Design method of geosynchronous orbit satellite drifting scheme based on eccentricity control

Abstract

This invention discloses a method for designing a satellite drifting scheme for geosynchronous orbit based on eccentricity control. The method includes: determining mission parameters and an overall maneuvering strategy based on the input drifting mission; the overall maneuvering strategy is designed as two drift initiation maneuvers and three braking maneuvers during the braking maneuver; estimating the total maneuvering amount ΔV of the drifting mission based on the mission parameters; determining the ignition time and maneuvering amount of the drift initiation maneuver based on ΔV and the eccentricity control requirements of the drift initiation point; estimating the ignition time and maneuvering amount of the braking maneuver based on ΔV and the braking point control requirements; adjusting the maneuvering time of the braking maneuver to control the satellite longitude and eccentricity into the target control box, thus completing the drifting scheme design. The method described in this invention achieves eccentricity control through the design of maneuvering time points and maneuvering amounts, reducing the potential collision risk during the drifting process.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft orbit technology, and in particular relates to a design method for a drifting satellite scheme based on eccentricity control in geosynchronous orbit. Background Technology

[0002] Geosynchronous orbit satellites usually operate in fixed orbits, but depending on mission requirements, they need to move to another orbit. The process of moving from one orbit to another is called satellite drift.

[0003] Keplerian orbital drift is typically achieved through tangential maneuvers. At the initial orbital position, a tangential maneuver raises or lowers the semi-major axis. Once near the target orbital position, a reverse tangential maneuver is performed to raise or lower the semi-major axis, ultimately resulting in a stationary position at the target orbital. When designing a Keplerian orbital drift scheme, constraints such as mission duration, collision risk, and fuel consumption must be considered. Tangential maneuvers not only affect the semi-major axis (one of the six elements of a Keplerian orbit) but also the eccentricity. The magnitude and direction of the eccentricity can be controlled to reduce the risk of collisions during the drift process. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a design method for a geosynchronous orbit satellite drifting scheme based on eccentricity control. By designing the maneuvering time point and maneuvering amount, the eccentricity can be controlled, thereby reducing the collision risk that may occur during the drifting process.

[0005] To address the aforementioned technical problems, this invention discloses a design method for a geosynchronous orbit satellite drift scheme based on eccentricity control, comprising:

[0006] Based on the input drifting mission, determine the mission parameters and overall maneuver strategy; the overall maneuver strategy is as follows: design two drifting maneuvers during the drift initiation maneuver and three braking maneuvers during the braking maneuver.

[0007] Estimate the total maneuverability ΔV of the drifting star mission based on the mission parameters;

[0008] Based on the control requirements of ΔV and the eccentricity of the drift initiation point, determine the ignition timing and maneuvering amount of the drift initiation maneuver;

[0009] Based on ΔV and braking point control requirements, estimate the ignition timing and maneuvering amount of the braking maneuver;

[0010] Adjusting the braking maneuver timing and controlling the satellite's longitude and eccentricity into the target control box completes the satellite drifting plan.

[0011] In the above design method for geosynchronous orbit satellite drifting schemes based on eccentricity control, the mission parameters include: starting drift longitude L. i Target longitude L tAnd task duration T.

[0012] In the above design method for geosynchronous orbit satellite drifting schemes based on eccentricity control, the total maneuvering amount ΔV of the drifting mission is estimated using the following formula:

[0013]

[0014] In the above design method for geosynchronous orbit satellite drifting schemes based on eccentricity control, the ignition timing and maneuvering amount of the drift initiation maneuver are determined according to ΔV and the eccentricity control requirements of the drift initiation point, including:

[0015] The amount of maneuvering in both drift maneuvers was determined to be the same.

[0016] The time interval between the ignition time of the second drift maneuver and the ignition time of the first drift maneuver was determined to be 12 hours.

[0017] Based on the actual orbital elements of the satellite obtained before drifting, the ignition time of the first drift maneuver is adjusted to ensure that the eccentricity is less than 0.0003 after drifting.

[0018] In the above design method for drifting satellites in geosynchronous orbit based on eccentricity control,

[0019] If there are no co-located satellites around the satellite, then any point in time can be chosen as the ignition time for the first drift maneuver.

