Validation of a flexible aircraft take-off and landing analysis (FATOLA) by Huey D Carden

Cover of: Validation of a flexible aircraft take-off and landing analysis (FATOLA) | Huey D Carden

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in Washington, Springfield, Va .

Written in English

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Subjects:

  • Airplanes -- Landing,
  • Airplanes -- Takeoff,
  • Airplanes -- Handling characteristics

Edition Notes

Book details

StatementHuey D. Carden and John R. McGehee
SeriesNASA technical paper ; 1025
ContributionsMcGehee, John R., joint author, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office
The Physical Object
Pagination50, [18] p. :
Number of Pages50
ID Numbers
Open LibraryOL14931799M

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Validation of a Flexible Aircraft Take-Off and Landing Analysis (FATOLA) Modifications to improve the analytical simulation capabilities of a multi-degree-of-freedom flexible aircraft take-off and landing analysis (FATOLA) computer program are discussed.

The FATOLA program was used to simulate the landing behavior of a stiff body XB reentry research vehicle and of a flexible body supersonic. Abstract. A multiple-degree-of-freedom takeoff and landing analysis, Flexible Aircraft TakeOff and Landing Analysis computer program (FATOLA), was used to predict the landing behavior of a rigid-body XB reentry research vehicle and of a flexible-body modified-delta-wing supersonic YF research : J.

Mcgehee and H. Carden. Validation of a flexible aircraft take-off and landing analysis (FATOLA) / By Huey D. Carden, joint author.

John R. McGehee and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office. Abstract. Issued Oct. Includes bibliographical of access: Internet. Magnetic levitation assisted aircraft take-off and landing (iv) the analysis of the safety and security aspects, (v) the concept validation and (vi) the estimation of the proposed concept impact in terms of aircraft weight, noise, emission, cost-benefit).

All results introduced here are compared to a medium size hypothetic passenger Cited by: 9. [21] Carden H. and McGehee J. R., “ Validation of a Flexible Aircraft Take-Off and Landing Analysis (FATOLA),” NASA Technical Paper, pp.

1– Google Scholar [22] Keye S., “ Fluid-Structure Coupled Analysis of a Transport Aircraft and Flight-Test Validation,” Journal of Aircraft, Vol.

48, No. 2,pp. – Cited by:   The landing of a civil transport aircraft is one of the most challenging phases.

The reason mainly lies in the need to satisfy different concurrent requirements in the face of a wide range of system variations and environmental perturbations. This poses the challenge to evaluate an area relatively quickly to determine whether the UAV will be able to take off and land on the available terrain.

Factors such as the take-off and landing length and width requirements (geometry), aircraft load (bearing capacity) and landing strip roughness (riding quality) are important to determine to.

FT Flight Testing Education and Training • Monday, 25 June • hrs. Landing gear is the undercarriage Validation of a flexible aircraft take-off and landing analysis book an aircraft and is typically designed to support the vehicle only at post-flight.

A strut is a structural component designed to resist longitudinal compression. Chapter 7 Aircraft Flotation Analysis Introduction The configuration of the landing gear has a direct impact on ground flotation, a term used to describe the capability of pavement and other surfaces to support an aircraft [32].

The number and arrangement of the wheels, along with the aircraft. aircraft; for some discussion about physics of wake vortex and its quantitative hazard evaluation see Shortle and Jeddi (), for example. Separation of an aircraft pair is a random variable due to the nature of the process inputs and components.

Thus, analysis of the landing capacity, utilization and. One last note: obtaining book performance requires you use the book technique. Most POH takeoff and landing data actually reflect short-field performance: Stand on the brakes until full throttle for takeoff; power off for a steep times Vso approach on short final for landing.

Summary. Flight Seven is an introduction to more sophisticated ways of getting into the air and back onto the ground. These new techniques include soft-field takeoffs and landings, short field takeoffs and landings, no-flap takeoffs and landings, an introduction to forward slips to landing, and crosswind landings.

