Method and device for adjusting ascending node right ascension of one-launch-multiple-satellite launched satellite

Abstract

The application provides a method and device for adjusting the ascending node right ascension of a satellite launched by one rocket and multiple satellites, the method comprising: adjusting the satellite to enter a drift orbit; wherein the satellite is a satellite launched by one rocket and multiple satellites; before the satellite enters a working orbit, the satellite is offset in ascending node right ascension based on a compensation amount of the ascending node right ascension of the satellite; wherein the compensation amount of the ascending node right ascension of the satellite is obtained by subtracting a nominal value of the ascending node right ascension of the satellite from an expected value of the ascending node right ascension of the working orbit of the satellite; after the offset amount of the ascending node right ascension of the satellite matches the compensation amount of the ascending node right ascension of the satellite, the satellite is controlled to enter the working orbit. The method and device for adjusting the ascending node right ascension of a satellite launched by one rocket and multiple satellites provided in the application embodiment improve the adjustment efficiency of the ascending node right ascension and reduce the risk of collision of satellites within a constellation.

Description

Technical Field

[0001] This application relates to the field of satellite launch technology, specifically to a method and device for adjusting the right ascension of the ascending node of satellites launched in a single rocket for multiple satellite launches. Background Technology

[0002] In large-scale constellation deployment missions in low or medium Earth orbit, launching multiple satellites with a single rocket has become the mainstream approach to improve deployment efficiency and reduce launch costs.

[0003] Multiple satellite launches typically send multiple satellites into the same initial orbit, whereby each satellite gradually ascends to its respective operational orbit through autonomous orbital maneuvers. During this process, to establish the constellation configuration, the orbital phase and orbital plane parameters of each satellite need to be controlled. Current technology allows for adjustments to the satellite's orbital phase via semi-major axis control, and after deployment, the satellite's right ascension of the ascending node is slowly corrected via inclination. However, this approach suffers from the drawbacks of a lengthy right ascension adjustment time and a high risk of collisions within the constellation during the adjustment process. Summary of the Invention

[0004] To address the problems in the prior art, this application provides a method and apparatus for adjusting the right ascension of the ascending node of satellites launched in a single rocket for multiple satellite launches, which can at least partially solve the problems existing in the prior art.

[0005] Firstly, this application proposes a method for adjusting the right ascension of the ascending node of satellites in a single launch of multiple satellites, including: Adjust the satellite to enter a drift orbit; wherein, the satellite is a satellite launched by a single rocket with multiple satellites in one launch vehicle; Before the satellite enters its working orbit, the right ascension of the ascending node of the satellite is offset based on the compensation amount of the right ascension of the ascending node; wherein, the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit. After the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite, the satellite is controlled to enter the working orbit.

[0006] Secondly, this application provides a device for adjusting the right ascension of the ascending node of satellites launched in a single rocket for multiple satellite launches, comprising: An adjustment module is used to adjust the satellite to enter a drift orbit; wherein the satellite is a satellite launched by a single rocket with multiple satellites in one launch vehicle; An offset module is used to offset the right ascension of the ascending node of the satellite based on the compensation amount of the right ascension of the ascending node of the satellite before the satellite enters its working orbit; wherein the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit. The control module is used to control the satellite to enter the working orbit after the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite.

[0007] Thirdly, this application provides a computer device, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the program to implement the method for adjusting the right ascension of the ascending node of a satellite in a single launcher for multiple satellites as described in any of the above embodiments.

[0008] Fourthly, this application provides a computer-readable storage medium storing a computer program / instruction that, when executed by a processor, implements the method for adjusting the right ascension of the ascending node of a satellite in a multi-satellite launch as described in any of the above embodiments.

[0009] Fifthly, this application provides a computer program product, including a computer program / instruction, which, when executed by a processor, implements the method for adjusting the right ascension of the ascending node of a satellite in a multi-satellite launch as described in any of the above embodiments.

[0010] The present application provides a method and apparatus for adjusting the right ascension of the ascending node of a satellite launched in a single rocket for multiple satellites. This method adjusts the satellite to enter a drift orbit. Before the satellite enters its working orbit, the right ascension of the ascending node of the satellite is offset based on a compensation amount. The compensation amount is obtained by subtracting the nominal value of the right ascension of the ascending node from the expected value of the right ascension of the ascending node in the working orbit. After the offset amount and the compensation amount are matched, the satellite is controlled to enter its working orbit. Because the right ascension of the ascending node is directly changed using the compensation amount before the satellite enters its working orbit, the deviation of the right ascension of the ascending node after entering the working orbit is reduced, improving the adjustment efficiency of the right ascension of the ascending node and reducing the risk of collisions between satellites within the constellation. Attached Figure Description

[0011] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 This is a flowchart illustrating the method for adjusting the right ascension of the ascending node of satellites in a multi-satellite launch provided in this application embodiment.

[0013] Figure 2This is a schematic diagram of the structure of a satellite ascending node right ascension adjustment device for launching multiple satellites with a single rocket, provided in an embodiment of this application.

