Orbit raising control method, system, device and medium applicable to low-earth orbit satellites

Abstract

The present invention discloses an orbit elevation control method, system, device and medium applicable to low-earth orbit satellites, relating to the technical field of satellite orbit transfer control. The method includes: formulating an orbit transfer control principle and a debris avoidance strategy for the low-earth orbit satellite to transfer from the current orbit to a preset orbit; determining a orbit transfer control strategy based on the orbit transfer control principle and the debris avoidance strategy; and using the orbit transfer control strategy to control the low-earth orbit satellite to transfer from the current orbit to the preset orbit. In the present invention, an orbit transfer control strategy is determined based on the orbit transfer control principle and the debris avoidance strategy, and then the orbit transfer control of the low-earth orbit satellite, such as orbit elevation control, etc., is carried out according to the orbit transfer control strategy. The engineering implementation has strong operability and is applicable to the large-scale deployment of low-earth orbit satellites such as low-earth orbit communication satellites, making the large-scale deployment of low-earth orbit satellites more convenient and fast.

Description

Background Art

[0002] All long - life satellites need to perform orbit adjustments. For example, the orbit adjustments of low - earth - orbit communication satellites include initial orbit capture, orbit maintenance during long - term operation, and large - amplitude orbit maneuvers as needed. Initial orbit capture, that is, initial orbit error correction, aims to correct the initial orbit of the satellite provided by the launch vehicle to an orbit within the allowable error range of the design. "Orbit maintenance during long - term operation" is to eliminate the influence of various perturbation factors, especially atmospheric drag, etc. on the satellite orbit to maintain the required operating trajectory of the satellite.

[0003] In recent years, providing broadband access services globally using large low - earth - orbit constellations has received extensive attention. Considering the launch capacity and the need to establish the on - orbit constellation configuration, low - earth - orbit constellation communication satellites often use launch vehicles to send them into a parking orbit. After stabilizing in the parking orbit, they perform orbit transfer according to the requirements of constellation establishment and transfer to the nominal orbit.

[0004] Satellite propulsion systems can be divided into cold - gas propulsion systems, chemical propulsion systems, electric propulsion systems, nuclear propulsion systems, etc. according to different types of propellants. Space test missions of electric propulsion systems began in the 1960s. Since then, electric propulsion systems have mostly been used for satellite on - orbit position keeping and some small - range orbit elevation tasks. In the establishment of low - earth - orbit communication constellations, there is little research and engineering implementation on using only electric propulsion systems to change orbits into the working orbit after the separation of the satellite and the launch vehicle. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method, system, device, and medium for orbit elevation control applicable to low - earth - orbit satellites in view of the deficiencies of the prior art, specifically as follows:

[0006] 1) In the first aspect, the present invention provides a method for orbit elevation control applicable to low - earth - orbit satellites, and the specific technical solution is as follows:

[0007] Formulate the orbit transfer control principle and debris avoidance strategy for the low - earth - orbit satellite to change its orbit from the current orbit to the preset orbit;

[0008] Based on the orbit transfer control principle and debris avoidance strategy, determine the orbit - changing control strategy;

[0009] Use the orbit - changing control strategy to control the low - earth - orbit satellite to change its orbit from the current orbit to the preset orbit.

[0010] The beneficial effects of the method for orbit elevation control applicable to low - earth - orbit satellites provided by the present invention are as follows:

[0011] Based on the orbit transfer control principle and debris avoidance strategy, determine the orbit transfer control strategy, and then perform orbit transfer control of the low-Earth orbit satellite according to the orbit transfer control strategy, such as orbit raising control, etc. The engineering implementation has strong operability and is applicable to the large-scale deployment of low-Earth orbit satellites such as low-Earth orbit communication satellites, making the large-scale deployment of low-Earth orbit satellites more convenient and fast.

[0012] Furthermore, it also includes: determining the budget mass of the propellant used for the low-Earth orbit satellite to transfer from the current orbit to the preset orbit.

[0013] Furthermore, the process of determining the budget mass of the propellant includes:

[0014] Using the propellant mass calculation formula, calculate the budget mass M of the propellant T , and the propellant mass calculation formula is: where M G represents the dry weight of the low-Earth orbit satellite, ΔV represents the velocity increment of the low-Earth orbit satellite from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

[0015] Furthermore, the process of obtaining the velocity increment ΔV of the low-Earth orbit satellite from the current orbit to the preset orbit includes:

[0016] Adopt the Hohmann transfer orbit for equivalent estimation to obtain the velocity increment ΔV of the low-Earth orbit satellite from the current orbit to the preset orbit.

