Modeling and Simulation to Study Flight Dynamics of a Morphable Wing Aircraft

Obradovic, Borna; Subbarao, Kamesh

doi:10.2514/6.2009-6240

Cited by 12 publications

(5 citation statements)

References 5 publications

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“…Substitution of equations (5) through (16) in equations (1) through (4) leads to nonlinear equations that can be written in the form (21).…”

Section: Aircraft Modelmentioning

confidence: 99%

“…There have been several studies in morphing aircraft that have focused on the steady-state benefits of altering a configuration for issues such as fuel consumption, range and endurance, cost and logistics, actuator energy, maneuverability and airfoil requirements [9][10][11][12][13][14][15][16][17] . There have also been studies with pre-dominant focus on aerodynamic performance and materials -these have demonstrated clear benefits of morphing as measured by aerodynamic performance metrics.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Single Network Adaptive Critic (SNAC) Architecture for Optimal Tracking Control of a Morphing Aircraft during a Pull-up Maneuver

Nobleheart

Lakshmikanth

Chakravarthy

et al. 2013

AIAA Guidance, Navigation, and Control (GNC) Conference

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In this paper, we discuss the application of a Single Network Adaptive Critic (SNAC) tracking controller on a morphing fighter aircraft modeled as a time-varying system. The performance of the aircraft is investigated from a flight dynamics perspective during a pull-up maneuver; and the time scale over which the morphing occurs is of the same order as the flight dynamics, due to which the influence of time-varying effects is significant. The time varying dynamical equations are adopted for a fighter aircraft which is assumed to be equipped with a variable-sweep wing. The SNAC controller is implemented on the longitudinal dynamic model of this aircraft. The neural network is trained to provide optimal tracking control over the aircraft flight envelope state space as the wing is swept along a specific morphing trajectory during the maneuver. Nomenclaturek = discrete time index j = sweep angle trajectory index = state input = co-state = control = lift-curve slope = static longitudinal stability derivative coefficient = sweep angle = time = System matrix = Control matrix = longitudinal velocity = normal velocity = pitch rate = pitch angle S = solution of Joseph stabilized version of Riccati equation Q = State weighting matrix R = Control weighting matrix = sampling time tol = training tolerance

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“…Substitution of equations (5) through (16) in equations (1) through (4) leads to nonlinear equations that can be written in the form (21).…”

Section: Aircraft Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Single Network Adaptive Critic (SNAC) Architecture for Optimal Tracking Control of a Morphing Aircraft during a Pull-up Maneuver

Nobleheart

Lakshmikanth

Chakravarthy

et al. 2013

AIAA Guidance, Navigation, and Control (GNC) Conference

View full text Add to dashboard Cite

show abstract

“…There have been several studies into morphing aircraft that have focused on the steady-state benefits of altering a configuration for issues such as fuel consumption, range and endurance, cost and logistics, actuator energy, maneuverability and airfoil requirements. [1][2][3][4][5][6][7][8][9] There have also been studies with pre-dominant focus on aerodynamic performance and materials-these have demonstrated clear benefits of morphing as measured by aerodynamic performance metrics. The introduction of morphing, or shape-changing actuation, to an aircraft will alter the shape and aerodynamics of the vehicle.…”

Section: Introductionmentioning

confidence: 99%

Optimal and Decentralized Controller Designs for an Elastically Shaped Aircraft

Nobleheart

Chakravarthy

Nguyen

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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In this paper, control design of an elastically shaped aircraft with highly flexible wings is discussed. The aircraft has the capability to actively change the wing twist and bending in flight so as to achieve a local angle of attack distribution that is optimal for the specific flight condition. The aircraft has 23 control surfaces and is longitudinally unstable in the open loop. Two design approaches are explored. In the first approach, a multi-objective performance index that includes an explicit drag minimization term is considered, and an optimal controller design is performed using this performance index. In the second approach, a decentralized controller that uses the elevator to control only the rigid body modes, and the wing flap and slat control surfaces to control the flexible modes, is developed. Simulation results demonstrate the validity of these controllers in stabilizing this elastic aircraft.

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“…Work done in the area of articulated MAVs has been largely based on the vast background knowledge available for rigid MAVs. Additional investigations of the several advantages wing articulation provides the MAV include MAV turning performance [ 13 ], steady and dynamic stability as well as flight control [ 14 ], vertical/updraft wind gust alleviation [ 8 ], shape optimization by actively moving the wings to new positions [ 10 ], and mission optimization using optimal MAV configurations [ 11 ]. Researchers such as Abdulrahim and Lind [ 15 ] studied changes that occur to the trim conditions as the MAV wing deflections change in wing loading and due to the control effort.…”

Section: Introductionmentioning

confidence: 99%

Gust Mitigation of Micro Air Vehicles Using Passive Articulated Wings

Oduyela

Slegers

2014

The Scientific World Journal

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Birds and insects naturally use passive flexing of their wings to augment their stability in uncertain aerodynamic environments. In a similar manner, micro air vehicle designers have been investigating using wing articulation to take advantage of this phenomenon. The result is a class of articulated micro air vehicles where artificial passive joints are designed into the lifting surfaces. In order to analyze how passive articulation affects performance of micro air vehicles in gusty environments, an efficient 8 degree-of-freedom model is developed. Experimental validation of the proposed mathematical model was accomplished using flight test data of an articulated micro air vehicle obtained from a high resolution indoor tracking facility. Analytical investigation of the gust alleviation properties of the articulated micro air vehicle model was carried out using simulations with varying crosswind gust magnitudes. Simulations show that passive articulation in micro air vehicles can increase their robustness to gusts within a range of joint compliance. It is also shown that if articulation joints are made too compliant that gust mitigation performance is degraded when compared to a rigid system.

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Modeling and Simulation to Study Flight Dynamics of a Morphable Wing Aircraft

Cited by 12 publications

References 5 publications

Single Network Adaptive Critic (SNAC) Architecture for Optimal Tracking Control of a Morphing Aircraft during a Pull-up Maneuver

Single Network Adaptive Critic (SNAC) Architecture for Optimal Tracking Control of a Morphing Aircraft during a Pull-up Maneuver

Optimal and Decentralized Controller Designs for an Elastically Shaped Aircraft

Gust Mitigation of Micro Air Vehicles Using Passive Articulated Wings

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