An earth-orbiting satellite has a perigee radius of 7000 km and an apogee radius of 1 km. what true anomaly (delta f) is swept out between t = 0.5 hr. and t = 1.5 hr. after perigee passage? what area is swept out by the position vector during that time interval? a satellite orbits venus with pericenter radius of 7, 000 km and apocenter radius of 70, 000 km. find: orbit eccentricity, orbit semimajor axis (km), orbit period (hr), orbit specific energy (km^2/sec^2), velocity at pericenter (km/s), and velocity at apocenter (km/sec). find in internet/book the value of the venus gravitational constant mu. consider an orbit with eccentricity e = 0.1 and semi-major axis a = 37,000 km, and a spacecraft located at the true anomaly phi =325. compute the time of (light (in hours) to another position characterized by the eccentric anomaly e_2 = 59.