You need to be proficient at working in the traffic pattern and to have. The framework is a multidisciplinary engineering analysis, supported by flight simulation, with software validation at several levels. A unique feature is the discussion of environmental performance focusing on four items: aircraft noise, contrail effects, landing and take-off emissions, and carbon dioxide emissions.

A multiple-degree-of-freedom takeoff and landing analysis, Flexible Aircraft TakeOff and Landing Analysis computer program (FATOLA), was used to predict the landing.

Introduction A helicopter is an amazing thing. It enables us to carry out tasks and jobs like no other machine in the world. Not only can we fly passengers from one place to another without the need for a runway but we can lift heavy equipment in remote areas, make films and even save lives.

Regardless of the task our helicopters perform, the goal is to have a safe flight – from the first. Takeoff and Landing Performance Assessment Validation Effort of the Runway Condition Assessment Matrix Inthe Takeoff and Landing Performance Assessment (TALPA) Aviation Rulemaking Committee (ARC) recommended that the Federal Aviation Administration (FAA) conduct a trial program or validation effort to assess the use of a Runway Condition Assessment.

For take-off and landing calculations, all MEL constraints can be automatically integrated. Maximum Control for Engineers Performance and flight operations engineers can enjoy full control of the underlying parameters; setting up aircraft and aircraft sub-fleets, selecting performance options according to company policies, editing airports and.

A simulation-based approach for take-off and landing performance assessments is presented in this work. In the context of aircraft design loops, it provides a detailed and flexible formulation that can be integrated into a wider simulation methodology for a complete commercial aviation mission.

As a matter of fact, conceptual and preliminary aircraft design activities require iterative. Aircraft landing gear assemblies comprise of various subsystems working in unison to enable functionalities such as taxiing, take-off and landing.

As development cycles and prototyping iterations begin to shorten, it is important to develop and improve practical methodologies to meet certain design metrics. This paper presents an efficient methodology that applies high-fidelity multi. The framework is a multidisciplinary engineering analysis, supported by flight simulation, with software validation at several levels.

A unique feature is the discussion of environmental performance focusing on four items: aircraft noise, contrail effects, landing and take-off emissions, and carbon dioxide : Antonio Filippone. • The landing gear should be able to absorb the energy of landing impact up to descent velocities of m/s (12 fps).

This requires a shock absorber with a considerable stroke in order to limit the loads occurring during landing impact. For a civil jet aircraft the ground speed during landing is in the range of to km/h. unmanned aircraft is by the function of an automatic system or an external operator on the.

Quadcopter (UAV) structure. A quadcopter, also called quad rotor a. helicopter orquad rotor, is a multirotor helicopter that is lifted and propelled by four rotors. Quadcopters are classified as rotorcraft, as opposed to fixed-wing aircraft.

particularly for the landing phase. Upon touchdown, the aircraft is still at a rather high velocity and therefore, it is vital that application of the brakes helps to slow it down within the allocated landing field length.

This function becomes equally important during the take-off phase whenever emergency take-off abortion takes place. Federal Aviation Administration. For decades, the speed of commercial aviation was constrained by the sound barrier.

Even with the Concorde, supersonic flight was unavailable except on a few routes and only for those willing and able to pay the high airfares. Commercially successful supersonic flight will only occur when technology.

Flight testing is a branch of aeronautical engineering that develops and gathers data during flight of an aircraft, or atmospheric testing of launch vehicles and reusable spacecraft, and then analyzes the data to evaluate the aerodynamic flight characteristics of the vehicle in order to validate the design, including safety aspects.

The flight test phase accomplishes two major tasks: 1. Frequency domain turbulence response – flexible aircraft General form of equations in the frequency domain Representation of the flight control system (FCS) Examples 17 Ground Manoeuvres Landing gear Taxi, take-off and landing roll Landing Braking Previous applications have shown that a wingtip treatment on a commercial airliner will reduce drag and increase fuel efficiency and the most common types of treatment are blended winglets and raked wingtips.

