Equation of motion for powered flight of particular stage of multistage vehicle is reduced to first-order linear differential equation in vehicle weight, whose coefficients are known functions of time, by assumption that trajectory is known; design parameters include total weight, payload weight, specific impulse, propellant mass fraction, and vehicle diameter; it is possible to include specified constraints on vehicle such as fineness ratio or burning rate of solid propellants; method for choosing best propellant and chamber pressure from given set of propellants, and example of determining optimum chamber pressure for sustainer stage of two-stage vehicle.
Rocket design for specified trajectory
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 2 , n 2
1965
5 pages
Article (Journal)
English
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Rocket design for a specified trajectory
AIAA | 1965
|Rocket trajectory optimization
Engineering Index Backfile | 1965
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