A stationary orbit position keeping method considering thrust direction and local time constraints

Abstract

A geostationary orbit position-keeping method considering thrust direction and local time constraints, belonging to the field of spacecraft control technology, employs one southward ignition and one northward ignition to achieve position-keeping, including three cases: Case 1, with only radial and normal thrust ratio constraints, assuming a 180-degree difference in longitude between southward and northward ignitions, analytical expressions for the ignition longitude and velocity pulse are obtained by solving equations; Case 2, with radial and normal thrust ratio constraints and ignition local time avoidance constraints, a longitude traversal algorithm is set to obtain the longitude and velocity pulse vector values ​​for the two ignitions. During the longitude traversal, an ignition strategy that satisfies the position-keeping requirements of drift rate, inclination angle, and eccentricity, and minimizes the velocity pulse, is selected; Case 3, based on Case 2, adds a constraint of zero tangential thrust on the north side. During the longitude traversal, an ignition strategy that, while satisfying drift rate and inclination angle maintenance, also considers eccentricity maintenance as much as possible is selected.

Description

Technical Field

[0001] This invention relates to a method for maintaining the position of a stationary orbit that takes into account thrust direction and local time constraints, and belongs to the field of spacecraft control technology. Background Technology

[0002] In terms of application background, traditional chemical propulsion position holding decouples east-west and north-south position holding. Existing electric propulsion position holding strategies address the phenomenon of thrust normal and radial coupling, including using multiple electric thrusters with fixed thrust directions to simultaneously hold east-west and north-south positions, and using electric thrusters with adjustable thrust directions under constraints to simultaneously hold east-west and north-south positions. However, published position holding strategies do not consider solutions for position holding strategies that simultaneously achieve east-west and north-south position holding, while also considering ignition timing and thrust direction constraints.

[0003] From a methodological perspective, published electric propulsion position-keeping strategies either employ complex methods such as numerical solutions, which are not conducive to on-board solutions, or the resulting strategies can be implemented but cannot guarantee the satisfaction of the equations. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a static orbit position holding method that considers thrust direction and local time constraints. When considering local time constraints, the method adopts the method of traversing the longitude of the position holding velocity pulse ignition position, solving the position holding pulse multiple times and selecting the optimal value, which ensures the speed and effectiveness of position holding strategy calculation.

[0005] The technical solution of the present invention is as follows: Firstly, a method for maintaining the position of a stationary orbit considering thrust direction and local time constraints, wherein when the longitude deviation exceeds a set limit, a strategy is adopted to simultaneously adjust the longitude, eccentricity, and orbital inclination using one southward ignition and one northward ignition, including three cases: Case 1: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value. There is no local avoidance constraint. In this case, the longitude of the south and north ignition differs by 180 degrees. Solve the preset equation set to obtain the ignition strategy. The ignition pulse includes the ignition longitude, the magnitude of radial thrust, the magnitude of tangential thrust, and the magnitude of normal thrust. Case 2: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is set to find the ignition strategy that satisfies the requirements of drift rate, tilt angle and local time position maintenance and minimizes the velocity pulse. Case 3: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the tangential thrust is zero when igniting on the north side. The local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is used to find an ignition strategy that satisfies the drift rate and tilt angle maintenance while taking into account the eccentricity maintenance as much as possible.

[0006] Furthermore, in the three cases, if the velocity increment on the south side is maintained at ΔV1=[ΔV R1 , ΔV T1 , ΔV N1 The velocity increment on the north side remains ΔV2 = [ΔV] R2 , ΔV T2 , ΔV N2 The constraint determining the ratio of normal thrust to radial thrust is: ΔV R1 = ΔV N1 / C yS , ΔV R2 = ΔV N2 / C yN The zero tangential thrust on the north side is represented by: ΔV T2 =0; where ΔV R1 To maintain the radial component of the ignition pulse in the south-facing position, ΔV R2 To maintain the radial component of the ignition pulse in the northward position, ΔV N1 To maintain the normal component of the ignition pulse in the southward position, V N2 To maintain the normal component of the pulse in the northward position, ΔV T1 To maintain the tangential component of the pulse in the southward position, ΔV T2 To maintain the tangential component of the pulse in the northward position; C yS To maintain the ratio of the normal to radial components of the ignition pulse in a south-facing position, C yN The ratio of the normal component to the radial component of the ignition pulse for the northward position.

