Investigation of Stored Energy Rotors for Recovery
Report Number: ASD-TDR-63-745
Author(s): Robinson, D. W., Jr., Goodale, B. A., Barzda, J. J.
Corporate Author(s): Kaman Aircraft Corporation
Laboratory: Flight Dynamics Laboratory
Corporate Report Number: R-467
Date of Publication: 1963-12
Pages: 261
Contract: AF 33(616)-7544
DoD Project: 6065
DoD Task: 606501
Identifier: AD0428998
AD Number: AD 428998
Abstract:
Analytical studies on the performance, stability, and control characteristics of rotary-wing decelerators in axial descent, controlled glide flight, and flared landings were performed to investigate the potential capabilities of stored energy rotor systems for the retardation and controlled recovery of payloads. Rotor parameters such as diameter, solidity, disc loading, mass, etc., were considered. Theoretical predictions are compared with experimental test results. Wind tunnel tests simulating typical re-entry trajectory altitude and dynamic conditions were performed on a rotary-wing decelerator system, similar in configuration and construction to the free-flight test rotor system, at speeds from Mach 0.5 to 3.0 to demonstrate feasibility of deploying and operating such systems at supersonic speeds in axial flow and to determine the rotor and governor characteristics for such an operation. Free-flight drop tests with remotely-controlled rotary wing test vehicles launched at subsonic speeds were performed to demonstrate the feasibility of controlled recovery, study stability and response to control, explore the performance potential, and determine problem areas requiring additional research or investigation. Potential applications for rotary-wing decelerator systems were studied. System characteristics are related to mission requirements. Conclusions formed on the basis of the analytical studies and experimental tests are presented and recommendations are made relative to additional research and applications.
Provenance: Bearcat
Author(s): Robinson, D. W., Jr., Goodale, B. A., Barzda, J. J.
Corporate Author(s): Kaman Aircraft Corporation
Laboratory: Flight Dynamics Laboratory
Corporate Report Number: R-467
Date of Publication: 1963-12
Pages: 261
Contract: AF 33(616)-7544
DoD Project: 6065
DoD Task: 606501
Identifier: AD0428998
AD Number: AD 428998
Abstract:
Analytical studies on the performance, stability, and control characteristics of rotary-wing decelerators in axial descent, controlled glide flight, and flared landings were performed to investigate the potential capabilities of stored energy rotor systems for the retardation and controlled recovery of payloads. Rotor parameters such as diameter, solidity, disc loading, mass, etc., were considered. Theoretical predictions are compared with experimental test results. Wind tunnel tests simulating typical re-entry trajectory altitude and dynamic conditions were performed on a rotary-wing decelerator system, similar in configuration and construction to the free-flight test rotor system, at speeds from Mach 0.5 to 3.0 to demonstrate feasibility of deploying and operating such systems at supersonic speeds in axial flow and to determine the rotor and governor characteristics for such an operation. Free-flight drop tests with remotely-controlled rotary wing test vehicles launched at subsonic speeds were performed to demonstrate the feasibility of controlled recovery, study stability and response to control, explore the performance potential, and determine problem areas requiring additional research or investigation. Potential applications for rotary-wing decelerator systems were studied. System characteristics are related to mission requirements. Conclusions formed on the basis of the analytical studies and experimental tests are presented and recommendations are made relative to additional research and applications.
Provenance: Bearcat