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CN-121973956-A - Method and system for planning orbit task of motor star

CN121973956ACN 121973956 ACN121973956 ACN 121973956ACN-121973956-A

Abstract

The invention discloses a planning method and a planning system for a motor star orbit task, and belongs to the field of aerospace simulation analysis. The method comprises the steps of creating a planning task, setting basic parameters of a maneuvering star, setting basic parameters of a target star and a central position point of a central control, performing maneuvering analysis by taking the parameters of the maneuvering star, the parameters of the target star and the central position point of the central control as constraints to obtain a task time window meeting the constraints, calling a track maneuvering multi-strategy algorithm to calculate after the task time window is determined to obtain a maneuvering mode and maneuvering parameter list of the maneuvering star reaching the task point, and finally entering a planning event processing module to sort events according to time and judge whether collision events exist or not to output success/failure states of the planning task. The master control center evaluates the fuel allowance in real time based on a fuel formula and supports a user to dynamically formulate and issue a track-changing scheme, so that the integrated planning of maneuvering star task window calculation, maneuvering strategy selection and safety check is realized.

Inventors

  • XU PEIHAO
  • LI CHENGUANG
  • ZHANG QING
  • Dang kang
  • WANG BOCHEN

Assignees

  • 中科星图测控技术股份有限公司

Dates

Publication Date
20260505
Application Date
20251230

Claims (10)

  1. 1. The planning method for the orbit task of the motor vehicle is characterized by comprising the following steps of: S1, creating a planning task and setting basic parameters of each mobile star; s2, setting basic parameters of a target star, wherein the target star refers to a satellite serving as a task object in the planning task; S3, taking the mobile star basic parameters and the target star basic parameters as constraint condition calling algorithms to carry out mobile analysis, wherein the result of the mobile analysis is a task time window meeting the constraint condition; S4, after the task time window is determined, a track maneuvering multi-strategy algorithm is called to calculate to obtain a maneuvering mode that the maneuvering star reaches a task point; S5, entering a planning event processing module after confirming the maneuvering mode, and judging whether an impact event exists according to the maneuvering mode by the planning event module so as to complete a planning task.
  2. 2. The planning method of claim 1, wherein the automotive star base parameters include orbit count, type of propellant, total fuel, load parameters, mission type, mission start end time, illumination angle of the automotive star.
  3. 3. The planning method of claim 1 wherein the target star base parameters include a target star orbit number, a distance of the mobile star from the target star, a time to mission point and a flight pattern.
  4. 4. The planning method of claim 1, wherein the maneuver analysis is obtained by an optical imaging satellite control window algorithm, a radar imaging satellite control window algorithm, an electronic interference satellite control algorithm.
  5. 5. A planning method according to claim 1, wherein the task time window is displayed in real time according to different preferred conditions, providing a multi-task synchronous calculation.
  6. 6. The planning method of claim 1, wherein the orbital maneuver multi-strategy algorithm maintains a plurality of maneuver modes, and the return parameters are a list of maneuver parameters including the number of tracks and the consumption of a single pulse.
  7. 7. The planning method of claim 1 wherein the planning event processing module orders events by event time and modifies historical events based on the impact events.
  8. 8. The planning method according to claim 1, wherein a master control center position point can be set in S2, the master control center analyzes the fuel allowance of the mobile star in real time according to a fuel formula, catalogs and orbits the target star and forecasts, a user can make the planning task maneuvering scheme again, and the control orbital transfer of the mobile star is sent to dynamically control the mobile star.
  9. 9. The method of planning of claim 8 wherein the fuel formula is: ; Wherein m0 represents the initial total mass of the rocket, mf represents the final mass of the rocket after acceleration is completed, Representing the mass of propellant consumed, deltav represents the required velocity increment in m/s, i.e. the speed of the rocket to be changed, isp represents the specific impulse (SpecificImpulse 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.
  10. 10. A planned event processing system for processing the maneuver of claim 1, comprising a planned event processing module, wherein the maneuver is used as an event to be input into the planned event processing module, the planned event processing module judges whether an impact event exists and divides the impact event into a pre-impact event, an impacted event and a post-impact event, judges the pre-impact event and the impacted event as a planned task success state, judges the post-impact event as a planned task failure state, and outputs a planned event state after traversing all the events.

