Trajectory of aerodynamically stable rocket during its thrust phase is obtained; rocket or missile is interpreted as point mass (with variable weight) acted upon by aerodynamic drag, thrust and gravity; method of solution is best suited to those cases wherein tangential acceleration is large, and may be applied to rocket and missile design problems.
Trajectory of rocket with thrust
Jet Propulsion
Jet Propulsion ; 28 , n 7
1958
7 pages
Article (Journal)
English
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