[0017] Furthermore, it also includes: determining the energy budget of the low-Earth orbit satellite from the current orbit to the preset orbit.

[0018] Furthermore, it also includes: comparing the orbit control result obtained by controlling using the orbit transfer control strategy with the preset orbit to obtain the deviation.

[0019] Furthermore, the low-Earth orbit satellite is a low-Earth orbit communication satellite.

[0020] 2) In the second aspect, the present invention also provides an orbit raising control system applicable to low-Earth orbit satellites, and the specific technical solution is as follows:

[0021] It includes a principle strategy formulation module, an orbit transfer control strategy determination module, and an orbit transfer control module;

[0022] The principle strategy formulation module is used for: formulating the orbit transfer control principle and debris avoidance strategy for the low-Earth orbit satellite to transfer from the current orbit to the preset orbit;

[0023] The orbit transfer control strategy determination module is used for: determining the orbit transfer control strategy based on the orbit transfer control principle and debris avoidance strategy;

[0024] The orbit transfer control module is used to: control the low-earth orbit satellite to transfer from the current orbit to a preset orbit by using the orbit transfer control strategy.

[0025] On the basis of the above solution, an orbit elevation control system for low-earth orbit satellites according to the present invention can also be improved as follows.

[0026] Furthermore, it further includes a budget mass determination module, which is used to: determine the budget mass of the propellant used for the low-earth orbit satellite to transfer from the current orbit to the preset orbit.

[0027] Furthermore, the budget mass determination module is specifically used to: use the propellant mass calculation formula M T , and calculate the budget mass of the propellant. The propellant mass calculation formula is: where M G represents the dry weight of the low-earth orbit satellite, ΔV represents the velocity increment of the low-earth orbit satellite from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

[0028] Furthermore, it further includes a velocity increment calculation module, which is used to: perform an equivalent estimation using the Hohmann transfer orbit to obtain the velocity increment ΔV of the low-earth orbit satellite from the current orbit to the preset orbit.

[0029] Furthermore, it further includes an energy budget determination module, which is used to: determine the energy budget of the low-earth orbit satellite from the current orbit to the preset orbit.

[0030] Furthermore, it further includes a comparison module, which is used to: compare the orbit control result obtained by controlling using the orbit transfer control strategy with the preset orbit to obtain a deviation.

[0031] Furthermore, the low-earth orbit satellite is a low-earth orbit communication satellite.

[0032] 3) In the third aspect, the present invention also provides a computer device, which includes a processor. The processor is coupled to a memory, and at least one computer program is stored in the memory. The at least one computer program is loaded and executed by the processor so that the computer device can implement any one of the above-mentioned orbit elevation control methods for low-earth orbit satellites.

[0033] 4) In the fourth aspect, the present invention also provides a computer-readable storage medium, in which at least one computer program is stored. The at least one computer program is loaded and executed by the processor so that the computer can implement any one of the above-mentioned orbit elevation control methods for low-earth orbit satellites.

[0034] It should be noted that for the beneficial effects achieved by the technical solutions and corresponding possible implementation manners of the second to fourth aspects of the present invention, reference may be made to the technical effects of the first aspect and its corresponding possible implementation manners described above, which will not be elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments when read in conjunction with the accompanying drawings:

[0036] Figure 1 Schematic flowchart of an orbit-raising control method for a low-earth orbit satellite according to an embodiment of the present invention;

[0037] Figure 2 Schematic diagram of a Hohmann transfer;

[0038] Figure 3 Schematic diagram of a satellite orbit control ignition strategy;

[0039] Figure 4 Schematic diagram of ignition in the shadow area and ignition in the sunlit area;

[0040] Figure 5 Schematic diagram of the structure of an orbit-raising control system for a low-earth orbit satellite according to an embodiment of the present invention;

[0041] Figure 6 Schematic diagram of the structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0042] To make the objectives, technical solutions, and advantages of the present invention clearer, the following will further describe the embodiments of the present invention in detail with reference to the accompanying drawings.

