This paper uses an Analytic Trajectory Optimization Model (ATOM) to develop efficient computational techniques for the use in the early phase of low-thrust mission analysis. The validity of the expression for burning time from ATOM is extended over the full acceleration range, from impulsive to continuous burning. The computational techniques are demonstrated in two problems: 1) the selection of propulsion system parameters for maximum payload and 2) the optimization of the “mix” of high-thrust chemical boost and low-thrust electrical propulsion.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering