1) For an orbit with perigee altitude of 300 km and apogee altitude of 800 km, what is the magnitude of the position vector (in km) when the spacecraft has just passed perigee by 30 deg? 2) The...

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1) For an orbit with perigee altitude of 300 km and apogee altitude of 800 km, what is the magnitude of the position vector (in km) when the spacecraft has just passed perigee by 30 deg? 2) The NPSAT-1 satellite was launched in June 2019 into a circular orbit of 720 km altitude by 24 deg inclination. What is its period in seconds? 3) For a spacecraft orbiting the earth with perigee altitude of 250 km and apogee altitude of 26,500 km, what is its specific mechanical energy (km2/sec2)? 4) (Not the same as previous question) For a spacecraft orbiting the earth with pergee altitude of 250 km and apogee altitude of 28,000 km. If the spacecraft's distance from earth's center is 30,000 km, what is its velocity in km/sec? 5) For a geosynchronous orbit (circular orbit) with period of 23 hours, 56 minutes, what is its semimajor axis in kilometers? 6) A Hohmann transfer is used to move a spacecraft from a circular orbit altitude of 225 km to a co-planar circular orbit altitude of 3500 km. What is the Total ΔV in meters per sec for the maneuver? 7) A spacecraft is in a circular orbit at 400 km altitude and 26 deg inclination. In order to make a simple plane change of the orbit to a 51.6 deg inclination, what is the magnitude in kilometers per second of the ΔV for the maneuver?