Determine the sea-level effective exhaust velocity

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Reference no: EM131401238

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;

(d) the initial acceleration;

(e) the mass inverse ratio m0/mf .

Reference no: EM131401238

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