Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Nicolosi, Fabrizio; Marco, Agostino De; Vecchia, Pierluigi Della

doi:10.1016/j.ast.2011.11.011

Cited by 33 publications

(18 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The simulation resulted in a shaft power requirement (thrust force x velocity) of 124 kW (167 hp), which the combined shaft power of the Tecnam's two Rotax power plants is capable of producing (150 kW or 200 hp); the aircraft drag is implicit in the power requirement and is therefore also deemed acceptable. The lift coefficient of C L = ~0.5 is a reasonable value for an aircraft of this type and is consistent with the lift coefficient obtained in cruise condition under test (Nicolosi, 2010).…”

Section: P2006t Modeling and Resultssupporting

confidence: 88%

Development and Implementation of a Flexible Model Architecture for Hybrid-Electric Aircraft

Batteh¹,

Gohl²,

Sielemann³

et al. 2019

Linköping Electronic Conference Proceedings

View full text Add to dashboard Cite

This paper describes the implementation of a flexible, modular, hybrid-electric aircraft modeling architecture for the development of a virtual and physical demonstrator system that will be used in the advancement of sustainable mobility systems by the National Research Council of Canada (NRC). The initial modeling architecture was established in Modelica based on the NASA X-57 electric flight demonstrator aircraft. A series of models were assembled from a high level aircraft system architecture to mimic the initial developmental path from the baseline conventional aircraft to the X-57 electric aircraft variant. The multi-physics component models describe the aircraft dynamics and performance, integrated with the relevant mechanical, electrical, and thermal dynamics of the electric aircraft power train. The proposed modular architecture allowed the simulation of three different aircraft configurations with different degrees of electrification, demonstrating its effectiveness and versatility in the design and development of hybrid-electric aircraft.

show abstract

Section: P2006t Modeling and Resultssupporting

confidence: 88%

Development and Implementation of a Flexible Model Architecture for Hybrid-Electric Aircraft

Batteh¹,

Gohl²,

Sielemann³

et al. 2019

Linköping Electronic Conference Proceedings

View full text Add to dashboard Cite

show abstract

“…Fabrizio Nicolosi et al [12] wrote a comprehensive analysis on the Tecnam P2006T a four-seater twin propeller aircraft during its flight. Flight quality was assessed, and stability derivatives were determined using longitudinal parameter estimation techniques.…”

Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

Aircraft Fuselage Recent Developments - A Review

Angelo¹,

Potty²,

Rao

et al. 2019

ujme

View full text Add to dashboard Cite

Over multiple iterations spanning many years of research a stable and aerodynamically workable fuselage structure has been zeroed down on. The fuselage being the segment holding the passengers and crew requires an immaculate degree of stability during takeoff, landing and flight. Aerodynamic optimisation presupposes every notion of this 'in flight stability'. The recent interest taken in the field of stability under unforeseen air conditions has led to remarkable developments in the field of aerodynamics. This paper attempts to categorically classify these interests into 3 sections-Theoretical, Experimental and Numerical. Various mathematical models and algorithms have been created to study and test the stability of the fuselage under turbulent conditions caused by weather. Turbulence caused by on flight equipment (propellers etc) and methods for its mitigation have also been mentioned. The chine angle analysis of the fuselage reveals that a sharper angle is more favorable in increasing the lift. The study of asymmetrical vortices and its evolution has enhanced the field of aerodynamic optimization. Unconventional aircraft designs like the BWB are studied and compared against the incumbent structures. Various modeling softwares like CATIA have extensively been used to design these structures. A compilation of these recent developments has been presented to those attempting to intensively analyse and study the field of aerodynamic stability.

show abstract

“…4 Nicolosi et al. 5 obtained the stability derivatives from the output error method (OEM), which is a known identification technique for P2006T twin-engine aircraft. Some of the stability derivatives obtained from the level flight test and scale wind tunnel test model with correction were used to estimate and assess the flight qualities and longitudinal parameters.…”

Section: Introductionmentioning

confidence: 99%

Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

Nguyen

Tyan

Lee

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The stability and control characteristics using a wind tunnel test data process are proposed and developed to investigate the stability and control characteristics of a CS-VLA certified aircraft and to comply with the CS-VLA subpart B at the preliminary design review (PDR) and critical design review (CDR) stage. The aerodynamic characteristics of a 20% scale model are provided and investigated with clean, rudder, aileron, elevator, and winglet effects. The Mach and Reynolds correction methods are proposed to correct the aerodynamics of the scale model for stability and control analysis to obtain more reliable and accurate results of the full-scale model. The aerodynamic inputs and moment of inertia (MOI) comparison between the PDR and CDR stage show good agreement in the trends of stability and control derivatives. The CDR analysis results with the corrected wind tunnel test data and accurate MOI are investigated with respect to the longitudinal and lateral stability, control, and handling qualities to comply with the CS-VLA 173, CS-VLA 177, and CS-VLA 181 for finalizing the configuration in the CDR stage.

show abstract

Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Cited by 33 publications

References 7 publications

Development and Implementation of a Flexible Model Architecture for Hybrid-Electric Aircraft

Development and Implementation of a Flexible Model Architecture for Hybrid-Electric Aircraft

Aircraft Fuselage Recent Developments - A Review

Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

Contact Info

Product

Resources

About