Investigation of an Attached Inflatable Decelerator with Mechanically Deployed Inlets at Mach Numbers from 2.25 to 4.75
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment, inflation, and steady-state characteristics of an attached inflatable decelerator with mechanically deployed inlets. Deployments were made at Mach numbers 3.0 and 4.4 at free-stream dynamic pressures of 120 and 73 psf, respectively. The mechanically deployed inlet system resulted in successful deployments of the three test models with inflation times of from 0.4 to 0.7 sec.
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