Test Results of Rotary-Wing Decelerator Feasibility Studies for Capsule Recovery Applications 630382
The feasibility of using a rotary-wing decelerator for controlled recovery of aerospace vehicles was explored by both theoretical studies and experimental testing.
The analytical studies examined the aerodynamic characteristics of a rotor in axial descent, controlled glide flight, and flared landings. Wind tunnel tests simulating typical re-entry trajectories were performed on the rotary wing system at speeds from Mach 0.5 to 3.0. The results of these tests are compared with theory.
Finally, free-flight drop tests with a remotely controlled rotary-wing test vehicle were performed. These tests demonstrated the feasibility of controlled recovery of payloads with rotary wing decelerators.
Citation: Barzda, J. and Schultz, E., "Test Results of Rotary-Wing Decelerator Feasibility Studies for Capsule Recovery Applications," SAE Technical Paper 630382, 1963, https://doi.org/10.4271/630382. Download Citation
Author(s):
J. J. Barzda, E. R. Schultz
Affiliated:
Kaman Aircraft Corp
Pages: 16
Event:
Pre-1964 SAE Technical Papers
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Wind tunnel tests
Wings
Propellers and rotors
Aerodynamics
Entry, descent, and landing
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