Geosynchronous orbit satellite drift scheme design method based on eccentricity rate control

Abstract

The invention discloses a geosynchronous orbit satellite drifting scheme design method based on eccentricity rate control, which comprises the following steps: determining task parameters and an overall maneuvering strategy according to an input drifting task; according to the overall maneuvering strategy, two-time floating maneuvering is designed during floating maneuvering, and three-time braking maneuvering is designed during braking maneuvering; estimating the total maneuvering amount delta V of the floating task according to the task parameters; according to the delta V and the eccentricity rate control requirement of the floating starting point, the ignition moment and the maneuvering amount of floating starting maneuvering are determined; according to the delta V and the brake point control requirement, the ignition time and the maneuvering amount of brake maneuvering are estimated; and the maneuvering time of braking maneuvering is adjusted, the longitude and eccentricity of the satellite are controlled into the target control box, and the satellite drifting scheme is formulated. According to the method, by designing the maneuvering time point and the maneuvering amount, control over the eccentricity rate is achieved, and the collision risk possibly generated in the satellite floating process is reduced.

Description

Technical Field

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

[0002] Geosynchronous orbit satellites usually operate in a fixed orbital position, but depending on mission requirements, they need to work in another orbital position. The process of moving from one orbital position to another is called drifting satellite.

[0003] Drifting is usually achieved through tangential maneuvers. Tangential maneuvers are performed at the initial orbit to raise or lower the semi-major axis. After reaching the vicinity of the target orbit, reverse tangential maneuvers are performed to lower or raise the semi-major axis and finally fix the target orbit. When designing a drifting plan, it is necessary to consider limiting factors such as mission duration, collision risk, and fuel consumption. Tangential maneuvers not only affect the semi-major axis of the six elements of Kepler orbit, but also the eccentricity. The size and direction of the eccentricity can be controlled to reduce the risk of collision during drifting. Summary of the invention

[0004] The technology of the present invention solves the problem: overcomes the shortcomings of the prior art and provides a method for designing 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] In order to solve the above technical problems, the present invention discloses a method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control, comprising:

[0006] According to the input drifting mission, the mission parameters and the overall maneuvering strategy are determined; the overall maneuvering strategy is: two drifting maneuvers are designed for the drifting maneuver, and three braking maneuvers are designed for the braking maneuver;

[0007] According to the mission parameters, estimate the total maneuvering volume ΔV of the drifting star mission;

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

[0009] Estimate the ignition timing and maneuvering amount of the braking maneuver based on ΔV and braking point control requirements;

[0010] Adjust the maneuvering time of the braking maneuver, input the satellite longitude and eccentricity into the target control box, and the drifting plan is completed.

[0011] In the above-mentioned geosynchronous orbit satellite drifting scheme design method based on eccentricity control, the mission parameters include: the drifting longitude L i 、Target longitude L tand task duration T.

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

[0013]

[0014] In the above-mentioned geosynchronous orbit satellite drifting scheme design method based on eccentricity control, the ignition time and maneuvering amount of the drifting maneuver are determined according to the ΔV and the eccentricity control requirements of the drifting point, including:

[0015] Make sure that the maneuvering amount of the two drifting maneuvers is the same, both

[0016] The time interval between the ignition time of the second drifting maneuver and the ignition time of the first drifting maneuver is determined to be 12 hours;

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

[0018] In the above-mentioned geosynchronous orbit satellite drifting scheme design method based on eccentricity control,

[0019] If there is no co-located satellite around the satellite, a time point is selected as the ignition moment for the first drift maneuver;

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

[0021] According to the orbit determination results of the binary star, the eccentricity vector difference of the binary star is determined The eccentricity adjustment direction of the first drift maneuver should be perpendicular to the eccentricity vector difference of the binary satellite; The polar coordinate form of is (e,θ);

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

[0023]

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

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

[0026] S41, preset the maneuver date of the first braking maneuver as D1+T-1; preset the maneuver amount of the first braking maneuver as The maneuvering amount of the second braking maneuver is The maneuvering amount of the third braking maneuver is 0.1; the preset time interval between the two braking maneuvers is 12 hours; the maneuvering direction of the braking maneuver is opposite to the maneuvering direction of the drifting maneuver;

