Study and Exploratory Free-Flight Investigation of Deployable Aerodynamic Decelerators Operating at High Altitudes and at High Mach Numbers

摘要

Thirteen parachute decelerator tests were performed at the Gulf Test Range of the Air Proving Ground Center at Eglin Air Force Base, Florida. These tests were accomplished through the use ofof multistage rockekket boosters. The Cree payyload vehicle was used as the test platform and data gathering system. These tests were conducted using both Hyperflo and Hemisflo parachutes which were deployed at predetermined Mach numberaltitude regimes. Tests were accomplished over a Mach number range of 0.2 to 4.4 and an altitude range of 45,000 to 190,000 feet. The data presented includes drag coefficients versus Mach number, dynamic pressure, Reynolds number and velocity, canopy angles of oscillation, canopy temperatures and general design considerations. From this parachute decelerator test program, it may be concluded that Perlon mesh roof Hyperflo parachutes perform satisfactorily through Mach 2.1, that Nomex ribbon Hyperflo parachutes perform satisfactorily through Mach 4.0 and that Nomex Hemisflo parachutes perform satisfactorily through Mach 3.4. (Author)