Abstract
Conceptual design stage is where the knowledge about the variation in system is still quite vague and herein we intend to analyze and compare various probable design concepts for Air Launched SLV by the use of basic variation mode and effect analysis. In this paper we present a methodology for the Variation Mode and Effect Analysis using Latin Hypercube Sampling based Design of Experiments for the conceptual Air launched Satellite Launch Vehicle. Variations are induced in the Control Variables based on knowledge and experience. The methodology is used to quantify the effect of Noise Factors on the performance of a conceptual Air Launched SLV. The insertion altitude of the Air Launched SLV is the Key Performance Indicator. Preliminary results of the performance and analysis for the simulated experiments are presented here. The performance of the proposed procedure has been tested and, thus, validated by the Air Launched SLV design problem. The Design of Experiment based Variation mode and effect analysis approach is intended for initial conceptual design purposes, thus, providing an immediate insight to the performance of the system in general and quantification of the sensitivity of the key performance indicator in particular, subject to the variations in noise factors prior to the detailed design phase.