Solid Rocket Motor Design Optimization Using Genetic Algorithm

2014 ◽  
Vol 905 ◽  
pp. 502-506 ◽  
Author(s):  
Fredy M. Villanueva ◽  
Lin Shu He ◽  
Da Jun Xu
Keyword(s):  
Genetic Algorithm ◽  
Design Optimization ◽  
Optimal Solution ◽  
Optimization Method ◽  
Rocket Motor ◽  
Design Parameters ◽  
Optimization Approach ◽  
Solid Rocket Motor ◽  
Conceptual Design Phase ◽  
Solid Rocket

A design optimization approach of a solid propellant rocket motor is considered. A genetic algorithm (GA) optimization method has been used. The optimized solid rocket motor (SRM) is intended to use as a booster of a flight vehicle, and delivering a specific payload following a predefined prescribed trajectory. Sensitivity analysis of the optimized solution has been conducted using Monte Carlo method to evaluate the effect of uncertainties in design parameters. The results show that the proposed optimization approach was able to find the convergence of the optimal solution with highly acceptable value for conceptual design phase.

Multidisciplinary Design Optimization of Small Canister-Launched Space Launch Vehicle Using Genetic Algorithm

2013 ◽  
Vol 302 ◽  
pp. 583-588 ◽  
Author(s):  
Fredy M. Villanueva ◽  
Lin Shu He ◽  
Da Jun Xu
Keyword(s):  
Genetic Algorithm ◽  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Optimal Solution ◽  
Optimization Method ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Multidisciplinary Design ◽  
Optimization Approach ◽  
Design Variables

A multidisciplinary design optimization approach of a three stage solid propellant canister-launched launch vehicle is considered. A genetic algorithm (GA) optimization method has been used. The optimized launch vehicle (LV) is capable of delivering a microsatellite of 60 kg. to a low earth orbit (LEO) of 600 km. altitude. The LV design variables and the trajectory profile variables were optimized simultaneously, while a depleted shutdown condition was considered for every stage, avoiding the necessity of a thrust termination device, resulting in reduced gross launch mass of the LV. The results show that the proposed optimization approach was able to find the convergence of the optimal solution with highly acceptable value for conceptual design phase.

scholarly journals Solid Rocket Motor Design Using Hybrid Optimization

2012 ◽  
Vol 2012 ◽  
pp. 1-9 ◽  
Author(s):  
Kevin Albarado ◽  
Roy Hartfield ◽  
Wade Hurston ◽  
Rhonald Jenkins
Keyword(s):  
Hybrid Approach ◽  
Optimal Solution ◽  
Solution Space ◽  
Axial Direction ◽  
Pattern Search ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Thin Sections ◽  
Solid Rocket

A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections along the axial direction. Grains with circular perforated stars, wagon wheels, and dog bones can be considered and multiple tapered sections can be constructed. The hybrid approach to optimization is capable of exploring large areas of the solution space through particle swarming, but is also able to climb “hills” of optimality through gradient based pattern searching. A preliminary method for designing tapered internal geometry as well as tapered outer mold-line geometry is presented. A total of four optimization cases were performed. The first two case studies examines designing motors to match a given regressive-progressive-regressive burn profile. The third case study studies designing a neutrally burning right circular perforated grain (utilizing inner and external geometry tapering). The final case study studies designing a linearly regressive burning profile for right circular perforated (tapered) grains.

Analysis of Lap Region between Skirt and Composite Case under Axial Force in Solid Rocket Motor

2011 ◽  
Vol 71-78 ◽  
pp. 4357-4360
Author(s):  
Hong Chao Liu ◽  
Chun Guang Wang ◽  
Yong Qiong Liu ◽  
Bo Yuan
Keyword(s):  
Carrying Capacity ◽  
Element Model ◽  
Optimization Method ◽  
Rocket Motor ◽  
Load Carrying Capacity ◽  
Solid Rocket Motor ◽  
Proposed Model ◽  
Load Carrying ◽  
Solid Rocket ◽  
Main Factor

To study load carrying capacity for Lap Region between the Skirt and Composite Case(LRSC) of the solid rocket motor(SRM),made the stress of layer out of skirt as the research object, established the two-dimensional axisymmetric finite element model for compsite case,analysed the main factor(lap length) for carrying capacity of LRSC,and verified the conclusions by calculation.Optimized the lap length ranged from 40mm to 60mm, proposed model of the optimal lap length and optimization method,calculated optimal lap length under different axial loads.The results show that, with the increase of lap length of skirt, the load bearing capacity of LRSC enhances first and depresses then,exists a great value,which of the corresponding lap length is optimal;With the increase of axial load,optimal lap length monotonously will increase.

Optimizing a solid rocket motor boosted ramjet powered missile using a genetic algorithm

2006 ◽  
Vol 181 (2) ◽  
pp. 1720-1736 ◽  
Author(s):  
Roy J. Hartfield ◽  
Rhonald M. Jenkins ◽  
John E. Burkhalter
Keyword(s):  
Genetic Algorithm ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket

Solid rocket motor design employing an efficient performance matching approach

2018 ◽  
Vol 233 (11) ◽  
pp. 4052-4065 ◽  
Author(s):  
Wu Zeping ◽  
Wang Donghui ◽  
Wang Wenjie ◽  
Patrick N Okolo ◽  
Zhang Weihua
Keyword(s):  
Rocket Motor ◽  
Test Cases ◽  
Optimization Approach ◽  
Solid Rocket Motor ◽  
One Dimensional ◽  
Time Stepping ◽  
Efficient Performance ◽  
Motor Design ◽  
Solid Rocket ◽  
Performance Validation

Solid rocket motor design matching the thrust requirement of the overall vehicle has become an exigent task. In the present research, an efficient performance matching optimization approach is proposed and applied to the solid rocket motor design. To obtain reliable solid rocket motor designs, refined performance evaluation is accomplished successfully based on the coupling of the level set grain burnback analysis and one-dimensional ballistic simulation by the time-stepping algorithm. Due to the heavy computing burden of the coupled performance solver, a novel progressive matching optimization approach is proposed. This approach depends on partial but not full-burn thrust profile to eliminate inferior candidates, predict superior candidates, advance the simulation and drive the candidates converging to the specified performance. Validation of the proposed solid rocket motor design approach is carried out by two test cases possessing different thrust requirements, and results indicate that the proposed approach is practical and efficient.

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