Control of Ducted Fan Aircraft Using Redundant Effectors

Ozdemir, Gurbuz Taha; Horn, Joseph F.

doi:10.2514/6.2009-5928

Cited by 4 publications

(3 citation statements)

References 6 publications

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“…Another expression for the velocity ν ∞ is found by substituting the Eqs. (5) and 7into (9). The final result after joint solution of the velocity ν ∞ is given as the newly formulated inflow equation.…”

Section: Ducted-fan System Forces and Momentsmentioning

confidence: 99%

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Flight Control Development and Test for an Unconventional VTOL UAV

Wang¹,

Chen²,

Ma³

et al. 2016

Autonomous Vehicle

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This chapter deals with the control system development and flight test for an unconventional flight vehicle, namely, a tandem ducted-fan experimental flying platform. The first-principle modeling approach combined with the frequency system identification has been adopted to obtain a high-fidelity dynamics model. It is inherently less stable and difficult to control. To accomplish the required practical flight tasks, the flying vehicle needs to work well even in windy conditions. Moreover, for flight control engineers, simple prescribed multi-loop controller structures are preferred. To handle the multiple problems, a structured velocity controller consisting of two feedback loops is developed, where inner loop provides stability augmentation and decoupling, and the outer loop guarantees desired velocity tracking performance. The simultaneous design of the two-loop controllers under multiple performance requirements in the usual H ∞ metrics can be cast as a nonsmooth optimization program. To compensate for changes in plant dynamics across the flight envelope, a smooth and compact polynomial scheduling formula is implemented as a function of the forward flight speed. Both simulations and flight test results have been presented in this work to showcase the potential for the proposed robust nonlinear control system to optimize the performance of UAV, specifically unconventional vehicles.

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Section: Ducted-fan System Forces and Momentsmentioning

confidence: 99%

“…A number of contribution focuses on the problems of feedback control design for such a class of systems. In [5], a dynamic inversion controller is proposed to govern the nonlinear dynamics of a ducted-fan aircraft. In [6], a framework of nonlinear robust control based on a path following strategy is applied to a ducted-fan miniature UAV .…”

Section: Introductionmentioning

confidence: 99%

Flight Control Development and Test for an Unconventional VTOL UAV

Wang¹,

Chen²,

Ma³

et al. 2016

Autonomous Vehicle

View full text Add to dashboard Cite

show abstract

“…In terms of the flight control design considered here, different approaches, ranging from linear control methods to more elaborate nonlinear control solutions, have been proposed for attitude and/or velocity stabilization and trajectory tracking applications . A dynamic inversion controller combined with a control allocation method was developed for a tandem ducted fan aircraft . The control strategy was able to reject considerable wind gusts and minimize attitude changes, but the design method was only validated in simulations and relied on an accurate dynamic model.…”

Section: Introductionmentioning

confidence: 99%

Robust Flight Control Using Nonsmooth Optimization for a Tandem Ducted Fan Vehicle

Chen

Wang

et al. 2016

Asian Journal of Control

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This work addresses the aerodynamic modeling and near-hover-flight control design for an unconventional aerial robot of the tandem ducted fan configuration, which is intended to be prototypical of a flight service vehicle. The main model elements of this novel unmanned vehicle, which exhibit highly nonlinear and unstable open-loop modes, are presented. A frequencydomain controllability analysis concerning the plant's behavior around the hovering flight condition is then adopted to determine the expected control performance, which is of important practical significance to controllability improvement through vehicle design changes. A robust controller that stabilizes the unmanned vehicle under wind disturbances is designed using a newly developed nonsmooth optimization algorithm, which rigorously and efficiently tunes the arbitrarily predefined structured controller against multiple control requirements. A successive two-loop architecture is employed in the designed controller. In this architecture, the inner loop provides stability augmentation and decoupling, and the outer loop guarantees the desired velocity tracking performance. Simulation results under stochastic wind gusts are presented to verify the performance of the proposed controllers. Preliminary flight tests are also carried out to demonstrate the performance of the system.

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