Satellite automatic orbit transfer method and device based on chemical propulsion system

Abstract

The application relates to a satellite automatic orbit transfer method and device based on a chemical propulsion system. The method comprises the following steps: acquiring a current firing thruster working condition of a satellite; determining an automatic orbit transfer parameter of the satellite according to the firing thruster working condition; wherein the automatic orbit transfer parameter comprises a firing time, a firing time length, a firing attitude and a firing thruster target working condition; before the firing time, sequentially performing automatic attitude adjustment, thruster opening and bottoming operation according to the firing attitude and the firing thruster target working condition; when the firing time is reached, firing the thruster to automatically transfer the orbit of the satellite; after the firing time length is reached, performing a shutdown operation according to the firing thruster target working condition; and after the firing is completed, the satellite is automatically adjusted again to complete the automatic orbit transfer. According to the scheme, the satellite can independently transfer the orbit according to the automatic orbit transfer parameter in a non-measurement and control arc segment, and the pressure of ground measurement and control is reduced.

Description

Technical Field

[0001] The embodiments of the present invention relate to the field of satellite engineering technology, and in particular to a method and apparatus for automatic orbit change of a satellite based on a chemical propulsion system. Background Technology

[0002] In related technologies, when a high-orbit satellite undergoes orbit change, it is usually operated remotely from the ground step by step. During the entire orbit change process, several commands need to be sent, and the ground telemetry and control system needs to be visible in real time. Therefore, it places high demands on the ground telemetry and control system.

[0003] Furthermore, during the satellite's orbit change process, if the rocket's launch altitude is insufficient or the engine malfunctions, the satellite may use thrusters to change orbit multiple times. In such cases, the ground control system will be unable to track the orbit change process in real time.

[0004] Therefore, based on the above problems, there is an urgent need for a method and device for automatic satellite orbit change based on a chemical propulsion system. Summary of the Invention

[0005] To address the issues of long ground-based telemetry and control time and poor controllability in traditional satellite orbit change methods, this invention provides a satellite automatic orbit change method and apparatus based on a chemical propulsion system.

[0006] In a first aspect, embodiments of the present invention provide a method for automatic orbit change of a satellite based on a chemical propulsion system, comprising:

[0007] Obtain the current ignition thruster status of the satellite;

[0008] Based on the operating conditions of the ignition thruster, the automatic orbit change parameters of the satellite are determined; wherein, the automatic orbit change parameters include ignition time, ignition duration, ignition attitude, and target operating conditions of the ignition thruster;

[0009] Before the ignition moment, automatic attitude adjustment, thruster activation and bottoming-out operations are performed sequentially according to the ignition attitude and the target operating condition of the ignition thruster.

[0010] When the ignition time is reached, the thruster is ignited to enable the satellite to automatically change its orbit;

[0011] After the ignition duration is reached, a shutdown operation is performed according to the target operating condition of the ignition thruster.

[0012] After ignition, the satellite automatically adjusts its attitude again to complete the automatic orbit change.

[0013] Secondly, embodiments of the present invention also provide a satellite automatic orbit change device based on a chemical propulsion system, the device comprising:

[0014] The acquisition unit is used to acquire the operating conditions of the satellite's ignition thrusters;

[0015] The determining unit is used to determine the automatic orbit change parameters of the satellite based on the operating conditions of the ignition thruster; wherein the automatic orbit change parameters include ignition time, ignition duration, ignition attitude, and target operating conditions of the ignition thruster.

[0016] The first execution unit is used to perform automatic attitude adjustment, thruster activation and bottoming-out operations sequentially according to the ignition attitude and the target operating condition of the ignition thruster before the ignition time.

[0017] The second execution unit is used to ignite the thruster to enable the satellite to automatically change its orbit when the ignition time is reached.

[0018] The third execution unit is used to perform a shutdown operation according to the target operating condition of the ignition thruster after the ignition duration is reached.

[0019] The fourth execution unit is used to automatically adjust the satellite's attitude again after ignition to complete the automatic orbit change.

[0020] Thirdly, embodiments of the present invention also provide a computing device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, it implements the method described in any embodiment of this specification.

[0021] Fourthly, embodiments of the present invention also provide a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the methods described in any embodiment of this specification.

