Primary and secondary satellite in-orbit maneuvering control method and device and storage medium

Abstract

The invention belongs to the technical field of spaceflight launching, and particularly relates to a primary and secondary satellite in-orbit maneuvering control method and device and a storage medium. The control method comprises the following steps: step 1, controlling a primary satellite and a secondary satellite to enter an orbit; 2, acquiring task requirements in real time, and calculating to obtain an on-orbit maneuvering strategy of the child satellites based on an autonomous maneuvering control algorithm; 3, potential attack and defense threats are analyzed, and the possible influence on in-orbit maneuver control is evaluated; key defense measures of the child satellite and the mother satellite in the maneuvering process are determined, and a coping strategy is formulated; and 4, establishing a real-time monitoring system, continuously collecting state information, orbit data and potential threat information of the child satellites, and adjusting a maneuvering control strategy according to the state information, the orbit data and the potential threat information of the child satellites. According to the method, the operation flexibility and the task response speed in a complex environment are improved.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace launch technology, and in particular relates to an on-orbit maneuvering control method, equipment and storage medium for a parent and child satellite. Background Art

[0002] In current multi-satellite missions, the coordination between satellites is only achieved through mission planning and task allocation, and does not rely on orbital or position maneuvers. Multiple satellites complete their respective tasks through communication and data sharing, while their orbits and positions remain stationary. Even if the sub-satellite system design is adopted in some space missions, once the sub-satellite is released or deployed, no further maneuvering operations are performed. The sub-satellite relies on the initial release speed and orbital parameters to operate in orbit, while the mother satellite continues to perform main tasks and data processing. The non-maneuverable sub-satellite system cannot flexibly adjust the orbit and attitude according to mission requirements, and it is difficult to respond to emergencies or new mission requirements. For example, when it is necessary to readjust the formation or accurately align with the target, the non-maneuverable system is stretched, limiting its mission expansion capabilities.

[0003] In addition, as mission requirements become more complex, satellites need to be dynamically adjusted on-orbit, but non-maneuverable systems can only perform preset static missions and are difficult to flexibly respond to environmental changes or dynamic mission adjustments. This system has poor adaptability in multi-task scenarios, especially in missions that require immediate response (such as satellite attack and defense, earth observation, or space science exploration), and shows great limitations. Moreover, in non-maneuverable satellite formations, although the satellites are precisely designed to form a formation at the initial launch, over time, due to external disturbances such as solar radiation pressure, the inhomogeneity of the earth's gravitational field, and aerodynamic drag, the formation may gradually become unstable, and the relative position deviation between satellites increases, affecting the execution accuracy and effect of the mission. Moreover, in complex mission scenarios, especially missions that require multiple satellites to work together (such as formation imaging, synchronous observation, etc.), non-maneuverable systems lack orbit and attitude adjustment capabilities, making it difficult to achieve precise relative position control, resulting in unsatisfactory collaborative work effects. The inability to adjust the relative position and attitude between satellites in real time according to mission requirements seriously affects the system's mission execution capability.

[0004] Therefore, it is necessary to invent an on-orbit maneuvering control method for a parent-child satellite to solve the above-mentioned defects existing in the non-maneuvering parent-child satellite system in the prior art in performing missions. Summary of the invention

[0005] In order to solve the technical problems in the prior art of non-maneuverable parent-child satellite systems in the execution of missions, such as lack of flexibility, poor mission adaptability, low formation stability, and inability to achieve precise coordinated control, the present invention proposes an on-orbit maneuverable control method, device and storage medium for parent-child satellites, so as to improve the mission flexibility of the parent-child satellite system, enhance the accuracy of mission execution, improve the autonomy and reliability of missions, and enhance the collaborative working ability of the system.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is: a method for controlling the on-orbit maneuverability of a parent and child satellite, comprising the following steps:

[0007] Step 1: Control the parent star and the sub-star into orbit;

[0008] Step 2: Obtain mission requirements in real time and calculate the satellite's on-orbit maneuvering strategy based on the autonomous maneuvering control algorithm;

[0009] Step 3: Analyze potential offensive and defensive threats and assess their impact on on-orbit maneuver control; determine key defensive measures for the satellite and the parent satellite during maneuvers and develop response strategies;

[0010] Step 4: Establish a real-time monitoring system to continuously collect sub-satellite status information, orbital data and potential threat information, and adjust the maneuver control strategy based on the sub-satellite status information, orbital data and potential threat information.

[0011] The described method for in-orbit maneuvering control of a parent and child satellite also includes the following steps: during the maneuvering and mission execution process, the collected data is encrypted and transmitted using a secure communication protocol to ensure the security of the information during transmission.

[0012] The described method for on-orbit maneuvering control of a parent-child satellite also includes the following steps: determining whether data leakage or system failure occurs, and if so, isolating the affected modules.

