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rocket::rocket(string name, double mass, double dia, const engine eng):
PI(3.1415926), rocket_name(name), diameter(dia), mass_dry(mass),
engine1(eng), drag_coefficient(0.75), grav_const(9.8),
area((diameter/2)*(diameter/2)*PI)
{
velocity = 0;
altitude = 0;
time = 0;
interval->tv_sec = 0.2;
interval->tv_nsec = 0;
G = 0;
F = 0;
drag_force = 0;
}
engine::engine(const engine& eng):pro_mass(eng.pro_mass), exit_area(eng.exit_area),
interval(eng.interval), type_name(eng.type_name), casing_mass(eng.casing_mass),
mass_decrement(eng.mass_decrement), thrust(0), impulse(0), burn_time(0),
press(20000)
{
}
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