Analytic approach to determine optimal conditions for maximizing altitude of sounding rocket: Flight in standard atmosphere

Abstract

The analytic approach to determine the optimal conditions for maximizing altitude of a sounding rocket is extended to the case in which the rocket flies in a standard atmosphere where the air density as well as the gravitational acceleration changes with altitude. The one-dimensional rocket momentum equation including thrust, gravitational force, and aerodynamic drag is solved. Flight in the standard atmosphere is analyzed by dividing the whole flight time into small intervals where the drag parameter and gravitational acceleration can be treated as constant in each interval. The analytic approach gives piecewise exact solutions of the rocket velocity and altitude that agree well with the numerical ones. A characteristic equation exists and provides accurate predictions of the optimal conditions for maximizing altitude at burn-out state or apogee.

Modeling and dynamic characteristic simulation of air-cooled proton exchange membrane fuel cell stack for unmanned aerial vehicle

“…The ambient temperature and oxygen partial pressure varies with altitude which greatly affect the performance of the stack. According to the International Standard Atmosphere (ISA) model [40,41], the variation of atmospheric temperature 𝑇𝑇 atmo (K)…”