[0022] This invention provides a method and apparatus for automatic orbit change of a satellite based on a chemical propulsion system. First, based on the satellite's current ignition thruster operating conditions, parameters such as ignition time, ignition duration, ignition attitude, and target thruster operating conditions are determined during the automatic orbit change process. Then, before the ignition time, automatic attitude adjustment, thruster activation, and bottoming operations are performed according to the determined automatic orbit change parameters. Upon reaching the ignition time, the thrusters are ignited according to the target thruster operating conditions to enable the satellite to automatically change its orbit. Finally, after the ignition duration is reached, the thrusters are shut down to complete the automatic orbit change. In this way, the satellite can autonomously change its orbit according to the aforementioned automatic orbit change parameters during non-tracking and control segments, reducing the pressure on ground tracking and control. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a flowchart of a satellite automatic orbit change method based on a chemical propulsion system provided in an embodiment of the present invention;

[0025] Figure 2 This is a hardware architecture diagram of a computing device provided in an embodiment of the present invention;

[0026] Figure 3 This is a structural diagram of a satellite automatic orbit change device based on a chemical propulsion system provided in an embodiment of the present invention. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0028] As mentioned earlier, traditional high-orbit satellite transfer orbit changes are generally performed remotely by ground personnel following a set of steps. The main orbit change process includes: establishing the orbit change attitude, adjusting the solar panel angle, activating the dual branches of the 10N thruster, activating the 490N engine bus, sinking to the bottom, igniting the 490N engine, stopping the 490N engine ignition, shutting down the 490N engine bus, shutting down the B branch of the 10N thruster, adjusting the solar panel angle, and establishing a solar (or Earth) attitude. Therefore, the entire orbit change process for a high-orbit satellite requires sending numerous commands to the satellite and requires real-time monitoring from the ground control system, making the entire process time-consuming and labor-intensive. Furthermore, if the rocket's launch altitude is insufficient or if the thrusters or engines malfunction during the orbit change process, the ground control system cannot accurately send commands to the satellite based on its on-orbit status, making it difficult to accurately perform the orbit change.

[0029] Therefore, based on the above problems, in order to reduce the pressure on ground telemetry and control during satellite orbit change and improve the accuracy of orbit change control, this embodiment of the invention proposes a general automatic orbit change control strategy based on a chemical propulsion system. According to the orbit change strategy, automatic orbit change parameters are injected into the arc segment visible to ground telemetry and control. The satellite can automatically perform orbit change operations according to the automatic orbit change parameters.

[0030] The following describes the specific implementation of the above concept.

[0031] Please refer to Figure 1 This invention provides a method for automatic orbit change of a satellite based on a chemical propulsion system, the method comprising:

[0032] Step 100: Obtain the current ignition thruster status of the satellite;

[0033] Step 102: Determine the automatic orbit change parameters of the satellite based on the ignition thruster operating conditions; wherein the automatic orbit change parameters include ignition time, ignition duration, ignition attitude, and target operating conditions of the ignition thruster.

[0034] Step 104: Before the ignition time, according to the ignition attitude and the target working condition of the ignition thruster, perform automatic attitude adjustment, thruster activation and bottoming-out operations in sequence.

[0035] Step 106: When the ignition time is reached, the thruster is ignited to enable the satellite to automatically change its orbit;

[0036] Step 108: After the ignition duration is reached, perform a shutdown operation according to the target operating condition of the ignition thruster.

[0037] Step 110: After ignition, the satellite automatically adjusts its attitude again to complete the automatic orbit change.

[0038] In this embodiment, firstly, based on the satellite's current ignition thruster operating conditions, parameters such as ignition time, ignition duration, ignition attitude, and target thruster operating conditions are determined during the satellite's automatic orbit change process. Then, before the ignition time, automatic attitude adjustment, thruster activation, and bottoming operations are performed according to the determined automatic orbit change parameters. Upon reaching the ignition time, the thrusters are ignited according to the target thruster operating conditions to enable the satellite to automatically change its orbit. Finally, after the ignition duration is reached, the thrusters are shut down to complete the automatic orbit change. In this way, the satellite can autonomously change its orbit according to the aforementioned automatic orbit change parameters during non-tracking and control segments, reducing the pressure on ground tracking and control.

[0039] For step 100:

[0040] In some embodiments, the ignition thruster includes a primary 10N thruster, a backup 10N thruster, and a 490N engine.