[0027] S42, determining an eccentricity control target for the braking maneuver according to the eccentricity control box of the target longitude and the date of the braking maneuver;

[0028] S43, calculate the eccentricity vector difference according to the number of track elements and the eccentricity control target before the first braking maneuver The polar coordinate expression of is (e1,θ1); then, 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, adaptively adjust the maneuvering amount of the second braking maneuver and the third braking maneuver through simulation to ensure that the eccentricity of the satellite is controlled to the target eccentricity range, and the absolute value of the satellite drift rate after three braking maneuvers is less than 0.001° / day.

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

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

[0033] ΔD=0.5+N

[0034] Wherein, 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] The present invention discloses a method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control, in which the eccentricity is controlled by designing the maneuvering time point and the maneuvering amount, thereby 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 The present invention is a flowchart of a method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control in an embodiment of the present invention. DETAILED DESCRIPTION

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

[0039] One of the core ideas of the present invention is: a design method for a geosynchronous orbit satellite drifting scheme based on eccentricity control is disclosed, which adopts a scheme of two drifting maneuvers + three braking maneuvers, and realizes eccentricity control by selecting the time and amount of each maneuver, and finally ensures that the drifting mission is completed while reducing the risk of collision during the drifting process. First, the total amount of drifting maneuvers is determined, and then the maneuvering time and amount of the two drifting maneuvers are determined to ensure that the eccentricity after drifting is as small as possible, and then the maneuvering amount and maneuvering time interval of the three braking maneuvers are determined to ensure that the longitude and eccentricity of the satellite are controlled near the target control box.

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

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

[0042] In this embodiment, the overall maneuvering strategy is: two drifting maneuvers are designed for the drifting maneuver, and three braking maneuvers are designed for the braking maneuver. Specifically: Since the tangential maneuver will affect the eccentricity, among the six elements of the Kepler orbit, the eccentricity is a vector. A single tangential orbit maneuver will only adjust the eccentricity in one direction, which is not conducive to the control of the eccentricity. Therefore, the drifting maneuver is designed to be two drifting maneuvers to facilitate the control of the eccentricity. During the braking maneuver, in order to avoid the influence of the maneuvering efficiency fluctuation 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 fluctuation has relatively little effect on the final braking result. The mission parameters mainly include: the drifting longitude L i 、Target longitude L t and task duration T.

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

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

[0045]

[0046] Step 3, determining the ignition timing and maneuvering amount of the drift start maneuver according to the ΔV and drift start point eccentricity control requirements.

[0047] In this embodiment, first, the drifting maneuver is designed as: tangential maneuver, the maneuvering amount of the two drifting maneuvers is the same, both 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, according to the actual orbital elements of the satellite obtained by orbit determination 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 is no co-located satellite around the satellite, then any time point can be selected as the ignition time for the first drift maneuver. If there is a co-located satellite around the satellite, the risk of collision with the co-located satellite must be considered, and the ignition time for the first drift maneuver must be determined as follows:

[0049] According to the orbit determination results of the binary star, the eccentricity vector difference of the binary star is determined The eccentricity adjustment direction of the first drift maneuver should be perpendicular to the eccentricity vector difference of the binary satellite; The polar coordinate form of is (e,θ).

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

[0051]

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

[0053] Step 4, based on ΔV and brake point control requirements, estimate the ignition timing and maneuvering amount of the brake maneuver.

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

[0055] S41, preset the maneuver date of the first braking maneuver as D1+T-1; preset the maneuver amount of the first braking maneuver as The maneuvering amount of the second braking maneuver is The maneuvering amount of the third braking maneuver is 0.1; the preset time interval between the two braking maneuvers is 12 hours. Among them, the maneuvering direction of the braking maneuver is opposite to the maneuvering direction of the drifting maneuver.

[0056] S42, determining an eccentricity control target for the braking maneuver according to the eccentricity control box of the target longitude and the date of the braking maneuver.

