ANALYSIS OF THE THERMOSTRUCTURAL REQUIREMENTS FOR THE ATMOSPHERIC RE-ENTRY OF SATELLITES AND SPACE VEHICLES
Abstract
BY THE AERODYNAMIC BRAKING EFFECTS OF THE ATMOSPHERE. The vehicle velocity and entry angle may be classed as approach variables and the aeroct shock.) (Materials, Metals, Ceramic materials, *Thermal insulation.) The thermostructural requirements of re-entry vehicles are determined by the kinetic energy of the vehicle on penetration of the atmosphere and by the program of the dissipation of this energy by conversion to heat, which is generated by the aerodynamic braking effects of the atmosphere. The vehicle velocity and entry angle may be classed as approach variables and the aerodynamic characteristics of the body as vehicle variables. These variables are discussed, with particular emphasis on the wide range of energy conversion programs which are made available by choice of the vehicle design. The possible types of re-entry vehicles are analyzed by a description of the aerodynamic characteristics of the various principal types. The aerodynamic features of re-entry vehicles may be classified into the two broad subdivisions of lift and drag flight. Lift flight vehicles are represented primarily by the glide aircraft and lifting capsule families, and drag flight vehicles by drag capsules, satellite bodies, and nose cones. The primary distinction is between bodies that rely on aerodynamic lift, with the associated drag for gradual deceleration from orbital to subsonic velocity, and bodies that undergo a shocklike deceleration to terminal fall velocity. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 15, 1961
- Accession Number
- AD0264753
Entities
People
- W.s. Pellini
Organizations
- United States Naval Research Laboratory