JAQAR Astrodynamics Package - ESA

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DATO Problem ModellingAscent Trajectory (3/4)Optimised Flight ParametersDATO is able to optimise both space vehicle design and its trajectory.For Vehicle Design: (each stage)• Thrust over Weight ratio at ignition• Initial propellant massGLOW(Gross Lift-Off Weight)
DATO Problem ModellingAscent Trajectory (4/4)Optimised Flight ParametersFor Trajectory Design:1. Lift-off sequence2. Gravity turn orOptimised pitch control lawMaximising the DE Fitnessascent functionThat includes payload massand Glow ratio, wanted altitudeand wanted velocity on theorbit as well as constraints onmaximum heat flux andejection of the fairing• In case selected by the user, best functioning of the upper stage isobtained via optimisation of Coast-arc duration.
Page 1 and 2: JAQAR Astrodynamics PackageTools fo
Page 3 and 4: Features• Dedicated tools for ded
Page 5 and 6: DATODescent & Ascent Trajectory Opt
Page 7 and 8: DATO Software Structure(1/2)DATO is
Page 9 and 10: DATO Optimisation MethodGenetic Alg
Page 11: DATO Problem ModellingAscent Trajec
Page 15 and 16: DATO Problem ModellingDescent Traje
Page 17 and 18: R # x $ y02 2DATO Problem Modelling
Page 19 and 20: R # x $ y02 2DATO Test CasesAscent
Page 21 and 22: R # x $ y02 2DATO Test CasesDescent
Page 23 and 24: R # x $ y02 2DATO Conclusions (1/2)
Page 25 and 26: JAQAR and STK• JAQAR and engineer
Page 27: Questions?For more information:•

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