Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part I Summary
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PRELIMINARY DESIGN AND EXPERIMENTAL INVESTIGATION OF THE FDL-5A UNMANNED HIGH L/D SPACECRAFT. PART 5. VEHICLE DESIGN.
A parametric analysis of a broad spectrum of thermostructural concepts is presented. A complete structural concept for the 35-foot entry test vehicle using the FDL-5 configuration is defined. Subsystems for the entry test vehicle are selected. A weight breakdown and a weight summary for the test vehicle are presented.
PRELIMINARY DESIGN AND EXPERIMENTAL INVESTIGATION OF THE FDL-5A UNMANNED HIGH L/D SPACECRAFT. PART I. SUMMARY.
Conceptual design and experimental wind tunnel testing of unmanned entry research vehicles having high hypersonic lift/drag ratio and high volume are described. Analytic parametric data are presented for two lifting body classes designated HLD-35 and FDL-5. The FDL-5 is a unique configuration which is aerodynamically stabilized without outboard fins. Experimental aerodynamic and heat transfer fata from the Arnold Engineering Development Center Wind Tunnels A, B, C, and F are compared with analytic data for the FDL-5. Candidate structure and subsystems are selected for performing unmanned hypersonic research with the vehicle. (Author).