Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Goulos, Ioannis; Pachidis, Vassilios; Pilidis, Pericles

doi:10.4050/jahs.59.042006

Cited by 20 publications

(23 citation statements)

References 16 publications

(33 reference statements)

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“…[9] and [10], and an engine off-design performance analysis [11]. The individual modeling methodologies are combined within an elaborate integral procedure, solving for the unknown initial aircraft AUM.…”

Section: Numerical Formulationmentioning

confidence: 99%

“…The incorporated mathematical rotor model employs the numerical approach presented in Refs, [9] and [10] for the treatment of rotor blade flexibility in the time domain. The method caters for the inclusion of all nonlinear inertial terms associated with large blade deflections as well as the helicopter's three-dimensional motion.…”

Section: Aeroelastic Rotor Modelmentioning

confidence: 99%

See 1 more Smart Citation

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

Goulos¹,

Giannakakis²,

Pachidis³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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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 integr-ated within a numerical procedure, solving for the total mission fuel consumption. The over-all simulation framewort 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 rvtor trim controls, power requirements, and unsteady blade str-uctural loads is pr-eserited. It is shown that, for the typical range of oper-ating 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 compr-ehensively evaluate integrated helicopter engine systems within complete thr-ee-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 r-otorcraft design process on designated operation types rather than on specific sets of flight conditions.

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Section: Numerical Formulationmentioning

confidence: 99%

Section: Aeroelastic Rotor Modelmentioning

confidence: 99%

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

Goulos¹,

Giannakakis²,

Pachidis³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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View full text Add to dashboard Cite

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“…[13,15] for the simulation of rotor blade elasticity in the time domain. The aeroeiastic rotor model used for the simulations performed in this paper is based on the numerical method described in Refs.…”

Section: Aeroeiastic Rotormentioning

confidence: 99%

“…[13,15,17]. The incorporated flight dynamics models have been extensively validated in terms of power requirement, trim control inputs, and unsteady rotor blade structural loads in Refs.…”

Section: Case Studymentioning

confidence: 99%

Rotorcraft Engine Cycle Optimization at Mission Level

Goulos

Hempert

Sethi

et al. 2013

Journal of Engineering for Gas Turbines and Power

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Rotorcraft Engine Cycie Optimization at iVIission LevelThis work investigates the potential to reduce fuel consumption associated with civil rotorcraft operations at mission level, through optimization of the engine design point cycle parameters. An integrated simulation framework, comprising models applicable to rotorcraft flight dynamics, rotor blade aeroelasticity, and gas turbine performance, has been deployed. A comprehensive and computationally efficient optimization strategy, utilizing a novel particle-swarm method, has been structured. The developed methodology has been applied on a twin-engine light and a twin-engine medium rotorcraft configuration. The potential reduction in fuel consumption has been evaluated in the context of designated missions, representative of modern rotorcraft operations. Optimal engine design point cycle parameters, in terms of total mission fuel consumption, have been obtained. Pareto front models have been structured, describing the optimum interrelationship between maximum shaft power and mission fuel consumption. The acquired results suggest that, with respect to technological limitations, mission fuel economy can be improved with the deployment of design specifications leading to increased thermal efficiency, while simultaneously catering for sufficient performance to satisfy aii-worthiness certification requirements. The developed methodology enables the identification of optimum engine design specifications using a single design criterion; the respective trade-off between fuel economy and payload-range capacity, through maximum contingency shaft power, that the designer is prepared to accept. Aircraft-Engine Design and Trajectory Optimization.A substantial amount of literature is available in the public domain, dealing with the investigation of operational procedures for aircraft and rotorcraft, potentially optimum in terms of fuel bum and environmental impact. D'Ippolito et al. [2] demonstrated the applicability of design of experiment (DOE) methods coupled with response surface models (RSM) to the optimization of a category A take-off maneuver for a twin-engine light rotorcraft. Their modeling approach included the use of the EUROPA rotorcraft flight dynamics code [7], the engine performance simulation tool GSP [8], and the noise propagation analysis tool HELENA [9]. Their optimization strategy included the deployment of a Latin hypercube design (LHD) DOE approach coupled with least square fitting Taylor polynomials to structure the required RSMs.

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“…Figure 6presents rotor trim controls and power requirement predictions obtained from nonlinear trim simulations carried out with the non linear flight dynamics model of HECTOR[4,10,11], Results are presented for straight and level flight as functions of advance ratio (m = V/QR), from hover (/< = 0) to high-speed flight (q « 0.36).o FOCA Upper limit □ FOCA Approx a F O C A L ow er limit --------Emission model With FOCA Approx --------Emission modelJUpper limit --------Emission model Lower limit Engine power (hp) Trim perform ance predictions for the Bo 105 rotorcraft-com parison with flight test data from Ref. [25]: (a) rotor power required, (b) collective pitch angle 90, (c) longitudinal cyclic pitch angle 01s, and (d) lateral cyclic pitch angle 01c…”

mentioning

confidence: 99%

A Multidisciplinary Approach for the Comprehensive Assessment of Integrated Rotorcraft–Powerplant Systems at Mission Level

Goulos

Ali

Tzanidakis

et al. 2014

Journal of Engineering for Gas Turbines and Power

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This paper presents an integrated methodology for the comprehensive assessment of com bined rotorcraft-powerplant systems at mission level. Analytical evaluation of existing and conceptual designs is carried out in terms of operational performance and environ mental impact. The proposed approach comprises a wide-range of individual modeling theories applicable to rotorcraft flight dynamics and gas turbine engine performance. A novel, physics-based, stirred reactor model is employed for the rapid estimation of nitro gen oxides (NOx) emissions. The individual mathematical models are implemented within an elaborate numerical procedure, solving for total mission fuel consumption and associ ated pollutant emissions. The combined approach is applied to the comprehensive analy sis of a reference twin-engine light (TEL) aircraft modeled after the Eurocopter Bo 105 helicopter, operating on representative mission scenarios. Extensive comparisons with flight test data are carried out and presented in terms of main rotor trim control angles and power requirements, along with general flight performance charts including payload-range diagrams. Predictions of total mission fuel consumption and NOx emis sions are compared with estimated values provided by the Swiss Federal Office of Civil Aviation (FOCA). Good agreement is exhibited between predictions made with the physics-based stirred reactor model and experimentally measured values ofNOx emission indices. The obtained results suggest that the production rates of NOx pollutant emissions are predominantly influenced by the behavior of total air inlet pressure upstream of the combustion chamber, which is affected by the employed operational procedures and the time-dependent all-up mass (AUM) of the aircraft.It is demonstrated that accurate esti mation of on-board fuel supplies ahead offlight is key to improving fuel economy as well as reducing environmental impact. The proposed methodology essentially constitutes an enabling technology for the comprehensive assessment of existing and conceptual rotor craft-powerplant systems, in terms of operational performance and environmental impact.

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Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Cited by 20 publications

References 16 publications

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

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

Rotorcraft Engine Cycle Optimization at Mission Level

A Multidisciplinary Approach for the Comprehensive Assessment of Integrated Rotorcraft–Powerplant Systems at Mission Level

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