[0020] If there are co-located satellites around the satellite, then:

[0021] Based on the orbit determination results of the binary stars, determine the eccentricity vector difference between the two stars. The eccentricity adjustment for the first drift maneuver should be perpendicular to the eccentricity vector difference between the two stars; where, The polar coordinate representation is (e,θ);

[0022] Selecting right ascension L m =θ+90° or θ+270° as the ignition time for the first drift maneuver, converted to UTC time, that is:

[0023]

[0024] Where T1 represents the ignition time of the first drift maneuver, T0 represents the UTC time corresponding to 12:00 local time at the longitude of the satellite, D1 represents the date of the maneuver, and D0 represents the vernal equinox of that year.

[0025] In the above design method for the drifting satellite scheme of geosynchronous orbit based on eccentricity control, the ignition timing and maneuver amount of the braking maneuver are estimated according to ΔV and braking point control requirements, including:

[0026] S41, the preset date for the first braking maneuver is D1+T-1; the preset maneuver amount for the first braking maneuver is... The amount of motion for the second braking maneuver is The third braking maneuver has a maneuver amount of 0.1; the preset time interval between the two braking maneuvers is 12 hours; the direction of the braking maneuver is opposite to the direction of the drift maneuver.

[0027] S42, Determine the eccentricity control target for braking maneuvers based on the target longitude eccentricity control box and the date of braking maneuvers;

[0028] S43, based on the track elements and eccentricity control target before the first braking maneuver, calculate the eccentricity vector difference. The polar coordinate representation is (e1, θ1); therefore, the ignition time T2 of the first braking maneuver is:

[0029]

[0030] S44. Using the parameters preset in step S41 and the ignition time T2 of the first braking maneuver determined in step S43 as simulation input, the maneuvering amount of the second and third braking maneuvers is adaptively adjusted through simulation to ensure that the satellite's eccentricity is controlled within the target eccentricity range, and that the absolute value of the satellite's drift rate after the three braking maneuvers is less than 0.001° / day.

[0031] In the above-mentioned design method for a geosynchronous orbit satellite drifting scheme based on eccentricity control, the maneuvering time of the braking maneuver is adjusted, and the satellite longitude and eccentricity are controlled into the target control box, thus completing the drifting scheme. This includes: adjusting the maneuvering date of the first braking maneuver and the time interval between the two braking maneuvers, and controlling the satellite longitude and eccentricity into the target control box.

[0032] In the above design method for the drifting satellite in geosynchronous orbit based on eccentricity control, the following requirements must be met when adjusting the time interval between two braking maneuvers:

[0033] ΔD=0.5+N

[0034] Where ΔD represents the time interval between two braking maneuvers, in days; N is a positive integer.

[0035] The present invention has the following advantages:

[0036] This invention discloses a design method for a geosynchronous orbit satellite drifting scheme based on eccentricity control. By designing the maneuvering time point and maneuvering amount, the eccentricity is controlled, reducing the collision risk that may occur during the drifting process; at the same time, the design efficiency of the eccentricity control strategy is improved. Attached Figure Description

[0037] Figure 1 This is a flowchart of a design method for a geosynchronous orbit satellite drifting scheme based on eccentricity control, as described in an embodiment of the present invention. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0039] One of the core ideas of this invention is to disclose a design method for a geostationary orbit satellite drifting scheme based on eccentricity control. This method employs a scheme of two initial drift maneuvers followed by three braking maneuvers. Eccentricity is controlled by selecting the timing and magnitude of each maneuver, ultimately ensuring the completion of the drifting mission while reducing the risk of collisions during the drifting process. First, the total amount of drift maneuvers is determined. Then, the timing and magnitude of the two initial drift maneuvers are determined to ensure that the eccentricity is minimized after drifting begins. Finally, the magnitude and time interval of the three braking maneuvers are determined to ensure that the satellite's longitude and eccentricity are controlled to be near the target control box.

[0040] like Figure 1 As shown, in this embodiment, the design method for a geostationary orbit satellite drifting scheme based on eccentricity control includes:

[0041] Step 1: Determine the mission parameters and overall maneuver strategy based on the input drifting star mission.

