CN-121454964-B - Low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception

CN121454964BCN 121454964 BCN121454964 BCN 121454964BCN-121454964-B

Abstract

A low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception comprises the following steps of S1, constructing an off-line mapping model, generating a mapping model between space environment parameters and an optimal orbit maintaining threshold by taking global fuel efficiency optimization as a target through simulation and optimization algorithm, S2, sensing and controlling on-line, namely sensing the space environment parameters in real time, dynamically determining the self-adaptive threshold under the current space environment based on the mapping model, monitoring the orbit attenuation of a satellite, and triggering the orbit to maintain maneuvering when the orbit attenuation reaches or exceeds the self-adaptive threshold. By constructing an intelligent mapping model of a space environment-optimal threshold value, the triggering threshold value kept by the track is updated from a fixed value to a variable dynamically self-adapting to space weather, so that the optimization of fuel consumption is realized on a global level, and meanwhile, the control efficiency of the space weather calm period, the track safety under extreme events such as magnetic storm and the like are effectively considered.

Inventors

CHEN BO
YU HAIQUAN
CHEN LUE
ZHANG YAMIN

Assignees

哈尔滨工业大学(深圳)(哈尔滨工业大学深圳科技创新研究院)

Dates

Publication Date: 20260505
Application Date: 20260106

Claims (9)

1. The low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception is characterized by comprising the following steps of: S1, constructing an offline mapping model, namely generating a mapping model between a space environment parameter and an optimal orbit maintenance threshold value by taking global fuel efficiency optimization as a target through simulation and an optimization algorithm, wherein the space environment parameter is a physical parameter capable of representing the dominant influence of a space weather state on the air density of a thermal layer, the global fuel efficiency optimization takes the fuel consumption of unit orbit attenuation as an optimization index, and the fuel efficiency is defined as the ratio of the orbit maneuvering total speed increment to the total resistance attenuation; s2, sensing and controlling on line, namely sensing space environment parameters in real time, dynamically determining an adaptive threshold value under the current space environment based on the mapping model, monitoring the attenuation of a satellite orbit, and triggering the orbit to keep maneuvering when the attenuation of the orbit reaches or exceeds the adaptive threshold value.
2. The method of claim 1, wherein the velocity delta calculation employs a pulsed thrust model or a continuous low thrust model; The pulse thrust model models the track maintenance maneuver as an instantaneous velocity impulse, wherein the velocity increment comprises a velocity increment part calculated based on a track transfer theory and a velocity increment part based on atmospheric resistance compensation, and the atmospheric resistance compensation is calculated in a dynamic environment comprising an atmospheric model through high-precision track integration; The continuous low thrust model models orbit maintenance maneuver as a continuous process, with velocity delta determined by integrating thrust acceleration, which is the ratio of thrust to satellite mass over time, over the maneuver period.
3. The method according to claim 1, wherein in step S1, the optimization algorithm comprises a parametric scan method or bayesian optimization; The parameter scanning method comprises the steps of discretely generating a candidate threshold sequence in a predefined threshold range, executing long-term track maintenance simulation on each candidate threshold, executing track restoration maneuver and recording speed increment when the track attenuation reaches the candidate threshold in the simulation, calculating fuel efficiency under the candidate threshold when the accumulated track attenuation reaches a preset value, and selecting the candidate threshold with optimal fuel efficiency as an optimal threshold after traversing all the candidate thresholds; The Bayesian optimization comprises the steps of constructing a relation between a proxy model fitting threshold and fuel efficiency, guiding iteration to select a candidate threshold for simulation through an acquisition function, updating the proxy model until convergence, and finding a global optimal threshold.
4. The method of claim 1, wherein the mapping model is in the form of a look-up table or a fitting function; The lookup table stores optimal thresholds corresponding to different space environment scenes, and the fitting function represents the mapping relation between the space environment parameters and the optimal thresholds through a mathematical function.
5. The method of claim 1, wherein in step S2, sensing the spatial environment parameters in real time includes acquiring geomagnetic activity indexes and solar activity parameters through a satellite-to-ground link or a satellite model; Dynamically determining the adaptive threshold based on the mapping model includes matching the perceived spatial environment parameters with parameter ranges in a lookup table to obtain an optimal threshold, or substituting the perceived spatial environment parameters into a fitting function to calculate the optimal threshold.
6. The method of claim 1, wherein monitoring the satellite orbit delta attenuation in step S2 comprises calculating an average orbit semi-major axis of the satellite in real time and calculating its delta attenuation relative to a nominal value.
7. The method of claim 1, wherein in step S2, triggering the track maintenance maneuver includes performing a track restoration using a pulsed thrust model or a continuous low thrust model; the pulse thrust model applies velocity impulse at a specific track point, and the continuous small thrust model starts the thruster to continuously work until the required velocity increment is accumulated.
8. The method of claim 1, wherein the spatial environment parameters include geomagnetic activity index and solar activity parameters.
9. A computer program product comprising a computer program which, when executed by a processor, implements a low-orbit satellite dynamic adaptive threshold orbit maintenance method based on spatial environment parameter perception according to any one of claims 1 to 8.

