Integrated Hypersonic Aeromechanics Tool (IHAT)

Baker, Myles L.; Sverdrup, Jacobs; Alston, Katherine; Munson, Michael J.

doi:10.2514/6.2002-5512

Cited by 24 publications

(7 citation statements)

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“…10,11 Another approach consists of using sizing and synthesis tools that encompasses all the disciplinary analyses required to calculate a launch vehicle mission. The Hypersonic Air Vehicle Optimization Code (HAVOC) 12 and the Integrated Hypersonic Aeromechanics Tool (IHAT) 13 are two examples for this approach.…”

Section: A Launch Vehicle Designmentioning

confidence: 99%

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A New Method of Architecture Selection for Launch Vehicles

Villeneuve

Mavris

2005

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference

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During the early stages of conceptual design, decisions regarding the vehicle and system configurations will have the most impact on the program cost and vehicle performance. For a launch vehicle, this phase consists of selecting the vehicle and system architectures. Since there are several complex systems forming such a vehicle, selecting the best configuration becomes a very difficult task. Traditionally, this phase is performed by disciplinary experts who select the architecture based on engineering intuition and personal preferences. However, because of the high level of complexity and interdependency between the systems of the vehicle, this approach is very inefficient. In order to address this concern, a Rapid Access-to-Space Analysis Code (RASAC) has been developed at the Aerospace Systems Design Lab at the Georgia Institute of Technology. The goal of this tool is to enable comparisons of launch vehicle architectures in a quick and accurate fashion. This paper will describe the underlying models of RASAC as well as an example of launch vehicle configuration selection. The benefits of this new approach will also be illustrated.

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Section: A Launch Vehicle Designmentioning

confidence: 99%

“…The maximum mass flow rate per unit area of the combustion products at Station 4 (the ramjet duct ahead of the nozzle) is modeled by the mass flow rate equation presented in Eq. (13). This equation serves to size the required ramjet area (A4) and to calculate the maximum allowable mass flow rate through the ramjet during the flight.…”

Section: Model Descriptionmentioning

confidence: 99%

A New Method of Architecture Selection for Launch Vehicles

Villeneuve

Mavris

2005

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference

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“…1 The DSM helps establish the inter-Module dependencies, which define the optimal Module execution order. In Figure 1, the rows indicate the outputs of the various Modules, and the columns indicate the inputs.…”

Section: Introductionmentioning

confidence: 99%

The Integrated Hypersonic Aeromechanics Tool Structures Module

Porter¹,

Baker²,

Sutton³

et al. 2003

12th AIAA International Space Planes and Hypersonic Systems and Technologies

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The Integrated Hypersonic Aeromechanics Tool (IHAT) System is a multi-disciplinary optimization (MDO) engineering analysis computer code used in the research and development arena, focused on the analysis and optimization of hypersonic tactical missiles. The IHAT System has elements (Modules) that model the major subsystems of the missile. The Modules include Geometry, Aerodynamics, Propulsion, Trajectory, Thermal Analysis, Structural Analysis, Stability & Control, Lethality, Sensors, and Cost. This paper addresses one element of the IHAT system -the Structural Module. This Module will be described and results will be presented from an air-launched missile example used in verification of the code. The Structural Module provides the structural subsystem data associated with the overall vehicle. This data includes a global finite element model, structural load conditions, structural concept/configuration, structural sizing, structural stiffness, flutter results and mass properties of the structural elements. All aspects of structural loading for the missile at any time during the flight trajectory or while the missile is attached to the launch platform (air or surface platforms) are considered, including captive flight, free flight maneuvering, ejection, arrested landing, catapult, and thermal load conditions. The IHAT System is being developed by a government/industry team using multiple, incremental builds. This paper describes the Structural Module through the second build (Build 2) of the IHAT System.

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“…This type of optimisation is suited for fine tuning of a specific design, but generally it is not suited for large geometry changes. Despite these drawbacks, grid perturbation techniques have proved useful in practice, (Carty and Davis 2004, Nemec et al 2004, Baker et al 2002, Rohl at al 1998. The second type of shape optimisation moves geometry generation inside the optimisation loop.…”

Section: Fig 1 Gas Turbine Discmentioning

confidence: 99%

CAD based shape optimization for gas turbine component design

Brujić

Ristić

Mattone

et al. 2009

Struct Multidisc Optim

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In order to improve product characteristics, engineering design makes increasing use of Robust Design and Multidisciplinary Design Optimisation. Common to both methodologies is the need to vary the object's shape and to assess the resulting change in performance, both executed within an automatic loop. This shape change can be realised by modifying the parameter values of a suitably parameterised Computer Aided Design (CAD) model. This paper presents the adopted methodology and the achieved results when performing optimisation of a gas turbine disk. Our approach to hierarchical modelling employing design tables is presented, with methods to ensure satisfactory geometry variation by commercial CAD systems. The conducted studies included stochastic and probabilistic design optimisation. To solve the multi-objective optimisation problem, a Pareto optimum criterion was used. The results demonstrate that CAD centric approach enables significant progress towards automating the entire process while achieving a higher quality product with the reduced susceptibility to manufacturing imperfections.

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Integrated Hypersonic Aeromechanics Tool (IHAT)

Cited by 24 publications

References 0 publications

A New Method of Architecture Selection for Launch Vehicles

A New Method of Architecture Selection for Launch Vehicles

The Integrated Hypersonic Aeromechanics Tool Structures Module

CAD based shape optimization for gas turbine component design

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