Optimal Robust Design of Hybrid Rocket Engines

Pastrone, Dario Giuseppe; Casalino, Lorenzo

doi:10.1007/978-3-319-41508-6_10

Cited by 7 publications

(1 citation statement)

References 19 publications

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“…This management of the intrinsic uncertainties represents a preliminary approach to robust design, which the authors improved in Ref. [49] embedding uncertain parameters variations inside the optimization procedure, in place of an "a posteriori" check of optimal solutions off-design performance. Thus, a new optimization merit function is introduced, combining linearly the payload mass, which is unaffected by the uncertainties, with the average altitude violation with respect to target altitude, which, on the contrary, is affected by uncertainty because the actual insertion orbit depends on the actual value of the regression rate.…”

Section: Upper Stagementioning

confidence: 99%

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

2021

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Optimization of Hybrid Rocket Engines at Politecnico di Torino began in the 1990s. A comprehensive review of the related research activities carried out in the last three decades is here presented. After a brief introduction that retraces driving motivations and the most significant steps of the research path, the more relevant aspects of analysis, modeling and achieved results are illustrated. First, criteria for the propulsion system preliminary design choices (namely the propellant combination, the feed system and the grain design) are summarized and the engine modeling is presented. Then, the authors describe the in-house tools that have been developed and used for coupled trajectory and propulsion system design optimization. Both deterministic and robust-based approaches are presented. The applications that the authors analyzed over the years, starting from simpler hybrid powered sounding rocket to more complex multi-stage launchers, are then presented. Finally, authors’ conclusive remarks on the work done and their future perspective in the context of the optimization of hybrid rocket propulsion systems are reported.

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Section: Upper Stagementioning

confidence: 99%

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

2021

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Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Messineo

Kitagawa

Carmicino

et al. 2020

Journal of Spacecraft and Rockets

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Burning tests of a laboratory-scale hybrid rocket engine were carried out with gaseous oxygen and a microcrystallinewax based fuel to look into the feasibility of using an intrusive resistor-based sensor for measuring the fuel regression rate.This initial screening was driven by the need for real-time control of the oxidizer-to-fuel ratio in altering-intensity swirlingflow-type hybrid rocket engines aiming at performance optimization. To build up a framework for comparison with the measured data, a traditional ballistic reconstruction technique was critically revised; with the measured aft-chamber pressure and oxygen mass flow rate time histories, the fuel regression-rate and port diameter were reconstructed over the firing, by estimating the combustion efficiency with the constraint that calculated and measured fuel mass consumed are equal. This technique invariably suffers from the issue of presenting multiple solutions for the fuel mass flow rate in the proximity of the optimum mixture ratio, for which a novel variable-efficiency approach is proposed. Reconstructed data show that regression rate is nearly constant in each firing, yielding dependence upon the port diameter other than the mass flux.Resistor-sensor raw data displayed large deviation from the ballistic results for the slower burning rate of the sensor support.A detailed analysis is presented.

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Novel Comprehensive Technique for Hybrid Rocket Experimental Ballistic Data Reconstruction

Carmicino

Pastrone

2018

Journal of Propulsion and Power

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Optimal Robust Design of Hybrid Rocket Engines

Cited by 7 publications

References 19 publications

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Novel Comprehensive Technique for Hybrid Rocket Experimental Ballistic Data Reconstruction

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