Numerical Investigation of Engine Effects on a Transport Aircraft with Circulation Control

Keller, Dennis; Rudnik, Ralf

doi:10.2514/1.c032724

Cited by 17 publications

(9 citation statements)

References 15 publications

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“…As a consequence, a nonlinear controller stabilizing this instability is essential. The latter and other aerodynamic effects were previously researched [1,[5][6][7][8] and are briefly presented in section III.…”

Section: Nomenclaturementioning

confidence: 99%

Adaptive Nonlinear Flight Control of STOL-Aircraft Based on Incremental Nonlinear Dynamic Inversion

Beyer

Kuzolap

Steen

et al. 2018

2018 Modeling and Simulation Technologies Conference

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In this paper an adaptive control system for a passenger aircraft with active high-lift system is presented. Failures in the high-lift system parts of such aircraft are critical and consequently need to be handled automatically. An adaptive controller is proposed which consists of incremental nonlinear dynamic inversion (INDI) with a reference model and linear controller. As the INDI is adaptive against uncertainties or system failures, no additional adaptive element like a neural network is needed. The implementation of the INDI requires a nonlinear system model which is permanently linearized during the runtime in order to obtain the current input matrix which here basically consists of the control surfaces effectiveness. It also requires feedback of the translational and rotational acceleration measurements which usually suffer from noise. In order to test the adaptivity of the INDI, a partial failure of the high-lift system during the landing approach is regarded. It shows that the INDI is capable of compensating the error by only using the conventional control surfaces. * Research Associate, Ph.D. Student, y.beyer@tu-bs.de. † Research Associate, Ph.D. Student, a.kuzolap@tu-bs.de. ‡ Senior Researcher, m.steen@tu-bs.de. § Research Scientist, jobst.diekmann@dlr.de. ¶ Scientific Advisor, nicolas.fezans@dlr.de Downloaded by Yasim Hasan on July 12, 2018 | http://arc.aiaa.org |

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Section: Nomenclaturementioning

confidence: 99%

Adaptive Nonlinear Flight Control of STOL-Aircraft Based on Incremental Nonlinear Dynamic Inversion

Beyer

Kuzolap

Steen

et al. 2018

2018 Modeling and Simulation Technologies Conference

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“…The flight dynamics of the aircraft are simulated by a 6-DoF flight mechanics model based on nonlinear highfidelity 3D CFD data sets created by partner projects of the SFB 880 [15]. The modeling approach follows a classical point mass approach with the acting forces and moments calculated by dimensionless coefficients.…”

Section: Modeling Approachmentioning

confidence: 99%

Controllability of an aircraft with active high-lift system using a segmentwise controllable flap system

et al. 2018

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Active high-lift aircraft needs exceptional aerodynamic control performance to operate at low airspeed. In this study, a new concept for the improvement of controllability is investigated, incorporating the special capabilities of a blown Coandȃ flap system. The blowing system along the flaps is divided into 12 independently controllable segments. This provides the opportunity to influence the lift distribution along the wingspan by individual blowing performance settings for each segment without changing the flap deflection. This offers the chance to control the airplane in the final approach phase with fully deflected flaps using only the blowing system and to dedicate specific control tasks to particular segments. A model for the blowing system influence on the local wing aerodynamics is implemented in an existing nonlinear full aircraft flight mechanics model. The system capabilities in terms of roll control and the climb performance are investigated by criteria' evaluation and dynamic simulation assessment. The ability to fly turn/altitude change maneuvers by utilizing the active high-lift system is proven and a corresponding control concept is presented. It also includes the compensation of different blowing failure cases, which leads to acceptable but still improvable aircraft reactions.

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“…For turbulence modeling, the Spalart-Allmaras one-equation model in its original formulation 17 , but with vortical and rotational flow correction based on the Spalart-Shur 18 is used to preserve comparability with the simulations carried on REF-2 configuration, see Ref. 12. Furthermore, it appears to be a quite suitable model for a preliminary analysis of the considered complex configuration.…”

Section: B Flow Solver and Simulations Proceduresmentioning

confidence: 99%

High Lift Design and Aerodynamic Assessment for an Over-the-Wing Pylon-Mounted Engines Configuration with STOL Capabilities

Savoni

Rudnik

Ronzheimer

et al. 2018

2018 Applied Aerodynamics Conference

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A CFD-based assessment of the low speed high lift performance of an over-the-wing mounted engine installations for a short range airliner with STOL capabilities is presented in this paper. The configuration is representative for a 100 passenger aircraft and characterized by pylon mounted over-the-wing installed UHBR-engines. The high lift system features active segmented and highly deflected Coanda flaps and a specifically designed droop nose at the leading edge of the wing. The study is part of the Collaborative Research Center 880 that develops technologies and configurations with quite STOL capabilities. The layout of the high lift system is described, together with the numerical approach and results for the considered test case. The objective of the present study is to investigate a short chord active plain flap in landing configuration and assess the maximum lift capabilities against target values from preliminary design studies of the CRC 880. It is a first step towards a more comprehensive assessment of variants of the high lift system. With the typical lift generation for a circulation control supported high lift system, the analysis of the stall behavior reveals a favorable smooth lift breakdown starting at the inner wing. Yet, the maximum lift properties fall short of the target value, so that an enlarged chord flap will be considered as a next step to comply with the maximum lift requirements.

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Numerical Investigation of Engine Effects on a Transport Aircraft with Circulation Control

Cited by 17 publications

References 15 publications

Adaptive Nonlinear Flight Control of STOL-Aircraft Based on Incremental Nonlinear Dynamic Inversion

Adaptive Nonlinear Flight Control of STOL-Aircraft Based on Incremental Nonlinear Dynamic Inversion

Controllability of an aircraft with active high-lift system using a segmentwise controllable flap system

High Lift Design and Aerodynamic Assessment for an Over-the-Wing Pylon-Mounted Engines Configuration with STOL Capabilities

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