Author: Fang Chen
Publisher:
ISBN:
Category : Technology
Languages : en
Pages :
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Book Description
To efficiently model fluid-thermal-structural problems for thermal protection design of hypersonic vehicles, a framework of Hypersonic Computational Coupling Dynamics (HyCCD) software integrates an independently developed program solving hypersonic aerthermodynamic simulation with a finite element analysis professional software. With the mathematical and physical description of multi-physics coupling mechanism, the corresponding efficient coupling strategies were proposed. Some representative coupling problems encountered in hypersonic vehicle were systematically analyzed to study the intrinsic fluid-thermal-structural coupling characteristics and mechanisms. The results can theoretically and technically support the studies on comprehensive performance assessment and optimization of thermal protection system and static or dynamic aerothermoelastic problem of hypersonic vehicles.
Author: Adam John Culler
Publisher:
ISBN:
Category :
Languages : en
Pages : 297
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Book Description
Abstract: This dissertation describes coupled fluid-thermal-structural modeling and analysis of a semi-infinite insulated metallic panel and a blade-stiffened carbon-carbon skin panel for aerothermoelasticity and forced response prediction in hypersonic flow.
Author: Ramesh K. Agarwal
Publisher: BoD – Books on Demand
ISBN: 9535139037
Category : Technology & Engineering
Languages : en
Pages : 186
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Book Description
The book describes the recent progress in some hypersonic technologies such as the aerodynamic modeling and numerical simulations of rarefied flows, boundary layer receptivity, coupled aerodynamics, and heat transfer problems, including fluid-thermal-structure interactions and launcher aerodynamic design as well as other miscellaneous topics, such as porous ceramic composite phase change control system and vehicle profile, following LQR design. Both the researchers and the students should find the material useful in their work.
Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 354089974X
Category : Technology & Engineering
Languages : en
Pages : 512
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Book Description
In this book selected aerothermodynamic design problems in hypersonic vehicles are treated. Where applicable, it emphasizes the fact that outer surfaces of hypersonic vehicles primarily are radiation-cooled, an interdisciplinary topic with many implications.
Author: Jaidev Khatri
Publisher:
ISBN:
Category : Airbreathing launch vehicles
Languages : en
Pages : 220
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Book Description
This thesis examines themodeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analyses. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite element methods are needed for more precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design. The model was used to examine the vehicle's static and dynamic characteristics over the vehicle's trimmable region. The vehicle has significant longitudinal coupling between the fuel equivalency ratio (FER) and the flight path angle (FPA). For control system design, a two-input two-output plant (FER - elevator to speed-FPA) with 11 states (including 3 flexible modes) was used. Velocity, FPA, and pitch were assumed to be available for feedback. Aerodynamic heat modeling and design for the assumed TPS was incorporated to original Bolender's model to study the change in static and dynamic properties. De-centralized control stability, feasibility and limitations issues were dealt with the change in TPS elasticity, mass and physical dimension. The impact of elasticity due to TPS mass, TPS physical dimension as well as prolonged heating was also analyzed to understand performance limitations of de-centralized control designed for nominal model.
Author:
Publisher:
ISBN: 9789535139041
Category :
Languages : en
Pages :
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Book Description
Author: Akshay Shashikumar Korad
Publisher:
ISBN:
Category : Flight control
Languages : en
Pages : 191
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Book Description
This thesis examines the modeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analysis. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite elementmethods are needed formore precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design. The model was used to examine the vehicles static and dynamic characteristics over the vehicles trimmable region. The vehicle has significant longitudinal coupling between the fuel equivalency ratio (FER) and the flight path angle (FPA). For control system design, a two-input two-output plant (FER - elevator to speed-FPA) with 11 states (including 3 flexible modes) was used. Velocity, FPA, and pitch were assumed to be available for feedback.
Author: Subramani Sockalingam
Publisher: LAP Lambert Academic Publishing
ISBN: 9783844385717
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 80
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Book Description
A frame work has been setup for the simulation of hypersonic reentry vehicles using commercial codes FLUENT and LS-DYNA. The main goal of this work was to set up a simple approach for the heat flux prediction and evaluation of the material thermal response during the reentry of the vehicle. Fluid thermal coupling for predicting the thermal response of a reusable non-ablating thermal protection system was set up. The computational fluid dynamics code (FLUENT) and the material thermal response codes (LS- DYNA) are loosely coupled to achieve the solution. The vehicle considered in the calculation is an axisymmetric vehicle flying at zero degree angle of attack. The frame work set up was validated with the results available in the literature. Good correlation was observed between the results from the commercial codes and the results from the literature. The mesh movement capability in LS-DYNA was implemented enabling future modeling of ablating thermal protection system.
Author: Salvatore Gerbino
Publisher: Springer Nature
ISBN: 3031159284
Category : Technology & Engineering
Languages : en
Pages : 1646
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Book Description
This book gathers contributions presented at the International Joint Conference on Mechanics, Design Engineering and Advanced Manufacturing (JCM 2022), held on June 1–3, 2022, in Ischia, Italy. It reports on cutting-edge topics in product design and manufacturing, such as industrial methods for integrated product and process design; innovative design; and computer-aided design. Further topics covered include virtual simulation and reverse engineering; additive manufacturing; product manufacturing; engineering methods in medicine and education; representation techniques; and collaborative and soft robotics. The book is organized into five main parts, reflecting the focus and primary themes of the conference. The contributions presented here not only provide researchers, engineers and experts in a range of industrial engineering subfields with extensive information to support their daily work; they are also intended to stimulate new research directions, advanced applications of the methods discussed and future interdisciplinary collaborations.
Author: Subramani Sockalingam
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
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Book Description
A frame work has been setup for the simulation of hypersonic reentry vehicles using commercial codes FLUENT and LS-DYNA. The main goal of this work was to set up a simple approach for the heat flux prediction and evaluation of the material thermal response during the reentry of the vehicle. Fluid thermal coupling for predicting the thermal response of a reusable non-ablating thermal protection system was set up. The computational fluid dynamics code (FLUENT) and the material thermal response codes (LS-DYNA) are loosely coupled to achieve the solution. The vehicle considered in the calculation is an axisymmetric vehicle flying at zero degree angle of attack. The frame work set up was validated with the results available in the literature. Good correlation was observed between the results from the commercial codes and the results from the literature. The mesh movement capability in LS-DYNA was implemented enabling future modeling of ablating thermal protection system.
