented by t0, the rocket's launch time is represented by A, and the rocket's launch azimuth angle is represented by a. e e represents the semi-major axis of the probe's Earth-Moon transfer orbit. e f represents the eccentricity of the probe's Earth-Moon transfer orbit. e This indicates the true perihelion angle of the probe's Earth-Moon transfer orbit.

[0170] When the inclination is 24.35°, the parameters of the Earth-Moon transfer orbit are:

[0171] The orbital insertion time is: 2029-05-17T00:14:03;

[0172] The semi-major axis is 6275.720 kilometers;

[0173] The eccentricity rate is: 0.97406;

[0174] The tilt angle is 24.187°.

[0175] The longitude of the ascending node is -19.616°.

[0176] The perigee argument is 233.986°.

[0177] The true nearest angle is 0.000°.

[0178] The results of iterative calculations based on the above parameters are shown in Table 6 below.

[0179]

[0180] Table 6

[0181] When the inclination is 24.35°, the parameters of the Earth-Moon transfer orbit are:

[0182] The orbital insertion time is: 2029-05-16T23:50:07;

[0183] The semi-major axis is 254,332.001 kilometers;

[0184] The eccentricity rate is: 0.97386;

[0185] The tilt angle is 28.540°;

[0186] The longitude of the ascending node is -6.983°.

[0187] The perigee argument is 218.187°.

[0188] The true nearest angle is 0.000°.

[0189] The results of iterative calculations based on the above parameters are shown in Table 7 below.

[0190]

[0191] Table 7

[0192] Table 8 is obtained by summarizing Tables 5, 6, and 7.

[0193] <![CDATA[i I / °]]> A / ° <![CDATA[t0]]> <![CDATA[t I ]]> <![CDATA[Δt p / s]]> <![CDATA[Δt f / s]]> 20.0 93.290° 2029-05-16T21：12：45 2029-05-16T21：57：26 1211.678 2681.131 24.35 104.135° 2029-05-16T23：56：19 2029-05-17T00：32：07 675.332 2147.678 28.7 104.753° 2029-05-17T01：05：18 2029-05-17T01：36：55 420.109 1896.924

[0194] Table 8

[0195] Based on Table 8, the orbital parameters of the probe corresponding to tilt angles of 20.0°, 24.35°, and 28.7° are respectively.

[0196] Based on the same technical concept, this application also provides a device for determining rocket launch parameters and probe orbital parameters. The principle of the device for determining rocket launch parameters and probe orbital parameters is similar to the above-mentioned method for determining rocket launch parameters and probe orbital parameters. Therefore, the implementation of the rocket launch device can refer to the implementation of the method for determining rocket launch parameters and probe orbital parameters, and the repeated parts will not be described again.

[0197] In one possible implementation, the structure of the device for determining rocket launch parameters and probe orbit parameters provided in this application embodiment is as follows: Figure 3 As shown, it includes a communication module 301 and a processing module 302. The functions of each module in the device for determining rocket launch parameters and probe orbital parameters are described below.

[0198] Communication module 301 is used for inputting and / or outputting information. Input information can be replaced by receiving information, and output information can be replaced by transmitting information. When outputting information, communication module 301 can output information to devices other than the device for determining rocket launch parameters and probe orbital parameters, or it can output information to other units within the device for determining rocket launch parameters and probe orbital parameters. In some embodiments, the communication module can be implemented through at least one of a physical interface, a communication module, a communication interface, and an input / output interface. In other embodiments, the communication module can be implemented through interface circuitry, such as a mobile communication module. The mobile communication module may include one or more of at least one antenna, at least one filter, a switch, a power amplifier, and a low-noise amplifier (LNA).

[0199] The processing module 302 can be used to support the device for determining rocket launch parameters and probe orbital parameters in performing the processing actions described in the above method embodiments. The processing module 302 can be implemented using one or more processors. For example, the processor can be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. A general-purpose processor can be a microprocessor or any conventional processor.

[0200] In one embodiment, the device for determining rocket launch parameters and probe orbital parameters is applied to the first device in this application embodiment. The specific functions of the communication module 301 and processing module 302 in this embodiment are described below.

