Kevin R. Scalera

Bio: Kevin R. Scalera is an academic researcher from Virginia Tech. The author has contributed to research in topics: Control reconfiguration & Flight dynamics. The author has an hindex of 2, co-authored 2 publications receiving 28 citations.

A Comparison of Control Allocation Methods for the F-15 ACTIVE Research Aircraft Utilizing Real-Time Piloted Simulations

Abstract: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ii Acknowledgments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iii Table of

Modification of a surplus navy 2f122a a-6e oft for flight dynamics research and instruction

Abstract: This paper describes the adaptation of a Navy Operational Flight Trainer (OFT) to a university flight dynamics instruction and research platform The requirements of the modified system are described and compared with the deficiencies of the system in its original state Completed and future modifications of the trainer to satisfy the requirements are detailed Representative uses of the flight simulator for classroom instruction as well as research are described

A closed-loop comparison of control allocation methods

Abstract: This paper compares closed- and open-loop performance measures for sixteen control allocation approaches. The approaches are regular and discrete time versions of direct allocation, linear programming, quadratic programming, and several variations of the weighted pseudo-inverse approach including a cascaded generalized inverse. The control allocation methods are first evaluated using open-loop measures including the percent volume of the attainable moment subset for which the allocation method produces admissible solutions and the ability to attain commanded moments for a prescribed rolling maneuver. Then, the control allocation methods are compared closed-loop using a dynamic inversion control law to perform the same rolling maneuver. All maneuver results are completed using a simplified 5 degree-of-freedom nonlinear simulation with seven control effectors. The results show that the open-loop measures do not necessarily translate to closed-loop performance.

Computationally efficient control allocation

Abstract: A computationally efficient method for calculating near-optimal solutions to the three-objective, linear control allocation problem is disclosed. The control allocation problem is that of distributing the effort of redundant control effectors to achieve some desired set of objectives. The problem is deemed linear if control effectiveness is affine with respect to the individual control effectors. The optimal solution is that which exploits the collective maximum capability of the effectors within their individual physical limits. Computational efficiency is measured by the number of floating-point operations required for solution. The method presented returned optimal solutions in more than 90% of the cases examined; non-optimal solutions returned by the method were typically much less than 1% different from optimal and the errors tended to become smaller than 0.01% as the number of controls was increased. The magnitude of the errors returned by the present method was much smaller than those that resulted from either pseudo inverse or cascaded generalized inverse solutions. The computational complexity of the method presented varied linearly with increasing numbers of controls; the number of required floating point operations increased from 5.5 i, to seven times faster than did the minimum-norm solution (the pseudoinverse), and at about the same rate as did the cascaded generalized inverse solution. The computational requirements of the method presented were much better than that of previously described facet-searching methods which increase in proportion to the square of the number of controls.

Nichtlineare adaptive Regelung eines unbemannten Fluggerätes

Abstract: Eine zentrale Anforderung an unbemannte Fluggerate ist die autonome Durchfuhrung der geplanten Flugmission. Zur Erreichung dieses Zieles muss das Regelungssystem des Flugzeuges ein hohes Mas an Robustheit gegenuber Modell- und Parameterunsicherheiten sowie die Anpassungsfahigkeit aufweisen, um Stor- und Ausfallsituationen meistern zu konnen. Ferner muss die Einhaltung von Betriebsgrenzen gewahrleistet sein. Es wird ein auf nichtlinearer dynamischer Inversion beruhendes adaptives Regelungskonzept vorgestellt, das die genannten Anspruche erfullt und das den Flug auf komplexen, dreidimensionalen Bahnen mit hoher Bandbreite und groser Fuhrungsgenauigkeit ermoglicht. Das System erlaubt die volle Ausnutzung der Flugleistungen der Konfiguration und berucksichtigt insbesondere auch Sattigungen in Ruderausschlagen und -stellraten. Der Nachweis der Funktionsfahigkeit erfolgt anhand nichtlinearer Simulationen unter Verwendung eines komplexen Simulationsmodells.

Evolution of Flying Qualities Analysis: Problems for a New Generation of Aircraft

Abstract: : A number of challenges in the development and application of flying qualities criteria for modern aircraft are addressed in this dissertation. The history of flying qualities is traced from its origins to modern day techniques as applied to piloted aircraft. Included in this historical review is the case that was made for the development of flying qualities criteria in the 1940s and 1950s when piloted aircraft became prevalent in the U.S. military. UAVs today are in the same context historically as piloted aircraft when flying qualities criteria were first developed. Two longitudinal flying qualities criteria were developed for application to autonomous UAVs. These criteria center on mission performance of the integrated aircraft and sensor system. The first criterion is based on a sensor platform's ability to reject aircraft disturbances in pitch attitude. The second criterion makes use of energy methods to create a metric to quantify the transmission of turbulence to the sensor platform. These criteria are evaluated with airframe models of different classes of air vehicles using the CASTLE 6 DOF simulation. Another topic in flying qualities is the evaluation of nonlinear control systems in piloted aircraft. An L1 adaptive controller was implemented and tested in a motion-based, piloted flight simulator. Results show that the adaptive controller was able to recover good flying qualities from a degraded aircraft. The final topic addresses a less direct, but extremely important challenge for flying qualities research and education: a capstone course in flight mechanics teaching flight techniques and featuring a motion-based flight simulator was implemented and evaluated. The course used a mixture of problem-based learning and role-based learning to create an environment in which students could explore key flight mechanics concepts. An evaluation of the course's effectiveness in promoting an understanding of key flight mechanics concepts is presented.