[0013] In step 1, the specific method of controlling the parent star and the sub-star to enter orbit is:

[0014] After determining the best launch window, the rocket is launched to ensure that the parent satellite and the sub-satellite enter the space according to the predetermined trajectory;

[0015] After the mother satellite and the sub-satellite reach the predetermined orbit, the orbit correction thrusters are used to perform preliminary maneuvers to ensure that the mother satellite and the sub-satellite accurately enter the target orbit.

[0016] In the step 1, after the parent satellite and the sub-satellite enter the target orbit, the step of real-time monitoring of the orbital parameters of the satellite is also included.

[0017] The step 2 also includes the following steps: controlling the sub-satellite to implement a predetermined on-orbit maneuver according to the on-orbit maneuver strategy, wherein the on-orbit maneuver includes orbit change, maintaining relative position and avoiding collision; when implementing the predetermined on-orbit maneuver, monitoring the status of the propulsion system in real time to ensure stability and effectiveness during the maneuver.

[0018] In addition, the present invention also provides a parent-child satellite on-orbit maneuvering control device, including: a processor and a memory connected to the processor in communication;

[0019] The memory stores computer-executable instructions;

[0020] The processor executes the computer-executable instructions stored in the memory to implement the on-orbit maneuvering control method for a parent-child satellite.

[0021] The described on-orbit maneuvering control device for a parent and child satellite also includes an orbital parameter monitoring module, which is used to collect the orbital parameters of the satellite in real time and then send them to the processor to meet the needs of on-orbit maneuvering.

[0022] The computer-executable instructions stored in the memory include:

[0023] Status monitoring module: used to obtain the orbital parameters of the satellite in real time and send them to the decision algorithm module;

[0024] Autonomous maneuvering control module: used to obtain mission requirements in real time and calculate the satellite's on-orbit maneuvering strategy based on the autonomous maneuvering control algorithm;

[0025] Decision-making algorithm module: used to adjust the maneuvering control strategy according to satellite status information, orbit data and potential threat information;

[0026] Emergency Response Module: used to analyze potential offensive and defensive threats and assess possible impacts on on-orbit maneuver control; determine key defense measures for satellites and the parent satellite during maneuvers and develop response strategies.

[0027] In addition, the present invention also provides a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, they are used to implement the method for in-orbit maneuvering control of a parent and child satellite.

[0028] The present invention proposes a method, device and storage medium for controlling the on-orbit maneuverability of a parent and child satellite, which have the following beneficial effects compared with the prior art:

[0029] 1. Enhanced autonomy of the mother-subsatellite system: The autonomous maneuvering control algorithm of the present invention enables the mother-subsatellite to autonomously adjust its orbit and attitude independently of the ground control center, thus improving operational flexibility and mission response speed in complex environments;

[0030] 2. Strong mission adaptability: The system of the present invention is flexible in design and can be configured and adjusted according to different mission requirements. Moreover, it can also realize task management and scheduling mechanism, handle multiple tasks simultaneously, ensure the cooperation between sub-satellites and the reasonable allocation of resources, and improve the efficiency of mission completion; it is suitable for various types of on-orbit maneuvering missions;

[0031] 3. Improve the attack and defense capabilities of satellites: Through real-time data processing and analysis, the present invention can effectively respond to potential attacks and interference, enhance the attack and defense capabilities of the parent and child satellites, ensure that they can respond quickly when facing potential attacks or interference, and improve the survivability of satellites and the safety of mission execution. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A schematic flow chart of an on-orbit maneuvering control method for a parent and child satellite provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments; based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0034] Embodiment 1

[0035] like Figure 1 As shown, the first embodiment of the present invention provides an on-orbit maneuvering control method for a parent and child satellite, comprising the following steps:

[0036] Step 1: Control the parent star and the sub-star into orbit.

[0037] Specifically, in step 1 of this embodiment, the specific method of controlling the parent satellite and the sub-satellite to enter orbit is:

[0038] After determining the best launch window, the rocket is launched to ensure that the parent satellite and the sub-satellite enter the space according to the predetermined trajectory;

[0039] After the mother satellite and the sub-satellite reach the predetermined orbit, the orbit correction thrusters are used to perform preliminary maneuvers to ensure that the mother satellite and the sub-satellite accurately enter the target orbit.

[0040] Furthermore, in step 1 of this embodiment, after the parent satellite and the sub-satellite enter the target orbit, a step of real-time monitoring of the orbital parameters of the satellite is also included. By real-time monitoring of the orbital parameters of the satellite, the needs of subsequent on-orbit maneuvers can be met.

[0041] Step 2: Obtain mission requirements in real time and calculate the on-orbit maneuvering strategy of the sub-satellite based on the autonomous maneuvering control algorithm.

