Simulation Framework for Orbit Propagation and Space Trajectory Visualization Figure 18. Inclination ðEi ¼ 0:073Þ: Figure 20. Argument ofperigee ðEv ¼ 0:142Þ: Figure 19. RAAN ðEV ¼ 0:241Þ: Figure 21. True anomaly ðEu ¼ 0:072Þ: Table 4. Relative Percentage Error of State Vectors Time (s) E^rx 2600 5200 7800 10 400 13 000 15 600 18 200 20 800 23 400 26 000 18 2.19E-04 8.55E-05 1.54E-04 3.60E-04 7.57E-04 1.55E-03 3.56E-03 1.75E-02 8.17E-03 3.96E-03 E^ry 3.56E-04 1.22E-03 1.32E-02 1.54E-04 2.00E-04 1.34E-04 3.05E-04 1.57E-03 6.80E-03 2.74E-02 E^rz E^vx 1.13E-04 2.56E-04 1.35E-03 2.45E-03 8.74E-04 3.87E-04 1.70E-04 1.31E-03 5.46E-03 5.78E-02 IEEE A&E SYSTEMS MAGAZINE 1.92E-04 1.76E-04 9.07E-04 1.51E-02 3.46E-03 2.14E-03 1.61E-03 8.14E-04 3.36E-03 2.66E-02 E^vy 1.24E-02 5.65E-04 1.54E-05 4.35E-05 3.71E-04 2.22E-03 7.14E-02 7.68E-03 4.82E-03 3.83E-03 E^vz 3.96E-04 3.39E-04 3.27E-04 1.82E-04 1.95E-04 1.27E-03 7.60E-03 1.20E-02 5.94E-03 1.79E-03 AUGUST 2021