[0041] Regarding step 102:

[0042] In some embodiments, the ignition thruster operating conditions include four operating conditions; wherein, operating condition 1: both 10N thrusters and the 490N engine are normal; operating condition 2: one 10N thruster and the 490N engine are normal, while the other 10N thruster is faulty; operating condition 3: both 10N thrusters are normal, while the 490N engine is faulty; operating condition 4: one 10N thruster is normal, while the other 10N thruster and the 490N engine are both faulty.

[0043] In some implementations, determining the satellite's automatic orbit change parameters based on the ignition thruster's operating conditions includes:

[0044] The ignition speed increment and ignition yaw angle are determined based on the orbital maneuvering optimization algorithm;

[0045] Based on the ignition rate increment, calculate the propellant consumption and ignition duration of the ignition thruster;

[0046] The ignition timing of the ignition thruster is calculated based on the stated duration and the current trajectory.

[0047] In this embodiment, the transfer orbit change adopts the Hohmann orbit change method, which comprehensively considers raising the semi-major axis of the orbit, reducing the orbit inclination and orbit eccentricity. There are many orbit maneuver optimization algorithms, such as exhaustive search, simplex method, or recursive quadratic programming algorithm, etc. After comprehensive optimization, the ignition position of the satellite thruster is determined to be near the perigee or apogee, and the ignition speed increment and ignition yaw angle (i.e. ignition attitude) of the ignition thruster are determined. Then, based on the ignition speed increment, the propellant consumption and ignition duration of the ignition thruster under the current operating conditions are calculated.

[0048] Specifically, the propellant consumption and ignition duration of the ignition thruster are calculated using the following formulas:

[0049]

[0050]

[0051] In the formula, m p Where m0 is the propellant consumption, m0 is the initial mass of the satellite, Δv is the ignition velocity increment, Isp is the specific impulse of the ignition thruster, Δt is the ignition duration of the ignition thruster, and mll is the mass flow rate of the propellant during ignition.

[0052] Finally, the ignition timing of the ignition thruster is calculated based on the ignition duration and the current satellite orbit parameters;

[0053]

[0054] When the satellite ignition is at perigee When the satellite ignition is at its apogee

[0055] In the formula, tTran is the ignition time, n is the average velocity of the satellite, M is the mean apogee angle of the satellite, ta is the current satellite time, Δt is the ignition duration of the ignition thruster, dM1 is the difference between the mean apogee angle and the apogee angle, and Angle2Pi is used to limit the ignition parameters to the range [0, 2π]. For example, if the value obtained by (-Δt / (2n)-M) when igniting at perigee is 370°, then Angle2Pi(-Δt / (2n)-M) is 10°.

[0056] In this embodiment, the automatic orbit change parameters corresponding to each ignition thrust condition are calculated in the above manner, and the automatic orbit change parameters are selected in real time according to the current ignition thrust condition of the satellite, which helps to ensure the accuracy of the satellite's automatic orbit change.

[0057] In some implementations, the target operating condition of the ignition thruster is determined in the following manner:

[0058] Based on the fault condition of the ignition thruster, the target operating condition of the ignition thruster is determined.

[0059] If both 10N thrusters and the 490N engine are functioning normally, then the target operating condition for the ignition thruster is confirmed as operating condition one.

[0060] If both the 10N thruster and the 490N engine are normal, but the other 10N thruster is faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition two.

[0061] If both 10N thrusters are normal, but the 490N engine malfunctions, then the target operating condition for the ignition thruster is confirmed to be operating condition three.

[0062] If one 10N thruster is normal, but the other 10N thruster and the 490N engine are both faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition four.

[0063] In this embodiment, before the satellite changes its orbit, the onboard software first obtains the current operating condition of the satellite's ignition thrusters. Different ignition thruster operating conditions correspond to different automatic orbit change parameters. That is, when the satellite's ignition thruster operating conditions are different, the ignition time, ignition duration, ignition attitude, and target operating condition of the ignition thrusters during the satellite's automatic orbit change process are all different. Therefore, in this embodiment, during the orbit change process, the automatic orbit change parameters applicable to the current ignition thruster operating condition of the satellite are automatically determined based on the current ignition thruster operating condition. At the same time, this embodiment considers various operating conditions of the ignition thrusters during the satellite's orbit change process and designs corresponding automatic orbit change parameters for each operating condition. In this way, the satellite can perform automatic orbit change according to the pre-set automatic orbit change parameters without the need for the ground control station to monitor the satellite status in real time. This not only reduces the pressure on the ground control station but also avoids the situation where the satellite's orbit change equipment malfunctions and the ground control system cannot detect the satellite status in real time and send commands to it for accurate orbit change.