[0014] Figure 3 This is a schematic diagram of the physical structure of the computer device provided in the embodiments of this application. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the embodiments of this application will be further described in detail below with reference to the accompanying drawings. Here, the illustrative embodiments and their descriptions are used to explain this application, but are not intended to limit this application. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be arbitrarily combined with each other. The acquisition, storage, use, and processing of data in the technical solutions of this application all comply with the relevant provisions of laws and regulations.

[0016] To facilitate understanding of the technical solution provided in this application, the relevant content of the technical solution in this application will be explained below.

[0017] During constellation deployment, satellites launched in a single launch exhibit in-plane and out-of-plane coupling under semi-major axis control. Due to the influence of Earth's non-spherical gravitational field, a dynamic coupling relationship exists between the orbital semi-major axis and the right ascension of the ascending node. The right ascension of the ascending node of a deployed satellite deviates from its nominal value and cannot be eliminated using semi-major axis control. This deviation significantly increases the risk of collisions within the constellation. For example, traditional control strategies that slowly change the right ascension of the ascending node using inclination offsets may result in satellites undergoing adjustment and newly deployed satellites simultaneously existing in the working orbit. The difference in right ascension between these two satellites can be substantial, posing a risk of triggering collisions within the constellation. Furthermore, the adjustment time is lengthy; for instance, an inclination offset of 0.01° would only change the right ascension of the ascending node by 0.4° over a year (typically, the maximum deviation of the right ascension of the ascending node after capture can reach 0.4° for satellites at approximately 550km altitude and a 50° inclination).

[0018] When launching multiple satellites into orbit using a single rocket, the initial phase and right ascension of the ascending node of each satellite are approximately the same. The deployment target points will be located on the same plane but with different phases or on different planes. A configuration-forming strategy is needed to guide each satellite to its respective target point. This adjustment process is typically achieved by constructing a drift orbit at a lower orbital altitude to create relative phase drift and relative drift of the ascending node's right ascension. Considering that the ascent process from the drift orbit to the operational orbit is roughly the same for satellites within the same constellation, and the drift orbit altitude can be the same, the difference in ascending node's right ascension and phase between satellites is mainly determined by the difference in the time the satellites spend in the drift orbit.

[0019] Due to differences in orbital altitude, the orbital angular velocity and right ascension drift rate of the drift orbit and the working orbit are different. Relative drift is achieved using the difference between the drift orbit and the working orbit. However, the relative phase drift and the relative right ascension drift occur simultaneously; changing the phase also changes the right ascension, and the cumulative changes are proportional. This proportional relationship is not significantly affected by altitude changes and is difficult to break through semi-major axis control. Since the rate of phase change is much greater than the rate of right ascension change, in practice, it is necessary to match the phase drift (fast variable) and the right ascension drift (slow variable). Typically, because phase has a greater impact on constellation coverage, accurate phase acquisition is prioritized. This results in a difference between the expected value of the satellite's right ascension in the working orbit and its nominal value.

[0020] The satellite's orbital angular velocity is:

[0021] in, Indicates the angular velocity of the satellite's orbit. Indicates the phase drift rate, denoted by , where α represents the gravitational constant and α represents the semi-major axis of the orbit.

[0022] Under the J2 term perturbation, the right ascension drift rate of the ascending node of the near-circular orbit is:

[0023] in, This represents the right ascension shift rate of the ascending node. This represents the Earth's second-order zone harmonic coefficients. Represents the Earth's equatorial radius. Let represent the gravitational constant, a represent the semi-major axis of the orbit, and i represent the orbital inclination.

[0024] Let the semi-major axis of the drift track be... , working track semi-major axis ( The dwell time on the drift track is When the satellite reaches its working orbit, the cumulative difference in right ascension of the ascending node... and phase difference for:

[0025] in, This represents the cumulative difference in right ascension of the ascending node of the satellite. This represents the Earth's second-order zone harmonic coefficients. Represents the Earth's equatorial radius. Let i represent the gravitational constant and i represent the orbital inclination. Indicates the semi-major axis of the drift track. Indicates the semi-major axis of the working track. This indicates the time a satellite spends in its drift orbit. This represents the cumulative phase difference of the satellite.

[0026] Cumulative phase difference of satellites The cumulative difference in right ascension of the ascending node with the satellite The ratio is:

[0027] This ratio k is relatively less affected by orbital altitude. For low-Earth orbit satellites with a specific inclination, it is difficult to break this ratio using semi-major axis control. The right ascension of the ascending node and the phase can only change proportionally. Therefore, for multiple satellites launched in a single launch, because the amount of change in the right ascension of the ascending node and the phase is different, it is impossible to achieve accurate capture of the phase and right ascension of the ascending node for all satellites at the same time. While ensuring accurate capture of the phase variable, an ascending node right ascension deviation will inevitably occur.

[0028] This application addresses the issue of ascending node right ascension deviation in multi-satellite launches under semi-major axis control, and proposes a method for adjusting the ascending node right ascension of satellites launched in a multi-satellite launch, which achieves rapid and accurate acquisition of the ascending node right ascension of satellites within the constellation while ensuring the safety of the constellation.