[0043] As Figure 1 shown, an orbit-raising control method for a low-earth orbit satellite according to an embodiment of the present invention includes the following steps:

[0044] S1. Formulate an orbit transfer control principle and a debris avoidance strategy for the low-earth orbit satellite to transfer from the current orbit to a preset orbit.

[0045] Among them, the orbit transfer control principle includes:

[0046] 1) The electric propulsion of the low-earth orbit satellite can enter the normal orbit control mode only after experiencing PPCU exhaust, exhaust pretreatment, two cathode pretreatments, and anode low-power ignition in sequence.

[0047] 2) The satellite orbit control work should be carried out when the states of each subsystem of the low-earth orbit satellite are stable and the energy state is good.

[0048] 3) The startup of each stage of the electric propulsion preprocessing for the low-earth orbit satellite and the first orbit transfer operation of the thruster shall be arranged within the measurement and control range of domestic ground measurement and control stations;

[0049] 4) Under the condition that the thruster works stably and the overall satellite status is good and normal in the early stage, the orbit control with the thruster firing overseas can be carried out to complete the orbit control work smoothly and in a timely manner;

[0050] 5) The on-board program control instruction capacity of the low-earth orbit satellite shall be no less than 1000, and the low-earth orbit satellite has the ability to upload programmed orbit control data blocks, supporting the simultaneous upload of multiple orbit data blocks to reduce the ground measurement and control support during orbit control;

[0051] 6) The arrangement of orbit control measurement and control passes needs to comprehensively consider factors such as orbit control requirements and the actual on-orbit status of the low-earth orbit satellite;

[0052] 7) The ignition start time interval between two adjacent passes shall be no less than 90 minutes;

[0053] 8) No payload service tasks shall be carried out within the orbit transfer pass.

[0054] Among them, the debris avoidance strategy includes:

[0055] 1) Determination of the safety distance. The relative safety distance between the satellite and the debris is 10 km;

[0056] 2) After a collision is predicted, at least half an orbital period in advance (delay) perform an avoidance action at the perigee (apogee), the electric propulsion system fires, raising (lowering) the semi-major axis of the flight orbit of the low-earth orbit satellite, so that the minimum relative distance when the low-earth orbit satellite approaches the obstacle is greater than the safety distance, thus preventing the collision from occurring.

[0057] Based on the debris avoidance strategy, conduct in-orbit operation collision warning, collision avoidance effect evaluation, and end-of-mission deorbiting evaluation for the low-earth orbit satellite.

[0058] S2. Based on the orbit transfer control principle and the debris avoidance strategy, determine the orbit transfer control strategy;

[0059] Among them, the debris avoidance strategy is:

[0060] After a collision is predicted, at least half an orbital period in advance (delay) perform an avoidance action at the perigee (apogee), the electric propulsion system fires, raising (lowering) the semi-major axis of the flight orbit of the low-earth orbit satellite, so that the minimum relative distance when the low-earth orbit satellite approaches the obstacle is greater than the safety distance. After the debris avoidance is completed, perform an orbit maneuver at the apogee (perigee), the electric propulsion system fires, lowering (raising) the semi-major axis of the flight orbit of the low-earth orbit satellite, so that the low-earth orbit satellite returns to the operating orbit before the debris avoidance.

[0061] Among them, the orbit transfer control strategy includes:

[0062] As Figure 3 and Figure 4 shown, ignition occurs in the sunny area in a certain orbit, and all subsequent N orbits are ignited in the sunny area. After N ignitions, it transfers to the shadow area for N ignitions after going through one or more complete sunny areas, and then transfers to the sunny area for N ignitions after going through one or more complete sunny areas again. That is, the first N orbits are ignited in the sunny area, the second N orbits are ignited in the shadow area, the third N orbits are ignited in the sunny area, and so on.

[0063] S3. Using the orbit transfer control strategy, control the low-orbit satellite to transfer from the current orbit to the preset orbit.

[0064] In the orbit-raising control method for low-orbit satellites according to the embodiments of the present invention, based on the orbit transfer control principle and the debris avoidance strategy, the orbit transfer control strategy is determined, and then the orbit transfer control of the low-orbit satellite is carried out according to the orbit transfer control strategy, such as orbit-raising control, etc. The engineering implementation is highly operable and applicable to the large-scale deployment of low-orbit satellites such as low-orbit communication satellites, making the large-scale deployment of low-orbit satellites more convenient and fast.

