Combined morphing assessment software using flight envelope data and mission based morphing prototype wing development (CHANGE

2015-12-31
"Morphing in aircrafts has been studied and used throughout recent time in order to increase their flight envelope. This characteristic is of the upmost importance in order to offer a greater efficiency, versatility and performance during the assigned mission. Moreover an aircraft with the capability to adapt itself to each given situation is prone to achieve positive results to a range of different missions instead of requiring a specific aircraft to conduct one specific mission. The main objective of this project is to study and develop a novel morphing system which integrates up to four different morphing mechanisms into in a single wing and to demonstrate this new ability in flight. This system would take advantage of all the performance improvements achieved by adopting its wing shape according to the mission requirements of each flight phase. Therefore, this project envisions to mitigate the required energy (and thus fuel consumption) to maintain the aircraft’s flight and to perform the necessary flight maneuvers by offering the capacity to mold the exterior of the aircraft in order to enhance the necessary aspect of flight so as to lessen the required energy, such as lift over drag ratio, efficiency in aerodynamic control, lower stall velocity or to change to a better planform to perform a required maneuver. In order to prepare the basis for an eventual cognitive morphing on-board controller which ability is focused in the autonomous control of all morphing system of the wing, it is necessary to develop a software that is capable of rendering the most efficient morphed wing based on the information of the current phase. This software would therefore, be able to conduct an assessment of the introduced flight conditions of the wing and display the accordant morphed wing (using a database with all current morphing systems) capable to fly with the highest performance."

Suggestions

Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...
Experimental Investigation of Optimal Gap Distance between Rotors of a Quadrotor UAV
Kaya, Dilber Derya; Kutay, Ali Türker; Tekinalp, Ozan (2017-06-09)
The effect of spacing between the rotors of a quadrotor Unmanned Aerial Vehicle (UAV) in hovering flight is investigated. Experiments are conducted to obtain a mathematical relation between the diameter of the rotor and gap distance between each rotor. Constraints such as the maximum thrust force and minimum energy consumption are imposed. Several rotors having different sizes are tested at various RPMs with a changing gap distances, and total thrust produced by four rotors is measured. The results are give...
Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins
Aslan, Göktuğ Murat; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2018)
In this thesis, a surface-to-surface missile model with laminated composite fins is examined with respect to one-way static aeroelastic response under constant supersonic flight conditions. Two different modified double wedge fins or control surfaces using for control actuation system of a missile are investigated and compared in terms of aerodynamic and linear structural characteristics in order to minimize tip deflection. A serial set of steady-state supersonic Computational Fluid Dynamics (CFD) analyses ...
Online Dynamic Trim and Control Limit Estimation
Yavrucuk, İlkay (American Institute of Aeronautics and Astronautics (AIAA), 2012-9)
The online estimation of a maneuvering steady-state condition of an aircraft, called the dynamic trim, is used to estimate the allowable control travel during flight, a key information in pilot cueing for envelope limit protection. In this paper a new methodology is presented where adaptive models are used to estimate online local dynamic trim conditions, while requiring very limited a priori vehicle information. Adaptive neural networks are employed to enable online learning. The models are used to estimat...
Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft
Özkan, Salih Volkan; Tekinalp, Ozan; Department of Aerospace Engineering (2022-2-10)
Robust control technique is utilized to develop flight control laws for highly maneuverable aircraft. A structured H-Infinity controller is used to optimize the gains of the proposed control algorithm. For this purpose systune algorithm available in Matlab is employed to successfully obtain the controller gains satisfying selected design requirements. Designed control laws are evaluated according to these requirements and validation of the methodology is presented.
Citation Formats
Y. Yaman, “Combined morphing assessment software using flight envelope data and mission based morphing prototype wing development (CHANGE ,” 2015. Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/58069.