INVESTIGATION OF AN ATTACHED INFLATABLE DECELERATOR SYSTEM FOR DRAG AUGMENTATION OF THE VOYAGER ENTRY CAPSULE AT SUPERSONIC SPEEDS
Final rept. 25 Jan 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment, inflation, and steady-state characteristics of an inflatable decelerator attached to the base of a Voyager entry capsule. Deployments were made at Mach numbers of 2.2 and 3.0 at a free-stream dynamic pressure of 120 psfa. The data obtained show that the preinflation method utilizing vaporization of sufficient liquid solution to completely inflate the decelerator volume resulted in full-inflation times of less than 0.25 sec. The decelerator remained fully inflated after each deployment and exhibited excellent stability.
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry