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Book/Book Chapter 
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2000 
American Institute of Aeronautics and Astronautics :: AIAA 
2000 
American Institute of Aeronautics and Astronautics 
Reston, VA 
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 
English 
has individual parts 8157336 Combustion response of ammonium perchlorate
has individual parts 8158514 A two-dimensional model of composite propellant flame structure and burning rate
has individual parts 8212218 Unsteady combustion of solid propellants: Simplified kinetics modeling
has individual parts 8331153 2D model for unsteady burning heterogeneous AP/binder solid propellants
has individual parts 8334463 A propellant model: Oxidizer and fuel with differing kinetic parameters
has individual parts 8542744 Modeling pressure responses of HMX including a condensed phase void fraction
has individual parts 8542907 Qualification and pedigree of the shock tube assembly (STA)
The proceedings contain 633 papers. The special focus in this conference is on Joint Propulsion. The topics include: On a self-tuning impact vibration damper for rotating turbomachinery; wake-filling and reduction of rotor HCF using stator trailing edge blowing; a phenomenological investigation of sequence effects on mistuned rotor response; investigation of unsteady inlet guide vane wakes in a F109 turbofan engine; early studies of RBCC applications and lessons learned for today; preliminary analysis and design of a rocket based combined cycle engine for efficient access to space; utilization of existing large subsonic aircraft elements to implement in-flight LOX collection; marquardt's mach 4.5 supercharged ejector ramjet high-performance aircraft engine project; high risk low cost manned mars mission scenarios; liquid methane/oxygen injector study for potential future mars ascent; a mars rocket vehicle using in-situ propellants; effect of swirl injector design and other important parameters on gas turbine combustion instabilities; PLIF measurements of combustion dynamics in a burner under forced oscillatory conditions; active feedback control of combustor dynamics with time delay and noise; the influence of injector dynamics on longitudinal combustion instabilities; LES modeling of combustion dynamics in a liquid-fueled flametube combustor; effects of pressure on unsteady flame stabilization; robust channel wall chambers for reliable upper stage engines; lightweight chambers for thrust cell applications; near-net shape powder metallurgy rhenium thrusters; creep in high temperature tensile testing of rhenium; data oscillation resolution of propellant flowmeter used in FASTRAC engine testing; high temperature fiber-optic pressure sensor with built-in temperature compensation; RSRM operational pressure transducer characterization; characterisation and use of bond stress sensors in tactical rocket motors; the USAF electric propulsion research program; overview of U.S. academic programs in electric propulsion; educational influences on whittle and von ohain on the development of the first jet engines; observation of backflow and prewhirl at rocket propellant pump inducer; Vinci hydrogen turbopump - a new step in safe, faster and cheaper developments; MS100 powerpack demonstrator status and future prospects; modeling and robust analysis of a liquid rocket engine; development and testing of ADN-based monopropellants in small rocket engines; a high pressure bipropellant micro-rocket engine; status of cryogenic thrust chamber development for Ariane 5 at astrium; comparison of two methods used for contouring launch vehicle's engine nozzles; unsteady combustion of solid propellants - simplified kinetics modelling; phase stabilized ammonium nitrate propellants; numerical analysis of moisture propagation and chemical reaction in a solid propellant; improvements in reusable solid rocket motor performance predictions; an overview of the development of HNF and HNF-based propellants; evaluation of CFD code CFD-ACE for application to rocket problems; modeling the effects of velocity coupling on the global dynamics of combustion chambers; external pulse effects on solid rocket internal ballistics; solid motor plume analyses for the STAR-1 spacecraft; improved mean-flow solution for slab rocket motors with regressing walls; modeling pressure responses of HMX including a condensed phase void fraction; noise suppression nozzles for a supersonic business jet; development and validation of a turbulent combustion model for imperfectly premixed reactants; lean premixed combustor emissions performance modeling using 3D CFD codes; suppression of HCN emission from GAP-HTPB based ram rocket propellants; LES calibration of a turbulent potential model for turbomachinery flows; progressive optimization for the inverse design of 2D cascades; investigation of the performance of a CFD-designed transonic compressor stage; unsteady disturbance theory and modeling for centrifugal compressors; bimodal NTRE for propulsion and planetary power; the synergistic application of chemical rocket component technologies to the ESCORT nuclear bimodal system; comparative analysis of current NASA human mars mission architectures; the constant volume limit of pulsed propulsion for a constant gamma ideal gas; deflagration to detonation transition study using simultaneous schlieren and OH PLIF images; an optimization-based approach to injector element design; modeling a hydrogen peroxide gas generator for rockets; 3-D linearized Euler simulation and evaluation of rotor-IGV interactions; passive control of discrete frequency tones generated by coupled detuned cascades; unsteady pressure response on a rearward-forced, isolated compressible-cascade vane; velocity field upstream of rods used for forcing unsteady compressible cascades; initiation process of combustion in a ram accelerator - influence of the tube diameter and design of the sabot; numerical study of the usage of an ignition tube for successful starting of the ram accelerator; numerical calculation of 3-D flow field around ram accelerator projectile; preliminary design optimization for a supersonic turbine for rocket propulsion; high head unshrouded impeller pump stage technology; a squeeze film Reynolds number for predicting squeeze film damper rotordynamic performance; innovative low power hall effect thruster; performance of a multi-kilowatt non-circular discharge hall thrusters; preliminary performance results of the high performance hall system SPT-140; multimode, high specific impulse hall thruster technology; development of a micro pulsed plasma thruster for the dawgstar nanosatellite; design of a triple probe experiment to measure the PPT plume from the exit plane to the backflow region; quantitative spectroscopic measurements of a pulsed-plasma microthruster; pulsed plasma thruster variations for improved mission capabilities; pulsed plasma thruster plume study - symmetry and impact on spacecraft surfaces; electrospray as a source of nanoparticles for efficient colloid thrusters; 3-D plume characterization of a FEEP thrusters; design for manufacturing improvements and demonstration of a 30 cm ion thrusters; results from numerical modelling of RF ion thrusters; new electrostatic thruster for small satellite application; early experimental programs of the American rocket society 1930-1941; bifurcational models of liquid rocket combustion; a regeneratively cooled thrust chamber for the fastrac engine; investigation of linear plug layouts of rocket engines for reusable launch vehicles; analysis of in-flight behavior of truncated plug nozzles; optimal performance of a tripropellant single-stage rocket; on the nozzle side force induced by entrance flow asymmetry; high frequency wave instability and combustion responses; numeric simulation for combustion instability of liquid propellant rocket engine; a nonlinear analytical model of high-frequency combustion instability in rocket engine; experimental study on extendible and dual-bell nozzles under high altitude conditions; studies on multijets with outward canting; generalized data reduction strategy for rocket engine applications; European research and technology test bench P8 for high pressure liquid rocket propellants; pintle motor challenges for tactical missiles; sensitivity of hydrocarbon combustion modeling for hypersonic missile design; comparisons of CFD calculations and measurements for a sonic jet in a supersonic crossflow. 
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit