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Interactive design of space manufacturing systems, optimality and opportunity

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Abstract

Increasing competitiveness in the space market, forces the industrialists and to pursuit ways to manufacture a high quality product at a minimal cost, to reduce the risk, optimize manufacturing cost and time, the developers have promoted focus on the interactive design of the products. This research focuses on Interactive Multidisciplinary Design and Optimization of Launch Vehicle Satellite with a three-stage liquid propellant. Recently, several works have been developed in the interactive Optimization Design Strategy and multidisciplinary design optimization. In this study, a new multidisciplinary design optimization approach has been involved in system space design including new disciplines. The design strategy has been successfully applied to design problems faced at space designers. The optimizer tool developed for interactive Optimization Design Strategy based on Heuristic Algorithms (Gravitational Search Algorithm, Stochastic Fractal Search, and Search Group Algorithm) proof the highest performance in terms of quality and convergence. The results of virtual reality manufacturing tool presented in this paper are significant in the preliminary system space design which presents an effective approach of development by reducing the cost and the time of analysis and that tool could help decision-makers to understand better the range of possibilities that confront them.

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Abbreviations

MDO:

Multidisciplinary Design Optimization

MDF:

Multi-Disciplinary Feasible

LVS:

Launch Vehicle Satellite

XDSM:

eXtended Design Structure Matrix

SFS:

Stochastic Fractal Search

SGA:

Search Group Algorithm

GSA:

Gravitational Search Algorithm

GLM:

Gross Launch Mass

m f :

The final mass

m i :

The initial mass

M sat :

The mass of satellite

m str :

The structural mass

m p :

The useful propellant mass

D stage :

Stage Diameter

λ :

Payload ratio

S f :

Surface of launch vehicle fairing

L f :

Length of launch vehicle fairing

ρ :

Density of composition material

e :

Thickness of launch vehicle fairing

M fairing :

Mass of launch vehicle fairing

ΔV mission :

Increment velocity of mission

T:

Thrust

Q:

Mass flow

v e :

Velocity ejection of gas

A N :

Nozzle area

D N :

Nozzle diameters

\( P_{c} \) :

Combustion pressure

P atm :

Atmospheric pressure

T c :

Temperature combustion

\( V_{lox} , V_{{H_{2} }} \) :

Volume of propellant thank

\( R_{m} \) :

Mixture ratio

\( \rho_{lox} \) :

Density of propellant

ΔV mission :

Velocity Increment

\( {\text{R}} \) :

The radius of orbit

\( \upmu \) :

The gravitational parameter of planet

g:

The gravitational acceleration

γ:

The flight path angle

\( {\text{D}} \) :

The drag force

\( m^{{\prime }} \) :

The mass of rocket at each time

ρ :

Density of air

v :

Velocity of vehicle

h :

Height above ground

S ref :

Cross-sectional area of launch vehicle

C d :

Coefficient based on geometry of fairing

g 0 :

The gravitational acceleration

a :

The angle of attack

H sat :

Height of satellite

D f :

Fairing diameter

a :

Largest section of satellite

\( m\;and\;M \) :

Represent term and total numbers required in series summation

P 0 :

The incident wave amplitude

J m :

Bessel’s function of first kind

\( H_{m} \) :

Hankel’s function

mth:

Order for variable coefficients

A m :

Coefficient

\( \gamma_{m} \) :

Phase angles

k :

Wave number

φ :

Azimuthally angle

W AO :

Overall acoustic power

η :

Acoustic efficiency

n A :

Number of nozzles

\( {\text{f}}_{{{\text{nat}}l}} \) :

The lateral natural frequency

δ l :

The lateral deflection

\( {\text{f}}_{{{\text{nat}}a}} \) :

The axial natural frequency

δ a :

The axial deflection

E :

Young modulus

L :

Satellite length

I :

Area momentum of inertia of satellite

A :

Cross-sectional area of satellite

n :

Load factor

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Acknowledgement

The authors wish to thank the Electrical Engineering Faculty of the University of Sciences and Technology of Oran and the Center of Satellites Development for their support to perform this project.

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Authors and Affiliations

  1. Laboratoire de Recherche en Système Intelligent (LARESI), Département d’électronique, Université des Sciences et de la Technologied’Oran Mohamed Boudiaf, USTO-Mb, BP 1505, El M’naouer, 31000, Oran, Algeria

    Mohammed Amine Zafrane

  2. Center of Satellite Development, Ibn Rochd USTO, P.O. Box 4065, Oran, Algeria

    Abdelamdjid Boudjemai

  3. Research Laboratory in Intelligent Systems, Department of Electronic, Université des Sciences et de la Technologied’Oran Mohamed Boudiaf, USTO-Mb, BP 1505, El M’naouer, 31000, Oran, Algeria

    Nabil Boughanmi

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  1. Mohammed Amine Zafrane
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  3. Nabil Boughanmi
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Correspondence to Mohammed Amine Zafrane.

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Zafrane, M.A., Boudjemai, A. & Boughanmi, N. Interactive design of space manufacturing systems, optimality and opportunity. Int J Interact Des Manuf 13, 773–796 (2019). https://doi.org/10.1007/s12008-018-0515-3

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  • DOI: https://doi.org/10.1007/s12008-018-0515-3

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