Multidisciplinary design and optimization of expendable launch vehicle for microsatellite missions

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Qasim Zeeshan ◽  
Amer Farhan Rafique ◽  
Ali Kamran ◽  
Muhammad Ishaq Khan ◽  
Abdul Waheed
Keyword(s):  
Research Effort ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Design And Development ◽  
Content Type ◽  
Design And Optimization ◽  
Design Variables ◽  
Development Costs

Purpose The capability to predict and evaluate various configurations’ performance during the conceptual design phase using multidisciplinary design analysis and optimization can significantly increase the preliminary design process’s efficiency and reduce design and development costs. This research paper aims to perform multidisciplinary design and optimization for an expendable microsatellite launch vehicle (MSLV) comprising three solid-propellant stages, capable of delivering micro-payloads in the low earth orbit. The methodology’s primary purpose is to increase the conceptual and preliminary design process’s efficiency by reducing both the design and development costs. Design/methodology/approach Multidiscipline feasible architecture is applied for the multidisciplinary design and optimization of an expendable MSLV at the conceptual level to accommodate interdisciplinary interactions during the optimization process. The multidisciplinary design and optimization framework developed and implemented in this research effort encompasses coupled analysis disciplines of vehicle geometry, mass calculations, aerodynamics, propulsion and trajectory. Nineteen design variables were selected to optimize expendable MSLV to launch a 100 kg satellite at an altitude of 600 km in the low earth orbit. Modern heuristic optimization methods such as genetic algorithm (GA), particle swarm optimization (PSO) and SA are applied and compared to obtain the optimal configurations. The initial population is created by passing the upper and lower bounds of design variables to the optimizer. The optimizer then searches for the best possible combination of design variables to obtain the objective function while satisfying the constraints. Findings All of the applied heuristic methods were able to optimize the design problem. Optimized design variables from these methods lie within the lower and upper bounds. This research successfully achieves the desired altitude and final injection velocity while satisfying all the constraints. In this research effort, multiple runs of heuristic algorithms reduce the fundamental stochastic error. Research limitations/implications The use of multiple heuristics optimization methods such as GA, PSO and SA in the conceptual design phase owing to the exclusivity of their search approach provides a unique opportunity for exploration of the feasible design space and helps in obtaining alternative configurations capable of meeting the mission objectives, which is not possible when using any of the single optimization algorithm. Practical implications The optimized configurations can be further used as baseline configurations in the microsatellite launch missions’ conceptual and preliminary design phases. Originality/value Satellite launch vehicle design and optimization is a complex multidisciplinary problem, and it is dealt with effectively in the multidisciplinary design and optimization domain. It integrates several interlinked disciplines and gives the optimum result that satisfies these disciplines’ requirements. This research effort provides the multidisciplinary design and optimization-based simulation framework to predict and evaluate various expendable satellite launch vehicle configurations’ performance. This framework significantly increases the conceptual and preliminary design process’s efficiency by reducing design and development costs.

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.

Using “Design Envelopes” to Aid in the Preliminary Design of Rotating Turbomachinery

2004 ◽  
Author(s):  
Aaron R. Byerley ◽  
Keith M. Boyer ◽  
Ian Halliwell
Keyword(s):  
Solution Space ◽  
Operating Conditions ◽  
Preliminary Design ◽  
Design And Optimization ◽  
Performance Requirements ◽  
Design Variables ◽  
Target Values ◽  
Angular Velocities ◽  
Stage Properties ◽  
Independent Design

This paper describes a systematic and graphical approach for leading undergraduates or other inexperienced designers through the preliminary design process of rotating turbomachinery. It is based upon the general principles of classic thermal system design and optimization. The paper explains the steps required to arrive at a combination of design variables that yield a “design envelope” or workable domain of aerodynamic and mechanical solution space. Once the “design envelopes” for both the compressor and the turbine have been identified, the rotor angular velocities are matched. The students are introduced to the design concept of moving from the workable to the optimal using two Mathcad®11 worksheets described in the paper. The process begins with obtaining the performance requirements and operating conditions form cycle analysis which leads to the selection of the aerodynamic design point. A system of equations based upon aerodynamic and mechanical principles is then optimized for both the compressor and the turbine. Two animated surface plots allow the designer to keep track of three independent design variables as they influence the value of an objective function that represents how close each design alternative is to achieving the target values of several important stage properties. Constraint maps reveal the range of acceptable rotor angular velocities for both the compressor and the turbine which enables a match to be made. The design approach is explained using a descriptive example of a multistage compressor and turbine operating on a high pressure spool. This paper provides a clear roadmap for systematically arriving at the correct combination of multiple design inputs that yield the appropriate multiple outputs required in the preliminary design of rotating turbomachinery.

