A method and system for planning a maneuvered star orbit mission

Abstract

The application discloses a kind of planning method and system of motorized star orbit mission, belong to spaceflight simulation analysis field.This method includes: creating planning mission and setting motorized star basic parameters;Setting target star basic parameters and total control center position point;With motorized star parameters, target star parameters and total control center position point as constraint, carry out motorized analysis, obtain the task time window satisfying constraint;After determining the task time window, call the orbit maneuver multi-strategy algorithm to obtain the motorized way and motorized parameter list of motorized star to reach mission point;Finally, enter the planning event processing module, sort events by time and judge whether there is a collision event, output planning mission success / failure state.Total control center based on fuel formula real-time evaluation fuel balance and support user dynamically formulate and issue orbit transfer scheme, realize the integration of motorized star mission window calculation, motorized strategy selection and safety check planning.

Description

Technical Field

[0001] This invention relates to the field of aerospace simulation analysis, specifically to a planning method and system for maneuvering satellite orbit missions. Background Technology

[0002] Maneuvering satellites refer to satellites with maneuvering capabilities. Current propulsion and maneuvering methods for maneuvering satellites mainly include chemical propulsion, electric propulsion, and cold gas propulsion. Chemical propulsion offers high thrust and fast response, but consumes a large amount of propellant and has a limited mission lifespan. Electric propulsion has high specific impulse and high propellant utilization, making it suitable for long-term orbit maintenance and transfer, but its thrust is relatively low and its maneuvering cycle is long, making it difficult to meet the needs of rapid maneuvers such as emergency avoidance. Cold gas propulsion has a simple structure, low pollution, and precise pulse control, but its Δv capability is limited. Meanwhile, attitude control typically relies on reaction wheels, magnetic torquers, or control moment gyroscopes. While these can achieve high attitude accuracy, under high maneuvering and frequent orbit changes, they are prone to problems such as momentum accumulation, increased energy consumption, and complex control coupling. Therefore, to meet diverse needs such as collision avoidance, reconnaissance and observation, and on-orbit servicing, there is an urgent need to invest in more maneuvering satellite platforms with stronger maneuverability, faster response, and higher control precision to improve mission adaptability, on-orbit safety, and space resource utilization efficiency. Summary of the Invention

[0003] Based on the above analysis, this invention provides a planning method for maneuvering satellite orbit missions, the specific implementation steps of which are as follows:

[0004] S1. Create a planning task and set the basic parameters of each maneuvering star;

[0005] S2. Set the basic parameters of the target satellite, where the target satellite refers to the satellite that is the object of the mission in the planned mission;

[0006] S3. Using the basic parameters of the maneuvering star and the basic parameters of the target star as constraints, the algorithm is invoked to perform maneuver analysis. The result of the maneuver analysis is the mission time window that satisfies the constraints.

[0007] S4. After determining the mission time window, call the orbital maneuver multi-strategy algorithm to calculate the maneuvering method of the maneuvering star to reach the mission point.

[0008] S5. After confirming the maneuvering mode, proceed to the planning event processing module. The planning event module determines whether a collision event exists based on the maneuvering mode in order to complete the planning task.

[0009] Preferably, the basic parameters of the maneuvering satellite include the orbital elements, propellant type, total fuel volume, payload parameters, mission type, mission start and end times, and illumination angle.

[0010] Preferably, the basic parameters of the target star include the target star's orbital elements, the distance between the maneuvering satellite and the target star, the time of arrival at the mission point, and the flight mode.

[0011] Preferably, the maneuver analysis is obtained through an optical imaging satellite control window algorithm, a radar imaging satellite control window algorithm, and an electronic jamming satellite control algorithm.

[0012] Preferably, the task time window can be sorted and displayed in real time according to different preferred conditions, providing multi-task synchronous calculation.

[0013] Preferably, the orbital maneuvering multi-strategy algorithm supports multiple maneuvering modes and returns a list of maneuvering parameters, including the number of orbital elements and the single pulse consumption.

[0014] Preferably, the event processing module sorts events by event time and modifies historical events based on the impact events.

[0015] Preferably, a central control center can be set in S2. The central control center analyzes the fuel remaining of the maneuvering satellite in real time according to the fuel formula, catalogs and determines the orbit of the target satellite and makes predictions. The user can formulate the planned mission maneuvering scheme again and send it to control the maneuvering satellite to change its orbit, so as to achieve dynamic control of the maneuvering satellite.

[0016] Preferably, the fuel formula is:

[0017]

[0018] Where m0 represents the initial total mass of the rocket, and mf represents the final mass of the rocket after acceleration. The value represents the mass of propellant consumed, Δv represents the required velocity increment in m / s, i.e., the magnitude of the change in velocity the rocket needs to undergo, Isp represents specific impulse (in seconds), which is an indicator of the efficiency of the propulsion system, g0 represents the standard gravitational acceleration, and e represents the base of the natural logarithm.

