| Nowadays,with the increasingly crowded Earth orbit,space missions closely related to human life are facing the threat of space debris.To ensure the safe progress of space missions and the implementation of Active Debris Removal(ADR),it is necessary to understand the rotational state of space debris.Currently,various observation methods such as optical observation,Satellite Laser Ranging(SLR),and radar provide multiple types of observation data for the study of rotational state.Due to the complexity of the space environment,the rotational state of space debris often undergoes significant changes that are difficult to determine over a long time scale,while it is often relatively stable over the time range of a single short arc.Research on space debris rotation state estimation methods based on multi-means short arc observ ation is conducive to obtaining more accurate and reliable instantaneous rotation state of multiple space objects,providing a foundation for the study of long-term evolution laws.Optical observation is an important and relatively easy observation method,which can obtain the light curve that describe the variation of space debris luminosity over time.In this paper,the light curve of Envisat(2002-009A),the prime candidate for ADR,from 2013 to 2015,is reanalyzed using the asteroid photometric astrometry method—Epoch method.The instantaneous rotation state estimated by the short arc changes over time.Compared with the controversial motion of the spin axis of Envisat in previous studies,a new law of long-term motion of the satellite’s spin axis is obtained.The spin axis of Envisat oscillates over a wide range between-55° and-85°from the orbital plane,with the peak values of the latitude distribution around-60° and-80°,instead of rotating steadily around the negative normal of the orbital plane.This conclusion provides observation data for the further study of Envisat dynamic model and supports the satellite removal work.In this paper,Epoch method is also used to analyze the light curve measured by the single photon counting system,and the rotation state of DMSP 5D-2 F11(1991-082A)is accurately estimated,which gives full play to the huge advantage of the ultra-high time resolution of the single photon light curve.Satellite laser ranging is the most accurate technology for tracking near-Earth objects,with a single ranging accuracy of up to millimeter level.The original observation data of SLR contain the distance to Earth of different positions of the satellite,and relative distance data reflecting rotation can be obtained through translation removal.Currently,the rotation state estimation methods based on SLR generally analyze the oscillation law of distance,which does not fully exploit the accuracy advantages of distance measurement and is difficult to be used for slow rotation targets.In addition,in order to meet the growing demand of space target monitoring,passive recognition,high-precision rotation state and orbit determination based on multiple Corner Cube Reflectors(CCRs)laser ranging are gradually studied and popularized.Therefore,this paper takes the observation data of multi-CCRs slow rotating rocket body CZ-2C R/B(2007-010B)as an example,and uses its high precision relative range sequence to study the rotation estimation method based on multi-CCRs spacecraft laser ranging.In order to solve the difficulty of short arc estimation of slow spin target,the distance measurement is combined with the vector azimuth measurement in the body coordinate system,and the observable attitude parameter is proposed based on the single reference vector method.The efficiency of initial value search is improved by reducing the dimension of the estimated parameter,and the initial value differential correction is used for higher accuracy attitude estimation.Then,from the analytical point of view,the complete mathematical relationship between the relative distance sequence and the target rotation state in laser ranging is studied,the analytical model of the rotation state solution is established,and a double vector attitude determination method based on the relative distance derivative is proposed.In addition,the 1-D distance measurement in laser ranging is extended to 2-D plane projection,which provides the basis for wider application of SLR.This study provides numerical,analytical and semi-numerical and semi-analytical methods for estimating the rotation state of multi-CCRs spacecraft,which makes up for the lack of effective methods for estimating the rotation state based on multi-CCRs relative distance sequence in traditional laser ranging studies.The research method is applicable to targets of various rotation speeds and rotation modes,and provides sufficient theoretical basis for spacecraft attitude analysis of different observation arcs and CCRs installation conditions in the future.Compared with previous studies on spin axis orientation estimation based on the law of range residual high frequency oscillation in ranging data,this study obtains more complete and accurate attitude information,which meets the growing practical needs of space target dynamic monitoring.Radar observation is an all-day,all-weather,active observation method that can measure the physical quantity that characterizes the ability of a target to scatter incident radar electromagnetic waves—Radar Cross Section(RCS).The RCS of complex scatterers such as satellites can fluctuate sharply with the change of incident angle of electromagnetic waves.With the improvement of the accurate calculation method of RCS,the RCS sequence based on radar observations can also estimate the rotational state of space debris.In this paper,the moment method commonly used in the calculation of RCS in the resonance region is used to simulate the RCS of the Object-B(2022-087B)at different incident wavelengths and angles.The instantaneous attitude of the three-axis stabilized satellite after failure is estimated by optimizing the cosine similarity between the simulation and the observation sequence of the RCS.In order to analyze the attitude change of the satellite,the possible rotation of the satellite after failure is studied by considering the rotation dynamics simulation of the gravity gradient moment of the Earth’s oblateness J2 term.It is found that the satellite will roll slowly and unstable when the initial angular velocity is very small,which is roughly consistent with the observation results of RCS.In addition,during the numerical extrapolation,it is found that the gravity gradient moment of the J2 term will produce a long-term term that accumulates with time on the spin of the satellite around the spindle,which indicates that the gravity gradient moment of different orders of Earth’s non-spherical gravitational field should also be considered in the research of space debris rotation dynamics with higher precision. |
PDF Full Text Request