[0065] Optionally, in the above technical solution, it further includes:

[0066] Determine the budget mass of the propellant used for the low-orbit satellite to transfer from the current orbit to the preset orbit. When designing the satellite, fill the propellant tank with fuel greater than the budget mass, that is, the propellant.

[0067] Optionally, in the above technical solution, the determination process of the budget mass of the propellant includes:

[0068] Use the propellant mass calculation formula to calculate the budget mass M T , and the propellant mass calculation formula is: Among them, M G represents the dry weight of the low-orbit satellite, ΔV represents the velocity increment of the low-orbit satellite transferring from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

[0069] Optionally, in the above technical solution, the process of obtaining the velocity increment ΔV of the low-orbit satellite transferring from the current orbit to the preset orbit includes:

[0070] As Figure 2 shown in the Hohmann transfer schematic diagram, orbit A is the initial orbit of the satellite, that is, the current orbit, and orbit B is the target orbit of the satellite, that is, the preset orbit. Denote v A and v B as the velocity magnitudes required for the satellite to orbit along circles with radii of r A and r B respectively, and their values are: where μ = 3.9860044118×10 5 km 3 / s 2 , which is the geocentric gravitational constant. The calculation methods of v1 and v2 are as follows: From this, the two velocity increments of the satellite during the Hohmann transfer process can be obtained as: Δv1 = v1 - v A , Δv2 = v B - v2. Therefore, the total velocity increment required for the satellite to maneuver from the initial orbit to the target orbit is: ΔV = Δv1 + Δv2.

[0071] Optionally, in the above technical solution, it further includes: determining the energy budget for the low-orbit satellite to change its orbit from the current orbit to the preset orbit. During the orbit control process, it is necessary to follow the satellite energy to achieve balance within the same circle.

[0072] Among them, the energy budget refers to: the power consumption, i.e., the power consumption, of the low-orbit satellite during the process of changing its orbit from the current orbit to the preset orbit, with the unit of W, specifically including: the power consumption of the electric propulsion, the power consumption of the flywheel, the power consumption of the communication payload, the power generation of the solar cell, etc.

[0073] Among them, the balance within the same circle means: the power consumption of the low-orbit satellite within the same circle is not greater than the power generation of the solar cell.

[0074] Optionally, in the above technical solution, it further includes: comparing the orbit control result obtained by using the orbit change control strategy with the preset orbit to obtain a deviation.

[0075] Optionally, in the above technical solution, the low-orbit satellite is a low-orbit communication satellite.

[0076] In another embodiment, it includes:

[0077] S11. Orbit transfer propellant budget:

[0078] The velocity increment ΔV required for the satellite transfer orbit can be equivalently estimated using the Hohmann transfer orbit. Figure 2 The figure shows a schematic diagram of the Hohmann transfer. Orbit A is the initial orbit of the satellite, i.e., the current orbit, and orbit B is the target orbit of the satellite, i.e., the preset orbit. Denote v A and v B as the magnitudes of the velocities required for the satellite to orbit along circles with radii of r A and r B respectively, and their values are: where μ = 3.9860044118×10 5 km 3 / s 2 , which is the geocentric gravitational constant. The calculation methods of v1 and v2 are as follows: Thus, the two velocity increments of the satellite during the Hohmann transfer are: Δv1 = v1 - v A , Δv2 = v B - v2. Therefore, the total velocity increment required for the satellite to maneuver from the initial orbit to the target orbit is: ΔV = Δv1 + Δv2.

[0079] Calculate the budget mass M of the propellant T , where M G is the dry mass of the satellite, I is the specific impulse of the propellant, and g is the acceleration due to gravity.

[0080] S12. Formulate the orbit transfer control principle:

[0081] After completing the above propellant budget, further clarify the orbit transfer control principle, which specifically includes:

[0082] 1) The satellite's electric propulsion must go through PPCU exhaust, exhaust pretreatment, pretreatment of two cathodes, and anode low-power ignition before it can enter the normal orbit control mode;

[0083] 2) The satellite orbit control work should be carried out when the states of each subsystem are stable and the energy state is good;

[0084] 3) The start of each stage of the satellite's electric propulsion pretreatment and the first orbit change action of the thruster should be arranged within the measurement and control range of the domestic ground measurement and control station;

[0085] 4) Under the condition that the thruster works stably and the overall satellite state is good and normal in the early stage, the orbit control of the thruster ignition outside the country can be carried out to complete the orbit control work smoothly and in a timely manner;

[0086] 5) The on-board program control instruction capacity is not less than 1000, and the satellite has the ability to upload programmed orbit control data blocks, supporting the simultaneous upload of multiple orbit data blocks to reduce the ground measurement and control support during orbit control;

[0087] 6) The arrangement of orbit control measurement and control passes needs to comprehensively consider factors such as orbit control requirements and the actual on-orbit state of the satellite;

[0088] 7) The start ignition time interval between two adjacent passes is not less than 90 minutes;

[0089] 8) No payload service tasks are carried out within the orbit change pass.

[0090] S13. Energy budget during orbit control, specifically:

[0091] 1) During orbit control, it is necessary to follow the principle that the satellite energy achieves balance within the same pass.

[0092] 2) Change the working time of the electric propulsion in real time according to the actual duration of the umbra and the change of the angle between the sailboard and the sunlight. It is required that the control energy margin is greater than 1.0 and the depth of discharge is less than 35%.

[0093] S14. Develop a debris avoidance strategy during the orbit transfer process:

[0094] Implement in-orbit operation collision warning and collision avoidance effect evaluation. For the possible collision warning and avoidance during orbit control, the detection and identification center conducts collision warning analysis. According to the warning result, select an appropriate control time to avoid collision.

[0095] S15. Determine the orbit transfer control strategy:

[0096] Figure 3 The following shows the schematic diagram of the satellite orbit control ignition strategy of the present invention. Figure 4 The following shows the schematic diagram of ignition in the umbra area and ignition in the sunlit area of the present invention. According to the on-board energy and thruster performance conditions, the satellite thruster can work continuously for N orbits per day, and the ignition duration for each orbit is Tmin. After the thruster ignites, it needs to go through a complete sunlit arc segment to complete the charging of the battery pack before the next ignition can be carried out. Therefore, the orbit control thruster ignition strategy in continuous multi-orbit orbit transfer is: Ignite in the sunlit area in a certain circle, and then all the subsequent N orbits are ignited in the sunlit area. After igniting N times, ignite in the umbra area after 2.5 orbits of transfer, that is, N orbits are ignited in the sunlit area on the first day, and N orbits are ignited in the umbra area on the second day (one control per orbit).

[0097] S16. Determine the deviation:

[0098] After the daily orbit transfer control is completed, evaluate the orbit control effect. Compare the designed orbit control result with the actual orbit parameters after control, and use the comparison error size to evaluate the result, which will guide the design of the next orbit control injection parameters.

[0099] In the above embodiments, although the steps are numbered S1, S2, etc., they are only specific embodiments given by the present invention. Those skilled in the art can adjust the execution order of S1, S2, etc. according to the actual situation, which is also within the protection scope of the present invention. It can be understood that in some embodiments, it may include some or all of the above embodiments.

[0100] Such as Figure 5 As shown in the figure, an orbit raising control system 200 for a low-earth orbit satellite according to an embodiment of the present invention includes a principle strategy formulation module 201, an orbit transfer control strategy determination module 202, and an orbit transfer control module 203;

[0101] The principle strategy formulation module 201 is used for: formulating the orbit transfer control principle and debris avoidance strategy for the low-earth orbit satellite to transfer from the current orbit to the preset orbit;

[0102] The orbit transfer control strategy determination module 202 is configured to: determine an orbit transfer control strategy based on the orbit transfer control principle and the debris avoidance strategy;

[0103] The orbit transfer control module 203 is configured to: use the orbit transfer control strategy to control the low-earth orbit satellite to transfer from the current orbit to a preset orbit.

[0104] Optionally, in the above technical solution, it further includes a budget mass determination module, and the budget mass determination module is configured to: determine the budget mass of the propellant used for the low-earth orbit satellite to transfer from the current orbit to the preset orbit.