[0201] The communication module 301 is used to obtain the launch date of the detector and the preset time of the detector entering orbit.

[0202] The processing module 302 is used to determine the probe orbit parameters corresponding to the probe's orbit insertion time based on the correspondence between the probe's orbit insertion time and the probe's orbit parameters. The probe orbit parameters include the probe orbit inclination angle, the probe orbit perigee argument angle, and the longitude of the probe orbit ascending node.

[0203] The processing module 302 is also used to determine the range of rocket inclination angle values ​​to which the probe's orbital inclination angle belongs from a preset set of rocket orbital inclination angles.

[0204] The processing module 302 is also used to determine the range of rocket glide time values ​​corresponding to the range of rocket inclination angle values ​​based on the preset correspondence between the rocket orbital inclination angle and the rocket glide time.

[0205] The processing module 302 is also used to determine the range of rocket perigee angle values ​​corresponding to the range of rocket glide time values ​​based on the preset correspondence between the rocket orbit perigee angle and the rocket glide time.

[0206] The processing module 302 is also used to determine the expected rocket glide time based on the range of the rocket perigee argument, the range of the rocket glide time, and the perigee argument of the probe's orbital insertion.

[0207] The processing module 302 is also used to determine the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of rocket orbital inclination angle, the range of rocket coasting time, and the expected rocket coasting time.

[0208] The processing module 302 is also used to determine the orbit insertion time difference between the probe and the rocket corresponding to the longitude of the probe's orbital ascending node and the longitude of the rocket's orbital ascending node, based on the correspondence between the longitude of the ascending node and time, and to determine whether the orbit insertion time difference between the probe and the rocket meets the set indicators.

[0209] The processing module 302 is also used to determine the expected rocket-satellite separation flight time based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, according to the probe's orbital inclination, the range of rocket inclination values, the expected rocket coasting time, and the range of rocket coasting time values.

[0210] The processing module 302 is also used to determine the rocket launch time based on the expected rocket-satellite separation flight time and the preset probe orbit insertion time.

[0211] The processing module 302 is also used to determine the rocket launch azimuth based on the preset correspondence between the rocket launch azimuth, the rocket orbital inclination, and the rocket coasting time, according to the probe orbital inclination, the range of rocket inclination values, the expected rocket coasting time, and the range of rocket coasting time values.

[0212] The processing module 302 is also used to launch the rocket according to the rocket launch time and rocket launch azimuth angle.

[0213] In one optional implementation, after determining the probe's orbital parameters corresponding to the probe's orbital insertion time, the processing module 302 is specifically used to: determine whether the longitude of the probe's ascending node meets the preset range of ascending node longitude values ​​for rocket orbits. When the longitude of the probe's ascending node does not meet the preset range of ascending node longitude values ​​for rocket orbits, the time corresponding to the longitude of the probe's ascending node is determined based on the correspondence between ascending node longitude and time, and the preset probe orbital insertion time is adjusted according to the time.

[0214] In one optional implementation, before determining the expected rocket glide time based on the range of the rocket's perigee argument, the range of the rocket's glide time, and the perigee argument of the probe's orbital insertion, the processing module 302 is further configured to: determine that the perigee argument of the probe's orbital insertion belongs to the range of the rocket's perigee argument.

[0215] In one optional implementation, the rocket's perigee argument range corresponding to a preset correspondence between the rocket's orbital perigee argument and its glide time is determined. This includes: a communication module 301, specifically used to acquire the perigee argument trajectory matrix, which is determined based on multiple sets of first rocket orbital parameters. These first rocket orbital parameters may include the rocket's orbital inclination, glide time, and perigee argument. The rocket's orbital corresponding to the first rocket orbital parameters is connected to the probe's orbital. A processing module 302, specifically used to process each rocket glide time within the rocket glide time range using a grid interpolation method based on the perigee argument trajectory matrix, to determine the rocket's perigee argument range corresponding to the rocket glide time range.