[0019] A planning event processing system for processing the maneuvering mode described in claim 1, characterized in that it includes a planning event processing module, wherein the maneuvering mode is used as an event input to the planning event processing module, the planning event processing module determines whether a collision event exists and divides the collision event into pre-collision event, collision event and post-collision event, determines the pre-collision event and collision event as a successful planning task state, determines the post-collision event as a failed planning task state, and outputs the planning event state after traversing all events.

[0020] The beneficial effects of this invention are as follows:

[0021] (1) Through multi-strategy orbital maneuvering algorithm and real-time mission time window sorting, it supports rapid calculation and synchronous multi-task processing of various propellant types and maneuvering modes, significantly shortens the planning cycle, meets diverse needs such as collision avoidance and reconnaissance observation, and improves the response speed of on-orbit missions.

[0022] (2) The integrated fuel balance real-time analysis formula combined with the dynamic control of the central control center enables precise propellant management and cataloging and orbit determination, reducing unnecessary consumption and improving the mission lifespan and space resource utilization efficiency of the maneuvering satellite.

[0023] (3) The planning event processing module automatically sorts events and determines the collision risk, and determines the pre-collision / collision event as a successful state and the post-collision event as a failed state, effectively avoiding potential collisions and ensuring the attitude stability and mission safety of the maneuvering star under high maneuverability conditions. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a flowchart of the steps in this invention;

[0026] Figure 2 This is a flowchart of the planning event processing module in this 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 only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention. Example

[0028] like Figure 1 As shown, a method for planning orbital missions of maneuvering satellites is presented. This invention provides an analysis of the maneuverability of multiple maneuvering satellites under the requirements of space environment resource scheduling and safety analysis, and further provides an effective and optimized method for orbital mission planning, as detailed below:

[0029] S1. Create a planning mission, set the orbital elements, propellant type and total fuel amount for each maneuvering satellite, and payload parameters. Payload parameters include optical telescope, SAR radar payload, lidar, beam angle (0-360°), distance, mission type (reconnaissance mission or control mission), mission start and end time, and illumination angle.

[0030] S2. Set the basic parameters of the target satellite. The target satellite refers to the satellite that is the target of the planned mission, specifically including:

[0031] S2.1 Set the target star's orbital elements and the distance between the maneuvering star and the target star.

[0032] S2.2 Set the arrival time and flight mode of the target satellite at the mission point. The flight modes include escort flight, fly-around flight, droplet fly-by flight and droplet fly-around flight. Generate the maneuvering satellite mission orbit elements based on the escort flight orbit, fly-around orbit algorithm and droplet configuration algorithm, and provide a visual orbit configuration display page.

[0033] S2.3. Set the location of the central control center on the settings page. The central control center is located on the ground and is the operation center for controlling the maneuvering satellite and the target satellite.

[0034] S3. Based on the above multiple constraint parameters, the control window algorithms for optical imaging satellites, radar imaging satellites, and electronic jamming satellites are invoked to perform maneuver analysis. The results of the maneuver analysis are mission time windows that satisfy all constraints. The mission time windows can be sorted and displayed in real time according to different optimization conditions, providing multi-mission synchronous calculation.

[0035] S4. After determining the mission time window, the orbital maneuver multi-strategy algorithm is called to calculate the maneuvering mode of the maneuvering satellite, such as double-pulse Lambert maneuver, multi-pulse Lambert maneuver, surface maneuver + radial-tangential linkage, CW double-pulse maneuver, and normal-tangential linkage. The return parameters of the orbital maneuver multi-strategy algorithm are a list of maneuvering mode parameters, including the number of orbital elements and the single pulse consumption. The orbital maneuver multi-strategy algorithm provides the maneuvering mode for the maneuvering satellite to reach the mission point.

[0036] S5. After determining the maneuvering mode of the maneuvering star, the system enters the planning event processing module. The planning event module determines whether a collision event exists based on the maneuvering mode to complete the planning task.

[0037] Preferably, the central control center analyzes the maneuvering satellite's fuel reserves in real time based on the fuel formula, catalogs and determines the target satellite's orbit, and provides forecasts. Users can then formulate new maneuvering plans and send them to control the maneuvering satellite's orbit changes, achieving dynamic control of the maneuvering satellite as it enters the situation simulation page. The fuel formula is as follows:

[0038]

[0039] Where m0 represents the initial total mass of the rocket carrying the maneuvering satellite, including the structure, payload and all propellant;

[0040] mf represents the final mass of the rocket after acceleration, that is, the dry mass after burning all the fuel;

[0041] Indicates the mass of propellant (fuel) consumed;

[0042] Δv represents the required velocity increment (unit: m / s), that is, the magnitude of the velocity change required for the rocket;

[0043] Isp stands for Specific Impulse (unit: seconds), a metric for measuring the efficiency of a propulsion system.

