Engineering topics
Publications and source records attributed to Runyan, H. L., Jr..
Passive flutter-suppression system has been developed to increase flutter speed of aircraft wings that are adversely affected by addition of large masses (stores) to the wings, such as external fuel tanks. Important features of system are its effectiveness for large variations in mass of store as well as unsensitivity of system to large change in location of store center-of-gravity.
As an alternative to alleviating wing/store flutter by conventional passive methods or by more advanced active control methods, a quasi-passive concept, referred to as the decoupler pylon, is investigated which combines desirable features of both methods. Passive soft-spring/damper elements are used to decouple wing modes from store pitch modes, and a low-power control system maintains store alignment under changing mean loads. It is shown by analysis and wind tunnel tests that the decoupler pylon provides substantial increase in flutter speed and makes flutter virtually insensitive to inertia and center-of-gravity location of the store.
Theoretical approach to the problem of predicting the sonic-boom signature due to a maneuvering aircraft, with outline of the resulting calculation method. This method includes the effects of a variable, stratified atmosphere, and is based on geometric-acoustic principles. A nonlinear distortion is used to account for the weak shock field. The analytical results are compared with experimental data and excellent agreement was found, particularly with regard to signature length.
Prediction method for aircraft caused sonic boom signatures
Structural dynamics problems in design of launch vehicles for lunar mission