[0007] Furthermore, in scenario one, the difference in right ascension between the two north and south positions is 180°; the preset equation set is:

[0008] in, The mean right ascension during a southward pulse. The variables given for the position-maintaining strategy are the change in drift rate, the change in the eccentricity vector projected onto the X-axis of the J2000 inertial frame, the change in the eccentricity vector projected onto the Y-axis of the J2000 inertial frame, the change in the tilt vector projected onto the X-axis of the J2000 inertial frame, and the change in the tilt vector projected onto the Y-axis of the J2000 inertial frame.

[0009] Furthermore, the velocity increments during the two position-holding phases are obtained by solving the preset set of equations. , The analytical expression for the southward ignition at right ascension α is as follows:

[0010] in: , , , The linear velocity of an ideal geostationary satellite, , , , For intermediate parameters, The orbital angular velocity of an ideal geostationary satellite.

[0011] Furthermore, when there are local time avoidance constraints, these constraints are transformed into the range of ignition mean ascension values: Calculate the mean right ascension corresponding to the local time; if the local time cannot be ignited, the range is [t]. l ,t u ],but: λ1= mod(t l – t0,24) ω e 3600+Ω+ω+M λ2= mod(t u - t0,24) ω e 3600+Ω+ω+M λ1= mod(λ1,2π);λ2= mod(λ2,2π) λ l =min(λ1, λ2);λ u =max(λ1, λ2) Where t0 is the current local time, Ω, ω, and M are classical orbital elements, and α s The range of values ​​for the right ascension of ignition; t l The lower limit for areas where ignition is impossible, t u The upper limit is when ignition is not possible, ω e The orbital angular velocity of an ideal geostationary satellite; Determine the range of right ascension for ignition; if |λ1-λ2|>(λ u -λ l ) 15 pi / 180 + 0.1, then the range of values ​​for the ignition right ascension is... = [λ l, λ u If |λ1-λ2| ≤ (λ u -λ l ) 15 pi / 180 + 0.1, the range of values ​​for the ignition mean right ascension. = [0,λ l ]U[λ u ,2π].

[0012] Furthermore, in case two, finding the solution that satisfies the position holding requirement and minimizes the velocity pulse includes: When ΔV R1 = ΔV N1 / CyS, ΔV R2 = ΔV N2 The range of values ​​for / CyN and ignition location time is: At that time, it was set at right ascension. Apply pulse at location In right ascension Apply pulse at location The solution that satisfies the position holding requirement and minimizes the velocity pulse is obtained by solving the following system of equations: .

[0013] Furthermore, in case two, the traversal of mean longitude includes: exist Traversal and Select the ignition strategy with the smallest velocity increment among the solutions of the equation set; for and Given any set of values ​​for , the system of equations is a system of linear equations with 4 independent variables and 5 equations. The first 4 equations in the system are used to solve for the variables. , Substitute the obtained variable values ​​into the last equation; if the last equation is true, then the system of equations has a solution; otherwise, the system of equations has no solution.

[0014] Furthermore, in scenario three, the range of values ​​for the ignition location time is: At that time, Traversing the Red Ascension and right ascension During the process, and Calculate any set of values ​​for . V T1 This makes the change in drift rate a set value. ,calculate and This makes the change in tilt angle equal to the set value. And select one that makes the change in eccentricity as close as possible to The velocity pulse solution is used as the position holding strategy.

[0015] In a second aspect, a computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the method for maintaining the position of a stationary orbit considering thrust direction and local time constraints.

[0016] Thirdly, a stationary orbit position holding device that takes into account thrust direction and local time constraints includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the stationary orbit position holding method that takes into account thrust direction and local time constraints.

[0017] The advantages of this invention compared to the prior art are: (1) This invention analyzes the position holding efficiency based on the characteristics of the normal and radial coupling of the position holding thrust, and transforms the thrust direction constraint into the ratio of the normal and radial velocity pulse components, which simplifies the calculation of the position holding strategy; (2) This invention achieves the simultaneous preservation of north-south and east-west positions by solving equations; (3) This invention realizes a method for solving the position-keeping ignition strategy by setting a longitude traversal algorithm, which uses the longitude and velocity pulse of two ignitions as variables when there is a local time range constraint for ignition; (4) This invention achieves position-keeping pulse calculation under the constraints of zero tangential component of position-keeping velocity pulse ignition local time and zero eccentricity under the premise of maintaining drift rate and tilt angle. Attached Figure Description