[0105] Optionally, in the above technical solution, the budget mass determination module is specifically configured to: use the propellant mass calculation formula to calculate the budget mass M of the propellant T , and the propellant mass calculation formula is: where M G represents the dry weight of the low-earth orbit satellite, ΔV represents the velocity increment of the low-earth orbit satellite transferring from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

[0106] Optionally, in the above technical solution, it further includes a velocity increment calculation module, and the velocity increment calculation module is configured to: perform an equivalent estimation using the Hohmann transfer orbit to obtain the velocity increment ΔV of the low-earth orbit satellite transferring from the current orbit to the preset orbit.

[0107] Optionally, in the above technical solution, it further includes an energy budget determination module, and the energy budget determination module is configured to: determine the energy budget of the low-earth orbit satellite transferring from the current orbit to the preset orbit.

[0108] Optionally, in the above technical solution, it further includes a comparison module, and the comparison module is configured to: compare the orbit control result obtained by controlling using the orbit transfer control strategy with the preset orbit to obtain a deviation.

[0109] Optionally, in the above technical solution, the low-earth orbit satellite is a low-earth orbit communication satellite.

[0110] It should be noted that the beneficial effects of the above-described orbit elevation control system 200 applicable to low-earth orbit satellites are the same as those of the above-described orbit elevation control method applicable to low-earth orbit satellites, and will not be elaborated here. In addition, when the above-described system implements its functions, only the above-described functional module division is used as an example for illustration. In practical applications, the above functions can be allocated to different functional modules according to needs, that is, the system can be divided into different functional modules according to the actual situation to complete all or part of the functions described above. In addition, the above-described system and method embodiments belong to the same concept, and the specific implementation process can be found in the method embodiment and will not be elaborated here.

[0111] As Figure 6 shown, a computer device 300 according to an embodiment of the present invention includes a processor 320. The processor 320 is coupled to a memory 310. At least one computer program 330 is stored in the memory 310. The at least one computer program 330 is loaded and executed by the processor 320 so that the computer device 300 implements any one of the above-mentioned orbit-raising control methods applicable to low-earth orbit satellites. Specifically:

[0112] The computer device 300 may vary greatly due to configuration or performance differences. It may include one or more processors 320 (Central Processing Units, CPUs) and one or more memories 310. Among them, at least one computer program 330 is stored in the one or more memories 310. The at least one computer program 330 is loaded and executed by the one or more processors 320 so that the computer device 300 implements any one of the orbit-raising control methods applicable to low-earth orbit satellites provided in the above embodiments. Of course, the computer device 300 may also have components such as a wired or wireless network interface, a keyboard, and an input / output interface for input / output. The computer device 300 may also include other components for implementing device functions, which will not be elaborated here.

[0113] A computer-readable storage medium according to an embodiment of the present invention stores at least one computer program. The at least one computer program is loaded and executed by a processor so that the computer implements any one of the above-mentioned orbit-raising control methods applicable to low-earth orbit satellites.

[0114] Optionally, the computer-readable storage medium may be a read-only memory (ROM), a random access memory (RAM), a compact disc read-only memory (CD-ROM), a magnetic tape, a floppy disk, an optical data storage device, etc.

[0115] In an exemplary embodiment, a computer program product or a computer program is also provided. The computer program product or the computer program includes computer instructions. The computer instructions are stored in a computer-readable storage medium. The processor of the computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions so that the computer device executes any one of the above-mentioned orbit-raising control methods applicable to low-earth orbit satellites.

[0116] It should be noted that the terms "first", "second", etc. in the description and claims of this application are used to distinguish similar objects, rather than to limit a specific order or sequence. In appropriate cases, the order of use of similar objects can be interchanged so that the embodiments of this application described herein can be implemented in an order other than the illustrated or described order.

[0117] Those skilled in the art know that the present invention can be implemented as a system, a method, or a computer program product. Therefore, the present invention can be specifically implemented in the following forms, that is: it can be all hardware, can also be all software (including firmware, resident software, microcode, etc.), and can also be a combination of hardware and software, which is generally referred to as "circuit", "module" or "system" in this article. In addition, in some embodiments, the present invention can also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable media contains computer-readable program code.

[0118] Any combination of one or more computer-readable media can be adopted. The computer-readable media can be a computer-readable signal medium or a computer-readable storage medium. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or component, or any combination of the above. More specific examples (non-exhaustive list) of the computer-readable storage medium include: an electrical connection having one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present invention, the computer-readable storage medium can be any tangible medium that contains or stores a program, and this program can be used by or in combination with an instruction execution system, device, or component.

