6. An Earth-orbiting satellite has the following position and velocity vectors expressed in polar coor- dinates: T=8250 (km) v = 1.2054++ 7.02630 (km/s) Determine a) Angular momentum (magnitude), h b) Specific energy, e c) Semimajor axis, a d) Parameter, p e) Eccentricity, e f) Perigee and apogee radii, r, and ra HW1, Due: September 19, 2019, AE 313 Space Mechanics g) Flight path angle, y, at this instant h) True anomaly, f, at this instant. Partial Ans.: a) h58000 km2/s (obtain the exact answer), c) a 8700 km (obtain the exact answer), f) r =10238.56 km, g) y 10 deg (obtain the exact answer)] 7. At a particular instant in time, a tracking station determines that a space vehicle is at an altitude of 390.4 km with an inertial velocity of 9.7023 km/s and flight-path angle of 1.905 deg. Is this space vehicle in a closed orbit about the Earth or is it following an open-ended trajectory that will eventually "escape" Earth? Justify your answer. 8. An Earth-orbiting satellite has semimajor axis a = 8230 km and eccentricity e=0.12. Determine the satellite's maximum altitude above the Earth's surface. [Ans. 2839.6 km] 9. Two satellites are being tracked by ground-based radar stations. Their altitudes, inertial velocities, and flight path angles at a particular instant in time are shown in Table 1. Are these two satellites in the same orbit? Explain your answer. Hint: Compute the orbital parameters of the two satellites.] altitude (km) velocity (km/s) flight path angle (deg) object Satellite A 1769.7560 Satellite B 676.3674 6.8164 7.8504 4.9665 -6.8903 Table 1: See Problem 9. | Partial Ans.: a) h≈ 58000 km2/s (obtain the exact answer), c) a 8700 km (obtain the exact answer), f) ra 10238.56 km, g) y 10 deg (obtain the exact answer) | 7. At a particular instant in time, a tracking station determines that a space vehicle is at an altitude of 390.4 km with an inertial velocity of 9.7023 km/s and flight-path angle of 1.905 deg. Is this space vehicle in a closed orbit about the Earth or is it following an open-ended trajectory that will eventually "escape" Earth? Justify your answer. 8. An Earth-orbiting satellite has semimajor axis a 8230 km and eccentricity e = 0.12. Determine the satellite's maximum altitude above the Earth's surface. [Ans. 2839.6 km 9. Two satellites are being tracked by ground-based radar stations. Their altitudes, inertial velocities, and flight path angles at a particular instant in time are shown in Table 1. Are these two satellites in the same orbit? Explain your answer. Hint: Compute the orbital parameters of the two satellites.] object Satellite A altitude (km) velocity (km/s) flight path angle (deg) 1769.7560 Satellite B 676.3674 6.8164 7.8504 4.9665 -6.8903 Table 1: See Problem 9. 10. The ratio of apoapsis and periapsis radii for a particular satellite orbit is ra/rp eccentricity of the orbit. Ans. e 0.2308] 1.6. Determine the 11. An Earth-orbiting satellite is at an altitude of 700 km with inertial velocity 7.3944 km/s and flight path angle y 0. Is the satellite at perigee or apogee? Justify your answer.