Vikram K. Singh
- Courses1
- Reviews2
- School: Miami University
- Campus: Oxford
- Department: Engineering
- Email address: Join to see
- Phone: Join to see
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Location:
501 E High St
Oxford, OH - 45056 - Dates at Miami University: March 2013 - January 2016
- Office Hours: Join to see
Biography
Miami University Oxford - Engineering
Experience
Louisiana State University
Visiting Assistant Professor
Vikram worked at Louisiana State University as a Visiting Assistant Professor
Miami University
Assistant Professor
Vikram worked at Miami University as a Assistant Professor
Miami University
Associate Professor
Vikram worked at Miami University as a Associate Professor
Miami University
Professor
Vikram worked at Miami University as a Professor
Air Force Research Laboratory
Summer Faculty Fellow
Research on Active Aeroelastic Control
Air Force Research Laboratory, Wright Patterson Air Force Base
Visiting Researcher
Research on Active Aeroelastic Control
University of Liverpool
Visiting Senior Fellow
Vikram worked at University of Liverpool as a Visiting Senior Fellow
Education
Birla Institute of Technology
BE
Mechanical Engineering
Louisiana State University
PhD
Mechanical Engineering
Louisiana State University
Visiting Assistant Professor
Publications
Effect of Embedded Control Surface Actuators on Active Aeroelastic Control
56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
In this research, the effect of the control surface dynamics (actuator dynamics) on realizing active aeroelastic control through control surface actuation is presented. The effect of actuator dynamics on the closed loop stability and flutter margins are investigated. It is shown that arbitrary selection of actuator may lead to instability of the actuator modes despite the control of aeroelastic poles for flutter suppression and flutter boundary extension. This is overcome by simultaneous control of aeroelastic and actuator poles. The formulation to achieve active aeroelastic control with multiple actuators having actuator dynamics is developed here. This also allows the selection of actuator parameters driving the control surfaces for a given cost objective. Numerical examples are presented to demonstrate the solution strategy
Effect of Embedded Control Surface Actuators on Active Aeroelastic Control
56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
In this research, the effect of the control surface dynamics (actuator dynamics) on realizing active aeroelastic control through control surface actuation is presented. The effect of actuator dynamics on the closed loop stability and flutter margins are investigated. It is shown that arbitrary selection of actuator may lead to instability of the actuator modes despite the control of aeroelastic poles for flutter suppression and flutter boundary extension. This is overcome by simultaneous control of aeroelastic and actuator poles. The formulation to achieve active aeroelastic control with multiple actuators having actuator dynamics is developed here. This also allows the selection of actuator parameters driving the control surfaces for a given cost objective. Numerical examples are presented to demonstrate the solution strategy
Mode Classification and Dynamic Analysis of Coupled “Motor-Compressor-Flexible-Foundation” Structures
Topics in Modal Analysis ,
The rotating machine structure along with the flexible foundation is a multibody dynamical system consisting of several coupled flexible elements i.e. rotating shafts, oil film bearings, bearing housing, machine and foundation structure. The interaction among these elements can influence the overall rotor dynamics behaviour of the drive train system. Recently, relationship between the dynamics of rotating machine and its flexible base connected at multiple coupling points are developed. Research is currently underway to extend this analysis to large industrial-scale structures such that they can become the basis for designing the coupling parameters for avoiding excessive vibration due to coupling. In this paper, an industrial-scale-rotor-bearing simulation model is developed. Through numerical simulation, the influence of foundation flexibility and coupling parameters on the coupled modes of rotor dynamic system is obtained. The classification of modes in the coupled system is carried out and the influence of the foundation flexibility on the response of various flexible components is investigated. It is anticipated that such a model will pave a way to seek structural modifications on the foundation or the coupling parameters such that overall vibration can be minimized and desired critical speeds of the coupled system can be designed.
