AAE 450: Aero-thermodynamics

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Presentation transcript:

AAE 450: Aero-thermodynamics Preliminary analysis and literature survey of design concepts for atmospheric Entry of MARS. By Santosh J. Kuruvilla 01/23/2001

Contents: Vehicle types, characteristics, and requirements for expected mission. Modeling atmospheric flight: EOM’s, Stagnation point heat flux calculations,constraints, and assumptions. Comparison of analysis to existing published data. Future additions to the model, and required analysis for the given mission. Related experiences and course work.

Vehicle Types Lifting Body Ballistic Winged Low Heat Load X-24 http://images.jsc.nasa.gov/ Mercury Enterprise Low Heat Load Simple Booster Configuration Maximum Volume Low weight Low L/D Vertical Landing Low Heat Load Good Booster compatibility High Volume Relatively Low structural weight Moderate Deceleration Moderate L/D Horizontal Landing High Heat Load Poor Booster Compatibility Low Volume High Weight Low Deceleration High L/D Horizontal Landings

Mission Requirements High Volume Low Weight Low Heat loading Hypersonic L/D 0.3 to 1 Good Booster compatibility Moderate Controllability using lifting surfaces, to effect plane changes or reduce velocity. = Lifting Body

Dynamic Model for atmospheric flight. EOM’s h : Altitude above surface V: Velocity : Flight Path angle : Heading angle  : Latitude  : Longitude : Bank angle L: Lift D: Drag Rm: Radius of mars : Gravitational Const Equations from: Hypersonic and planetary entry flight mechanics. By Vinh, Busemann, Culp. Assumptions: Constant angle of attack The planet & Atmosphere does not rotate. mass of vehicle is constant (no thrust) Density varies exponentially with altitude, scale height of 49km density of 0.00047 kg/m^3. Ignore Coriolis acceleration

Heat Flux Stagnation point Equations: Assumptions: q:Convective Heat Flux rn: Nose radius V: Free stream velocity Cp: Wall Specific heat coefficient Tw:Wall Temperature : Stefan Boltzmann const. :emissivity Assumptions: Valid only for stagnation point qr Ignored (valid only for LEO entry, I could not find an equation for this)

Comparison

Comparison cont’d

Future Additions to model Add altitude and g-force constraints. Use data to size actual heat shield. Find acceptable wall temperatures

Related experience and course work AAE 440, AAE415, AAE 590G, AAE 532, AAE 251 Program Knowledge: MATLAB, FORTRAN77, IRONCAD, CMARC, JPL’s quick.