[0216] In one optional implementation, the predicted longitude of the ascending node of the rocket's orbital insertion trajectory is determined based on the range of rocket orbital inclination angle, the range of rocket glide time, and the estimated rocket glide time. This includes: a communication module 301, specifically used to acquire the ascending node trajectory matrix. The ascending node longitude trajectory matrix is ​​determined based on multiple sets of second rocket orbital parameters, including the rocket orbital inclination angle, rocket glide time, and the longitude of the ascending node. The rocket orbital corresponding to the second rocket orbital parameters is connected to the probe's orbital insertion trajectory. A processing module 302 is specifically used to determine the predicted longitude of the ascending node of the rocket's orbital insertion trajectory based on the ascending node trajectory matrix, using a grid interpolation method to process the range of rocket orbital inclination angle, the range of rocket glide time, and the estimated rocket glide time.

[0217] In one optional implementation, when the time difference between the probe and the rocket's entry into orbit does not meet the set target, the processing module 302 is further configured to: adjust the preset probe entry into orbit time according to the time difference between the probe and the rocket's entry into orbit.

[0218] In one optional implementation, determining the rocket launch time includes: a communication module 301, specifically used to acquire the rocket-satellite separation flight time trajectory matrix. This matrix is ​​determined based on multiple sets of third rocket orbital parameters, including the rocket's orbital inclination, rocket glide time, and rocket-satellite separation flight time. The rocket's orbital trajectory corresponding to these parameters is aligned with the probe's orbital trajectory. A processing module 302, specifically used to process the probe's orbital inclination, the rocket's inclination range, the expected rocket glide time, and the expected rocket glide time range using a grid interpolation method based on the rocket-satellite separation flight time trajectory matrix to obtain the expected rocket-satellite separation flight time. The rocket launch time is obtained by subtracting the preset probe orbital launch time from the expected rocket-satellite separation flight time.

[0219] In one optional implementation, determining the rocket launch azimuth includes: a communication module 301, specifically used to acquire the rocket launch azimuth trajectory matrix, which is determined based on multiple sets of fourth rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and rocket launch azimuth. The rocket orbit corresponding to the fourth rocket orbital parameters is connected to the probe orbital. A processing module 302, specifically used to, based on the rocket launch azimuth trajectory matrix, use a grid interpolation method to process the probe orbital inclination, the rocket inclination range, the expected rocket glide time, and the rocket glide time range to obtain the rocket launch azimuth.

[0220] Having introduced the method and apparatus for determining rocket launch parameters and probe orbit parameters according to exemplary embodiments of this application, we will now introduce an electronic device according to another exemplary embodiment of this application.

[0221] The following reference Figure 4 To describe an electronic device 130 implemented according to this embodiment of the present application. Figure 4 The electronic device 130 shown is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of this application.

[0222] like Figure 4 As shown, the electronic device 130 is presented in the form of a general-purpose electronic device. The components of the electronic device 130 may include, but are not limited to: at least one processor 131, at least one memory 132, and a bus 133 connecting different system components (including memory 132 and processor 131).

[0223] Bus 133 represents one or more of several bus structures, including a memory bus or memory controller, peripheral bus, processor, or local bus using any of the various bus structures.

[0224] The memory 132 may include a readable medium in the form of volatile memory, such as random access memory (RAM) 1321 and / or cache memory 1322, and may further include read-only memory (ROM) 1323.

[0225] The memory 132 may also include a program / utility 1325 having a set (at least one) of program modules 1324, including but not limited to: an operating system, one or more application programs, other program modules, and program data, each or some combination of these examples may include an implementation of a network environment.

[0226] Electronic device 130 can also communicate with one or more external devices 134 (e.g., keyboard, pointing device, etc.), and with one or more devices that enable a user to interact with electronic device 130, and / or with any device that enables electronic device 130 to communicate with one or more other electronic devices (e.g., router, modem, etc.). This communication can be performed via input / output (I / O) interface 135. Furthermore, electronic device 130 can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN), and / or public networks, such as the Internet) via network adapter 136. As shown, network adapter 136 communicates with other modules used in electronic device 130 via bus 133. It should be understood that, although not shown in the figures, other hardware and / or software modules can be used in conjunction with electronic device 130, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0227] In an exemplary embodiment, a storage medium is also provided, which, when executed by a processor of an electronic device, enables the electronic device to perform any of the methods described above for determining rocket launch parameters and probe orbit parameters. Optionally, the storage medium may be a non-transitory computer-readable storage medium, such as a ROM, random access memory (RAM), CD-ROM, magnetic tape, floppy disk, and optical data storage device.