[0042] Specifically, the step 2 also includes the following steps: controlling the sub-satellite to implement a predetermined on-orbit maneuver according to the on-orbit maneuver strategy, wherein the on-orbit maneuver includes orbit change, maintaining relative position and avoiding collision; when implementing the predetermined on-orbit maneuver, monitoring the status of the propulsion system in real time to ensure stability and effectiveness during the maneuver.

[0043] In this embodiment, the autonomous maneuver control algorithm based on real-time data and threat assessment enables the satellite to perform precise orbit adjustment and attitude control according to mission requirements. The maneuver strategy is designed to achieve orbit change, maintain relative position and avoid collision, and enhance the autonomous capability of the satellite. The scheduled on-orbit maneuver is implemented, and the status of the propulsion system is monitored in real time to ensure stability and effectiveness during the maneuver.

[0044] Step 3: Analyze potential offensive and defensive threats, evaluate the impact on on-orbit maneuver control, and obtain potential threat information; determine the key defense measures of the satellite and the parent satellite during the maneuver process, and formulate response strategies.

[0045] In this embodiment, after the sub-satellite and the mother satellite successfully enter orbit, potential attack and defense threats are analyzed and the possible impact on the on-orbit maneuvering control is evaluated to obtain potential threat information, which can provide a reference for the subsequent on-orbit maneuvering control strategy adjustment. Determining the key defense measures of the sub-satellite and the mother satellite during the maneuvering process and formulating a response strategy can ensure the safety of the system.

[0046] Step 4: Establish a real-time monitoring system to continuously collect sub-satellite status information, orbital data and potential threat information, and adjust the maneuver control strategy based on the sub-satellite status information, orbital data and potential threat information.

[0047] In this embodiment, a real-time monitoring and intelligent feedback mechanism is established. A real-time monitoring system is established to continuously collect satellite status information, orbital data and potential threat information, and dynamically adjust the maneuvering control strategy according to the monitoring data to ensure the adaptability and safety of the satellite in complex environments.

[0048] Furthermore, the on-orbit maneuvering control method of a parent satellite in this embodiment also implements a data and emergency response mechanism. Specifically, it also includes the following steps: during the maneuvering and mission execution process, the collected data is encrypted and transmitted using a secure communication protocol to ensure the security of the information during transmission.

[0049] Furthermore, a method for on-orbit maneuvering control of a parent and child satellite in this embodiment also includes the following steps: determining whether data leakage or system failure occurs, and if so, isolating the affected modules.

[0050] In response to potential security incidents, such as data leakage or system failure, a method for on-orbit maneuvering control of a mother-subsatellite in this embodiment can ensure that the rocket system can quickly isolate the affected modules and protect the overall safety of the system.

[0051] The feasibility of the present invention has been proved through a series of simulation verifications. The following is part of the implementation source code:

[0052]

[0053]

[0054]

[0055]

[0056] Embodiment 2

[0057] Embodiment 2 of the present invention provides an on-orbit maneuvering control device for a parent satellite, characterized in that it includes: a processor and a memory in communication with the processor;

[0058] The memory stores computer-executable instructions;

[0059] The processor executes the computer-executable instructions stored in the memory to implement the on-orbit maneuvering control method for a parent and child satellite as described in Embodiment 1.

[0060] Furthermore, a parent-child satellite on-orbit maneuvering control device of this embodiment also includes an orbital parameter monitoring module, which is used to collect the orbital parameters of the satellite in real time and then send them to the processor to meet the needs of on-orbit maneuvers.

[0061] Furthermore, in this embodiment, the computer executable instructions stored in the memory include:

[0062] Status monitoring module: used to obtain the orbital parameters of the satellite in real time and send them to the decision algorithm module;

[0063] Autonomous maneuvering control module: used to obtain mission requirements in real time and calculate the satellite's on-orbit maneuvering strategy based on the autonomous maneuvering control algorithm;

[0064] Decision-making algorithm module: used to adjust the maneuvering control strategy according to satellite status information, orbit data and potential threat information;

[0065] Emergency response module: used to analyze potential offensive and defensive threats, evaluate the impact on on-orbit maneuver control and send it to the decision algorithm module; also used to determine the key defense measures of the satellite and the mother satellite during the maneuver process, and formulate response strategies.

[0066] Embodiment 3

[0067] Embodiment 3 of the present invention provides a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, they are used to implement the on-orbit maneuvering control method of a parent-child satellite described in Embodiment 1.

