1. For a satellite cruising in a circular orbit at an altitude of 500 km, determine the period of revolution, the flight speed, and the energy expended to bring a unit mass into this orbit.
2. A large ballistic rocket vehicle has the following characteristics: propellant mass flow rate: 12 slugs/sec (1 slug = 32.2 lbm = 14.6 kg); nozzle exit velocity: 7100 ft/sec; nozzle exit pressure: 5 psia (assume no separation); atmospheric pressure: 14.7 psia (sea level); takeoff weight: 12.0 tons (1ton = 2000 lbf); burning time: 50 sec; nozzle exit area: 400 in. 2 Determine
(a) the sea-level thrust;
(b) the sea-level effective exhaust velocity;
(c) the initial thrust-to-weight ratio;
(d) the initial acceleration;
(e) the mass inverse ratio m0/mf .