Multidisciplinary Design Optimization Approach to Conceptual Design of a LEO Earth Observation Microsatellite

Ravanbakhsh, Alí; Mortazavi, Mahdi; Roshanian, Jafar

doi:10.2514/6.2008-3259

Cited by 20 publications

(11 citation statements)

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“…In traditional satellite MDO applications, designers are typically interested in formulating optimization problems using mass of the satellite [Ravanbakhsh et al., ], cost of the satellite [Scialom, ], or some combination of characteristics as the objective function [Hassan and Crossley, , ; John et al., ]. These objectives are chosen as proxies for the true preference, such as profit or mission success.…”

Section: Study 1—consistency In System Preferencementioning

confidence: 99%

“…However, typical MDO objective functions are generally only proxies for the true system preference (e.g., cost, weight, or performance). For example, in satellite design, cost or mass are often used as proxies for profit, given the assumption that lowest mass will reduce costs or that the direct minimization of cost will produce greater profit [Mosher, ; Wertz and Larson, ; Futron, ; Hassan and Crossley, ; Scialom, ; Richie, Lappas, and Palmer, ; Hassan and Crossley, ; Ravanbakhsh, Mortazavi, and Roshanian, ; Ebrahimi, Farmani, and Roshanian, ; Wang, Xu, and Xia, ; Wu, Huang, and Wu, ; John et al., ; Wu et al., ]. Often, multiobjective optimization is used as a means of including more than one objective in a single function in an attempt to explore trade‐offs among these objectives [Hassan and Crossley, ; Jilla and Miller, ].…”

Section: Introductionmentioning

confidence: 99%

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Increased System Consistency through Incorporation of Coupling in Value‐Based Systems Engineering

2017

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The design of large-scale complex engineered systems involves hundreds to thousands of designers making decisions across different organizations and at different levels of organizational hierarchy. These systems are designed within a systems engineering framework, where requirements are used as proxies for stakeholder preference. Requirements drive the development process and are flowed across organizations and down through the organizational hierarchies. Value-driven design offers a new perspective where the preferences of the stakeholder are communicated directly through a decomposable value function, rather than decomposable requirements, thereby enabling improved consistency in system preference. This paper investigates two key aspects of achieving improved system consistency through a valuebased systems engineering approach, using a commercial satellite system as a testbed. The paper first contrasts the diverse systems that result from traditional requirements-based versus preference-based formulations, demonstrating how a value-based approach aids in capturing the true preferences of the stakeholder in problem formulation. The paper demonstrates the importance of using system couplings to enable an improved accuracy for value function decomposition. The paper demonstrates that ensuring system analysis consistency through use of system sensitivities can overcome issues pertaining to: dependencies of attributes; inadequately capturing system interactions; and direct modification of attributes to determine value impact. C⃝ 2017 Wiley Periodicals, Inc. Syst Eng 20: 21-44, 2017

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Section: Study 1—consistency In System Preferencementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Increased System Consistency through Incorporation of Coupling in Value‐Based Systems Engineering

2017

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“…Multidisciplinary design optimization (MDO) focuses on maximizing the performance and reducing the costs of complex systems that involve multiple interacting disciplines [16][17][18][19][20]. Specifically in this work, MDO takes into account the structural mass, aerodynamics, propulsion, and trajectory disciplines in the design of the vehicle.…”

Section: System Modeling and Optimization Algorithm Descriptionsmentioning

confidence: 99%

A Multiobjective, Multidisciplinary Design Optimization of Solid Propellant Based Space Launch Vehicle

Zafar

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper proposes an approach for the multidisciplinary design & optimization of space launch vehicle, wherein the structure/mass, aerodynamics, propulsion and the trajectory system design are performed simultaneously using non-dominated sorting based genetic algorithm. The design problem is posed as an optimization problem in which all the discipline parameters constitute the design variables, which are used to optimize the multi-objective function, thereby resulting in an optimal overall design. The approach is demonstrated by application to the integrated design of a four stage solid launch vehicle. The mission is to deliver predefined payload to the low earth (circular) orbit. An existing, real world system has been used to validate the multistage launch vehicle system model. Nomenclature E a = ratio of thrust in vacuum to thrust in ground D = solid rocket motor diameter, m cr d = throat diameter, m ex d = exit diameter, m o G = vehicle liftoff mass, kg I G = mass of guidance system, steering system and instrument section, kg prop G = mass of propulsion system, kg noz G = mass of nozzle, kg case G = mass of motor case, kg shell G = mass of combustion chamber shell, kg coating G = mass of coating inside, kg silver G = mass of grain silver, kg red G = mass of redundancy of grain, kg aux G = mass of auxiliary parts, kg E spo I = ground effective specific impulse, sec c p = combustion chamber pressure, N/m 2 m p = ratio of total mass to x-sectional area, kg/m 2 k t = running time of ith stage solid rocket motor, sec ε = expansion ratio 1 Doctoral student, School of Astronautics, Student member AIAA, zafar6909@yahoo.com 2 Professor, School of Astronautics, helinshu@sina.com 3 Associate Professor, School of Astronautics, xdj@buaa.edu.cn Downloaded by ROKETSAN MISSLES INC. on February 4, 2015 | http://arc.aiaa.org | 2 gn λ = fineness of grain k µ = ratio of dry mass to total mass o ν = mass to thrust ratio

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“…In traditional satellite MDO applications, designers are interested in formulating optimization problems using mass of the satellite, cost of the satellite or some combination of characteristics as the objective function [26,51,[72][73][74][75][76][77][78][79][80][81]. These objectives are chosen as proxies for the true preference, such as profit or mission success.…”

Section: Chapter 3 Satellite Systemmentioning

confidence: 99%

An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study

Kannan¹

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The following specific research questions were formed based on the issues identified in the current systems engineering processes. Research question 1 "Can Value-Driven Design (VDD) and Multidisciplinary Design Optimization (MDO) together enable system designs that are consistent with stakeholder desires and consistent in system physics?" This research question will be addressed by creating a value function formulation associated with a satellite system example that captures the true preference(s) of the stakeholder and by capturing the couplings present in the system using multidisciplinary analysis thereby ensuring consistency in system physics. Comparisons will be made between traditional objective function formulations and value formulation to reflect how a value-based approach yields the stakeholder-desired system design. Research question 2 "Can incorporation of coupling information in value function decomposition in a hierarchically decomposed system provide greater potential for system optimization by enabling consistency in communication of system value preferences as well as enabling more realistic and informed tradeoffs?" This research question will be tackled by proposing a Value-Based Systems Engineering (VBSE) framework that is founded on VDD and MDO principles that supports system optimization in a

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Multidisciplinary Design Optimization Approach to Conceptual Design of a LEO Earth Observation Microsatellite

Cited by 20 publications

References 1 publication

Increased System Consistency through Incorporation of Coupling in Value‐Based Systems Engineering

Increased System Consistency through Incorporation of Coupling in Value‐Based Systems Engineering

A Multiobjective, Multidisciplinary Design Optimization of Solid Propellant Based Space Launch Vehicle

An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study

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