Multidisciplinary design optimization of a small solid propellant launch vehicle using system sensitivity analysis

2008 ◽  
Vol 38 (1) ◽  
pp. 93-100 ◽  
Author(s):  
Jahangir Jodei ◽  
Masoud Ebrahimi ◽  
Jafar Roshanian
Keyword(s):  
Sensitivity Analysis ◽  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Solid Propellant ◽  
Launch Vehicle ◽  
Multidisciplinary Design ◽  
System Sensitivity

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.

scholarly journals Multifidelity Multidisciplinary Design Optimization of Integral Solid Propellant Ramjet Supersonic Cruise Vehicles

2019 ◽  
Vol 2019 ◽  
pp. 1-18 ◽  
Author(s):  
Xiaojian Sun ◽  
Jianquan Ge ◽  
Tao Yang ◽  
Qiangqiang Xu ◽  
Bin Zhang
Keyword(s):  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Solid Propellant ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Flight Trajectory ◽  
Traditional Design ◽  
Study Results ◽  
Optimization Parameters ◽  
Different Levels

Integral solid propellant ramjet (ISPR) supersonic cruise vehicles share the characteristic that they are highly integrated configurations. The traditional design of vehicles cannot achieve a balance between computational expense and accuracy. A multifidelity multidisciplinary design optimization (MDO) platform has been developed in this study. The focus of the platform is on ISPR supersonic cruise vehicles. Firstly, codes of discipline with different levels of fidelity (LoF) were established, such as geometry, aerodynamics, radar cross-section calculations, propulsion, mass, and trajectory discipline codes. Secondly, two MDO frameworks were constructed through discipline codes. A low LoF MDO framework is suitable for conceptual design, and a medium LoF MDO framework is suitable for preliminary design. Finally, taking the optimization problem with the minimum overall detection probability of flight trajectory as an example, the low LoF framework first explores the entire design space to achieve the mission requirements, and then, the medium LoF MDO framework accepts the low LoF framework optimization parameters. Hence, the optimization target is reached with more detailed parameters and higher fidelity. Additionally, an example for a solid propellant missile with minimum total mass is tested by the platform. The study results show that the multifidelity MDO framework not only exploits interactions between the disciplines but also improves the accuracy of optimization results and reduces the iteration time.

scholarly journals Preliminary study on launch vehicle design: Applications of multidisciplinary design optimization methodologies

2017 ◽  
Vol 26 (1) ◽  
pp. 93-103 ◽  
Author(s):  
Loïc Brevault ◽  
Mathieu Balesdent ◽  
Sébastien Defoort
Keyword(s):  
Design Optimization ◽  
Design Process ◽  
Concurrent Engineering ◽  
Multidisciplinary Design Optimization ◽  
Launch Vehicle ◽  
Multidisciplinary Design ◽  
Vehicle Design ◽  
Launch Vehicles ◽  
Data Set ◽  
Launch Vehicle Design

The design of complex systems such as launch vehicles involves different fields of expertise that are interconnected. To perform multidisciplinary studies, concurrent engineering aims at providing a collaborative environment which often relies on data set exchange. In order to efficiently achieve system-level analyses (uncertainty propagation, sensitivity analysis, optimization, etc.), it is necessary to go beyond data set exchange which limits the capabilities of performance assessments. Multidisciplinary design optimization methodologies is a collection of engineering methodologies to optimize systems modelled as a set of coupled disciplinary analyses and is a key enabler to extend concurrent engineering capabilities. This article is focused on several examples of recent developments of multidisciplinary design optimization methodologies (e.g. multidisciplinary design optimization with transversal decomposition of the design process, multidisciplinary design optimization under uncertainty) with applications to launch vehicle design to illustrate the benefices of taking into account the coupling effects between the different physics all along the design process. These methods enable to manage the complexity of the involved physical phenomena and their interactions in order to generate innovative concepts such as reusable launch vehicles beyond existing solutions.

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