[0029] This application adopts a direct correction and adjustment strategy for the right ascension of the ascending node. It aims to construct a correction and compensation amount for the right ascension of the ascending node by directly controlling the right ascension of the ascending node before the satellite reaches its working orbit, so that the phase and the right ascension of the ascending node can be accurately and synchronously acquired when the satellite reaches its working orbit.

[0030] From the constant thrust governing equations for near-circular orbits, the change in right ascension of the ascending node is:

[0031] in, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, Indicates the length of the thrust arc. The phase at the center of the arc segment is represented by 'i', and the orbital inclination angle is represented by 'i'. Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

[0032] From the above equation, the right ascension of the ascending node can be directly adjusted by the normal thrust, controlling the center of the arc segment to be located at... With an arc length within 120° and a value of 90° or 270°, the control efficiency is relatively high.

[0033] This application calculates the deviation of the right ascension of the ascending node of the satellite before it is expected to be in position, and then uses this deviation as a correction compensation amount. By taking advantage of the time the satellite drifts or climbs its orbit at a lower altitude, the application applies a normal maneuver to the satellite to directly change the right ascension of the ascending node.

[0034] The following describes the implementation process of the method for adjusting the right ascension of the ascending node of a satellite launched by a single rocket for multiple satellites, using the ground control center as the executing entity as an example. The executing entity of the method for adjusting the right ascension of the ascending node of a satellite launched by a single rocket for multiple satellites proposed in this application is not limited to the ground control center.

[0035] Figure 1 This is a flowchart illustrating the method for adjusting the right ascension of the ascending node of satellites in a multi-satellite launch provided in this application embodiment. Figure 1 As shown in the embodiment of this application, the method for adjusting the right ascension of the ascending node of satellites in a multi-satellite launch includes: S101. Adjust the satellite to enter a drift orbit; wherein, the satellite is a satellite launched by a single rocket with multiple satellites in one launch vehicle; Specifically, for satellites launched in a single launch, the ground control center can adjust each satellite to enter a drift orbit. Each satellite will then climb from the drift orbit to its operational orbit. The altitude of the drift orbit is lower than that of the operational orbit.

[0036] S102. Before the satellite enters its working orbit, the right ascension of the ascending node of the satellite is offset based on the compensation amount of the right ascension of the ascending node of the satellite; wherein, the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit. Specifically, the ground control center can obtain the expected and nominal values ​​of the right ascension of the ascending node of the satellite's working orbit. It then calculates the compensation amount for the ascending node by subtracting the nominal value from the expected value. Before the satellite enters its working orbit, the ascending node is offset based on this compensation amount, constructing a correction compensation for the ascending node. The expected value of the ascending node is pre-calculated based on the current orbital elements and the half-major axis control climb strategy, while the nominal value is pre-determined by referencing the constellation configuration and the reference satellite.

[0037] In one embodiment of this application, the right ascension of the satellite's ascending node can be offset by applying a normal thrust to the satellite.

[0038] In one embodiment of this application, the right ascension of the satellite's ascending node can be offset by adjusting the angle between the satellite's thrust direction and its heading.

[0039] In one embodiment of this application, the right ascension of the ascending node of the satellite can be offset multiple times.

[0040] In one embodiment of this application, when the right ascension of the ascending node of the satellite is offset multiple times, the offset amount of the right ascension of the ascending node is equal each time.

[0041] In one embodiment of this application, the right ascension offset of the ascending node can be performed synchronously for multiple satellites launched by a single rocket.

[0042] S103. After the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite, the satellite is controlled to enter the working orbit.

[0043] Specifically, the ground control center compares the offset of the satellite's right ascension of the ascending node with the compensation of the satellite's right ascension of the ascending node. If the offset of the satellite's right ascension of the ascending node matches the compensation of the satellite's right ascension of the ascending node, it means that the satellite has completed the adjustment of the right ascension of the ascending node, and then the ground control center can control the satellite to enter the working orbit.

[0044] In one embodiment of this application, the satellite performs multiple ascending node right ascension offsets, and the offset amount of the satellite's ascending node right ascension is the cumulative adjustment amount of the ascending node right ascension after the satellite has already performed ascending node right ascension offsets.

[0045] In one embodiment of this application, matching the offset of the satellite's right ascension to its ascending node with its compensation means that the absolute value of the difference between the offset and the compensation of the satellite's right ascension to its ascending node is less than a threshold. This threshold is set according to actual needs and is not limited in this embodiment.

[0046] In one embodiment of this application, after the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite, the ground control center can control the satellite to enter its working orbit through semi-major axis control. Semi-major axis control of the satellite is prior art and will not be described in detail here.