[0018] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 Flowchart for solving position-preserving strategies with local time constraints; Figure 2 This is a diagram illustrating the effect of maintaining position without time avoidance. Figure 3 To maintain the ignition mean ascension and local time distribution map when time avoidance is not required; Figure 4A diagram showing the three-axis component variation of the south-side ignition velocity vector when no time avoidance is performed. Figure 5 A diagram showing the three-axis component variation of the north side ignition velocity vector when no time avoidance is performed. Figure 6 A diagram illustrating the effect of maintaining position during a 6-hour avoidance maneuver; Figure 7 Maintain the ignition right ascension and local time distribution map for the location during the 6-hour time avoidance; Figure 8 A graph showing the three-axis component variation of the south side ignition velocity vector during a 6-hour avoidance period. Figure 9 A graph showing the three-axis component variation of the north side ignition velocity vector during a 6-hour avoidance period. Figure 10 Image showing the position retention effect when there is no tangential pulse component on the north side and a 2-hour time avoidance period; Figure 11 For a 2-hour time avoidance, when there is no tangential pulse component on the north side, the location maintains the ignition right ascension and local time distribution map; Figure 12 A diagram showing the three-axis component variation of the ignition velocity vector on the south side when there is no tangential pulse component on the north side and a 2-hour time avoidance period. Figure 13 The diagram shows the variation of the three-axis components of the ignition velocity vector on the north side when there is no tangential pulse component on the north side and the time is 2 hours for avoidance. Detailed Implementation

[0019] To better understand the above technical solutions, the technical solutions of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical solutions of the present invention, rather than limitations thereof. In the absence of conflict, the embodiments of the present invention and the technical features in the embodiments can be combined with each other.

[0020] The following description, in conjunction with the accompanying drawings, provides a more detailed explanation of a method for maintaining the position of a stationary orbit that considers thrust direction and local time constraints, as provided in the embodiments of the present invention. Figure 1 Specific implementation methods may include: when the longitude deviation exceeds the set limit, a strategy of simultaneously adjusting the longitude, eccentricity, and orbital inclination by one southward ignition and one northward ignition is adopted, including three cases: Case 1: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value. There is no local avoidance constraint. In this case, the longitude of the south and north ignition differs by 180 degrees. Solve the preset equation set to obtain the ignition strategy. The ignition pulse includes the ignition longitude, the magnitude of radial thrust, the magnitude of tangential thrust, and the magnitude of normal thrust. Case 2: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is set to find the ignition strategy that satisfies the requirements of drift rate, tilt angle and local time position maintenance and minimizes the velocity pulse. Case 3: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the tangential thrust is zero when igniting on the north side. The local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is used to find an ignition strategy that satisfies the drift rate and tilt angle maintenance while taking into account the eccentricity maintenance as much as possible.

[0021] In the solution provided in this embodiment of the invention, when igniting on the south and north sides, the speed increment on the south side is maintained as ΔV1=[ΔV R1 , ΔV T1 , ΔV N1 The velocity increment on the north side remains ΔV2 = [ΔV] R2 , ΔV T2 , ΔV N2 And the thrust ratio relationship satisfies: ΔV R1 = ΔV N1 / C yS , ΔV R2 = ΔV N2 / C yN .

[0022] The difference in mean right ascension between the two positions, north and south, is 180°. Let the right ascension during the southward pulse be... In relation to the north-south ignition ratio, the position maintains the thrust requirement:

[0023] in The amount of change given for the position preservation strategy, The linear velocity of an ideal stationary orbit. Let be the angular velocity of an ideal stationary orbit. Solving the system of equations yields the velocity increments during the two position-holding phases. , Right Ascension α:

[0024] in: , , The simulation results of a one-year position-holding experiment using this strategy are as follows: Figures 2-5 As shown. Figure 2 The left side shows the longitude-drift rate curve, and the right side shows the latitude and longitude curve. As can be seen from the figure, for an initial orbit that does not meet the requirements for latitude and longitude variation, after two position hold cycles, the latitude and longitude variation can be maintained within 0.1°. Figure 3 The distribution of right ascension shows that the ignition longitude is still concentrated around 90° and 270°, which means that the north-south position remains the most efficient position; the local time distribution map shows angles, and the local time changes by 1 hour for every 15 degrees; Figure 4 and Figure 5 This indicates that the thrust vector satisfies the constraints.