[0057] S43, calculate the eccentricity vector difference according to the number of track elements and the eccentricity control target before the first braking maneuver The polar coordinate expression of is (e1,θ1); then, 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, adaptively adjust the maneuvering amount of the second braking maneuver and the third braking maneuver through simulation to ensure that the eccentricity of the satellite is controlled to the target eccentricity range, and the absolute value of the satellite drift rate after three braking maneuvers is less than 0.001° / day.

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

[0061] In this embodiment, after step 4, the eccentricity of the satellite has met the control requirements, but the longitude may not enter the target control box, so it is necessary to adjust the maneuver date of the first braking maneuver (without adjusting the ignition time point) and the time interval between the two braking maneuvers as needed to ensure that the satellite longitude and eccentricity are controlled into the target control box. Among them, when adjusting the time interval between the two braking maneuvers, the following requirements must be met:

[0062] ΔD=0.5+N

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

[0064] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0065] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control, characterized in that: include: According to the input drifting mission, the mission parameters and the overall maneuvering strategy are determined; the overall maneuvering strategy is: two drifting maneuvers are designed for the drifting maneuver, and three braking maneuvers are designed for the braking maneuver; According to the mission parameters, estimate the total maneuvering volume ΔV of the drifting star mission; According to the control requirements of ΔV and drift point eccentricity, determine the ignition timing and maneuvering amount of the drift maneuver; Estimate the ignition timing and maneuvering amount of the braking maneuver based on ΔV and braking point control requirements; Adjust the maneuvering time of the braking maneuver, input the satellite longitude and eccentricity into the target control box, and the drifting plan is completed.

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

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

4. The method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control according to claim 1, characterized in that: According to the control requirements of ΔV and drift point eccentricity, determine the ignition timing and maneuvering amount of the drift maneuver, including: Make sure that the maneuvering amount of the two drifting maneuvers is the same, both The time interval between the ignition time of the second drifting maneuver and the ignition time of the first drifting maneuver is determined to be 12 hours; According to the actual orbital elements of the satellite obtained by orbit determination before drifting, the ignition time of the first drifting maneuver is adjusted to ensure that the eccentricity after drifting is less than 0.0003.

5. The method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control according to claim 4, characterized in that: If there is no co-located satellite around the satellite, a time point is selected as the ignition moment for the first drift maneuver; If there are co-located stars around the satellite, then: Based on the orbit determination results of the binary star, the eccentricity vector difference of the binary star is determined The eccentricity adjustment direction of the first drift maneuver should be perpendicular to the eccentricity vector difference of the binary satellite; The polar coordinate form of is (e,θ); Select right ascension L m =θ+90° or θ+270° as the ignition time of the first drift maneuver, converted into UTC time, that is: Wherein, T1 represents the ignition time of the first drift maneuver, T0 represents the UTC time corresponding to 12:00 local time of the satellite's longitude, D1 represents the maneuver date, and D0 represents the vernal equinox of that year.

6. The method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control according to claim 5, characterized in that: According to the ΔV and braking point control requirements, estimate the ignition timing and maneuvering amount of the braking maneuver, including: S41, preset the maneuver date of the first braking maneuver as D1+T-1; preset the maneuver amount of the first braking maneuver as The maneuvering amount of the second braking maneuver is The maneuvering amount of the third braking maneuver is 0.1; the preset time interval between the two braking maneuvers is 12 hours; the maneuvering direction of the braking maneuver is opposite to the maneuvering direction of the drifting maneuver; S42, determining an eccentricity control target for the braking maneuver according to the eccentricity control box of the target longitude and the date of the braking maneuver; S43, calculate the eccentricity vector difference according to the number of track elements and the eccentricity control target before the first braking maneuver The polar coordinate expression of is (e1,θ1); then, 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, adaptively adjust the maneuvering amount of the second braking maneuver and the third braking maneuver through simulation to ensure that the eccentricity of the satellite is controlled to the target eccentricity range, and the absolute value of the satellite drift rate after three braking maneuvers is less than 0.001° / day.

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

8. The method for designing a geosynchronous orbit satellite drifting scheme based on eccentricity control 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 Wherein, ΔD represents the time interval between two braking maneuvers, in days; N is a positive integer.

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