alexa Parameterization of Micro Satellite Launch Vehicle
ISSN: 2168-9792

Journal of Aeronautics & Aerospace Engineering
Open Access

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Research Article

Parameterization of Micro Satellite Launch Vehicle

Adetoro MA Lanre1*, Fashanu TA1 and Osheku A Charles2
1Department of Systems Engineering, University of Lagos, Akoka, Yaba, Lagos, Nigeria
2National Space Research and Development Agency, P.M.B 437, Abuja, Nigeria
*Corresponding Author : Adetoro MA Lanre
Department of Systems Engineering
University of Lagos, Akoka, Yaba, Lagos, Nigeria
Tel: +2348033202436
Received September 04, 2014; Accepted September 27, 2014; Published October 03, 2014
Citation: Lanre AMA, Fashanu TA, Charles OA (2014) Parameterization of Micro Satellite Launch Vehicle. J Aeronaut Aerospace Eng 3:134. doi: 10.4172/2168-9792.1000134
Copyright: © 2014 Lanre AMA, et al. This is an open-access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.


The new trends in micro satellites mission for wide range of applications has motivated worldwide research in design and development of micro satellite launch vehicles (MSLVs) as a vital options in the deployment of such satellites into their respective mission orbits. Presently, most micro satellites are launched through rideshares with rockets or rocket-like systems, which were developed essentially in the seventieth and eightieth of the last century. The MSLV as a proportional micro satellite launch vehicle, up till now has only the status of technology and system study work and is well known that the research and development of MSLV are diversified in different fields. However, the realization of MSLVs is rigorous since such vehicles compound the inherent difficulties of traditional launch experiment with intrinsic problems of uneven mass distribution, slenderness, high frequency and amplitude of vibration etc. MSLV are also more likely to be affected by wind gusts and other disturbances than their conventional counterpart, and the physical parameters such as mass distribution and moments of inertia can be easily altered by changing the payload location and unpredictable propellant burning. All these factors compromise the additional velocities to overcome the aerodynamic drag, to account for steering of the vehicle and other losses. Consequently, We prototype a three stage micro-satellite launch equipment as a similitude of the European Space Agency’s VEGA launcher using a scale down derivation model and parameterized using existing VEGA launch vehicle (LV) technical data. VEGA launch data, total orbital velocity requirement including the losses and stage payload ratio are inferred and applied to the model of parameterization of launch vehicles through coupledparameters simulations. This approach can be helpful in viability and performance insights in terms of payload mass, stage mass distribution and material properties precision and effectiveness. It can also serve as a background for the development of time optimal waypoint trajectory of micro satellite launchers.


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