[0044] g0 represents the standard gravitational acceleration, which is approximately 9.80665 m / s².

[0045] e represents the base of the natural logarithm (approximately 2.71828).

[0046] The fuel formula analyzes the fuel remaining of the maneuvering satellite in real time, catalogs and determines the orbit of the target point and makes predictions. Users can then formulate a new maneuvering plan and send it to control the maneuvering satellite to change its orbit, thus achieving the goal of dynamic control of the maneuvering satellite. Example

[0047] A planning event processing system for implementing the method of Embodiment 1 includes a planning event processing module, as detailed below:

[0048] The event planning module sorts events by time and identifies historical event collisions. For example... Figure 2 As shown, the process begins by inputting an event list and sorting it chronologically. The sorted event list is then checked for collision events: if no collision events exist, all events are iterated through, marked as successful (status indicating whether the event was successfully planned), and then handed over to the event manager for processing, ending the process. If collision events exist, the process proceeds to the next step. All collision events are filtered by event type to form a collision event list. The earliest time (the earliest occurrence time of the collision event) is extracted from the collision event list. All events are iterated through, and based on the earliest collision time, they are categorized into three types: Collided events (events that are inherently collision events, marked as successful); Pre-collision events (events with times earlier than the earliest collision time, marked as successful); and Post-collision events (events with times later than the earliest collision time, marked as failed). All categorized events (success / failure status) are then handed over to the event manager for processing, ending the process.

[0049] The preceding description of this disclosure is intended to enable any person skilled in the art to make or use this disclosure. Various modifications to this disclosure will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not intended to be limited to the examples and designs described herein, but should be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0050] The embodiments of the present invention have been described in detail above. The description of the embodiments above is only for the purpose of helping to understand the method and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A planning method for a maneuvering satellite orbit mission, characterized in that, Includes the following steps: S1. Create a planning task and set the basic parameters of each maneuvering star; S2. Set the basic parameters of the target satellite. The target satellite refers to the satellite that is the object of the planned mission. Set the position point of the central control center. The central control center analyzes the fuel remaining of the maneuvering satellite in real time according to the fuel formula, catalogs and determines the orbit of the target satellite, and makes predictions. The user can formulate the maneuvering plan for the planned mission again and send it to perform control orbit changes of the maneuvering satellite to achieve dynamic control of the maneuvering satellite. The fuel formula is: Where m0 represents the initial total mass of the rocket, mf represents the final mass of the rocket after acceleration, mfuel=m0−mf represents the mass of propellant consumed, Δv represents the required velocity increment in m / s, i.e. the magnitude of the velocity change required by the rocket, Isp represents specific impulse, which is an indicator of the efficiency of the propulsion system, g0 represents standard gravitational acceleration, and e represents the base of the natural logarithm. S3. Using the basic parameters of the maneuvering satellite and the basic parameters of the target satellite as constraints, the algorithm is invoked to perform maneuver analysis. The maneuver analysis is obtained through the optical imaging satellite control window algorithm, the radar imaging satellite control window algorithm, and the electronic jamming satellite control algorithm. The result of the maneuver analysis is the mission time window that satisfies the constraints. S4. After determining the mission time window, the orbital maneuver multi-strategy algorithm is called to calculate the maneuvering mode of the maneuvering satellite to reach the mission point. The return parameters of the orbital maneuver multi-strategy algorithm are a list of maneuvering parameters, including the number of orbital elements and the single pulse consumption. S5. After confirming the maneuvering mode, proceed to the planning event processing module. The planning event module determines whether a collision event exists based on the maneuvering mode in order to complete the planning task.

2. The planning method according to claim 1, characterized in that, The basic parameters of the maneuvering satellite include the orbital elements, propellant type, total fuel volume, payload parameters, mission type, mission start and end times, and illumination angle.

3. The planning method according to claim 1, characterized in that, The basic parameters of the target satellite include the orbital elements of the target satellite, the distance between the maneuvering satellite and the target satellite, the time of arrival at the mission point, and the flight mode.

4. The planning method according to claim 1, characterized in that, The task time windows can be sorted and displayed in real time according to different optimization conditions, providing multi-task synchronous calculation.

5. The planning method according to claim 1, characterized in that, The event planning module sorts events by event time and modifies historical events based on the impact events.

6. A planning event processing system for processing the method of claim 1, characterized in that, The system includes a planning event processing module. The planning event processing module takes the motor mode as the event input. The planning event processing module determines whether there is a collision event and divides the collision event into pre-collision event, collision event and post-collision event. The pre-collision event and collision event are determined as planning task success status, and the post-collision event is determined as planning task failure status. After traversing all events, the planning event status is output.

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