Integrated Approach to Flight Dynamics and Aeroservoelasticity of Whole Flexible Aircraft - Part I: System Modeling

2002 ◽  
Author(s):  
Leonard Meirovitch ◽  
Ilhan Tuzcu
Keyword(s):  
System Modeling ◽  
Flight Dynamics ◽  
Integrated Approach ◽  
Flexible Aircraft

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

2014 ◽  
Vol 59 (4) ◽  
pp. 1-18 ◽  
Author(s):  
Ioannis Goulos ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Real Time ◽  
Rotor Blade ◽  
Flight Dynamics ◽  
Integrated Approach ◽  
Flight Simulation ◽  
Response Characteristics ◽  
Helicopter Flight ◽  
Finite State ◽  
The Time Domain ◽  
Blade Loads

This paper presents a mathematical model for the simulation of rotor blade flexibility in real-time helicopter flight dynamics applications that also employs sufficient modeling fidelity for prediction of structural blade loads. A matrix/vector-based formulation is developed for the treatment of elastic blade kinematics in the time domain. A novel, second-order-accurate, finite-difference scheme is employed for the approximation of the blade motion derivatives. The proposed method is coupled with a finite-state induced-flow model, a dynamic wake distortion model, and an unsteady blade element aerodynamics model. The integrated approach is deployed to investigate trim controls, stability and control derivatives, nonlinear control response characteristics, and structural blade loads for a hingeless rotor helicopter. It is shown that the developed methodology exhibits modeling accuracy comparable to that of non-real-time comprehensive rotorcraft codes. The proposed method is suitable for real-time flight simulation, with sufficient fidelity for simultaneous prediction of oscillatory blade loads.

Formulation of the Flight Dynamics of Flexible Aircraft Using General Body Axes

AIAA Journal ◽  
2016 ◽  
Vol 54 (11) ◽  
pp. 3516-3534 ◽  
Author(s):  
Antônio B. Guimarães Neto ◽  
Roberto G. A. Silva ◽  
Pedro Paglione ◽  
Flávio J. Silvestre
Keyword(s):  
Flight Dynamics ◽  
Flexible Aircraft ◽  
General Body

Flight Dynamics of Highly Flexible Aircraft

2008 ◽  
Vol 45 (2) ◽  
pp. 538-545 ◽  
Author(s):  
Chong-Seok Chang ◽  
Dewey H. Hodges ◽  
Mayuresh J. Patil
Keyword(s):  
Flight Dynamics ◽  
Flexible Aircraft

scholarly journals Modeling the Supporting Ecosystem Services of Depressional Wetlands in Agricultural Landscapes

Wetlands ◽  
2020 ◽  
Vol 40 (5) ◽  
pp. 1061-1069
Author(s):  
David M. Mushet ◽  
Cali L. Roth
Keyword(s):  
Ecosystem Services ◽  
Crop Production ◽  
System Modeling ◽  
Integrated Approach ◽  
Agricultural Landscapes ◽  
Floral Resources ◽  
Depressional Wetlands ◽  
Native Plant ◽  
Des Moines Lobe ◽  
Des Moines

Abstract We explored how a geographic information system modeling approach could be used to quantify supporting ecosystem services related to the type, abundance, and distribution of landscape components. Specifically, we use the Integrated Valuation of Ecosystem Services and Tradeoffs model to quantify habitats that support amphibians and birds, floral resources that support pollinators, native-plant communities that support regional biodiversity, and above- and below-ground carbon stores in the Des Moines Lobe ecoregion of the U.S. We quantified services under two scenarios, one that represented the 2012 Des Moines Lobe landscape, and one that simulated the conversion to crop production of wetlands and surrounding uplands conserved under the USDA Agricultural Conservation Easement Program (ACEP). While ACEP easements only covered 0.35% of the ecoregion, preserved wetlands and grasslands provided for 19,020 ha of amphibian habitat, 21,462 ha of grassland-bird habitat, 18,798 ha of high-quality native wetland plants, and 27,882 ha of floral resources for pollinators. Additionally, ACEP protected lands stored 257,722 t of carbon that, if released, would result in costs in excess of 45-million USD. An integrated approach using results from a GIS-based model in combination with process-based model quantifications will facilitate more informed decisions related to ecosystem service tradeoffs.

scholarly journals Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model

2013 ◽  
Vol 135 (9) ◽  
Author(s):  
Ioannis Goulos ◽  
Panagiotis Giannakakis ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Fuel Consumption ◽  
Three Dimensional ◽  
Numerical Procedure ◽  
Engine Performance ◽  
Flight Dynamics ◽  
Flight Test ◽  
Integrated Approach ◽  
Operating Conditions ◽  
Main Rotor ◽  
Engine Systems

This paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter engine designs within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity, and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements, and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine rather than on airframe rotor performance. The implications associated with the implicit coupling between aircraft and engine performance are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter engine systems within complete three-dimensional operations using modeling fidelity designated for main rotor design applications is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types rather than on specific sets of flight conditions.

scholarly journals Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model

2013 ◽  
Author(s):  
Ioannis Goulos ◽  
Panos Giannakakis ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Fuel Consumption ◽  
Three Dimensional ◽  
Numerical Procedure ◽  
Engine Performance ◽  
Flight Dynamics ◽  
Flight Test ◽  
Integrated Approach ◽  
Operating Conditions ◽  
Main Rotor ◽  
Engine Systems

This paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter–engine designs, within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine, rather than on airframe–rotor performance. The implications associated with the implicit coupling between aircraft and engine performance, are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter–engine systems within complete three-dimensional operations, using modeling fidelity designated for main rotor design applications, is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types, rather than on specific sets of flight conditions.

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