Implementation of the Conceptual Design Framework for Medium-Class Launch Vehicles Based on Response Surface Method (RSM)

Document Type : Original Article

Authors

1 Assistant Professor, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

2 Master's student, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

Abstract

The main aim of the research is to create a comprehensive database for medium-class space launch vehicles (with payload masses ranging from 1 to 3 tons) and perform the conceptual design based on statistical data. Thus, comprehensive data was gathered for five space launch vehicles with two stages and liquid propellant (fuel and oxidizer) in a series (not strap-on) configuration. The Design-Expert software was used to establish the design space of the main parameters and produce the response surface. Also, 16 design main parameters were considered as inputs to the software, and the main design space was generated. 163 outputs of the Design Expert software are plotted as response surfaces. Based on the flowchart of the statistical design of a specific mission of the launch vehicle, using MATLAB code, a search is done in the design space exclusive to response surfaces. Then, the statistical coefficients of the output response surfaces are compared with the ranges of statistical coefficients of the existing (real) launch vehicles, and samples that differ by more than 30% are eliminated. Finally, one data point was selected as the design point from the remaining data (approximately 25% of the total). To validate the proposed design method and flowchart, the CZ-2 launch vehicle was selected and the design results and flight simulation were examined. The comparison of the statistical design results with the existing launch vehicle confirms the accuracy of the proposed method and flowchart for the conceptual design phase.

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Main Subjects


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