Accession Number : ADA590178


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


Descriptive Note : Final rept. 15 Mar 2007-14 Sep 2009


Corporate Author : ZONA TECHNOLOGY INC SCOTTSDALE AZ


Personal Author(s) : Chen, Ping-Chih ; Starkey, Ryan ; Chang, Kai-Ti ; Sengupta, Ayan


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a590178.pdf


Report Date : 04 Dec 2009


Pagination or Media Count : 337


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).


Descriptors :   *HYPERSONIC VEHICLES , *INTEGRATED SYSTEMS , AEROELASTICITY , AEROTHERMOELASTICITY , AIR BREATHING , ENGINES , FLOW , INLETS , INTERACTIONS


Subject Categories : Research and Experimental Aircraft
      Computer Systems


Distribution Statement : APPROVED FOR PUBLIC RELEASE