com.github.amsacode.predict4java

Class DeepSpaceSatellite

java.lang.Object

com.github.amsacode.predict4java.AbstractSatellite

com.github.amsacode.predict4java.DeepSpaceSatellite

All Implemented Interfaces:

Satellite

public class DeepSpaceSatellite
extends AbstractSatellite

DeepSpaceSatellite.

Author:

g4dpz

Field Summary

Fields inherited from class com.github.amsacode.predict4java.AbstractSatellite

ASTRONOMICAL_UNIT, CK4, EARTH_GRAVITATIONAL_CONSTANT, EARTH_RADIUS, EARTH_ROTATIONS_PER_SIDERIAL_DAY, EARTH_ROTATIONS_RADIANS_PER_SIDERIAL_DAY, MFACTOR, PERIGEE_156_KM, QOMS2T, RHO, S, SOLAR_RADIUS, SOLAR_RADIUS_KM, SPEED_OF_LIGHT

Fields inherited from interface com.github.amsacode.predict4java.Satellite

CK2, DEG2RAD, EARTH_RADIUS_KM, EPSILON, J2_HARMONIC, J3_HARMONIC, J4_HARMONIC, TWO_PI, TWO_THIRDS, XKE

Constructor Summary

Constructors

Constructor and Description
DeepSpaceSatellite(TLE tle) DeepSpaceSatellite Constructor.

Method Summary

Modifier and Type	Method and Description
protected void	calculateSDP4(double tsince) This function is used to calculate the position and velocity of deep-space (period > 225 minutes) satellites.

Methods inherited from class com.github.amsacode.predict4java.AbstractSatellite

calculatePhase, calculatePositionAndVelocity, calculateSatelliteGroundTrack, calculateSatelliteVectors, calculateSatPosForGroundStation, converge, getEclipseDepth, getPosition, getQoms24, getS4, getTLE, invert, julianDateOfYear, magnitude, mod2PI, setPerigee, sqr, willBeSeen

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

DeepSpaceSatellite

public DeepSpaceSatellite(TLE tle)

DeepSpaceSatellite Constructor.

Parameters:

tle - the three line elements

Method Detail

calculateSDP4

protected void calculateSDP4(double tsince)

This function is used to calculate the position and velocity of deep-space (period > 225 minutes) satellites. tsince is time since epoch in minutes, tle is a pointer to a tle_t structure with Keplerian orbital elements and pos and vel are vector_t structures returning ECI satellite position and velocity. Use Convert_Sat_State() to convert to km and km/S.

Parameters:

tsince - time since the epoch

position - the position

velocity - the velocity

satPos - the position of the satellite