M Dileep

Design of Fuzzy Logic Controller for Lateral Dynamics Control of Aircraft by Considering the Cross-Coupling Effect of Yaw and Roll on Each Other

In this paper, we explore fuzzy logic approach for lateral control of aircrafts. Here the effect of roll on yaw and that of yaw on roll is taken into account. The dynamic modeling of lateral control system that controls the lateral dynamics of an aircraft.is presented. The aircraft being considered in this work is a standard NAVION Transport aircraft [1]. A suitable mathematical model to describe the dynamics of an aircraft is derived. A single fuzzy controller is designed which will control both yaw and roll of the aircraft simultaneously. In this paper the transfer functions for yaw and roll is derived and their effects on each other is taken into account so that the system will have greater accuracy and efficiency than the application of two separate controllers. This design is very cost effective and will significantly reduce instability and increases maneuverability. Simulation results for the response of lateral controller are presented in time domain. Finally, the performance of lateral control system is analyzed based on common criteria of step’s response

New Programming Approach for Steepest Descent Optimization of Rocket Trajectories

In this paper a new programming methodology for optimizing rocket trajectories using steepest descent technique is presented. The programming is done in Matlab platform. At first the dynamical equations of rocket is derived and for the proper derivation and analysis of the equations ,Eulers integration method is used. A new programming approach is designed and the equations are optimized using steepest descent technique, assuming certain boundary conditions. The results obtained are verified and it is seen that the optimal trajectory is attained with all objectives satisfied. This project is done at Vikram Sarabhai Space Centre(VSSC),a constituent of Indian Space Research Organization(ISRO).

Optimal trajectory generation of launch vehicle using PSO algorithm

This paper presents an approach to solve a trajectory optimization problem for a launch vehicle using particle swarm optimization. Trajectory generation for a single stage liquid propellant launch vehicle is considered by using angle of attack as a control variable. The problem is solved by considering minimization of terminal error as an objective with some path constraints and fixed boundary conditions. The burning time of the liquid rocket engine is fixed, leading to fixed time problem. Two different types of inertia weight is examined in this problem, one is the random function and the other is linearly varying. The effectiveness is verified using simulation results obtained from Matlab simulation environment.