[0047] The method for adjusting the right ascension of the ascending node of a satellite in a multi-satellite launch provided in this application embodiment adjusts the satellite to enter a drift orbit. Before the satellite enters its working orbit, the right ascension of the ascending node of the satellite is offset based on the compensation amount of the right ascension of the ascending node. The compensation amount of the right ascension of the ascending node is obtained by subtracting the nominal value of the right ascension of the ascending node from the expected value of the right ascension of the ascending node of the satellite's working orbit. After the offset amount of the right ascension of the ascending node of the satellite is matched with the compensation amount of the right ascension of the ascending node of the satellite, the satellite is controlled to enter the working orbit. Since the right ascension of the ascending node of the satellite is changed based on the compensation amount of the right ascension of the ascending node before the satellite enters the working orbit, the deviation of the right ascension of the ascending node after the satellite enters the working orbit is reduced, the adjustment efficiency of the right ascension of the ascending node is improved, and the risk of collision between satellites within the constellation is reduced.

[0048] Based on the above embodiments, the step of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node right ascension further includes: During the period when the satellite is parked in its drift orbit, the right ascension of the ascending node of the satellite is adjusted multiple times by applying a normal thrust to the satellite; wherein, after the satellite undergoes multiple adjustments to the right ascension of the ascending node, the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite.

[0049] Specifically, during the satellite's parking period in its drift orbit, the ground control center applies normal thrust to the satellite's thrusters to adjust its right ascension of the ascending node. Multiple adjustments to the ascending node's right ascension can be performed, ensuring that the offset of the satellite's ascending node's right ascension matches the compensation amount after these adjustments, thus completing the adjustment during the drift orbit parking period. Each adjustment yields a corresponding offset, which is equal to the sum of the offsets from multiple adjustments. The number of adjustments is set according to actual needs and is not limited in this embodiment.

[0050] Adjusting the right ascension of the ascending node while the satellite is stationary in its drift orbit allows all thrust to be used in the normal direction. The change in right ascension of the ascending node in a single operation is relatively large, which helps to reduce the number of maneuvers required.

[0051] In one embodiment of this application, the bias amount of the right ascension adjustment of the ascending node can be obtained by controlling the duration of a single normal maneuver.

[0052] In one embodiment of this application, the ascending node right ascension of each satellite launched by a single rocket can be adjusted synchronously. Since the compensation amount for the ascending node right ascension differs among different satellites, the number of ascending node right ascension adjustments for each satellite can be set to be the same. The compensation amount for the ascending node right ascension of each satellite is proportional to the adjustment amount for a single ascending node right ascension adjustment. For example, if the number of ascending node right ascension adjustments for a satellite is n, the compensation amount for the ascending node right ascension of the satellite is P, and the adjustment amount for a single ascending node right ascension adjustment is P / n, thereby achieving synchronous adjustment of the ascending node right ascension of different satellites.

[0053] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... Calculated, where, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, Indicates the length of the thrust arc. This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. Indicates the normal thrust acceleration. This indicates the duration of a single maneuver for the satellite, which is set according to actual needs. The longer the duration of a single maneuver, the greater the offset of the right ascension adjustment of the ascending node.

[0054] In one embodiment of this application, the duration of a single maneuver is... The orbital period is less than 1 / 3 of the orbital period of the satellite's drift orbit to ensure control efficiency.

[0055] Based on the above embodiments, further, in order to improve computational efficiency, the formula can be modified. To simplify, the efficiency factor term is used during the time it takes for a single right ascension adjustment of the ascending node in the drift orbit. Approximately 1, and Choose 90° or 270° to make It can be simplified to ,in, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The value represents the orbital velocity, and 'i' represents the orbital inclination angle. Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

[0056] Specifically, and i are determined by the satellite's orbital parameters and are known quantities. It is determined through on-orbit calibration of the satellite's thrust system and is a known quantity. The duration of each satellite maneuver is controlled. This allows for control over the adjustment of the right ascension of the ascending node in a single instance.

[0057] Based on the above embodiments, the step of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node right ascension further includes: During the satellite's ascent, the angle between the satellite's thrust direction and its heading is adjusted to achieve multiple adjustments to the right ascension of the ascending node; wherein, after multiple adjustments to the right ascension of the ascending node, the offset of the satellite's right ascension of the ascending node is matched with the compensation of the satellite's right ascension of the ascending node.

[0058] Specifically, the right ascension of the satellite's ascending node can be adjusted during the ascent from its drift orbit to its working orbit. The ground control center adjusts the angle between the satellite's thrust direction and heading by controlling its attitude, and rationally distributes the normal thrust and heading thrust to achieve the adjustment of the satellite's right ascension. Multiple adjustments to the right ascension can be performed, ensuring that the offset of the satellite's right ascension matches its compensation after these adjustments, thus completing the adjustment during the ascension process.

[0059] The right ascension of the ascending node of the satellite is adjusted during the satellite's ascent. The satellite's ascent and the adjustment of the right ascension of the ascending node are carried out simultaneously, which can save time for the satellite to enter its working orbit.

[0060] In one embodiment, multiple satellites launched on a single rocket can simultaneously adjust their ascending node right ascension. By designing the angle between the thrust direction and the heading, different adjustment speeds can be constructed for each satellite, enabling them to simultaneously adjust their ascending node right ascension while maintaining the same altitude. Maintaining the same altitude for all satellites helps prevent relative phase drift.

[0061] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... Calculated, where, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, Indicates the length of the thrust arc. This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

[0062] Where 'a' is the semi-major axis of the satellite's orbit. The values ​​a and V represent the changes in the semi-major axis, determined by parameters of the satellite's orbit. These are design quantities, and they are known. To ensure that the semi-major axis change is the same for all satellites, It must be a constant value. With V fixed, k can be considered a constant. This is achieved by controlling the angle between the satellite's thrust direction and its heading. This allows for control over the adjustment of the right ascension of the ascending node in a single instance.

[0063] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The value represents the orbital velocity, and 'i' represents the orbital inclination angle. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

[0064] Specifically, in order to ensure that the semi-major axis change is the same for each satellite while achieving different adjustments to the right ascension of the ascending node, it is necessary to control the angle between the thrust direction and the heading. The change in the semi-major axis is At the angle between the thrust direction and the heading Down, , f represents the thrust acceleration of the satellite. This represents the satellite's normal thrust acceleration. This represents the azimuth thrust acceleration of a satellite. To ensure that the semi-major axis change is the same for all satellites, it is necessary to make... Based on the constant thrust control equations for near-circular orbits, the offset for adjusting the right ascension of the satellite's ascending node in a single operation is:

[0065] Will and , , Let the orbital acceleration be denoted as , then substituting it into the above formula, we get:

[0066] We can obtain: Choose 90° or 270° to make 1. Ultimately, we can obtain:

[0067] 'a' represents the semi-major axis of the satellite's orbit. The values ​​a and V represent the changes in the semi-major axis, determined by parameters of the satellite's orbit. These are design quantities, and they are known. To ensure that the semi-major axis change is the same for all satellites, It must be a constant value. With V fixed, k can be considered a constant. This is achieved by controlling the angle between the satellite's thrust direction and its heading. This allows for control over the adjustment of the right ascension of the ascending node in a single instance. Among other things, Greater than or equal to -90° and less than or equal to 90°.

[0068] Based on the above embodiments, the duration of the single adjustment of the right ascension of the ascending node of the satellite is less than 1 / 3 of the orbital period of the satellite's drift orbit.

[0069] Specifically, in order to ensure the efficiency of the right ascension adjustment of the ascending node, the duration of a single adjustment of the right ascension of the ascending node of the satellite is less than 1 / 3 of the orbital period of the satellite's orbit.

[0070] Based on the above embodiments, furthermore, the right ascension of the ascending node of each satellite launched by a single rocket is simultaneously offset.

[0071] Specifically, in order to reduce the risk of collisions among satellites launched by a single rocket and to ensure that all satellites can enter their working orbits as a whole as quickly as possible, the right ascension of the ascending node of each satellite can be offset simultaneously.

[0072] In one embodiment of this application, the right ascension of the ascending node of each satellite can be adjusted the same number of times, and the adjustment of the right ascension of the ascending node can be performed synchronously each time.

[0073] The following example illustrates the specific implementation process of the method for adjusting the right ascension of the ascending node of satellites in a single launch, which provides an embodiment of the present invention, using the launch of four satellites in one rocket as an example.

[0074] Assuming the orbital inclination of the four satellites is 50°, the initial orbital altitude is 490km, the drift altitude is 500km, the deployment altitude is 550km, and after deployment, the four satellites are evenly distributed on the same orbital plane, that is, the phase difference between adjacent satellites is 90°, the nominal thrust of the satellite is 150mN, and the satellite mass is 500kg.

[0075] Before launching a satellite, the number of times the right ascension of the ascending node is adjusted (N) and the compensation amount for the right ascension of the ascending node of each satellite are determined in advance.

[0076] First, the right ascension compensation of the ascending node for each satellite is determined based on the half-major axis control climb strategy. Taking the second satellite as the adjustment reference, the phase differences that need to be changed for the four satellites are -90°, 0°, 90°, and 180° respectively. The difference between the expected value of the right ascension of the ascending node of each satellite's working orbit and the nominal value of the right ascension of the ascending node after the half-major axis control climb strategy is 0.1871°, 0°, -0.1871°, and -0.3743° respectively. That is, the right ascension compensation of the ascending node for each satellite is -0.1871°, 0°, 0.1871°, and 0.3743° respectively.

[0077] Taking the example of constructing the drift orbit compensation by applying a normal thrust to the satellite during its parking in the drift orbit, the process of determining the number of times the right ascension of the ascending node is adjusted, is given.

