Dynamic Simulation and Control of Mass-Actuated Airplane

Erturk, Sukru Akif; Dogan, Atilla

doi:10.2514/6.2017-1637

Cited by 6 publications

(10 citation statements)

References 23 publications

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“…The Fig. 3 presents the simulations results accordingly [11]. According to the results, NACA4412, which is an airfoil that can be used for many different things, isn't as stable or aerodynamic as the other airfoils.…”

Section: Ground Effect On Vehicle Static Height Stability and Aerodyn...mentioning

confidence: 99%

The recent progress and state-of-art applications of aerodynamics for airplanes

Wang¹

2022

HSET

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In general, computational fluid dynamics (CFD) and wind tunnel experiments are the two core and widely implemented approaches to aircraft design and testing. This paper summarizes current developments in terms of CFD and wind tunnels in aircraft design and engineering. Information retrieval and Literature analysis are employed in order to investigate the state-of-art approaches and applications. Specifically, computational investigation of static height stability and aerodynamics of ground effect vehicles is discussed. According to the analysis, the ground effect is important for improving the realism of piloted simulation and estimating key crosswinds. The analytical modelling helps for better pilot training on various flight simulators. Moreover, further studies focus on increasing the realism of CFD simulation results ought to be carried out. These results offer a guideline for the investigation of the feasibility of CFD and wind tunnel experiments.

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Section: Ground Effect On Vehicle Static Height Stability and Aerodyn...mentioning

confidence: 99%

The recent progress and state-of-art applications of aerodynamics for airplanes

Wang¹

2022

HSET

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“…The translational and rotational dynamic equations are represented by Equations (9) and (10) respectively [34][35][36][37]:…”

Section: Model 2 Aircraft Dynamicsmentioning

confidence: 99%

“…The tail mass linear displacement or angular deflection on the other hand, functions as an alternative moment generator, changing pitching moment [34]. For Model 1, the control inputs are the tail mass positions (ρ tb x , ρ tb y , ρ tb z ) and for Model 2, the control inputs are the tail mass angular deflections (φ T , θ T , ψ T ) relative to the body frame.…”

Section: Control Inputsmentioning

confidence: 99%

Longitudinal Actuated Abdomen Control for Energy Efficient Flight of Insects

et al. 2020

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The actuated abdomens of insects such as dragonflies have long been suggested to play a role in optimisation and control of flight. We have examined the effect of this type of actuation in the simplified case of a small fixed wing aircraft to determine whether energetic advantages exist in normal flight when compared to the cost of actuation using aerodynamic control surfaces. We explore the benefits the abdomen/tail might provide to balance level flight against trim changes. We also consider the transient advantage of using alternative longitudinal control effectors in a pull up flight maneuver. Results show that the articulated abdomen significantly reduces energy consumption and increase performance in isolated manoeuvres. The results also indicate a design feature that could be incorporated into small unmanned aircraft under particular circumstances. We aim to highlight behaviours that would increase flight efficiency to inform designers of micro aerial vehicles and to aid the analysis of insect flight behaviour and energetics.

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“…Using equations (12), (16), (17), and (18) along with the drag model given in equation 5, the expression for the total thrust required to maintain the trim condition given in equation (23) simplifies to…”

Section: Endurance and Battery Lifementioning

confidence: 99%

“…m is the rotational speed of the motor, R is the phase resistance of the motor, L is the phase inductance of the motor, K e is the electrical constant of the motor, K f is the friction constant of the motor, K T is the torque constant of the motor, J p þ J m is the combined propeller and motor shaft inertia, m is the torque required to spin the propeller at a given speed ! i , and s is the voltage supplied from the battery (see Erturk and Kiruthika et al 12,13 ). Assuming a linear relation between the voltage supplied and the maximum voltage of the battery, the throttle input is given as…”

Section: Propulsion System Modelmentioning

confidence: 99%

Semi-analytical range and endurance computation of battery-powered multi-copter unmanned aerial systems under steady wind conditions

Godbole

Subbarao

Dogan

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The range and endurance of an unmanned aerial system operating nominally in an outdoor environment depends upon the available power and environmental factors like the magnitude and direction of the prevailing wind. This paper focuses on the development of semi-analytical approaches to computing the range and endurance of battery-powered multi-copter unmanned aerial system under varying wind conditions. The analytically derived range is verified against a comprehensive unmanned aerial system simulation which includes experimentally validated elements such as the propulsion system and electric power consumption modules. It is shown that the analytical approach yields the range maps in close agreement with the simulation results.

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Dynamic Simulation and Control of Mass-Actuated Airplane

Cited by 6 publications

References 23 publications

The recent progress and state-of-art applications of aerodynamics for airplanes

The recent progress and state-of-art applications of aerodynamics for airplanes

Longitudinal Actuated Abdomen Control for Energy Efficient Flight of Insects

Semi-analytical range and endurance computation of battery-powered multi-copter unmanned aerial systems under steady wind conditions

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