Hybrid rocket motors present a competitive edge among space applications, as they are flexible, safe, reliable, and low-cost. The motor design and operation are contingent on the type of designated mission; therefore, it is useful to couple design and trajectory optimization. This approach is especially needed for hybrid rockets in which a unique combustion process links thrust and specific impulse. In this chapter, a multidisciplinary optimization code is described for the use of designing hybrid rocket motors. There are few parameters which define the design of the hybrid engine, whereas the trajectory optimization is characterized by continuous controls. Due to the difference between these unknowns, a mixed optimization procedure has been developed. To maximize mission performance, direct optimization of engine design variables is coupled with the trajectory indirect optimization. Some interesting applications of the the aforementioned procedure are presented.

Integrated Design-Trajectory Optimization for Hybrid Rocket Motors / Pastrone, Dario Giuseppe; Casalino, Lorenzo - In: Modeling and Optimization in Space Engineering / G. fasano, J.D. Pinter. - STAMPA. - New York Heidelberg Dordrecht London : Springer, 2012. - ISBN 9781461444688. - pp. 343-362 [10.1007/978-1-4614-4469-5]

Integrated Design-Trajectory Optimization for Hybrid Rocket Motors

PASTRONE, Dario Giuseppe;CASALINO, LORENZO
2012

Abstract

Hybrid rocket motors present a competitive edge among space applications, as they are flexible, safe, reliable, and low-cost. The motor design and operation are contingent on the type of designated mission; therefore, it is useful to couple design and trajectory optimization. This approach is especially needed for hybrid rockets in which a unique combustion process links thrust and specific impulse. In this chapter, a multidisciplinary optimization code is described for the use of designing hybrid rocket motors. There are few parameters which define the design of the hybrid engine, whereas the trajectory optimization is characterized by continuous controls. Due to the difference between these unknowns, a mixed optimization procedure has been developed. To maximize mission performance, direct optimization of engine design variables is coupled with the trajectory indirect optimization. Some interesting applications of the the aforementioned procedure are presented.
2012
9781461444688
9781461444695
Modeling and Optimization in Space Engineering
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/2503593
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