[0228] In an exemplary embodiment, the electronic device of this application may include at least one processor and a memory communicatively connected to the at least one processor, wherein the memory stores a computer program executable by the at least one processor, and when the computer program is executed by the at least one processor, the at least one processor may perform the steps of any of the methods for determining rocket launch parameters and probe orbit parameters provided in the embodiments of this application.

[0229] In an exemplary embodiment, a computer program product is also provided, which, when executed by an electronic device, enables the electronic device to implement any of the exemplary methods provided in this application.

[0230] Furthermore, computer program products may employ any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of readable storage media (a non-exhaustive list) include: electrical connections having one or more wires, portable disks, hard disks, RAM, ROM, erasable programmable read-only memory (EPROM), flash memory, optical fiber, compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0231] The program product used to determine rocket launch parameters and probe orbit parameters in the embodiments of this application can be a CD-ROM and include program code, and can run on a computing device. However, the program product of this application is not limited to this. In this document, the readable storage medium can be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device.

[0232] A readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, carrying readable program code. This propagated data signal may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A readable signal medium may also be any readable medium other than a readable storage medium, capable of sending, propagating, or transmitting a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0233] The program code contained on the readable medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, radio frequency (RF), or any suitable combination thereof.

[0234] Program code for performing the operations of this application can be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java and C++, as well as conventional procedural programming languages ​​such as C or similar languages. The program code can execute entirely on the user's computing device, partially on the user's computing device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server. In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, such as a Local Area Network (LAN) or a Wide Area Network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0235] It should be noted that although several units or sub-units of the device have been mentioned in the detailed description above, this division is merely exemplary and not mandatory. In fact, according to embodiments of this application, the features and functions of two or more units described above can be embodied in one unit. Conversely, the features and functions of one unit described above can be further divided and embodied by multiple units.

[0236] Furthermore, although the operations of the method of this application are described in a specific order in the accompanying drawings, this does not require or imply that these operations must be performed in that specific order, or that all the operations shown must be performed to achieve the desired result. Additionally or alternatively, certain steps may be omitted, multiple steps may be combined into one step, and / or one step may be broken down into multiple steps.

[0237] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0238] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0239] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0240] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0241] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0242] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, then this application also includes such modifications and variations.

Claims

1. A method for determining rocket launch parameters and probe orbital parameters, characterized in that, The method includes: Obtain the launch date and preset orbit insertion time of the probe; The orbital parameters corresponding to the probe's orbital insertion time are determined based on the correspondence between the probe's orbital insertion time and the probe's orbital parameters. The orbital parameters include the probe's orbital inclination angle, the probe's orbital perigee argument angle, and the longitude of the probe's orbital ascending node. The range of rocket inclination angles to which the probe's orbital inclination angle belongs is determined from a preset set of rocket orbital inclination angles; The range of rocket glide time values ​​corresponding to the range of rocket inclination angle values ​​is determined based on the preset correspondence between the rocket's orbital inclination angle and the rocket's glide time. The range of rocket perigee arguments corresponding to the range of rocket glide time values ​​is determined based on the preset correspondence between the rocket's perigee argument and the rocket's glide time. The estimated rocket glide time is determined based on the range of the rocket's perigee angle, the range of the rocket's glide time, and the perigee angle of the probe's orbital insertion. The longitude of the ascending node of the rocket's orbital insertion trajectory is determined based on the range of values ​​for the rocket's orbital inclination angle, the range of values ​​for the rocket's coasting time, and the estimated rocket coasting time. Based on the correspondence between the longitude of the ascending node and time, the orbit insertion time difference between the probe and the rocket corresponding to the longitude of the ascending node of the probe's orbit and the longitude of the ascending node of the rocket's orbit is determined, and it is determined that the orbit insertion time difference between the probe and the rocket meets the set index. Based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, the estimated rocket-satellite separation flight time is determined according to the probe's orbital inclination, the range of the rocket's inclination, the estimated rocket coasting time, and the range of the rocket coasting time. The launch time of the rocket is determined based on the expected rocket-satellite separation flight time and the preset probe orbit insertion time; Based on the preset correspondence between the rocket launch azimuth angle, the rocket's orbital inclination angle, and the rocket's coasting time, the rocket launch azimuth angle is determined according to the probe's orbital inclination angle, the range of the rocket's inclination angle, the expected rocket coasting time, and the range of the rocket coasting time. Launch the rocket according to the rocket launch time and the rocket launch azimuth angle.

2. The method as described in claim 1, characterized in that, After determining the probe orbit parameters corresponding to the probe's orbit insertion time, the method further includes: Determine whether the longitude of the ascending node of the probe's orbit meets the preset longitude value of the ascending node within the range of the rocket's orbital longitude. When the longitude of the ascending node of the probe's orbit does not meet the preset range of ascending node longitude values ​​for rocket orbits, the time corresponding to the ascending node longitude of the probe's orbit is determined based on the correspondence between ascending node longitude and time, and the preset probe orbit insertion time is adjusted according to the time.

3. The method as described in claim 1, characterized in that, Before determining the estimated rocket glide time based on the range of the rocket's perigee angle, the range of the rocket's glide time, and the perigee angle of the probe's orbital insertion, the method further includes: It was determined that the perigee angle of the probe's orbital insertion falls within the range of the rocket's perigee angle values.

4. The method as described in claim 1, characterized in that, The determination of the rocket perigee argument range corresponding to the rocket's glide time range based on the preset correspondence between the rocket's orbital perigee argument and its glide time includes: The perigee argument trajectory matrix is ​​obtained. The perigee argument trajectory matrix is ​​determined based on multiple sets of first rocket orbital parameters. The first rocket orbital parameters may include the rocket orbital inclination, rocket glide time, and rocket orbital perigee argument. The rocket orbital corresponding to the first rocket orbital parameters is connected to the probe orbital. Based on the perigee argument trajectory matrix, a grid interpolation method is used to process each rocket glide time within the range of rocket glide time values ​​to determine the range of rocket perigee argument values ​​corresponding to the range of rocket glide time values.

5. The method as described in claim 1, characterized in that, The step of determining the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of the rocket's orbital inclination angle, the range of the rocket's coasting time, and the expected rocket coasting time includes: The ascending node trajectory matrix is ​​obtained. The ascending node longitude trajectory matrix is ​​determined based on multiple sets of second rocket orbital parameters, including the rocket orbital inclination, rocket glide time, and the longitude of the ascending node of the rocket orbital. The rocket orbital corresponding to the second rocket orbital parameters is connected to the probe orbital. Based on the ascending node trajectory matrix, a grid interpolation method is used to process the range of rocket orbit inclination angle, the range of rocket glide time, and the expected rocket glide time to determine the expected longitude of the ascending node of the rocket's orbital insertion trajectory.

6. The method as described in claim 1, characterized in that, When the time difference between the probe and the rocket's orbital insertion does not meet the set target, the method further includes: The preset probe insertion time is adjusted based on the time difference between the probe and the rocket's insertion time.

7. The method as described in claim 1, characterized in that, Determining the rocket launch time includes: The rocket-satellite separation flight time trajectory matrix is ​​obtained. The rocket-satellite separation flight time trajectory matrix is ​​determined based on multiple sets of third rocket orbital parameters. The third rocket orbital parameters include the rocket orbital inclination angle, rocket glide time, and rocket-satellite separation flight time. The rocket orbital corresponding to the third rocket orbital parameters is connected to the probe orbital. Based on the rocket-satellite separation flight time trajectory matrix, the expected rocket-satellite separation flight time is obtained by processing the probe's orbital inclination angle, the range of the rocket inclination angle, the expected rocket coasting time, and the range of the rocket coasting time using a grid interpolation method. The rocket launch time is obtained by subtracting the preset probe orbit insertion time from the expected rocket-satellite separation flight time.

