FEASIBILITY STUDY OF HYPERSONIC PARACHUTE FREE FLIGHT TEST CAPABILITY. PHASE I
Abstract
A study was conducted to determine the feasibility of establishing a free-flight test capability for aerodynamic decelerators at supersonic and hypersonic velocities. Methods for boosting test vehicle eights of 250, 500, 800, and 2000 lb. to various altitudes and Mach numbers utilizing presently available rocket motors and range f cilities are evaluated. Te t altitudes vary from 2000 to 250,000 ft for a Mach number range of 1.0 to 10. Instrumentation requirements for measuring decelerator performance characteristics and vehicle flight parameters are investigated. Methods for water and land recovery of the payload section of the vehicles are presented. The results of the study indic te that presently available v hicle design and instrumentation techniques, as well as existing range facilities, may be employed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1962
- Accession Number
- AD0275578