[0068] In summary, the present invention proposes a method, device and storage medium for controlling the on-orbit maneuverability of a parent and child satellite, which have the following beneficial effects compared with the best existing technologies:

[0069] 1. Enhanced autonomy of the mother-subsatellite system: The autonomous maneuvering control algorithm of the present invention enables the mother-subsatellite to autonomously adjust its orbit and attitude independently of the ground control center, thus improving operational flexibility and mission response speed in complex environments;

[0070] 2. Strong mission adaptability: The system of the present invention is flexible in design and can be configured and adjusted according to different mission requirements. Moreover, it can also realize task management and scheduling mechanism, handle multiple tasks simultaneously, ensure the cooperation between sub-satellites and the reasonable allocation of resources, and improve the efficiency of mission completion; it is suitable for various types of on-orbit maneuvering missions;

[0071] 3. Improve the attack and defense capabilities of satellites: Through real-time data processing and analysis, the present invention can effectively respond to potential attacks and interference, enhance the attack and defense capabilities of the parent and child satellites, ensure that they can respond quickly when facing potential attacks or interference, and improve the survivability of satellites and the safety of mission execution.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for controlling on-orbit maneuvers of a parent and child satellite, characterized in that: The following steps are involved: Step 1: Control the parent star and the sub-star into orbit; Step 2: Obtain mission requirements in real time and calculate the satellite's on-orbit maneuvering strategy based on the autonomous maneuvering control algorithm; Step 3: Analyze potential offensive and defensive threats, evaluate their impact on on-orbit maneuver control, and obtain potential threat information; determine the key defense measures for the satellite and the parent satellite during the maneuver process, and formulate response strategies; Step 4: Establish a real-time monitoring system to continuously collect sub-satellite status information, orbital data and potential threat information, and adjust the maneuver control strategy based on the sub-satellite status information, orbital data and potential threat information.

2. The on-orbit maneuvering control method of a parent-child satellite according to claim 1, characterized in that: The following steps are also included: During maneuvers and mission execution, the collected data is encrypted and transmitted using secure communication protocols to ensure the security of information during transmission.

3. The on-orbit maneuvering control method of a parent-child satellite according to claim 1, characterized in that: The following steps are also included: Determine whether data leakage or system failure has occurred. If so, isolate the affected module.

4. The on-orbit maneuvering control method of a parent-child satellite according to claim 1, characterized in that: In step 1, the specific method of controlling the parent star and the sub-star to enter orbit is: After determining the best launch window, the rocket is launched to ensure that the parent satellite and the sub-satellite enter the space according to the predetermined trajectory; After the mother satellite and the sub-satellite reach the predetermined orbit, the orbit correction thrusters are used to perform preliminary maneuvers to ensure that the mother satellite and the sub-satellite accurately enter the target orbit.

5. The on-orbit maneuvering control method of a parent-child satellite according to claim 1, characterized in that: In the step 1, after the parent satellite and the sub-satellite enter the target orbit, the step of real-time monitoring of the orbital parameters of the satellite is also included.

6. The on-orbit maneuvering control method of a parent-child satellite according to claim 1, characterized in that: The step 2 also includes the following steps: controlling the sub-satellite to implement a predetermined on-orbit maneuver according to the on-orbit maneuver strategy, wherein the on-orbit maneuver includes orbit change, maintaining relative position and avoiding collision; when implementing the predetermined on-orbit maneuver, monitoring the status of the propulsion system in real time to ensure stability and effectiveness during the maneuver.

7. An on-orbit maneuvering control device for a mother-daughter satellite, characterized in that: include: A processor and a memory communicatively connected to the processor; The memory stores computer-executable instructions; The processor executes the computer-executable instructions stored in the memory to implement the on-orbit maneuvering control method for a parent-child satellite as described in any one of claims 1 to 6.

8. The on-orbit maneuvering control device for a parent and child satellite according to claim 7, characterized in that: It also includes an orbital parameter monitoring module, which is used to collect the orbital parameters of the satellite in real time and then send them to the processor to meet the needs of on-orbit maneuvers.

9. The on-orbit maneuvering control device for a parent and child satellite according to claim 7, characterized in that: The computer-executable instructions stored in the memory include: Status monitoring module: used to obtain the satellite's orbital parameters in real time and send them to the decision algorithm module; Autonomous maneuvering control module: used to obtain mission requirements in real time and calculate the satellite's on-orbit maneuvering strategy based on the autonomous maneuvering control algorithm; Decision-making algorithm module: used to adjust the maneuvering control strategy according to satellite status information, orbit data and potential threat information; Emergency response module: used to analyze potential offensive and defensive threats, evaluate the impact on on-orbit maneuver control and send it to the decision algorithm module; also used to determine the key defense measures of the satellite and the mother satellite during the maneuver process, and formulate response strategies.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer-executable instructions, which, when executed by a processor, are used to implement an on-orbit maneuvering control method for a parent-child satellite as described in any one of claims 1 to 6.

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