With Boeing currently investigating novel designs for its next generation of airliners, a variable geometry raked wingtip novel control effector (VGRWT/NCE) was studied to determine the. The launch and recovery systems are just one example of the changes from the Nimitz Class to the Ford class.

A key change is with how weapons move from the lower decks of the shop to aircraft. In this paper, nonlinear vibration analysis of a typical aircraft oleo pneumatic landing gear has been done.

Mathematical model of the main landing gear is developed, and dynamic equations have been written incorporating the effect of lift force, friction force to study the landing gear behaviour at touchdown condition. The nonlinear effect of stiffness, damping coefficient properties are.

The behavior of a 'pilot-automaton-aircraft-operating environment' system (the System) in off-nominal situations with multiple risks can be unpredictably dangerous. Most multifactorial flight scenarios (corner cases) are considered as theoretically improbable.

Such anomalies do nonetheless occur in. frequency domain turbulence response – flexible aircraft; general form of equations in the frequency domain; representation of the flight control system (fcs) examples; ground manoeuvres.

landing gear; taxi, take-off and landing roll; landing; braking; ‘spin-up’ and ‘spring-back. The aim of this project is to design a quiet 55 passenger Mach aircraft such that the FAA can use the predicted take-off and landing noise levels for developing their new certification standards.

Students will utilize ASDL computational design tools to assist in the conceptual design process. A collapse of a landing gear during the landing roll can have devastating effects on the aircraft. This paper seeks to investigate the methods used in the design of landing gear, with an introduction to the kinematics of landing gear design and a detailed structural analyses.

As a result, the empirical validation formula deviation averaged only % and % during take-off and landing respectively from the actual noise and the theoretical validation.

Furthermore, the new modeling was verified as a derivation from the grand theory of inverse square law and could be applied for master plan design. Another difference lies in the type of aircraft used; operators either fly very light jets (VLJs) or small piston aircraft.

A VLJ typically seats between four and seven passengers, can be flown by a single pilot, has a maximum take-off weight of less t lb ( kg), and an average range of around 2, km (Budd & Graham,p The research activity dealing with the design of aircraft and spacecraft aims at the development of innovative solutions and efficient computational models.

Particular attention is paid to: Development of numerically efficient stick models for the analysis of complex structures made of metallic and composite materials.

1D and 2D models are. Nowadays, aeronautics discovers new ways of flights near the critical regimes, unconventional aircraft forms, utilizing the micro–electro-mechanical technologies in flow and aircraft control, adaptive and morphing structures, using the structures and controls based on the biological principles, developing highly flexible structures, etc.

Before deployment, these new technologies and. An increasing number of people live in the vicinity of major airports and experience considerable noise and air pollution.

Raised blood pressure (BP) is a major risk factor for coronary heart disease and the major risk factor for stroke (Whitworth ).Environmental noise is a significant problem in Europe, and it is estimated that roughly 20% of the European Union’s population (close to.

The self-sustained oscillation of aircraft landing gear is an inherently nonlinear and dynamically complex phenomenon.

Although such oscillations are ultimately driven from the interaction between the tires and the ground, other effects, such as mechanical freeplay, and geometric nonlinearity, may influence stability and add to the complexity of observed behavior.Aircraft Propulsion and Gas Turbine Engines - Ebook written by Ahmed F.

El-Sayed. Read this book using Google Play Books app on your PC, android, iOS devices. Download for offline reading, highlight, bookmark or take notes while you read Aircraft Propulsion and Gas Turbine Engines.The study shows the great capability of DADS in the modeling, simulation and analysis of aircraft ground operations.

Rather than writing a generic FORTRAN source code, using the DADS is much easier and more flexible for the user to model and study most types of landing gear systems in a .

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