Description

Method and system for planning orbit task of motor star Technical Field The invention relates to the field of aerospace simulation analysis, in particular to a planning method and a planning system for a motor star orbit task. Background The motorized star refers to a satellite with motorized capability, and the existing motorized star propulsion and motorized means mainly comprise chemical propulsion, electric propulsion, cold air propulsion and the like. The chemical propulsion has the advantages of larger thrust, quick response, higher propellant consumption, limited task life, higher electric propulsion ratio, high propellant utilization rate, suitability for long-term track maintenance and transfer, smaller thrust, long maneuvering period, difficulty in meeting the quick maneuvering demands such as emergency avoidance and the like, simple cold air propulsion structure, small pollution, fine pulse control and limited deltav capacity. Meanwhile, the gesture control usually depends on a reaction flywheel, a magnetic torquer or a control moment gyro and the like, and high gesture precision can be realized, but under the conditions of high maneuvering and frequent track changing, the problems of momentum accumulation, energy consumption increase, control coupling complexity and the like are easy to occur. Therefore, aiming at the diversified demands of collision avoidance, reconnaissance observation, on-orbit service and the like, more mobile star platforms with stronger maneuverability, quick response and higher control precision are needed to be put into charge so as to improve task adaptability, on-orbit safety and space resource utilization efficiency. Disclosure of Invention Based on the analysis, the invention provides a planning method for a motor star orbit task, which comprises the following specific implementation steps: S1, creating a planning task and setting basic parameters of each mobile star; s2, setting basic parameters of a target star, wherein the target star refers to a satellite serving as a task object in the planning task; S3, taking the mobile star basic parameters and the target star basic parameters as constraint condition calling algorithms to carry out mobile analysis, wherein the result of the mobile analysis is a task time window meeting the constraint condition; S4, after the task time window is determined, a track maneuvering multi-strategy algorithm is called to calculate to obtain a maneuvering mode that the maneuvering star reaches a task point; S5, entering a planning event processing module after confirming the maneuvering mode, and judging whether an impact event exists according to the maneuvering mode by the planning event module so as to complete a planning task. Preferably, the automotive star basic parameters comprise the orbit number of the automotive star, the type of the material propellant, the total amount of fuel, the load parameter, the type of task, the start and end time of the task and the illumination angle. Preferably, the target star base parameters include a target star orbit number, a distance of the mobile star from the target star, a time to mission point and a flight pattern. Preferably, the maneuver analysis is obtained by an optical imaging satellite control window algorithm, a radar imaging satellite control window algorithm, an electronic interference satellite control algorithm. Preferably, the task time window can be displayed in real time according to different preferred conditions, so as to provide multi-task synchronous calculation. Preferably, the track maneuvering multi-strategy algorithm maintains a plurality of maneuvering modes, and the return parameters are a maneuvering parameter list comprising track numbers and single pulse consumption. Preferably, the planning event handling module orders events by event time and modifies historical events according to the impact events. Preferably, a central control center position point can be set in the S2, the central control center analyzes the fuel allowance of the maneuvering star in real time according to a fuel formula, catalogs and orbits the target star and predicts the target star, and a user can make the planning task maneuvering scheme again and send the maneuvering star to control orbit change so as to dynamically control the maneuvering star. Preferably, the fuel formula is: Wherein m0 represents the initial total mass of the rocket, mf represents the final mass of the rocket after acceleration is completed, Representing the mass of propellant consumed, deltav represents the required velocity increment in m/s, i.e. the speed of the rocket to be changed, isp represents the specific impulse (SpecificImpulse 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. A planned event processing system for processing the maneuver of claim 1, comprising a planne