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Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System
- 1. Masahiro Kanazaki Tokyo Metropolitan University Atthaphon Ariyarit Tokyo Metropolitan University Kazuhisa Chiba Hokkaido Institute of Technology Koki Kitagawa Japan Aerospace Exploration Agency Toru Shimada Japan Aerospace Exploration Agency Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System The Eighth China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems ○ May 25-29, 2014, Gyeongju, Korea
- 2. Background1 What is hybrid rocket engine? 2 Beneficial feature of HRE ・Low cost due to simple stricture ・Stop and restart of combustion⇒ Control・Safety Hybrid Rocket Engine(HRE) ： rocket which stores fuel and oxidizer by different phases. Solid fuel + Liquid oxidizer :
- 3. 3 Background2 Difference compared with existent rocket Solid rocket Liquid rocket HRE：Fuel and oxidizer are mixed after the ignition is initiated. → Fuel and oxidizer are preliminary mixd. Several parameter should be optimized for suitable combustion → Design using heuristic approach Multi-combustion by the control of the oxidizer supplement Solid fuel rocket Liquid fuel rocket
- 4. Backgourng3 multi-combustion Stop/restart of combustion during total combustion time Maximize down range by coasting Minimization of maximum acceleration Maximization of duration time over the target altitude 4 Off On On
- 5. 5 Contents Background What is hybrid rocket engine? Multi-combustion Objectives Design methods HRE design using evolutionary algorithm Formulation Maximization of altitude and minimization of gross weight(problem1) Minimization of maximum acceleration and minimization of gross weight (problem2) Maximization of duration time over target altitude and minimization of gross weight(problem3) Results and discussions Conclusions
- 6. Objective Design exploration of launch vehicle (LV) using HRE which can carried out multi-combustion Discussion of beneficial feature via several design problem Non-dominated solution by genetic algorithm (GA) Comparison between HRE w/ multi-combustion and w/o multi-combustion 6
- 7. Design method1/2 Overview of evaluation process of HRE 7 tGatr n oxiport )( K., Kosugi, A. Oyama, K. Fujii, and M. Kanazaki., "Multidisciplinary and Multi-objective Design Exploration Methodology for Conceptual Design of a Hybrid Rocket," Infotech@aerospace2011, (2011) AIAA 2011-1634
- 8. Design method2/2 Optimizer and visualization Non-dominated Sorting Genetic Algorithm-II (NSGA-II) 20populations and 200generation Parallel coordinate plot : PCP 8 Evaluation of LV
- 9. Formulation1/3 Problem1 Maximization of maximum altitude (Altmax)/ minimization of gross weight(Mtot) 9 Design variables for LV Design variables for multi-combustion L/D：Aspect ratio of vehicle
- 10. Formulation2/3 Problem2 Minimization of maximum acceleration(accmax)/ minimization of gross weight(Mtot) 10 MT-135 （JAXA’s rocket for weather observation（Altmax=60 km）） Alttarget：target altitude Design variables for LV Design variables for multi-combustion
- 11. Formulation3/3 Problem3 Maximization of duration time over Alttarget(Tduration)/ minimization of gross weight(Mtot) 11 Design variables for LV Design variables for multi-combustion
- 12. Result1/8 12 Non-dominated soluitions（Problem1） Maximization of Altmax minimization Mtot Similar result Difference for high altitude 50generations100generations150generations200generations
- 13. Result2/8 Design Space(problem1) Similar trend in design space Interval time of combustion dv8(tinter) is almost zero. →Multi-combustion has not been required. w/o multi-combustion w/ multi-combustion
- 14. Result3/8 Problem1 Multi-combustion is not effective for maximization of Altmax → Altmax is only reduced by the temporal stop of combustion. 14
- 15. Result4/8 Non-dominated solutions（Problem2） Minimization accmax and minimization Mtot 15 accmax is reduced by multi-combustion 50generations100generations150generations200generations
- 16. Result5/8 Design space(problem2) Trend of dv4(tburn) is different between two cases. Sorting by accmax，difference of dv5(Pc) could be observed. Due to multi-combustion，accmax could be reduced. w/o multi-combustion w/ multi-combustion
- 17. Result6/8 Design space(problem2) Colored by dv7(tstop) (w/ multi-combustion) ) Correlation between dv4(tburn)，dv8(tinter)
- 18. Result7/8 Problem2 Acceleration is stopped, when the combustion is stopped. Convergence of MOGA is not good because it is difficult to satisfy of the constraint regarding the altitude. 18
- 19. Result8/8 Non-dominated solutions（Problem４） Maximization Tduration and minimization Mtot 19 Difference is little. 200generations
- 20. Conclusions Design exploration for the LV using HRE which can carried out multi-combustion Evaluation for HRE which can carried out multi- combustion has been developed Design problem evaluation by solving several deign problems Multi-combustion is not effective to maximize the altitude/ the duration time. Better solution could be obtained by the multi- combustion in the minimization of maximum acceleration. 20