8. The method as described in claim 1, characterized in that, Determining the rocket launch azimuth includes: The rocket launch azimuth trajectory matrix is ​​obtained. The rocket launch azimuth trajectory matrix is ​​determined based on multiple sets of fourth rocket orbital parameters. The fourth rocket orbital parameters include the rocket orbital inclination, rocket glide time, and rocket launch azimuth. The rocket orbital corresponding to the fourth rocket orbital parameters is connected to the probe orbital. Based on the rocket launch azimuth trajectory matrix, the rocket launch azimuth is obtained by processing the probe's orbital inclination, the rocket inclination range, the expected rocket coasting time, and the rocket coasting time range using a grid interpolation method.

9. A device for determining rocket launch parameters and probe orbital parameters, characterized in that, The device includes: The communication module is used to obtain the launch date and preset orbit insertion time of the probe. The processing module is used to determine the probe orbit parameters corresponding to the probe's orbit insertion time based on the correspondence between the probe's orbit insertion time and the probe's orbit parameters. The probe orbit parameters include the probe orbit inclination angle, the probe orbit perigee argument angle, and the probe orbit ascending node longitude. The processing module is also used to determine the range of rocket inclination angle values ​​to which the probe's orbital inclination angle belongs from a preset set of rocket orbital inclination angles; The processing module is also used to determine the range of rocket glide time values ​​corresponding to the range of rocket inclination angle values ​​based on the preset correspondence between the rocket orbital inclination angle and the rocket glide time. The processing module is also used to determine the range of rocket perigee angle values ​​corresponding to the range of rocket glide time values ​​based on the preset correspondence between the rocket orbit perigee angle and the rocket glide time. The processing module is also used to determine the expected rocket glide time based on the range of the rocket perigee argument, the range of the rocket glide time, and the perigee argument of the probe's orbital insertion. The processing module is also used to determine the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of the rocket orbital inclination angle, the range of the rocket coasting time, and the expected rocket coasting time. The processing module is also used to determine the orbit insertion time difference between the probe and the rocket corresponding to the longitude of the ascending node of the probe's orbit and the longitude of the ascending node of the rocket's orbit, based on the correspondence between the longitude of the ascending node and time, and to determine that the orbit insertion time difference between the probe and the rocket meets the set index. The processing module is also used to determine the expected rocket-satellite separation flight time based on the preset correspondence between the rocket's orbital inclination and the rocket-satellite separation flight time, according to the probe's orbital inclination, the range of the rocket's inclination, the expected rocket coasting time, and the range of the rocket coasting time. The processing module is also used to determine the rocket launch time based on the expected rocket-satellite separation flight time and the preset probe orbit insertion time; The processing module is also used to determine the rocket launch azimuth angle based on the preset correspondence between the rocket launch azimuth angle, the rocket orbital inclination angle, and the rocket coasting time, according to the probe orbital inclination angle, the range of the rocket inclination angle, the expected rocket coasting time, and the range of the rocket coasting time. The processing module is also used to launch the rocket according to the rocket launch time and the rocket launch azimuth angle.

10. The apparatus as claimed in claim 9, characterized in that, After determining the probe orbit parameters corresponding to the probe's orbit insertion time, the processing module is specifically used for: Determine whether the longitude of the ascending node of the probe's orbit meets the preset longitude value of the ascending node within the range of the rocket's orbital longitude. When the longitude of the ascending node of the probe's orbit does not meet the preset range of ascending node longitude values ​​for rocket orbits, the time corresponding to the ascending node longitude of the probe's orbit is determined based on the correspondence between ascending node longitude and time, and the preset probe orbit insertion time is adjusted according to the time.