[0064] Regarding step 104:

[0065] In some implementations, step 104 includes the following steps:

[0066] S1 seconds before the ignition time, the satellite automatically adjusts its attitude to the ignition attitude, and the solar panels automatically adjust to the ignition position.

[0067] S2 seconds before the ignition moment, the ignition thruster is automatically activated according to the target operating condition of the ignition thruster.

[0068] S3 seconds before the ignition time, the satellite automatically begins the sinking operation; where S1 > S2 > S3.

[0069] In this embodiment, after automatically selecting the matching satellite automatic orbit change parameters according to the current ignition thruster operating condition of the satellite, the satellite will determine the ignition time in real time, and automatically switch to the inertial pointing mode for ground orientation in the S1 seconds before the ignition time. The satellite begins to autonomously adjust its attitude to the preset ignition attitude, and at the same time, the solar panel drive mechanism is adjusted to the ignition position.

[0070] After completing automatic attitude adjustment, S2 seconds before ignition, the satellite automatically activates the ignition thruster according to the target operating condition. For example, when the target operating condition of the ignition thruster is determined to be condition one (i.e., the main 10N thruster, backup 10N thruster, and 490N engine are all in normal working condition), the backup 10N thruster and 490N engine bus are automatically activated. As another example, when the target operating condition of the ignition thruster is determined to be condition four (i.e., the main 10N thruster is in normal working condition, and the backup 10N thruster and 490N engine are both faulty), since the satellite's main 10N thruster is normally activated, there is no need to perform the 10N ignition thruster activation operation in this embodiment.

[0071] After the ignition thruster is activated, in order to ensure the stability of the satellite's operation during subsequent orbit changes, the satellite automatically begins to sink to the bottom in the first S3 seconds before ignition. This transfers the chemical additives required for ignition to the same location, which not only helps to ensure the continuity of ignition thruster ignition but also helps to ensure the stability of satellite operation.

[0072] For steps 106 to 110:

[0073] In this embodiment, when the onboard satellite detects the arrival of the ignition time in real time, it automatically ignites the engine according to the target operating condition of the ignition thruster. When the target operating condition of the ignition thruster is condition three or condition four, the ignition duration of the ignition thruster is the same as the sinking duration of the satellite corresponding to the current target operating condition. That is, the sinking operation of the satellite and the ignition operation of the ignition thruster are carried out simultaneously, which is conducive to the smooth automatic orbit change of the satellite. When the onboard satellite detects that the preset ignition duration has been reached, it automatically performs the shutdown operation of the ignition thruster according to the ignition thruster usage. For example, when it is determined that the target operating condition of the ignition thruster is condition one, the 490N engine, the 490N engine bus and the backup 10N thruster are automatically shut down in sequence. For another example, when it is determined that the target operating condition of the ignition thruster is condition four, the backup 10N thruster is automatically shut down and the sinking operation is stopped.

[0074] In some implementations, step 110 includes the following steps:

[0075] Four seconds after ignition, the satellite adjusts its attitude to face the Earth and autonomously adjusts the angle of its solar panels.

[0076] S5 seconds after ignition, the satellite autonomously injects solar orientation to complete automatic orbit change; where S5 > S4.

[0077] For example, the satellite's current ignition thruster operating condition is that the primary 10N thruster, the backup 10N thruster, and the 490N engine are all in normal working order. Based on the current ignition thruster operating condition, the satellite's automatic orbit change parameters are determined as follows: ignition time is set to T0 = 172540800, ignition duration is set to 1.5 hours, ignition attitude is set to a pitch offset angle of 90°, and the target operating condition for ignition using thrusters is condition one, namely the 490N engine + primary and backup 10N thrusters. The satellite determines the ignition time in real time, and 4200 seconds before the ignition time, the satellite begins to autonomously adjust its attitude to the ignition attitude, and the solar panel drive mechanism is adjusted to... Ignition position; 360 seconds before ignition, the thruster activation operation is automatically performed: the backup 10N thruster and the 490N engine bus are activated sequentially; 300 seconds before ignition, the satellite automatically switches to ignition mode and begins the 10N bottoming operation; at the ignition time, the 490N engine is automatically activated for ignition. During ignition, the satellite autonomously calculates the ignition duration. After 1.5 hours of ignition, the 490N engine, the 490N engine bus, and the backup 10N thruster are sequentially shut down; 400 seconds after ignition ends, the satellite autonomously switches to inertial pointing mode for Earth orientation and autonomously adjusts the solar panel angle; 800 seconds after ignition ends, the satellite autonomously switches to solar orientation mode. In summary, through practical application, this embodiment requires no additional hardware equipment; only software parameters need to be set, and the satellite can automatically change orbits according to a preset program, achieving the expected orbit-changing effect and increasing the system's autonomy.