[0025] To achieve time avoidance, the right ascension of the two pulse ignitions needs to be used as an optimization variable. Let the right ascension be... Apply pulse at location In right ascension Apply pulse at location The equation can be obtained as follows:

[0026] Considering , The unknown quantity in the above formula can be considered as , Two ignitions at equal longitude and .

[0027] If the local time [t] l ,t u If ignition is not possible between these points, then the range of ignition longitude values ​​is as follows: The following can be calculated: λ1= mod(t l – t0,24) ω e 3600+Ω+ω+M; λ2= mod(t u - t0,24) ω e 3600+Ω+ω+M; λ1= mod(λ1,2π);λ2= mod(λ2,2π); λ l =min(λ1, λ2);λ u =max(λ1, λ2); If |λ1-λ2|>(λ) u -λ l ) 15 pi / 180 + 0.1, then = [λ l , λ u ];otherwise: = [0,λ l ]U[λ u[,2π]; where t0 is the current local time, Ω, ω, M are classical orbital elements, and α s This represents the range of values ​​for the right ascension of the ignition point.

[0028] The strategy for solving longitude traversal is as follows: Figure 1 As shown. In Traversal and ,for and When the value of is arbitrary, the formula in claim 5 is a system of 5 linear equations with 4 independent variables. Four equations from the system are used to solve for the variables, and the resulting variable values ​​are substituted into the last equation. If the last equation holds true, the system of equations has a solution; otherwise, it has no solution. When the system of equations has a solution, the velocity increment is recorded, and the pulse with the smallest velocity increment is selected as the ignition strategy. When ignition is not allowed between 0:00 and 6:00 a.m., the simulation results for one year are as follows: Figures 6-9 As shown. By Figure 7 It can be seen that the ignition longitude is mostly around 90° and 270°, with a few diverging.

[0029] If fixed V T2 =0, then during the traversal and At that time, and For any set of values, calculate such that The formula is true V T1 , making Established and : And choose to make The solution that best satisfies the requirements is used as the position-preserving strategy.

[0030]

[0031]

[0032] When ignition is not permitted between 4:00 AM and 6:00 AM, and there is no tangential thrust from the north side, the simulation results for one year are as follows: Figures 10-13 As shown. Figure 11 b) No ignition pulse when the included angle is between 60 and 90 degrees. (Comparison) Figure 11 and Figure 7 It can be seen that the absence of tangential thrust on one side has a slightly lower impact on the distribution of ignition longitude than on local time.

[0033] This invention provides a computer-readable storage medium storing computer instructions that, when executed on a computer, cause the computer to perform... Figure 1 The method described.

[0034] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention 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 and optical storage) containing computer-usable program code.

[0035] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. 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 illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0036] 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.

[0037] 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.

[0038] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

[0039] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for maintaining the position of a stationary orbit considering thrust direction and local time constraints, characterized in that, When the longitude deviation exceeds the set limit, a strategy is adopted to simultaneously adjust the longitude, eccentricity, and orbital inclination using one southward ignition and one northward ignition, including three cases: Scenario 1: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and there is no local avoidance constraint. In this case, the longitude of the southward and northward ignition differs by 180 degrees. Solve the preset equation set to obtain the ignition strategy. The ignition pulse includes the ignition longitude, the magnitude of radial thrust, the magnitude of tangential thrust, and the magnitude of normal thrust. Case 2: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is set to find the ignition strategy that satisfies the requirements of drift rate, tilt angle and local time position maintenance and minimizes the velocity pulse. Case 3: The thrust direction constraint is that the ratio of normal thrust to radial thrust is equal to the set value, and the tangential thrust is zero when igniting on the north side. The local time constraint is that ignition will not occur within a preset time before sunrise. In this case, the longitude traversal algorithm is used to find an ignition strategy that satisfies the drift rate and tilt angle maintenance while taking into account the eccentricity maintenance as much as possible.

