Three translational and 3 rotational equilibrium equations for orbital vehicle subject to aerodynamic and jet reaction forces are derived using modified flight-path axis system for translational equations; analog computer mechanization of these equations in both real and fast time; novel technique for division which preserves favorable multiplier scaling; specific machine results demonstrate accurate solution of close-satellite trajectories, including re-entry from satellite altitudes to sea level.
Flight simulation of orbital and re-entry vehicles
IRE -- Trans Electronic Computers
IRE -- Transactions on Electronic Computers ; EC-11 , n 4
1962
9 pages
Aufsatz (Zeitschrift)
Englisch
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