* Member ASME ABSTRACT The vibro-acoustic environment inside a launch vehicle payload fairing is extremely violent resulting in excessive development costs for satellites and other payloads. The development of smart structures and active noise and vibration control technologies promised to revolutionize the design, construction and, most importantly, the acoustic environment within these fairin...

This paper presents an attitude control algorithm for a Reusable Launch Vehicle (RLV) with a low lift/drag ratio (L/D < 0.5), in the presence of external disturbances, model uncertainties, control output constraints and the thruster model. The main novelty of proposed control strategy is a new combination of the attitude control methods included backstepping, dynamic inversion and adaptive cont...

Attitude control of a flexible launch vehicle is addressed in this study. A ground experimental model is developed for verification of different stabilization strategies. The experimental set up duplicates planar motion of flexible launch vehicles as a coupled hybrid dynamics of rigid body pitching motion and flexible vibration. In particular, adaptive notch filter, which updates filter paramet...

Information and communication technologies (ICT) play significant role in modern smart grids (SG). SG functionalities require implementation of devices with computing performance into the grids and communication network between these devices. This has also been the case in a low-voltage direct current (LVDC) electricity distribution system, to which remote and automated grid monitoring and cont...

the amount of analysis and testing required per mission must be reduced over that performed for the partially re-usable Space Shuttle. A goal for future RLV flight control is to design and test the flight control system to operate within a prescribed flight envelope and loading margin, and requiring only payload/fuel parameters and “route” to be specified for a given mission. It has been estima...

This paper describes the fundamental principles of launch vehicle flight control analysis and design. In particular, the classical concept of “drift-minimum” and “load-minimum” control principles is re-examined and its performance and stability robustness with respect to modeling uncertainties and a gimbal angle constraint is discussed. It is shown that an additional feedback of angle-of-attack...

The control system of the NASA Crew Launch Vehicle is designed to meet performance and robustness requirements during its ascent flight phase. However, the controller bandwidth and the attainable level of robust performance is limited by the degree of flexibility inherent in the long and slender design that has been adopted for this vehicle. Since there remains a substantial degree of uncertain...

Improvement of the launch phase of a jet powered Unmanned Aerial Vehicle (UAV) with Jet Assisted Take Off (JATO), has been the subject of attention in the UAV industry. Use of flight simulation tools reduces the risk and required some amount of flight testing for complex aerospace systems. Full nonlinear equations of motion are used to study and simulate this maneuver and three case studies of ...