[0078] Considering the need to ensure control efficiency at the right ascension of the ascending node, the duration of a single maneuver... It is recommended to use a period less than 1 / 3 of the orbital period of the satellite's drift orbit. Since the orbital period of a 500km altitude orbit is approximately 94 minutes, a 30-minute period should be used as the input to calculate the maximum permissible right ascension maneuver at the ascending node. The value is taken as 1800s, and the orbital velocity of each satellite is also considered. That is, the orbital speed at 500km is 7612.6m / s. Take 90°, thrust arc length according to and orbital angular velocity The calculated value is 114.15°, the orbital inclination angle i is 50°, and the normal thrust acceleration is... The total thrust acceleration of the satellite, calculated from the satellite thrust and satellite mass, is 3 × 10⁻⁶. -4 m / s 2 It can be done through formulas. The maximum permissible right ascension maneuver at the ascending node is calculated to be approximately 0.0045°. Since the maximum compensation for the right ascension at the ascending node is 0.3743°, the number of adjustments N to the right ascension at the ascending node should be greater than the ratio of the two, i.e., greater than 83.7 times.

[0079] If N is taken as 100, then the right ascension compensations for the ascending nodes of the four stars are -0.0019°, 0°, 0.0019°, and 0.0037° respectively, which can be calculated using the formula... and will Substitute the values ​​and iteratively solve for the duration of a single maneuver. The single maneuver duration of the four stars is 648.75s (because the compensation is negative, the maneuver duration along the normal direction is...). Taking 270°, during maneuvering along the negative normal direction Take 90°), 0s, 648.75s and 1408.03s.

[0080] After launching four satellites in one launch, the four satellites were adjusted to enter drift orbits.

[0081] During their stay in drift orbit, the four satellites underwent multiple adjustments to their right ascension of the ascending node by applying normal thrust and controlling the duration of each maneuver. The specific process is as follows: First adjustment of right ascension of ascending node: Apply normal thrust F to each satellite and control the duration of each maneuver. The times are 648.75s, 0s, 648.75s, and 1408.03s; where the orbital velocities of each satellite are... It is 7612.6 m / s. The thrust arc length is set to 270°, 90°, 90°, and 90°. The inclinations are 41.14°, 0°, 41.14°, and 89.29°, the orbital inclination i is 50°, and the normal thrust acceleration is... 3×10 -4 m / s 2 It can be done through formulas. The offset of the right ascension adjustment of the ascending node for each satellite was calculated as -0.0019°, 0°, 0.0019°, and 0.0037°, respectively.

[0082] Second ascending node right ascension adjustment: Apply a normal thrust F to each satellite and control the duration of each maneuver. The times are 648.75s, 0s, 648.75s, and 1408.03s; where the orbital velocities of each satellite are... It is 7612.6 m / s. The thrust arc length is set to 270°, 90°, 90°, and 90°. The inclinations are 41.14°, 0°, 41.14°, and 89.29°, the orbital inclination i is 50°, and the normal thrust acceleration is... 3×10 -4 m / s 2 It can be done through formulas. The offset of the right ascension adjustment of the ascending node for each satellite was calculated as -0.0019°, 0°, 0.0019°, and 0.0037°, respectively.

[0083] Repeat the above process for the Nth adjustment of the right ascension of the ascending node: apply a normal thrust F to each satellite and control the duration of each maneuver. The times are 648.75s, 0s, 648.75s, and 1408.03s; where the orbital velocities of each satellite are... It is 7612.6 m / s. The thrust arc length is set to 270°, 90°, 90°, and 90°. The inclinations are 41.14°, 0°, 41.14°, and 89.29°, the orbital inclination i is 50°, and the normal thrust acceleration is... 3×10 -4 m / s 2 It can be done through formulas. The offset of the right ascension adjustment of the ascending node for each satellite was calculated as -0.0019°, 0°, 0.0019°, and 0.0037°, respectively.

[0084] After N adjustments to the right ascension of the ascending node, the offset values ​​of these N adjustments for each satellite are summed to obtain the offset value of the ascending node's right ascension. During actual adjustments, the above single control value can be fine-tuned according to the actual deviation and control requirements.

[0085] After the offset of the right ascension of the ascending node of each satellite is matched with the corresponding compensation of the right ascension of the ascending node, the satellites are put into working orbit through semi-major axis control.

[0086] Figure 2 This is a schematic diagram of the structure of a satellite ascending node right ascension adjustment device for multi-satellite launch provided in an embodiment of this application, as shown below. Figure 2 As shown in the embodiment of this application, the satellite ascending node right ascension adjustment device for multi-satellite launches includes an adjustment module 201, an offset module 202, and a control module 203, wherein: The adjustment module 201 is used to adjust the satellite to enter the drift orbit; wherein the satellite is a satellite launched by a single rocket; the offset module 202 is used to offset the right ascension of the ascending node of the satellite based on the compensation amount of the right ascension of the ascending node of the satellite before the satellite enters the working orbit; wherein the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit; the control module 203 is used to control the satellite to enter the working orbit after the offset amount of the right ascension of the ascending node of the satellite matches the compensation amount of the right ascension of the ascending node of the satellite.

[0087] Specifically, for satellites launched in a single rocket carrying multiple satellites, the adjustment module 201 can adjust each satellite to enter a drift orbit. Each satellite will then climb from the drift orbit to its operational orbit. The altitude of the drift orbit is lower than that of the operational orbit.

