A tracking method for a satellite using a prediction system, the prediction system including a space surveillance network (SSN) radar, an optical wide-field patrol network (OWL-Net), and a server, wherein the server includes a communication interface, a storage medium, and a processor, the method comprising:
- receiving, by the server through the communication interface, osculating orbital elements of a satellite transmitted from the OWL-Net or two-line elements (TLE) of the satellite from the SSN radar;
- storing, by the server through the processor, the osculating orbital elements of the satellite or the TLE of the satellite in the storage medium in the server;
- obtaining, by the server through the processor, an initial orbit information of the satellite with respect to an observation epoch from the osculating orbital elements or the two-line elements (TLE), and an initial value of a parallactic refraction scale factor;
- performing, by a high-precision orbit propagator in the server, orbit propagation with respect to an observation epoch by applying a dynamics model;
- performing, by the processor, observer-centered satellite optical observation modeling including the parallactic refraction scale factor to calculate estimated observation data;
- obtaining, by the server through the communication interface, actual optical observation data from an actual optical observation device including the OWL-Net or the SSN radar;
- calculating, by the processor in the server, an observation residual between the actual optical observation data and the estimated observation data calculated via the observation modeling reflecting a parallactic refraction;
- obtaining, by the processor in the server, an estimated value of the parallactic refraction scale factor and an estimated satellite position and velocity using the observation residual and a batch least square estimation algorithm;
- and
- tracking, by the processor in the server, an orbit of the satellite using the estimated value of the parallactic refraction scale factor and the estimated satellite position and velocity to control the satellite such that a risk of a collision between the satellite and space debris is minimized,
- wherein the estimated observation data includes a right ascension (α) and a declination (δ), and the right ascension (α) and the declination (δ) are calculated according to Equation 1:
- α
- =
- α
- 0
- +
- ε
- Aaberr
-
- _
-
- RA
- +
- ε
- Daberr
-
- _
-
- RA
- +
- Δ
-
- t
- ·
- α
- .
- +
- K
- ·
- Δ
-
- R
-
- sin
-
- q
- cos
-
- δ
- 0
- ,
- [
- Equation
-
- 1
- ]
- δ
- =
- δ
- 0
- +
- ε
- Aaberr
-
- _
-
- DEC
- +
- ε
- Daberr
-
- _
-
- DEC
- +
- Δ
-
- t
- ·
- δ
- .
- +
- K
- ·
- Δ
-
- R
-
- cos
-
- q
- ,
- where, α0 and δ0 denote the right ascension and declination in the J2000 coordinate system, respectively;
- εAaberr_RA and εDaberr_RA denote corrections of annual aberration and diurnal aberration for the right ascension, respectively;
- εAaberr_DES and εDaberr_DEC denote corrections of annual aberration and diurnal aberration for the declination, respectively;
- Δt denotes a time bias correction value;
- {dot over (α)} and {dot over (δ)} denotes a ratio of ascension to declination;
- ΔR denotes the parallactic refraction;
- q denotes a parallactic angle;
- and K denotes a value of the parallactic refraction scale factor.