11. The apparatus as claimed in claim 9, characterized in that, Before determining the estimated rocket glide time based on the range of the rocket's perigee angle, the range of the rocket's glide time, and the perigee angle of the probe's orbital insertion, the processing module is further configured to: It was determined that the perigee angle of the probe's orbital insertion falls within the range of the rocket's perigee angle values.

12. The apparatus as claimed in claim 9, characterized in that, The determination of the rocket perigee argument range corresponding to the rocket's glide time range based on the preset correspondence between the rocket's orbital perigee argument and its glide time includes: The communication module is specifically used to obtain the perigee argument trajectory matrix. The perigee argument trajectory matrix is ​​determined based on multiple sets of first rocket orbital parameters. The first rocket orbital parameters may include the rocket orbital inclination, rocket glide time, and rocket orbital perigee argument. The rocket orbital corresponding to the first rocket orbital parameters is connected to the probe orbital. The processing module is specifically used to process each rocket glide time in the range of rocket glide time values ​​using a grid interpolation method based on the perigee argument trajectory matrix, and to determine the range of rocket perigee argument values ​​corresponding to the range of rocket glide time values.

13. The apparatus as claimed in claim 9, characterized in that, The step of determining the expected longitude of the ascending node of the rocket's orbital insertion trajectory based on the range of the rocket's orbital inclination angle, the range of the rocket's coasting time, and the expected rocket coasting time includes: The communication module is specifically used to obtain the ascending node trajectory matrix. The ascending node longitude trajectory matrix is ​​determined based on multiple sets of second rocket orbital parameters. The second rocket orbital parameters include the rocket orbital inclination, rocket glide time, and the longitude of the ascending node of the rocket orbital. The rocket orbital corresponding to the second rocket orbital parameters is connected to the probe orbital. The processing module is specifically used to determine the expected longitude of the ascending node of the rocket's orbital trajectory by processing the range of the rocket's orbital inclination angle, the range of the rocket's coasting time, and the expected rocket coasting time based on the ascending node trajectory matrix using a grid interpolation method.

14. The apparatus as claimed in claim 9, characterized in that, When the time difference between the probe and the rocket's orbital insertion does not meet the set target, the processing module is further configured to: The preset probe insertion time is adjusted based on the time difference between the probe and the rocket's insertion time.

15. The apparatus as claimed in claim 9, characterized in that, Determining the rocket launch time includes: The communication module is specifically used to acquire the rocket-satellite separation flight time trajectory matrix. The rocket-satellite separation flight time trajectory matrix is ​​determined based on multiple sets of third rocket orbital parameters. The third rocket orbital parameters include the rocket orbital inclination angle, rocket glide time, and rocket-satellite separation flight time. The rocket orbital corresponding to the third rocket orbital parameters is connected to the probe orbital. The processing module is specifically used to process the probe's orbital inclination, the range of the rocket inclination angle, the expected rocket coasting time, and the range of the rocket coasting time based on the rocket-satellite separation flight time trajectory matrix using a grid interpolation method to obtain the expected rocket-satellite separation flight time. The rocket launch time is obtained by subtracting the preset probe orbit insertion time from the expected rocket-satellite separation flight time.

16. The apparatus as claimed in claim 9, characterized in that, Determining the rocket launch azimuth includes: The communication module is specifically used to obtain the rocket launch azimuth trajectory matrix. The rocket launch azimuth trajectory matrix is ​​determined based on multiple sets of fourth rocket orbital parameters. The fourth rocket orbital parameters include the rocket orbital inclination, rocket glide time, and rocket launch azimuth. The rocket orbital corresponding to the fourth rocket orbital parameters is connected to the probe orbital. The processing module is specifically used to obtain the rocket launch azimuth angle by processing the probe's orbital inclination angle, the range of the rocket inclination angle, the expected rocket coasting time, and the range of the rocket coasting time values ​​based on the rocket launch azimuth trajectory matrix using a grid interpolation method.

17. A storage medium, characterized in that, When the computer program in the storage medium is executed by the processor of the electronic device, the electronic device is able to perform the method as described in any one of claims 1-8.

18. A computer program product, characterized in that, Includes a computer program that, when executed by a processor, implements the method described in any one of claims 1-8.

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