[0088] The offset module 202 can obtain the expected and nominal values ​​of the right ascension of the ascending node of the satellite's working orbit. It then calculates the compensation amount for the ascending node by subtracting the nominal value from the expected value. Before the satellite enters its working orbit, the ascending node is offset based on this compensation amount, constructing a correction compensation for the ascending node. The expected value of the ascending node's right ascension is predetermined, and the nominal value is pre-selected.

[0089] The control module 203 compares the offset of the right ascension of the ascending node of the satellite with the compensation of the right ascension of the ascending node of the satellite. If the offset of the right ascension of the ascending node of the satellite matches the compensation of the right ascension of the ascending node of the satellite, it means that the satellite has completed the adjustment of the right ascension of the ascending node, and then the ground control center can control the satellite to enter the working orbit.

[0090] The ascending node right ascension adjustment device for multi-satellite launch provided in this application adjusts the satellites to enter drift orbits. Before the satellites enter their working orbits, the ascending node right ascension of the satellites is offset based on the compensation amount of the ascending node right ascension. The compensation amount of the ascending node right ascension is obtained by subtracting the nominal value of the ascending node right ascension from the expected value of the ascending node right ascension of the satellite's working orbit. After the offset amount of the ascending node right ascension is matched with the compensation amount, the satellites are controlled to enter their working orbits. Because the ascending node right ascension of the satellites is changed based on the compensation amount before they enter their working orbits, the ascending node right ascension deviation after the satellites enter their working orbits is reduced, improving the adjustment efficiency of the ascending node right ascension and reducing the risk of collisions between satellites within the constellation.

[0091] Based on the above embodiments, the step of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node right ascension further includes: During the period when the satellite is parked in its drift orbit, multiple adjustments to the right ascension of its ascending node are made by applying normal thrust to the satellite and controlling the duration of each maneuver. After multiple adjustments to the right ascension of the ascending node, the offset of the right ascension of the ascending node is matched with the compensation of the right ascension of the ascending node.

[0092] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. This indicates the orbital velocity of the satellite. Indicates the length of the thrust arc. This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

[0093] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The orbital velocity is represented by , and the inclination angle of the satellite is represented by . Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

[0094] Based on the above embodiments, the step of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node right ascension further includes: During the satellite's ascent, the angle between the satellite's thrust direction and its heading is adjusted to achieve multiple adjustments to the right ascension of the ascending node; wherein, after multiple adjustments to the right ascension of the ascending node, the offset of the satellite's right ascension of the ascending node is matched with the compensation of the satellite's right ascension of the ascending node.

[0095] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. Indicates the length of the thrust arc. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

[0096] Based on the above embodiments, the offset amount of the satellite's single ascending node right ascension adjustment is further calculated according to the formula... It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The value represents the orbital velocity, and 'i' represents the orbital inclination angle. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

[0097] Based on the above embodiments, the duration of the adjustment of the right ascension of the ascending node of the satellite is further less than 1 / 3 of the orbital period of the satellite's orbit.

[0098] Based on the above embodiments, furthermore, the right ascension of the ascending node of each satellite launched by a single rocket is simultaneously offset.

[0099] The embodiments of the apparatus provided in this application can be used to execute the processing flow of the above-described method embodiments. Its functions will not be repeated here, but can be referred to the detailed description of the above-described method embodiments.

[0100] Figure 3 This is a schematic diagram of the physical structure of the computer device provided in the embodiments of this application, such as... Figure 3 As shown, the computer device may include a processor 301, a communications interface 302, a memory 303, and a communication bus 304. The processor 301, communications interface 302, and memory 303 communicate with each other via the communication bus 304. The processor 301 can call logical instructions in the memory 303 to execute the following methods: adjusting a satellite to enter a drift orbit; wherein the satellite is a satellite launched by a single rocket; before the satellite enters its working orbit, offsetting the right ascension of the satellite's ascending node based on a compensation amount; wherein the compensation amount of the satellite's ascending node is obtained by subtracting the nominal value of the satellite's ascending node's right ascension from the expected value of the satellite's working orbit's ascending node's right ascension; after the offset amount of the satellite's ascending node's right ascension matches the compensation amount of the satellite's ascending node's right ascension, controlling the satellite to enter the working orbit.

[0101] Furthermore, the logical instructions in the aforementioned memory 303 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0102] This embodiment discloses a computer program product, which includes a computer program stored on a non-transitory computer-readable storage medium. The computer program includes program instructions, and when the program instructions are executed by a computer, the computer can perform the methods provided in the above-described method embodiments, such as: adjusting a satellite to enter a drift orbit; wherein the satellite is a satellite launched by a single rocket; before the satellite enters its working orbit, offsetting the right ascension of the satellite's ascending node based on a compensation amount; wherein the compensation amount of the satellite's ascending node is obtained by subtracting the nominal value of the satellite's ascending node's right ascension from the expected value of the satellite's working orbit's ascending node's right ascension; and after the offset amount of the satellite's ascending node's right ascension matches the compensation amount of the satellite's ascending node's right ascension, controlling the satellite to enter the working orbit.

