Concepts of Reentry Technology Experimental Vehicles

“…1). 5 Because the vehicle size is severely constrained by the payload fairing, a lifting-body-type configuration is considered more appropriate than a wing-body configuration because of its volumetric efficiency and aeroheating characteristics.…”

Section: Introductionmentioning

confidence: 99%

“…5 In this study, a vehicle is launched into low Earth orbit by an H-IIA rocket inside an off-theshelf payload fairing. After completing a single orbit, it deorbits and reenters the atmosphere, decelerates to subsonic speed, and lands softly with a parachute or a parafoil and an airbag (Fig.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performances of Lifting-Body Configurations for a Reentry Vehicle

Kawato¹,

Watanabe²,

Yamamoto³

et al. 2005

Journal of Spacecraft and Rockets

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Aerodynamic characteristics of four lifting-body-type configurations for a reentry vehicle, namely, a baseline configuration, a fin-off configuration, a 45-deg canted fin configuration and an upswept upper-aftbody configuration, are investigated by wind-tunnel tests and compared, focusing on aerodynamic performance aspects such as longitudinal trim capability, longitudinal and lateral/directional static stability, and subsonic lifting surface loading. The upswept upper-aftbody configuration showed the best performance from longitudinal trim, and longitudinal and lateral/directional static stability points of view, which suggests that modifying the upper aft part of the fuselage of the baseline configuration is the most promising approach to improving its characteristics. Nomenclatureratio of moment of inertia around z and x axes LB = fuselage length, m M = freestream Mach number S = fuselage planform area, m 2 W = vehicle weight, kg W/CLS = lifting surface loading, kg/m 2 Xcg = center of gravity, origin at the nose Xcp/LB = center of pressure normalized by LB, origin at the nose Xnp/LB = longitudinal neutral point normalized by LB, origin at the nose Xnp,y dyn = lateral/directional neutral point normalized by LB, origin at the nose α = angle of attack, deg β = sideslip angle, deg δe = elevator deflection angle, deg ε = emissivity Presented as Paper 2002-5265 at the AIAA/AAAF 11th International

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