[0042] In this embodiment, the overall maneuvering strategy is as follows: two drift maneuvers are designed for the initial drift maneuver, and three braking maneuvers are designed for the braking maneuver. Specifically: Since tangential maneuvers affect eccentricity, and eccentricity is a vector among the six elements of Keplerian orbit, a single tangential orbital maneuver will only adjust the eccentricity in one direction, which is not conducive to eccentricity control. Therefore, two drift maneuvers are designed for the initial drift maneuver to facilitate eccentricity control. During the braking maneuver, to avoid the impact of maneuvering efficiency fluctuations on the final braking result, three braking maneuvers are designed. The third braking maneuver is relatively small to correct the efficiency of the first two maneuvers, and its efficiency fluctuations have a relatively small impact on the final braking result. The main mission parameters include: drift longitude L. i Target longitude L t And task duration T.

[0043] Step 2: Estimate the total maneuverability ΔV of the drifting star mission based on the mission parameters.

[0044] In this embodiment, without considering the influence of the Earth's mean longitude drift acceleration, the total maneuvering amount of the spacecraft mission can be roughly estimated using the following formula:

[0045]

[0046] Step 3: Determine the ignition timing and maneuvering amount of the drift initiation maneuver based on ΔV and the drift initiation point eccentricity control requirements.

[0047] In this embodiment, the initial drift maneuver is designed as a tangential maneuver, and the amount of maneuver in both initial drift maneuvers is the same. The time interval between the ignition time of the second drift maneuver and the ignition time of the first drift maneuver is 12 hours. Then, based on the actual orbital elements of the satellite obtained before drifting, the ignition time of the first drift maneuver is adjusted to ensure that the eccentricity after drifting is less than 0.0003.

[0048] Furthermore, if there are no co-located satellites in the vicinity of the satellite, any point in time can be chosen as the ignition time for the first drift maneuver. If there are co-located satellites in the vicinity of the satellite, the risk of collision with the co-located satellites must be considered, and the ignition time for the first drift maneuver must be determined as follows:

[0049] Based on the orbit determination results of the binary stars, determine the eccentricity vector difference between the two stars. The eccentricity adjustment for the first drift maneuver should be perpendicular to the eccentricity vector difference between the two stars; where, The polar coordinate representation is (e, θ).

[0050] Selecting right ascension L m =θ+90° or θ+270° as the ignition time for the first drift maneuver, converted to UTC time, that is:

[0051]

[0052] Where T1 represents the ignition time of the first drift maneuver, T0 represents the UTC time corresponding to 12:00 local time at the longitude of the satellite, D1 represents the date of the maneuver, and D0 represents the vernal equinox of that year.

[0053] Step 4: Estimate the ignition timing and maneuvering amount of the braking maneuver based on ΔV and braking point control requirements.

[0054] In this embodiment, the estimation process for the ignition timing and maneuver amount of the braking maneuver is as follows:

[0055] S41, the preset date for the first braking maneuver is D1+T-1; the preset maneuver amount for the first braking maneuver is... The amount of motion for the second braking maneuver is The third braking maneuver has a maneuver amount of 0.1; the preset time interval between the two braking maneuvers is 12 hours. The direction of the braking maneuver is opposite to the direction of the drift maneuver.

[0056] S42, determine the eccentricity control target for braking maneuvers based on the target longitude eccentricity control box and the date of braking maneuvers.

[0057] S43, based on the track elements and eccentricity control target before the first braking maneuver, calculate the eccentricity vector difference. The polar coordinate representation is (e1, θ1); therefore, the ignition time T2 of the first braking maneuver is:

[0058]

[0059] S44. Using the parameters preset in step S41 and the ignition time T2 of the first braking maneuver determined in step S43 as simulation input, the maneuvering amount of the second and third braking maneuvers is adaptively adjusted through simulation to ensure that the satellite's eccentricity is controlled within the target eccentricity range, and that the absolute value of the satellite's drift rate after the three braking maneuvers is less than 0.001° / day.

[0060] Step 5: Adjust the maneuvering time of the braking maneuver, and input the satellite longitude and eccentricity into the target control box. The satellite drifting plan is now complete.

[0061] In this embodiment, after step 4, the satellite's eccentricity meets the control requirements, but its longitude may not be entered into the target control box. Therefore, it is necessary to adjust the maneuver date of the first braking maneuver (without adjusting the ignition time) and the time interval between the two braking maneuvers as needed to ensure that the satellite's longitude and eccentricity are controlled into the target control box. When adjusting the time interval between the two braking maneuvers, the following requirements must be met:

[0062] ΔD=0.5+N

[0063] Where ΔD represents the time interval between two braking maneuvers, in days; N is a positive integer.

[0064] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

[0065] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for designing a drifting satellite scheme based on eccentricity control in geosynchronous orbit, characterized in that, include: Based on the input drifting mission, determine the mission parameters and overall maneuver strategy; the overall maneuver strategy is as follows: design two drifting maneuvers during the drift initiation maneuver and three braking maneuvers during the braking maneuver. Estimate the total maneuverability ΔV of the drifting star mission based on the mission parameters; Based on the control requirements of ΔV and the eccentricity of the drift initiation point, determine the ignition timing and maneuvering amount of the drift initiation maneuver; Based on ΔV and braking point control requirements, estimate the ignition timing and maneuvering amount of the braking maneuver; Adjusting the braking maneuver timing and controlling the satellite's longitude and eccentricity into the target control box completes the satellite drifting plan.

2. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 1, characterized in that, Mission parameters include: starting longitude L i Target longitude L t And task duration T.

3. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 2, characterized in that, The total maneuverability ΔV of the drifting mission can be estimated using the following formula:

4. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 2, characterized in that, Based on the control requirements of ΔV and the eccentricity of the drift initiation point, determine the ignition timing and maneuver amount of the drift initiation maneuver, including: The amount of maneuvering in both drift maneuvers was determined to be the same. The time interval between the ignition time of the second drift maneuver and the ignition time of the first drift maneuver was determined to be 12 hours. Based on the actual orbital elements of the satellite obtained before drifting, the ignition time of the first drift maneuver is adjusted to ensure that the eccentricity is less than 0.0003 after drifting.

5. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 4, characterized in that, If there are no co-located satellites around the satellite, then any point in time can be chosen as the ignition time for the first drift maneuver. If there are co-located satellites around the satellite, then: Based on the orbit determination results of the binary stars, determine the eccentricity vector difference between the two stars. The eccentricity adjustment for the first drift maneuver should be perpendicular to the eccentricity vector difference between the two stars; where, The polar coordinate representation is (e,θ); Selecting right ascension L m =θ+90° or θ+270° as the ignition time for the first drift maneuver, converted to UTC time, that is: Where T1 represents the ignition time of the first drift maneuver, T0 represents the UTC time corresponding to 12:00 local time at the longitude of the satellite, D1 represents the date of the maneuver, and D0 represents the vernal equinox of that year.

6. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 5, characterized in that, Based on ΔV and braking point control requirements, estimate the ignition timing and maneuvering amount of the braking maneuver, including: S41, the preset date for the first braking maneuver is D1+T-1; the preset maneuver amount for the first braking maneuver is... The amount of motion for the second braking maneuver is The third braking maneuver has a maneuver amount of 0.1; the preset time interval between the two braking maneuvers is 12 hours; the direction of the braking maneuver is opposite to the direction of the drift maneuver. S42, Determine the eccentricity control target for braking maneuvers based on the target longitude eccentricity control box and the date of braking maneuvers; S43, based on the track elements and eccentricity control target before the first braking maneuver, calculate the eccentricity vector difference. The polar coordinate representation is (e1, θ1); therefore, the ignition time T2 of the first braking maneuver is: S44. Using the parameters preset in step S41 and the ignition time T2 of the first braking maneuver determined in step S43 as simulation input, the maneuvering amount of the second and third braking maneuvers is adaptively adjusted through simulation to ensure that the satellite's eccentricity is controlled within the target eccentricity range, and that the absolute value of the satellite's drift rate after the three braking maneuvers is less than 0.001° / day.

7. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 6, characterized in that, The timing of the braking maneuver was adjusted, and the satellite longitude and eccentricity were entered into the target control box. The satellite drifting plan was completed, including: adjusting the date of the first braking maneuver and the time interval between the two braking maneuvers, and entering the satellite longitude and eccentricity into the target control box.

8. The method for designing a drifting satellite scheme based on eccentricity control for geosynchronous orbit according to claim 7, characterized in that, When adjusting the time interval between two braking maneuvers, the following requirements must be met: ΔD=0.5+N Where ΔD represents the time interval between two braking maneuvers, in days; N is a positive integer.

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