Abstract
Probability of collision between non-cooperative space object (NCSO) and the reference spacecraft (RS) has been increased drastically over the past few decades. The traditional method is difficult to identify the maneuvering of non-cooperative space object. In the present paper, not only positions and velocities, but also accelerations of non-cooperative space object are estimated as parameters by the extended Kalman filtering based on setting up the state linear equation and measurement model of the non-cooperative space object. The algorithm for predicting collision probability is derived from position error ellipsoid, and the algorithm for determining maneuvering probability is derived from maneuvering acceleration and its error ellipsoid, which can be employed to identify whether the upcoming space object is being maneuvered. An epoch Earth-centered inertial (EECI) coordinate system is suggested to replace Earth-centered inertial (ECI) to simplify coordinate transformation. Finally, a set of simulations were conducted to validate the proposed algorithms with the simulated measurement data of the reference spacecraft space-borne millimeter-wave (MMW) radar.
Highlights
The non-cooperative space object (NCSO) refers to the space object which cannot provide effective information, such as the disabled or discarded satellites, space debris, or the rival spacecraft in space which may surveil or harm the reference spacecraft (RS) that is performing a mission
epoch Earth-centered inertial (EECI) coordinate system does not rotate with the rotation of the Earth and its directions are fixed in the inertial space, so it is convenient to describe motion of the spacecraft or space objects
The first set of simulation is utilized as an example to verify the proposed algorithm, and the latter three sets of simulations are performed for further testing and statistical analysis
Summary
The non-cooperative space object (NCSO) refers to the space object which cannot provide effective information, such as the disabled or discarded satellites, space debris, or the rival spacecraft in space which may surveil or harm the reference spacecraft (RS) that is performing a mission. The orbit determination methods for primary spacecraft and other space objects were presented by Qui et al, and the criteria for collision prediction algorithm and to filter the cataloged objects were proposed [9]. Orbit parameters (such as the classic orbital elements, or positions and velocities) of NCSO are determined in the Earth-centered inertial (ECI) coordinate system In this process, there are some problems to be solved. In addition to positions and velocities, accelerations of NCSO are estimated as parameters based on the linear state equation of the NCSO, using measurement data provided by RS space-borne MMW radar [8]. An epoch Earth-centered inertial (EECI) coordinate system is suggested to replace ECI, the amount of on-orbit calculation for the transformation between coordinate systems can be reduced
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