STRUCTURE AND MATERIALS ASPECTS OF THE PRIME FLIGHT TEST VEHICLE
Abstract
The structure and thermal protection system being developed as part of the START Program is described. The program is concerned with the design and flight test of a small maneuverable lifting reentry vehicle of the SV-5 configuration (hypersonic lift-to-drag ratio of approximately 1.3) with an ablative heat shield. Reentry conditions will simulate those encountered in return from low earth orbit. This program is expected to produce technology that could be applicable to manned, maneuverable reentry. A description of the thermal/structural configuration, load paths, materials used, discontinuities and attachment to the launch vehicle is given. The influence of primary structural material on heat shield integrity and vehicle weight is discussed. Loading conditions and vehicle thermal/structural design criteria are described. The reentry environment of the vehicle is compared with related systems. Heating rates, total heats, shear loads, and pressures are shown, and thermochemical and thermophysical properties of various heat shield materials are discussed. Materials tests and data are compared with many applicable heat shield materials.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 31, 1965
- Accession Number
- AD0480808
Entities
People
- J. I. Slaughter
- J. Meltzer
- J. Rossoff
- J. Sterhardt
Organizations
- The Aerospace Corporation