Morphing Hypersonic Inflatable Aerodynamic Decelerator

Green, Justin

doi:10.18130/v3w65b

Cited by 1 publication

(1 citation statement)

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“…Decelerating at higher altitudes allows HIADs to achieve lower peak heating rates and peak deceleration values. It will also increase the timeline margin for the descent and landing phases 4 .…”

Section: Hypersonic Inflatable Aerodynamic Deceleratormentioning

confidence: 99%

Morphing Hypersonic Inflatable Aerodynamic Decelerator

Green

Dunn

Lindberg

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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The incorporation of Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology into entry vehicle designs opens up a new avenue for trajectory control through shape morphing of the inflatable structure. In this work, we explore the effects of shape morphing utilizing the super ellipse model for aeroshell shape generation, the Modified Newtonian Impact Theory for aerodynamic evaluation, a three degree-of-freedom (3 DOF) trajectory simulation, and a stagnation point heating model to evaluate morphed aeroshell shapes and their effect on trajectory. The Inflatable Reentry Vehicle Experiment (IRVE) -3 flight project and the High Energy Atmospheric Reentry Test (HEART) mission concept serve as the two HIAD case studies for our work. Our evaluation of this new control strategy focuses on three goals: 1) developing a tool for evaluating morphed aeroshell shapes; 2) determining a morphed aeroshell shape that will generate a useful change in lift-over-drag, while keeping the stagnation point heat flux below the practical limit of 30 W/cm 2 ; and 3) providing a basis for future research into morphing HIAD structures. Nomenclature= Area [m 2 ] = Semimajor axis length of a blunt body [m] = Semiminor axis length of a blunt body [m] = Aerodynamic force coefficient = Pitching moment coefficient about the aeroshell center of mass (CoM) = Pitching moment coefficient about the nose for the aeroshell = Coefficient of pressure = Aeroshell base diameter [m] , , = Radiative heat flux constants / = Lift-over-drag M = Mach number = Entry vehicle mass [kg] = Number of sides in the superellipse = Total number of sections in which to divide the conical base = Number of the section of the conical base = Outward facing normal of a surface = Superelliptic parameter that governs corner roundness = Heat load [J/cm 2 ] = Stagnation point heat flux [W/cm 2 ] = Planetary radius [m] = Radius [m] = Effective radius of curvature for the radiative heat transfer calculation [m] 2 = Distance from the axis of symmetry to the tangency point between the main aeroshell geometry and the corner radius [m] = Entry velocity [m/s] !, ", # = Coordinate axes $, %, & = Coordinate positions [m] α = Angle of attack [rad] ( = Ratio of specific heats ( = Flight path angle [rad] Δ = Change in Δ * = Stagnation point shock standoff distance for a nonzero angle of attack, + [m] , = Eccentricity -. = Half cone angle [rad] -= Half spherical segment angle [rad] / = Longitude with respect to the inertial coordinate system [rad] 0 = Density [kg/m 3 ] 1 = Sweep angle [rad] 1 = Latitude with respect to the inertial coordinate system [rad] 2 = Angle used to generate the nose radius [rad] 2 . = Angle used to generate the corner radius [rad] 2 = Planetary angular rotation rate [rad/s] subscripts 0 = Location at tip of nose, stagnation point 1 = Upstream of the normal shock 2 = Downstream of the normal shock = Axial = Referenced from the body coordinate system 6 = Corner 67 8 = Convective = Drag 9, : = Indices = Lift = Normal = Nose ;= Projected = Designates axial profile geomet...

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Section: Hypersonic Inflatable Aerodynamic Deceleratormentioning

confidence: 99%