Integrated Aero-Servo-Thermo-Propulso-Elasticity (ASTPE) for Hypersonic Scramjet Vehicle Design/Analysis

Abstract

For air-breathing hypersonic vehicles with scramjet engines, waverider-like forebodies are employed in order to reduce pressure leakage from the lower to upper surface and/or satisfy a shock-on-cowl lip condition to achieve superior inlet flow quality at a given design condition. However, any aeroelastic or dynamic perturbations will give rise to a non-ideal inlet flow field. This may induce vehicle instability in terms of the interaction of hypersonic aerodynamic, aeroelastic, aeroservoelastic, as well as aerothermoelastic interaction. This STTR Phase II project is to develop a "Conceptual-Design/Analysis" (CDA) tool for precisely the purpose of rapid assessment of vehicle stability and control law implementation. Resulting ASTPE package includes Aero-Servo-Thermo-Propulso-Elasticity disciplines and a Graphical User Interface (GUI) has been created to assist driving individual modules in ASTPE package. Case studies include Single Engine Missile (SEM) and Single Engine Demonstrator (SED).

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Document Details

Document Type
Technical Report
Publication Date
Dec 04, 2009
Accession Number
ADA590178

Entities

People

  • Ayan Sengupta
  • Kai-ti Chang
  • Ping-chih Chen
  • Ryan Starkey

Tags

Communities of Interest

  • Ground and Sea Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Stability
  • Aeroelasticity
  • Air Force
  • Aircrafts
  • Airframes
  • Case Studies
  • Computational Fluid Dynamics
  • Computational Science
  • Fluid Dynamics
  • Geometry
  • Graphical User Interface
  • Heat Transfer
  • Hypersonic Missiles
  • Hypersonic Vehicles
  • Mechanics
  • Supersonic Combustion Ramjet Engines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Software Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow