Comparison of Optimization Techniques and Objective Functions Using Gas Generator and Staged Combustion LPRE Cycles

This paper compares various optimization techniques and objective functions to obtain optimum rocket engine performances. This research proposes a modular optimization framework that provides an optimum design for Gas Generator (GG) and Staged Combustion (SC) Liquid Propellant Rocket Engines. This p...

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Bibliographic Details
Published in:Applied sciences 2022-10, Vol.12 (20), p.10462
Main Authors: Khan, Suniya Sadullah, Qamar, Ihtzaz, Sohail, Muhammad Umer, Swati, Raees Fida, Ahmad, Muhammad Azeem, Qureshi, Saad Riffat
Format: Article
Language:English
Subjects:
Algorithms
Combustion
Design
design optimization
Designers
Engines
Estimates
Gas generators
genetic algorithm
Genetic algorithms
hybrid technique
Liquid Propellant Rocket Engine (LPRE)
Liquid propellant rocket engines
Liquid propellants
Objective function
Optimization
Optimization techniques
Propellant combustion
Search algorithms
Simulated annealing
Specific impulse
Thrust
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Summary:This paper compares various optimization techniques and objective functions to obtain optimum rocket engine performances. This research proposes a modular optimization framework that provides an optimum design for Gas Generator (GG) and Staged Combustion (SC) Liquid Propellant Rocket Engines. This process calculates the ideal rocket engine performance by applying seven different optimization techniques: Simulated Annealing (SA), Nelder Mead (NM), Cuckoo Search Algorithm (CSA), Particle Swarm Optimization (PSO), Pigeon-Inspired Optimization (PIO), Genetic Algorithm (GA) and a novel hybrid GA-PSO technique named GA-Swarm. This new technique combines the superior search capability of GA with the efficient constraint matching capability of PSO. This research also compares objective functions to determine the most suitable function for GG and SC cycle rocket engines. Three single objective functions are used to minimize the Gross Lift-Off Weight and to maximize Specific Impulse and the Thrust-to-Weight ratio. A fourth multiobjective function is used to simultaneously maximize both Specific Impulse and Thrust-to-Weight ratio. This framework is validated against a pump-fed rocket, and results are within 1% of the actual rocket engine mass. The results of this research indicate that PSO and GA-Swarm produce optimum results for all objective functions. Finally, the most suitable objective function to use while comparing these two cycles is the Gross Lift-Off Weight.
ISSN:2076-3417
2076-3417
DOI:10.3390/app122010462