2. The method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, In the three cases, if the velocity increment on the south side is maintained at ΔV1=[ΔV R1 , ΔV T1 , ΔV N1 The velocity increment on the north side remains ΔV2 = [ΔV] R2 , ΔV T2 , ΔV N2 The constraint determining the ratio of normal thrust to radial thrust is: ΔV R1 = ΔV N1 / C yS , ΔV R2 = ΔV N2 / C yN The zero tangential thrust on the north side is represented by: ΔV T2 =0; where ΔV R1 To maintain the radial component of the ignition pulse in the south-facing position, ΔV R2 To maintain the radial component of the ignition pulse in the northward position, ΔV N1 To maintain the normal component of the ignition pulse in the southward position, V N2 To maintain the normal component of the pulse in the northward position, ΔV T1 To maintain the tangential component of the pulse in the southward position, ΔV T2 To maintain the tangential component of the pulse in the northward position; C yS To maintain the ratio of the normal to radial components of the ignition pulse in a south-facing position, C yN The ratio of the normal component to the radial component of the ignition pulse for the northward position.

3. The method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, In scenario one, the difference in right ascension between the two north and south positions is 180°; the preset equation set is: in, The mean right ascension during a southward pulse. The variables given for the position-maintaining strategy are the change in drift rate, the change in the eccentricity vector projected onto the X-axis of the J2000 inertial frame, the change in the eccentricity vector projected onto the Y-axis of the J2000 inertial frame, the change in the tilt vector projected onto the X-axis of the J2000 inertial frame, and the change in the tilt vector projected onto the Y-axis of the J2000 inertial frame.

4. The method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, The velocity increments during the two position maintenance cycles are obtained by solving the preset equations. , The analytical expression for the southward ignition at right ascension α is as follows: in: , , , The linear velocity of an ideal geostationary satellite, , , , For intermediate parameters, The orbital angular velocity of an ideal geostationary satellite.

5. A method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, When there are local time avoidance constraints, these constraints are converted into the range of ignition mean ascension values: Calculate the mean right ascension corresponding to the local time; if the local time cannot be ignited, the range is [t]. l ,t u ],but: λ1= mod(t l – t0.24) oh e 3600+Ω+ω+M λ2= mod(t u - t0.24) oh e 3600+Ω+ω+M λ1= mod(λ1,2π);λ2= mod(λ2,2π) l l =min(λ1, λ2);λ u =max(λ1, λ2) Where t0 is the current local time, Ω, ω, and M are classical orbital elements, and α s The range of values ​​for the right ascension of ignition; t l The lower limit for areas where ignition is impossible, t u The upper limit is when ignition is not possible, ω e The orbital angular velocity of an ideal geostationary satellite; Determine the range of right ascension for ignition; if |λ1-λ2|>(λ u -λ l ) 15 pi / 180 + 0.1, then the range of values ​​for the ignition right ascension is... = [λ l , λ u If |λ1-λ2| ≤ (λ u -λ l ) 15 pi / 180 + 0.1, the range of values ​​for the ignition mean right ascension. = [0,λ l ]U[λ u ,2π].

6. A method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, In case two, finding the solution that satisfies the position holding requirement and minimizes the velocity pulse includes: When ΔV R1 = ΔV N1 / CyS, ΔV R2 = ΔV N2 The range of values ​​for / CyN and ignition local time is: At that time, it was set at right ascension. Apply pulse at location In right ascension Apply pulse at location The solution that satisfies the position holding requirement and minimizes the velocity pulse is obtained by solving the following system of equations: 。 7. A method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, In scenario two, the longitude traversal includes: exist Traversal and Select the ignition strategy with the smallest velocity increment among the solutions of the equation set; for and Given any set of values ​​for , the system of equations is a system of linear equations with 4 independent variables and 5 equations. The first 4 equations in the system are used to solve for the variables. , Substitute the obtained variable values ​​into the last equation; if the last equation is true, then the system of equations has a solution; otherwise, the system of equations has no solution.

8. A method for maintaining the position of a stationary orbit considering thrust direction and local time constraints according to claim 1, characterized in that, In scenario three, the range of the ignition location time is: At that time, Traversing the Red Ascension and right ascension During the process, and Calculate any set of values ​​for . V T1 This makes the change in drift rate a set value. ,calculate and This makes the change in tilt angle equal to the set value. And select one that makes the change in eccentricity as close as possible to The velocity pulse solution is used as the position holding strategy.

9. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method as described in any one of claims 1 to 8.

10. A stationary orbital position holding device considering thrust direction and local time constraints, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, it implements the steps of the method as described in any one of claims 1 to 8.

Images