Description

Low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception Technical Field The invention relates to a space orbit control technology, in particular to a low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception. Background Currently, in orbit maintenance control of low-orbit satellites, a reactive control strategy based on a fixed threshold is a mainstream technical scheme commonly adopted and disclosed in the industry. The scheme sets a constant orbit height or orbit semi-major axis deviation tolerance (i.e., a fixed threshold), and when it is monitored that the satellite orbit attenuation reaches a preset tolerance, the triggering orbit remains mobile, returning the satellite orbit to the nominal height. The working principle and flow of the existing low orbit satellite orbit maintenance scheme can be summarized as the following steps of ① setting a fixed threshold value, namely presetting a fixed orbit maintenance threshold value (upper limit and lower limit of an orbit semi-long axis) in a ground planning or on-board control system, ② orbit monitoring, namely continuously monitoring orbit parameters of a satellite, particularly a semi-long axis and an average semi-long axis, of the satellite during the orbit running period through an on-board navigation system (such as a GPS), ③ threshold value judging, namely comparing the real-time monitored orbit semi-long axis with a nominal semi-long axis, calculating attenuation, ④ triggering and executing, namely triggering orbit maneuver to restore the orbit semi-long axis to the nominal value (or the preset semi-long axis upper limit) when the attenuation reaches or exceeds the fixed threshold value (or the semi-long axis is attenuated to the preset semi-long axis lower limit), and ⑤ circulation, namely re-entering the monitoring state after the maneuver is completed, and the process is repeated. Although the fixed threshold strategy is simple and easy to implement, its inherent "one-touch" static nature results in significant drawbacks in a dynamically changing spatial environment. On the one hand, in severe space weather (such as geomagnetic storm), the safety is poor, the fuel cost is increased sharply, when strong geomagnetic storm occurs, the high-rise atmospheric density is increased sharply, the satellite orbit attenuation rate is increased greatly, the fixed threshold strategy is possibly too large, the reaction is slow, the excessive attenuation of the satellite orbit is possibly caused, even the satellite orbit is lower than the safety altitude, task risks are brought, the required speed increment for returning the satellite from the excessively low orbit is increased in a nonlinear way, the mechanical energy consumption is increased sharply, the high-cost passive response is realized, on the other hand, in calm space weather, the high-rise atmospheric density is kept too conservative, the fuel waste is caused, the existing strategy is to ensure the safety in extreme space weather (such as strong magnetic storm), the set fixed threshold is usually kept conservative (namely the threshold is smaller), however, in the space weather calm period, the atmospheric resistance is small, the orbit attenuation is slow, the excessively small fixed threshold forces the satellite to move too frequently, the orbit keeps moving, the additional energy consumption is accumulated, the orbit life of the satellite is limited, and in essence, the existing technology is used for dealing with most of the extreme situations, and the fuel efficiency is sacrificed in normal situations. In summary, existing fixed threshold orbit maintenance strategies, due to their static nature, have the problem of being unable to respond to dynamic changes in the spatial environment, resulting in wasted fuel due to excessive control during calm periods, and potentially compromising safety due to slow reactions during extreme spatial weather events. It should be noted that the information disclosed in the above background section is only for understanding the background of the application and thus may include information that does not form the prior art that is already known to those of ordinary skill in the art. Disclosure of Invention The invention aims to overcome the defects in the background art and provide a low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter sensing. In order to achieve the above purpose, the present invention adopts the following technical scheme: A low-orbit satellite dynamic self-adaptive threshold orbit maintaining method based on space environment parameter perception comprises the following steps: S1, constructing an offline mapping model, namely generating a mapping model between space environment parameters and an optimal track maintenance threshold value by taking global