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Multidisciplinary Design Optimization of an Air Launch Satellite Launch Vehicle by Considering the Coupled Slosh–vehicle Dynamics

Keshavarz Mohammadian, Moein | 2020

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53916 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Fathi, Mohsen
  7. Abstract:
  8. In this thesis, the multidisciplinary design of liquid propellant satellite launch vehicle has been done by taking into consideration the effects of fuel sloshing. At first, the theory of multidisciplinary design and one-level architecture with the label of multidisciplinary feasibility have been used. In the following, Gravitational Search Algorithm (GSA) and Particle swarm optimization (PSO) have been developed. Then, the multidisciplinary design cycle began with the design of the liquid propellant system. In the propulsion section, the selection of the optimal fuel, the design of the nozzle, motor and the selection of the optimal engine cycle considering the geometric and mass calculations of the propulsion system have been done. In the next step, examining the aerodynamic issues and nose design with thermal constraints, and shell design based on aerodynamic loading have been done. Then, the calculation of reliability and cost estimation have been performed based on semi-empirical relationships obtained from space project data and space market. Afterwards, with the help of Bézier curve, the optimal launch vehicle trajectory design has been done. In the next step, the control-ability of the satellite against the sloshing has been investigated and finally the results have been validated with the available samples. The final results of the optimal multidisciplinary design cycle are given
  9. Keywords:
  10. Slosh Dynamics ; Fuel Sloshing ; Launch Vehicle ; Reliability ; Multi-Disciplinary Design Optimization ; Launch Vehicle Cost

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