[0078] like Figure 2 , Figure 3 As shown, this embodiment of the invention provides a satellite automatic orbit change device based on a chemical propulsion system. The device embodiment can be implemented through software, hardware, or a combination of both. From a hardware perspective, as... Figure 2 The diagram shown is a hardware architecture diagram of a computing device housing a satellite automatic orbit change device based on a chemical propulsion system, according to an embodiment of the present invention. (Except for...) Figure 2 In addition to the processor, memory, network interface, and non-volatile memory shown, the computing device in the embodiment may also include other hardware, such as a forwarding chip responsible for processing packets. Taking software implementation as an example, such as... Figure 3 As shown, a device in a logical sense is formed by the CPU of its computing device reading the corresponding computer program from non-volatile memory into memory and running it. This embodiment provides a satellite automatic orbit-changing device based on a chemical propulsion system, the device comprising:

[0079] Acquisition unit 300 is used to acquire the ignition thruster operating status of the satellite;

[0080] The determining unit 302 is used to determine the automatic orbit change parameters of the satellite based on the ignition thruster operating conditions; wherein, the automatic orbit change parameters include ignition time, ignition duration, ignition attitude and ignition thruster target operating conditions;

[0081] The first execution unit 304 is used to perform automatic attitude adjustment, thruster activation and bottoming-out operations sequentially according to the ignition attitude and the target operating condition of the ignition thruster before the ignition time.

[0082] The second execution unit 306 is used to ignite the thruster to enable the satellite to automatically change its orbit when the ignition time is reached.

[0083] The third execution unit 308 is used to perform a shutdown operation according to the target operating condition of the ignition thruster after the ignition duration is reached.

[0084] The fourth execution unit 310 is used to automatically adjust the satellite's attitude again after ignition to complete the automatic orbit change.

[0085] In this embodiment of the specification, the acquisition unit 300 can be used to execute step 100 in the above method embodiment, the determination unit 302 can be used to execute step 102 in the above method embodiment, the first execution unit 304 can be used to execute step 104 in the above method embodiment, the second execution unit 306 can be used to execute step 106 in the above method embodiment, the third execution unit 308 can be used to execute step 108 in the above method embodiment, and the fourth execution unit 310 can be used to execute step 110 in the above method embodiment.

[0086] In one embodiment of the present invention, in the acquisition unit 300, the ignition thruster includes a primary 10N thruster, a backup 10N thruster, and a 490N engine.

[0087] In one embodiment of the present invention, in the acquisition unit 300, the ignition thruster operating conditions include four operating conditions; wherein, operating condition 1: both 10N thrusters and the 490N engine are normal; operating condition 2: one 10N thruster and the 490N engine are normal, while the other 10N thruster is faulty; operating condition 3: both 10N thrusters are normal, while the 490N engine is faulty; operating condition 4: one 10N thruster is normal, while the other 10N thruster and the 490N engine are both faulty.

[0088] In one embodiment of the present invention, the determining unit 302 is configured to perform the following operations:

[0089] The process of determining the satellite's automatic orbit change parameters based on the ignition thruster's operating conditions includes:

[0090] The ignition speed increment and ignition yaw angle are determined based on the orbital maneuvering optimization algorithm;

[0091] Based on the ignition rate increment, calculate the propellant consumption and ignition duration of the ignition thruster;

[0092] The ignition timing of the ignition thruster is calculated based on the ignition duration and the current orbital parameters.

[0093] In one embodiment of the present invention, the propellant consumption of the ignition thruster and the ignition duration are calculated using the following formulas:

[0094]

[0095]

[0096] In the formula, m p Where m is the propellant consumption, m0 is the initial mass of the satellite, Δv is the ignition velocity increment, Isp is the specific impulse of the ignition thruster, Δt is the ignition duration of the ignition thruster, and mll is the mass flow rate of the propellant during ignition.

