Performance Maximization of Tactical Unmanned Aerial Vehicles via Integrated Passive and Active Morphing

In this conference paper integrated passive andactive morphing methodology is used on tactical unmannedaerial vehicles (TUAVs) in order to maximize autonomous flightperformance. For this drive dynamic modeling of TUAVsproduced in Erciyes University Faculty of Aeronautics andAstronautics Model Aircraft Laboratory is followed in order toget state-space models and a simulation model. This TUAVcalled as ZANKA-III is 50 kg, has range of around 3000 km,endurance of around 28 h, and ceiling altitude of around 12500m. Von-Karman turbulence modeling is benefited in order tomodel atmospheric turbulence in simulation environment. Astochastic optimization method namely simultaneousperturbation stochastic approximation (i.e. SPSA) is applied inorder to get optimum morphing parameters (e.g. assemblyposition of tailplane to fuselage and extension ratio of wingspan)

Effect of the Simultaneous Variation in Blade Root Chord Length and Blade Taper on Helicopter Flight Control Effort

In this study, the effect of simultaneous variation in blade root chord length and blade taper on the control effort of helicopter flight control system (i.e., FCS) of a helicopter is investigated. Therefore, helicopter models (i.e., complex, control-oriented, and physics-based models) including the main physics and essential dynamics are used. The effect of simultaneous variation in the blade root chord length and blade taper (i.e., in both chordwise and lengthwise directions dependently) on the control effort of an FCS of a helicopter and also on the closed-loop responses is studied. Comparisons in terms of the control effort and peak values with and without variations in the blade root chord and blade taper changes are carried out. For helicopter FCS variance-constrained controllers, specific output variance-constrained controllers are beneficial

Helicopter Control Energy Reduction Using Moving Horizontal Tail

Helicopter moving horizontal tail (i.e., MHT) strategy is applied in order to save helicopter flight control system (i.e., FCS) energy. For this intention complex, physics-based, control-oriented nonlinear helicopter models are used. Equations of MHT are integrated into these models and they are together linearized around straight level flight condition. A specific variance constrained control strategy, namely, output variance constrained Control (i.e., OVC) is utilized for helicopter FCS. Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated. Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA). In order to observe improvement in behaviors of classical controls closed loop analyses are done

Simultaneous arm morphing quadcopter and autonomous flight system design

Purpose: The purpose of this paper is to obtain values that stabilize the lateral and longitudinal flight of the quadrotor for which the morphing amount and the best Proportional-Integral-Derivative (PID) coefficients are determined by using the simultaneous perturbation stochastic approximation (SPSA) optimization algorithm. Design/methodology/approach: Quadrotor consists of body and arms; there are propellers at the ends of the arms to take off and rotors that rotate them. By reducing the angle between mechanism 1 and the rotors with the horizontal plane, the angle between mechanism 2 and the arms, the rotors rise and different configurations are obtained. Conventional multi-rotor aircraft has a fixed fuselage and does not need a tail rotor to change course as helicopters do. The translational and rotational movements are provided by the rotation of the rotors of the aircraft at different speeds by creating moments about the geometric center in 6-degree-of-freedom (DOF) space. These commands sent from the ground are provided by the flight control board in the aircraft. The longitudinal and lateral flight stability and properties of different configurations evaluated by dynamic analysis and simulations in 6 DOF spaces are investigated. An algorithm and PID controller are being developed using SPSA to achieve in-flight position and attitude control of an active deformable aircraft. The results are compared with the results of the literature review and the results of the previous article. Findings: With SPSA, the best PID coefficients were obtained in case of morphing. Research limitations/implications: The effects of quadrotor arm height and hub angle changes affect flight stability. With the SPSA optimization method presented in this study, the attitude is quickly stabilized. Practical implications: With the optimization method, the most suitable PID coefficients and angle values for the lateral and longitudinal flight stability of the quadrotor are obtained. Social implications: The transition rate and PID coefficients are determined by using the optimization method, which is advantageous in terms of cost and practicality. Originality/value: With the proposed method, the aircraft can change shape to adapt to different environments, and the parameters required for more stable flight for each situation will be calculated, and this will be obtained more quickly and safely with the SPSA optimization method. © 2023, Emerald Publishing Limited

Stochastic longitudinal autopilot tuning for best autonomous flight performance of a morphing decacopter

In this conference paper autonomous flight performance maximization of a morphing decacopter is considered by using stochastic optimization approach. For flight controller a PID based hierarchical control system is chosen. In this paper PID controller which is used for pitch angle is considered. In this application only longitudinal flight and longitudinal autopilot is considered where the pitch motion is in primary interest and the used controller is the pitch control. For optimization technique simultaneous perturbation stochastic approximation (i.e., SPSA) is selected. It is fast and safe in stochastic optimization problems when it is not possible to evaluate gradient analytically. At the end a cost function consisting terms that settling time, rise time and overshoot is minimized. A detailed graphical analysis is done in order to better present effect of morphing on longitudinal flight of decacopter flight. Moreover, the cost function consist of rise time, settling time, and overshoot during trajectory tracking. © 2023 Published by ISRES Publishing: www.isres.org