Multidisciplinary Design Optimization Approach for a Small Solid Propellant Launch Vehicle Conceptual Design Using Hybrid Simulated Annealing

2011 ◽  
Vol 110-116 ◽  
pp. 4765-4771 ◽  
Author(s):  
Masoud Ebrahimi ◽  
Jafar Roshanian ◽  
Farnaz Barzinpour
Keyword(s):  
Simulated Annealing ◽  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Solid Propellant ◽  
Launch Vehicle ◽  
Multidisciplinary Design ◽  
Optimization Approach ◽  
Design Variables ◽  
Base Method ◽  
Hybrid Simulated Annealing

Multidisciplinary Design Optimization (MDO) of a two-stage Small Solid Propellant Launch Vehicle (SSPLV) by simulated annealing (SA) Method is investigated. Propulsion, weight, aerodynamic (geometry) and 3degree of freedom (3DOF) trajectory simulation disciplines are used in an appropriate combination. Suitable design variables, technological-functional constraints and minimum launch weight objective function are considered. To handle constraints augmentation of constraints to cost using penalty coefficients are used. Results are compared with gradient-base method that shows the ability of SA to escape local optimums.

Multidisciplinary Design and Optimization for Fluid-Structure Interactions

2002 ◽  
Author(s):  
Franco Mastroddi ◽  
Claudia Bonelli ◽  
Luigi Morino ◽  
Giovanni Bernardini
Keyword(s):  
Incompressible Flow ◽  
Multidisciplinary Optimization ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Fluid Structure Interactions ◽  
Design And Optimization ◽  
Induced Drag ◽  
Introductory Overview ◽  
Modeling Techniques ◽  
Numerical Formulation

The paper presents an introductory overview of modeling techniques used by the authors for MDO–PD (MultiDisciplinary Optimization – Preliminary Design). The algorithms used by the authors in their MDO–PD code for modeling aerodynamics and aeroelasticity are reviewed. For the aerodynamic analysis, a boundary–element potential–flow method is used (for simplicity, only the incompressible–flow formulation is presented). The methodology is geared specifically towards MDO–PD for civilian aircraft. The numerical formulation is applied to a specific, highly–innovative aircraft configuration proposed by Frediani, which has, as a distinguishing feature, a low induced drag. A comparison with an MDO-PD of a standard wing configuration has been included.

Fuzzy risk assessment for electro-optical target tracker

2016 ◽  
Vol 33 (6) ◽  
pp. 830-851 ◽  
Author(s):  
Soumen Kumar Roy ◽  
A K Sarkar ◽  
Biswajit Mahanty
Keyword(s):  
Failure Mode ◽  
Failure Modes ◽  
Linear Equations ◽  
Mode Analysis ◽  
Failure Behavior ◽  
Membership Functions ◽  
Design And Development ◽  
Effect Analysis ◽  
Content Type ◽  
Criticality Analysis

Purpose – The purpose of this paper is to evolve a guideline for scientists and development engineers to the failure behavior of electro-optical target tracker system (EOTTS) using fuzzy methodology leading to success of short-range homing guided missile (SRHGM) in which this critical subsystems is exploited. Design/methodology/approach – Technology index (TI) and fuzzy failure mode effect analysis (FMEA) are used to build an integrated framework to facilitate the system technology assessment and failure modes. Failure mode analysis is carried out for the system using data gathered from technical experts involved in design and realization of the EOTTS. In order to circumvent the limitations of the traditional failure mode effects and criticality analysis (FMECA), fuzzy FMCEA is adopted for the prioritization of the risks. FMEA parameters – severity, occurrence and detection are fuzzifed with suitable membership functions. These membership functions are used to define failure modes. Open source linear programming solver is used to solve linear equations. Findings – It is found that EOTTS has the highest TI among the major technologies used in the SRHGM. Fuzzy risk priority numbers (FRPN) for all important failure modes of the EOTTS are calculated and the failure modes are ranked to arrive at important monitoring points during design and development of the weapon system. Originality/value – This paper integrates the use of TI, fuzzy logic and experts’ database with FMEA toward assisting the scientists and engineers while conducting failure mode and effect analysis to prioritize failures toward taking corrective measure during the design and development of EOTTS.

Minimizing supply chain disruption risk through enhanced flexibility

2009 ◽  
Vol 39 (5) ◽  
pp. 404-427 ◽  
Author(s):  
Joseph B. Skipper ◽  
Joe B. Hanna
Keyword(s):  
Supply Chain ◽  
Multiple Regression ◽  
Planning Process ◽  
Research Effort ◽  
Risk Exposure ◽  
Contingency Planning ◽  
Management Support ◽  
Supply Chain Disruption ◽  
Content Type ◽  
Disruption Risk

PurposeThe purpose of this paper is to examine the use of a strategic approach (contingency planning) to minimize risk exposure to a supply chain disruption. Specifically, the relationship between several attributes of a contingency planning process and flexibility are examined.Design/methodology/approachThis effort develops a model that will provide both researchers and practitioners a means of determining the attributes with the highest relationship to flexibility. The model is then tested using multiple regression techniques.FindingsBased on the sample used in this survey, top management support, resource alignment, information technology usage, and external collaboration provide the largest contributions to flexibility. Flexibility has been shown to enhance the ability to minimize risk exposure in the event of a supply chain disruption.Research limitations/implicationsIn this research effort, the multiple regression results produced an R2 of 0.45, indicating that additional variables of interest may need to be identified and investigated. Furthermore, a wider range of respondents could make the results more generalizable.Practical implicationsThis effort will help to allow managers at multiple levels to understand the primary planning attributes to use to increase flexibility.Originality/valueThe paper develops a model that can be used to identify the specific areas that can lead to improved flexibility. Based on the model, managers, and planners can develop appropriate strategies for minimizing risk exposure in the event of a supply chain disruption.

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