[0097] In one embodiment of the present invention, the ignition timing is calculated using the following formula:

[0098]

[0099] For near-geometry ignition:

[0100] For remote ignition:

[0101] In the formula, tTran is the ignition time, n is the average velocity of the satellite, M is the mean apogee angle of the satellite, ta is the current satellite time, Δt is the ignition duration of the ignition thruster, and dM1 is the difference between the mean apogee angle and the apogee angle.

[0102] In one embodiment of the present invention, the target operating condition of the ignition thruster is determined in the following manner:

[0103] Based on the fault condition of the ignition thruster, the target operating condition of the ignition thruster is determined.

[0104] Based on the fault condition of the ignition thruster, the target operating condition of the ignition thruster is determined.

[0105] If both 10N thrusters and the 490N engine are functioning normally, then the target operating condition for the ignition thruster is confirmed as operating condition one.

[0106] If both the 10N thruster and the 490N engine are normal, but the other 10N thruster is faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition two.

[0107] If both 10N thrusters are normal, but the 490N engine malfunctions, then the target operating condition for the ignition thruster is confirmed to be operating condition three.

[0108] If one 10N thruster is normal, but the other 10N thruster and the 490N engine are both faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition four.

[0109] In one embodiment of the present invention, the first execution unit 304 is configured to perform the following operations:

[0110] S1 seconds before the ignition time, the satellite automatically adjusts its attitude to the ignition attitude, and the solar panels automatically adjust to the ignition position.

[0111] S2 seconds before the ignition moment, the ignition thruster is automatically activated according to the target operating condition of the ignition thruster.

[0112] S3 seconds before the ignition time, the satellite automatically begins the sinking operation; where S1 > S2 > S3.

[0113] In one embodiment of the present invention, the fourth execution unit 310 is configured to perform the following operations:

[0114] Four seconds after ignition, the satellite adjusts its attitude to face the Earth and autonomously adjusts the angle of its solar panels.

[0115] S5 seconds after ignition, the satellite autonomously injects solar orientation to complete automatic orbit change; where S5 > S4.

[0116] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on a satellite automatic orbit change device based on a chemical propulsion system. In other embodiments of the present invention, a satellite automatic orbit change device based on a chemical propulsion system may include more or fewer components than illustrated, or combine some components, or split some components, or have different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0117] The information interaction and execution process between the modules in the above-mentioned device are based on the same concept as the method embodiment of the present invention, and the specific details can be found in the description of the method embodiment of the present invention, and will not be repeated here.

[0118] This invention also provides a computing device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements a satellite automatic orbit change method based on a chemical propulsion system according to any embodiment of this invention.

[0119] This invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, causes the processor to perform a satellite automatic orbit change method based on a chemical propulsion system according to any embodiment of this invention.

[0120] Specifically, a system or apparatus equipped with a storage medium may be provided, on which software program code implementing the functions of any of the embodiments described above is stored, and the computer (or CPU or MPU) of the system or apparatus may read and execute the program code stored in the storage medium.

[0121] In this case, the program code read from the storage medium can itself implement the function of any of the above embodiments, and therefore the program code and the storage medium storing the program code constitute part of the present invention.

[0122] Examples of storage media used to provide program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, program code can be downloaded from a server computer via a communication network.

[0123] Furthermore, it should be clear that not only can the program code read by the computer be executed, but also the operating system or other components operating on the computer can be instructed based on the program code to perform some or all of the actual operations, thereby realizing the function of any of the embodiments described above.

[0124] Furthermore, it is understood that the program code read from the storage medium is written to the memory set in the expansion board inserted into the computer or to the memory set in the expansion module connected to the computer. Then, based on the instructions of the program code, the CPU or other components installed on the expansion board or expansion module execute some and all of the actual operations, thereby realizing the function of any of the above embodiments.

[0125] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0126] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media that can store program code, such as ROM, RAM, magnetic disk, or optical disk.

