Modeling and Simulation for Helicopter Task Analysis

Hess, Ronald A.; Zeyada, Yasser; Heffley, Robert K.

doi:10.4050/jahs.47.243

Cited by 29 publications

(34 citation statements)

References 10 publications

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“…As shown in Figure 2, the Handling Qualities Sensitivity Function analysis predicts increasingly worsening handling qualities in response to increasing vestibular feedback, based on the theoretical boundaries proposed in the literature [8], as indicated by the progressively larger amplitude peak that develops. This is in stark disagreement with experiment.…”

Section: Vestibular Feedbackmentioning

confidence: 88%

“…Proprioceptive feedback fundamentally accounts for the ability of the pilot model to make corrections to his control inputs based on the perception of stick displacement. Hess [8] argues that this is a key parameter in the prediction of handling qualities. A key feature of this approach is the modeling of the inceptor dynamic response to pilot force inputs ( ) inside of the proprioceptive feedback loop.…”

Section: Structural Pilot Modelmentioning

confidence: 99%

“…This is achieved by specifying the pilot crossover frequency, which effectively serves as an independent tuning parameter to the model. Herein, estimates of the crossover frequency were obtained from an inverse dynamic analysis [8].…”

Section: Handling Qualities Metricmentioning

confidence: 99%

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Analysis of Handling Qualities Design Criteria for Active Inceptor Force-Feel Characteristics

Malpica

Lusardi

2013

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BackgroundThe force-feel system characteristics of the cyclic inceptors of most helicopters are set based on the characteristics of the mechanical components in the control system (mass, springs, friction dampers, etc.). For these helicopters, the force-feel characteristics typically remain constant over the entire flight envelope, with perhaps a trim release to minimize control forces while maneuvering. With the advent of fly-by-wire control systems and active inceptors in helicopters, the force-feel characteristics are now determined by the closed-loop response of the active inceptor itself as defined by the inertia, force/displacement gradient, damping, breakout force and detent shape configuration parameters in the inceptor control laws. These systems give the flexibility to dynamically prescribe different feel characteristics for different control modes or flight conditions, and the ability to provide tactile cueing to the pilot through the actively controlled side-stick or center-stick cyclic inceptor.

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Section: Vestibular Feedbackmentioning

confidence: 88%

Section: Structural Pilot Modelmentioning

confidence: 99%

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Analysis of Handling Qualities Design Criteria for Active Inceptor Force-Feel Characteristics

Malpica

Lusardi

2013

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“…1 has been developed and applied in several projects spanning the past ten years. [1][2][3][4][5] The TPV model is able to represent the combined pilotvehicle system in a context that represents realistic performance of real-world flight tasks and maneuvers. It is the basis of a rapid prototyping tool that has been applied in several ways.…”

Section: Introductionmentioning

confidence: 99%

Use of a Task-Pilot-Vehicle (TPV) Model as a Tool for Fight Simulator Math Model Development

Heffley

2010

AIAA Modeling and Simulation Technologies Conference

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The Task-Pilot-Vehicle (TPV) model structure is able to represent the combined pilotvehicle system in order to produce realistic performance of many real-world flight tasks and maneuvers. The scheme employs a set of graphical user interfaces for setting up flight task scenarios, setting pilot decision and control parameters, running simulations, and analyzing results. It includes a concise method for defining flight tasks and maneuvers, and pilot control strategy and technique. The TPV model has run with several vehicle math models, including CASTLE, FlightLab©, RotorGen2©, as well as linear state-space models. The current TPV model is implemented in Simulink® and uses FlightGear open-source software to provide a visual 3D display of the simulation. The TPV model scheme is useful for rapid prototyping system design and as a simulation or flight planning tool. This paper describes use of the TPV modeling scheme in the context of its application to vehicle math model development.

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“…This is a technique which is finding increasing application [4][5][6], but much of the work in developing it and applying it to practical problems has been performed at Glasgow [7][8][9][10]. The main focus of this work has been the development of the helicopter inverse simulation package, Helinv.…”

Section: Introductionmentioning

confidence: 99%

A Simulation Study of Helicopter Ship Landing Procedures Incorporating Measured Flow-Field Data

Thomson

Coton

Galbraith

2005

Proceedings of the Institution of Mechanical Engineers, Part G:

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The aim of this article is to investigate the use of inverse simulation to help identify those regions of a ship's flight deck which provide the safest locations for landing a rotorcraft in various atmospheric conditions. This requires appropriate information on the wind loading conditions around a ship deck and superstructure, and for the current work, these data were obtained from wind tunnel tests of a ship model representative of a typical helicopter carrier/ assault ship. A series of wind tunnel tests were carried out on the model in the University of Glasgow's 2.65 Â 2.04 m wind tunnel and three-axis measurements of wind speed were made at various locations on the ship deck. Measurements were made at four locations on the flight deck at three different heights. The choice of these locations was made on the basis of preliminary flow visualization tests which highlighted the areas where the most severe wind effects were most likely to occur. In addition, for the case where the wind was from 308 to starboard, measurements were made at three further locations to assess the extent of the wake of the superstructure. The generated wind profiles can then be imposed on the inverse simulation, allowing study of the vehicle and pilot response during a typical landing manoeuvre in these conditions. The power of the inverse simulation for this application is demonstrated by a series of simulations performed using configurational data representing two aircraft types, a Westland Lynx and a transport helicopter flying an approach and landing manoeuvre with the worst atmospheric conditions applied. It is shown from the results that attempting to land in the area aft of the superstructure in a 308 crosswind might lead to problems for the transport configuration due to upgusts in this area. Attempting to perform the landing manoeuvre in an aggressive manner is also shown to lead to diminished control margin in higher winds.

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Modeling and Simulation for Helicopter Task Analysis

Cited by 29 publications

References 10 publications

Analysis of Handling Qualities Design Criteria for Active Inceptor Force-Feel Characteristics

Analysis of Handling Qualities Design Criteria for Active Inceptor Force-Feel Characteristics

Use of a Task-Pilot-Vehicle (TPV) Model as a Tool for Fight Simulator Math Model Development

A Simulation Study of Helicopter Ship Landing Procedures Incorporating Measured Flow-Field Data

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