[0119] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. An orbit raising control method applicable to low Earth orbit satellites, characterized in that, Including: Formulating the orbit transfer control principle and debris avoidance strategy for the low-earth orbit satellite to transfer from the current orbit to the preset orbit; Determining the orbit transfer control strategy based on the orbit transfer control principle and the debris avoidance strategy; Using the orbit transfer control strategy to control the low-earth orbit satellite to transfer from the current orbit to the preset orbit; Wherein, the orbit transfer control strategy is: Igniting in the sunlit area of any orbit, and then igniting in the sunlit area for all subsequent N orbits. After igniting N times, transferring to the shaded area to ignite N times after experiencing one or more complete sunlit areas, and then transferring to the sunlit area to ignite N times after experiencing one or more complete sunlit areas; It also includes: Determining the budget mass of the propellant used for the low-earth orbit satellite to transfer from the current orbit to the preset orbit; The process of determining the budget mass of the propellant includes: Using the propellant mass calculation formula, the budget mass M of the propellant is calculated T , and the propellant mass calculation formula is as follows: where M G represents the dry weight of the low-earth orbit satellite, ΔV represents the velocity increment of the low-earth orbit satellite from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

2. The orbit elevation control method for low-earth orbit satellites according to claim 1, characterized in that The process of obtaining the velocity increment ΔV of the low-earth orbit satellite transferring from the current orbit to the preset orbit includes: Using the Hohmann transfer orbit for equivalent estimation to obtain the velocity increment ΔV of the low-earth orbit satellite transferring from the current orbit to the preset orbit.

3. A method for orbit raising control applicable to low-earth orbit satellites according to claim 1, characterized in that, It also includes: Determining the energy budget for the low-earth orbit satellite to transfer from the current orbit to the preset orbit.

4. A method for orbit raising control applicable to low-earth orbit satellites according to any one of claims 1 to 3, characterized in that, It also includes: Comparing the orbit control result obtained by controlling using the orbit transfer control strategy with the preset orbit to obtain the deviation.

5. A method for orbit raising control applicable to low-earth orbit satellites according to any one of claims 1 to 3, characterized in that, The low-earth orbit satellite is a low-earth orbit communication satellite.

6. An orbit raising control system applicable to low-earth orbit satellites, characterized in that, Including a principle and strategy formulation module, an orbit transfer control strategy determination module, and an orbit transfer control module; The principle and strategy formulation module is used to: Formulate the orbit transfer control principle and debris avoidance strategy for the low-earth orbit satellite to transfer from the current orbit to the preset orbit; The orbit transfer control strategy determination module is used to: Determine the orbit transfer control strategy based on the orbit transfer control principle and the debris avoidance strategy; The orbit transfer control module is used to: Use the orbit transfer control strategy to control the low-earth orbit satellite to transfer from the current orbit to the preset orbit; Wherein, the orbit transfer control strategy is: Igniting in the sunlit area of any orbit, and then igniting in the sunlit area for all subsequent N orbits. After igniting N times, transferring to the shaded area to ignite N times after experiencing one or more complete sunlit areas, and then transferring to the sunlit area to ignite N times after experiencing one or more complete sunlit areas; It also includes a budget mass determination module, and the budget mass determination module is used to: Determine the budget mass of the propellant used for the low-earth orbit satellite to transfer from the current orbit to the preset orbit; The budget quality determination module is specifically configured to: use the propellant mass calculation formula M T , calculate the budget mass of the propellant, and the propellant mass calculation formula is: where M G represents the dry weight of the low-earth orbit satellite, ΔV represents the velocity increment of the low-earth orbit satellite from the current orbit to the preset orbit, I represents the specific impulse of the propellant, and g represents the acceleration due to gravity.

7. A computer device, characterized in that, The computer device includes a processor, the processor is coupled with a memory, and at least one computer program is stored in the memory. The at least one computer program is loaded and executed by the processor so that the computer device implements an orbit elevation control method for a low-earth orbit satellite as described in any one of claims 1 to 5.

8. A computer-readable storage medium, characterized in that, At least one computer program is stored in the computer-readable storage medium, and the at least one computer program is loaded and executed by a processor so that a computer implements an orbit elevation control method for a low-earth orbit satellite as described in any one of claims 1 to 5.

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