Launch Vehicle Propulsion Parameter Design Multiple Selection Criteria

Name: Launch Vehicle Propulsion Parameter Design Multiple Selection Criteria
Brand: Biblioscholar
SKU: 9781288915248
Price: 298.73 RON
Availability: InStock

Autor: Joey Dewayne Shelton

Limbă:

Legare: Carte broșată

Editura: Biblioscholar

Disponibilitate: În depozitul extern

Expediem în 14-21 zile

298.73 lei

The optimization tool described herein addresses and emphasizes the use of computer tools to model a...

Informații despre carte

Autor

Joey Dewayne Shelton

Limbă

engleză

Legare

Carte - Carte broșată

Publicat

2013

Pagini

182

EAN

9781288915248

ISBN

9781288915248

Enbook ID

08287317

Editura

Biblioscholar

Greutate

336

Dimensiuni

189 x 246 x 10

Descriere completă

The optimization tool described herein addresses and emphasizes the use of computer tools to model a system and focuses on a concept development approach for a liquid hydrogen/liquid oxygen single-stage-to-orbit system, but more particularly the development of the optimized system using new techniques. This methodology uses new and innovative tools to run Monte Carlo simulations, genetic algorithm solvers, and statistical models in order to optimize a design concept. The concept launch vehicle and propulsion system were modeled and optimized to determine the best design for weight and cost by varying design and technology parameters. Uncertainty levels were applied using Monte Carlo Simulations and the model output was compared to the National Aeronautics and Space Administration Space Shuttle Main Engine. Several key conclusions are summarized here for the model results. First, the Gross Liftoff Weight and Dry Weight were 67% higher for the design case for minimization of Design, Development, Test and Evaluation cost when compared to the weights determined by the minimization of Gross Liftoff Weight case. In turn, the Design, Development, Test and Evaluation cost was 53% higher for optimized Gross Liftoff Weight case when compared to the cost determined by case for minimization of Design, Development, Test and Evaluation cost. Therefore, a 53% increase in Design, Development, Test and Evaluation cost results in a 67% reduction in Gross Liftoff Weight. Secondly, the tool outputs define the sensitivity of propulsion parameters, technology and cost factors and how these parameters differ when cost and weight are optimized separately. A key finding was that for a Space Shuttle Main Engine thrust level the oxidizer/fuel ratio of 6.6 resulted in the lowest Gross Liftoff Weight rather than at 5.2 for the maximum specific impulse, demonstrating the relationships between specific impulse, engine weight, tank volume and tank weight. Lastly, the optimum chamber pressure for

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Launch Vehicle Propulsion Parameter Design Multiple Selection Criteria

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