[0103] This embodiment provides a computer-readable storage medium storing a computer program that causes a computer to execute the methods provided in the above-described method embodiments, such as: adjusting a satellite to enter a drift orbit; wherein the satellite is a satellite launched by a single rocket; before the satellite enters its working orbit, offsetting the right ascension of the satellite's ascending node based on a compensation amount; wherein the compensation amount of the satellite's ascending node is obtained by subtracting the nominal value of the satellite's ascending node's right ascension from the expected value of the satellite's working orbit's ascending node's right ascension; and after the offset amount of the satellite's ascending node's right ascension matches the compensation amount of the satellite's ascending node's right ascension, controlling the satellite to enter the working orbit.

[0104] 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.

[0105] 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.

[0106] 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.

[0107] 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.

[0108] In the description of this specification, the references to terms such as "an embodiment," "a specific embodiment," "some embodiments," "for example," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0109] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this application. It should be understood that the above descriptions are merely specific embodiments of this application and are not intended to limit the scope of protection of this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. A method for adjusting the right ascension of the ascending node of satellites launched in a single rocket for multiple satellite launches, characterized in that, include: Adjust the satellite to enter a drift orbit; wherein, the satellite is a satellite launched by a single rocket with multiple satellites in one launch vehicle; Before the satellite enters its working orbit, the right ascension of the ascending node of the satellite is offset based on the compensation amount of the right ascension of the ascending node; wherein, the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit. After the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite, the satellite is controlled to enter the working orbit.

2. The method according to claim 1, characterized in that, The process of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node includes: During the period when the satellite is parked in its drift orbit, multiple adjustments to the right ascension of its ascending node are made by applying normal thrust to the satellite and controlling the duration of each maneuver. After multiple adjustments to the right ascension of the ascending node, the offset of the right ascension of the ascending node is matched with the compensation of the right ascension of the ascending node.

3. The method according to claim 2, characterized in that, The offset of the satellite's single ascending node right ascension adjustment is based on the formula. It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, Indicates the length of the thrust arc. This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

4. The method according to claim 2, characterized in that, The offset of the satellite's single ascending node right ascension adjustment is based on the formula. It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The orbital velocity is represented by , and the inclination angle of the satellite is represented by . Indicates the normal thrust acceleration. This indicates the duration of a single maneuver by the satellite.

5. The method according to claim 1, characterized in that, The process of offsetting the right ascension of the satellite's ascending node based on the compensation amount of the satellite's ascending node includes: During the satellite's ascent, the angle between the satellite's thrust direction and its heading is adjusted to achieve multiple adjustments to the right ascension of the ascending node; wherein, after multiple adjustments to the right ascension of the ascending node, the offset of the satellite's right ascension of the ascending node is matched with the compensation of the satellite's right ascension of the ascending node.

6. The method according to claim 5, characterized in that, The offset of the satellite's single ascending node right ascension adjustment is based on the formula. It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. Indicates orbital velocity, This indicates the phase at the center of the arc segment, and the right ascension control for the ascending node. Take 90° or 270°, where i represents the track inclination angle. Indicates the length of the thrust arc. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

7. The method according to claim 5, characterized in that, The offset of the satellite's single ascending node right ascension adjustment is based on the formula. It is confirmed that, among them, This represents the bias amount adjusted for the right ascension of the ascending node in a single instance. The value represents the orbital velocity, and 'i' represents the orbital inclination angle. 'a' represents the semi-major axis of the satellite's orbit. This indicates the change in the semi-major axis. This indicates the angle between the thrust direction and the heading of the satellite.

8. The method according to claim 2 or 5, characterized in that, The duration of the single adjustment of the right ascension of the ascending node of the satellite is less than 1 / 3 of the orbital period of the satellite's orbit.

9. The method according to claim 1, characterized in that, The right ascension of the ascending node of each satellite launched by a single rocket is simultaneously offset.

10. A device for adjusting the right ascension of the ascending node of satellites launched by a single rocket for multiple satellites, characterized in that, include: An adjustment module is used to adjust the satellite to enter a drift orbit; wherein the satellite is a satellite launched by a single rocket with multiple satellites in one launch vehicle; An offset module is used to offset the right ascension of the ascending node of the satellite based on the compensation amount of the right ascension of the ascending node of the satellite before the satellite enters its working orbit; wherein the compensation amount of the right ascension of the ascending node of the satellite is obtained by subtracting the nominal value of the right ascension of the ascending node of the satellite from the expected value of the right ascension of the ascending node of the satellite's working orbit. The control module is used to control the satellite to enter the working orbit after the offset of the right ascension of the ascending node of the satellite is matched with the compensation of the right ascension of the ascending node of the satellite.

11. A computer device, comprising a memory, a processor, and a computer program stored in the memory, characterized in that, The processor executes the computer program to implement the method according to any one of claims 1 to 9.

12. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program / instructions that, when executed by a processor, implement the method described in any one of claims 1 to 9.

13. A computer program product comprising a computer program / instructions, characterized in that, When the computer program / instructions are executed by the processor, they implement the method described in any one of claims 1 to 9.

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