Abstract—The paper presents some aspects regarding the mathematical model and performance evaluation of a three stages microlauncher with a payload up to 50 kg. This work uses two separate models dedicated for each flight phase. For the ascending phase, we will use a three degrees of freedom model in quasi–velocity frame. For the orbital phase we will use a Kepler model, and for the orbital injection a Gauss perturbing model. The results analyzed will be in quasi-velocity frame but also some orbital parameters will be presented. Using these models, the microlauncher performances will be evaluated. The novelty of the paper consists in orbital injection approach, with optimal maneuvers description.
Index Terms—Mathematical model, microlauncher performances, orbital injection, optimal maneuvers.
Teodor-Viorel Chelaru is with University Politehnica of Bucharest, Romania (e-mail: teodor.chelaru@upb.ro).
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Cite: Teodor-Viorel Chelaru, "Performances Evaluation for Microlauncher, Mathematical Model," International Journal of Modeling and Optimization vol. 8, no. 4, pp. 197-201, 2018.