[0127] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for automatic orbit change of a satellite based on a chemical propulsion system, characterized in that, include: Obtain the current ignition thruster status of the satellite; Based on the operating conditions of the ignition thrusters, the automatic orbit change parameters of the satellite are determined; wherein, the automatic orbit change parameters include ignition time, ignition duration, ignition attitude, and target operating conditions of the ignition thrusters; the ignition thrusters include two sets of 10N thrusters (primary and backup) and a 490N engine; the operating conditions of the ignition thrusters include four conditions: Condition 1: both 10N thrusters and the 490N engine are normal; Condition 2: one set of 10N thrusters and the 490N engine are normal, while the other 10N thruster is faulty; Condition 3: both 10N thrusters are normal, while the 490N engine is faulty; Condition 4: one set of 10N thrusters is normal, while the other 10N thruster and the 490N engine are both faulty. The target operating condition of the ignition thruster is determined in the following manner: Based on the fault condition of the ignition thruster, the target operating condition of the ignition thruster is determined. If both 10N thrusters and the 490N engine are functioning normally, then the target operating condition for the ignition thruster is confirmed as operating condition one. If both the 10N thruster and the 490N engine are normal, but the other 10N thruster is faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition two. If both 10N thrusters are normal, but the 490N engine malfunctions, then the target operating condition for the ignition thruster is confirmed to be operating condition three. If one 10N thruster is normal, but the other 10N thruster and the 490N engine are both faulty, then the target operating condition of the ignition thruster is confirmed to be operating condition four. Before the ignition moment, automatic attitude adjustment, thruster activation and bottoming-out operations are performed sequentially according to the ignition attitude and the target operating condition of the ignition thruster. S1 seconds before the ignition time, the satellite automatically adjusts its attitude to the ignition attitude, and the solar panels automatically adjust to the ignition position. S2 seconds before the ignition moment, the ignition thruster is automatically activated according to the target operating condition of the ignition thruster. S3 seconds before the ignition time, the satellite automatically begins the bottom sinking operation; where S1 > S2 > S3. When the ignition time is reached, the thruster is ignited to enable the satellite to automatically change its orbit; After the ignition duration is reached, a shutdown operation is performed according to the target operating condition of the ignition thruster. After ignition, the satellite automatically adjusts its attitude again to complete the automatic orbit change.

2. The method according to claim 1, characterized in that, The process of determining the satellite's automatic orbit change parameters based on the ignition thruster's operating conditions includes: The ignition speed increment and ignition yaw angle of the ignition thruster are determined based on the orbital maneuvering optimization algorithm. Based on the ignition rate increment, calculate the propellant consumption and ignition duration of the ignition thruster; The ignition timing of the ignition thruster is calculated based on the ignition duration and the current orbital parameters.

3. The method according to claim 2, characterized in that, The propellant consumption of the ignition thruster and the ignition duration are calculated using the following formulas: In the formula, m p The propellant consumption is given by m0, the initial mass of the satellite is given by Δv, the ignition velocity increment is given by Isp, the specific impulse of the ignition thruster is given by Δt, the ignition duration of the ignition thruster is given by mll, and the mass flow rate of the propellant at ignition is given by mll; and / or The ignition timing is calculated using the following formula: For near-geometry ignition: For remote ignition: In the formula, tTran is the ignition time, n is the average velocity of the satellite, M is the mean apogee angle of the satellite, ta is the current satellite time, Δt is the ignition duration of the ignition thruster, and dM1 is the difference between the mean apogee angle and the apogee angle.

4. The method according to claim 1, characterized in that, After ignition, the satellite readjusts its attitude again to complete the automatic orbit change, including: Four seconds after ignition, the satellite adjusts its attitude to face the Earth and autonomously adjusts the angle of its solar panels. S5 seconds after ignition, the satellite autonomously injects solar orientation to complete automatic orbit change; where S5 > S4.

5. A satellite automatic orbit change device based on a chemical propulsion system, characterized in that, For implementing the method as described in any one of claims 1 to 4, comprising: The acquisition unit is used to acquire the operating conditions of the satellite's ignition thrusters; The determining unit is used to determine the automatic orbit change parameters of the satellite based on the operating conditions of the ignition thruster; wherein the automatic orbit change parameters include ignition time, ignition duration, ignition attitude, and target operating conditions of the ignition thruster. The first execution unit is used to perform automatic attitude adjustment, thruster activation and bottoming-out operations sequentially according to the ignition attitude and the target operating condition of the ignition thruster before the ignition time. The second execution unit is used to ignite the thruster to enable the satellite to automatically change its orbit when the ignition time is reached. The third execution unit is used to perform a shutdown operation according to the target operating condition of the ignition thruster after the ignition duration is reached. The fourth execution unit is used to automatically adjust the satellite's attitude again after ignition to complete the automatic orbit change.

6. A computing device comprising a memory and a processor, wherein the memory stores a computer program, and the processor, when executing the computer program, implements the method as described in any one of claims 1-4.

7. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the method of any one of claims 1-4.

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