Robust fixed-order $H_2$ controller for micro air vehicle-design and validation (2006)
Meenakshi, M, Bhat, Seetharama M
Design and real-time validation of a robust fixed-order $H_2$ optimal controller for micro aerial vehicle,named Sarika-2, is presented. Strengthened discrete optimal projection equations, which...
Robust fixed-order $H_2$ controller for micro air vehicle-design and validation (2006)
Meenakshi, M, Bhat, Seetharama M
Design and real-time validation of a robust fixed-order $H_2$ optimal controller for micro aerial vehicle,named Sarika-2, is presented. Strengthened discrete optimal projection equations, which...
Star Pattern Identification Using Discrete Attitude Variation Technique (2005)
Rao, Nagendra G, Bhat, Seetharama M, Alex, TK
Two star pattern identification methods that use a discrete attitude variation algorithm are presented. When a spacecraft is lost in space, these methods determine the inertial attitude of the...
Longitudinal Hinfinity Stability Augmentation System for a Thrust-Vectored Unmanned Aircraft (2005)
The development of discrete longitudinal H infinity stability augmentation system to improve the handling qualities of a radio-controlled unmanned aircraft is presented. The aircraft features...
Fast access method for onboard star catalog (2005)
Rao, Nagendra G, Bhat, Seetharama M, Alex, TK
A new method to retrieve the star data from the onboard catalog is presented. A query to find stars that lie within a cone of uncertainty angle of a given unit vector is answered quickly. If stars...
Output Feedback-Based Discrete-Time Sliding-Mode Controller Design for Model Aircraft (2005)
Chaudhuri, Anirban, Bhat, Seetharama M
Model aircraft provide a low-cost test bed for the design and validation of control algorithms. The control system should improve the transient response and have good disturbance-rejection...
Output Feedback-Based Discrete-Time Sliding-Mode Controller Design for Model Aircraft (2005)
Chaudhuri, Anirban, Bhat, Seetharama M
Model aircraft provide a low-cost test bed for the design and validation of control algorithms. The control system should improve the transient response and have good disturbance-rejection...
Star Pattern Identification Using Discrete Attitude Variation Technique (2005)
Rao, Nagendra G, Bhat, Seetharama M, Alex, TK
Two star pattern identification methods that use a discrete attitude variation algorithm are presented. When a spacecraft is lost in space, these methods determine the inertial attitude of the...
Longitudinal Hinfinity Stability Augmentation System for a Thrust-Vectored Unmanned Aircraft (2005)
The development of discrete longitudinal H infinity stability augmentation system to improve the handling qualities of a radio-controlled unmanned aircraft is presented. The aircraft features...
Fast access method for onboard star catalog (2005)
Rao, Nagendra G, Bhat, Seetharama M, Alex, T K
A new method to retrieve the star data from the onboard catalog is presented. A query to find stars that lie within a cone of uncertainty angle of a given unit vector is answered quickly. If stars...
In this paper a discrete variable structure controller with sliding sector is designed for tracking the lateral acceleration command for a dual-input air-to-air missile. A new algorithm is developed...
Vibration control in a composite box beam with piezoelectric actuators (2004)
Mitra, Mira, Gopalakrishnan, S, Bhat, Seetharama M
This work presents a theoretical and experimental investigation of vibration control of composite box beams using distributed, surface mounted piezoelectric (PZT) patches as actuators. The finite...
A new super convergent thin walled composite beam element for analysis of box beam structures (2004)
Mitra, Mira, Gopalakrishnan, S, Bhat, Seetharama M
In this paper, a new composite thin wall beam element of arbitrary cross-section with open or closed contour is developed. The formulation incorporates the effect of elastic coupling, restrained...
In this paper a discrete variable structure controller with sliding sector is designed for tracking the lateral acceleration command for a dual-input air-to-air missile. A new algorithm is developed...
A new super convergent thin walled composite beam element for analysis of box beam structures (2004)
Mitra, Mira, Gopalakrishnan, S, Bhat, Seetharama M
In this paper, a new composite thin wall beam element of arbitrary cross-section with open or closed contour is developed. The formulation incorporates the effect of elastic coupling, restrained...
Vibration control in a composite box beam with piezoelectric actuators (2004)
Mitra, Mira, Gopalakrishnan, S, Bhat, Seetharama M
This work presents a theoretical and experimental investigation of vibration control of composite box beams using distributed, surface mounted piezoelectric (PZT) patches as actuators. The finite...
Mohanty, Subhasish, Bhat, Seetharama M
The optimal utilization of smart sensors and actuators in complex aerospace structure largely depends on the position of the actuators and sensors. Since piezo-ceramic material for active component...
Mohanty, Subhasish, Bhat, Seetharama M
The optimal utilization of smart sensors and actuators in complex aerospace structure largely depends on the position of the actuators and sensors. Since piezo-ceramic material for active component...
Finite elements for vibration analysis of unsymmetric laminated composite plates (1998)
Bhattacharya, B, Murty, Krishna AV, Bhat, Seetharama M
A 38-DOF (degrees-of-freedom), high precision triangular element if developed for vibration analysis of laminated composite panels with explicitly defined stiffness and mass matrices. A new,...
Robust low order dynamic controller for flexible spacecraft (1991)
Bhat, Seetharama M, Sreenatha, AG, Shrivastava, SK
The design of an optimal low-order dynamic controller with a-shift (alpha-shift) for attitude control is attempted for a flexible satellite which is a solar electric propulsion spacecraft. The...
An Explicit Closed-Loop Guidance for Launch Vehicles (1991)
Vittal, Vijay R, Bhat, Seetharama M
An explicit, near optimal, closed-loop steering logic common to both, 2- and 3-dimensional launch trajectories is presented. This scheme uses a single steering angle in a canted plane, which can then...
Robust low order dynamic controller for flexible spacecraft (1991)
Bhat, Seetharama M, Sreenatha, AG, Shrivastava, SK
The design of an optimal low-order dynamic controller with a-shift (alpha-shift) for attitude control is attempted for a flexible satellite which is a solar electric propulsion spacecraft. The...
An Explicit Closed-Loop Guidance for Launch Vehicles (1991)
Vittal, Vijay R, Bhat, Seetharama M
An explicit, near optimal, closed-loop steering logic common to both, 2- and 3-dimensional launch trajectories is presented. This scheme uses a single steering angle in a canted plane, which can then...
An optimal dynamic output feedback controller for a flexible spacecraft (1990)
Sreenatha, AG, Bhat, Seetharama M, Shrivastava, SK
The design of a low-order dynamic output feedback controller for a flexible spacecraft is carried out using modified linear quadratic Gaussian (LQG) theory. The necessary conditions for optimization...
An optimal dynamic output feedback controller for a flexible spacecraft (1990)
Sreenatha, AG, Bhat, Seetharama M, Shrivastava, SK
The design of a low-order dynamic output feedback controller for a flexible spacecraft is carried out using modified linear quadratic Gaussian (LQG) theory. The necessary conditions for optimization...