3 edition of Expanded envelope concepts for aircraft control-element failure detection and identification found in the catalog.
Expanded envelope concepts for aircraft control-element failure detection and identification
by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Center in Hampton, Va, [Springfield, Va
Written in English
|Statement||Jerold L. Weiss, John Y. Hsu.|
|Series||NASA contractor report -- 181664., NASA contractor report -- NASA CR-181664.|
|Contributions||Hsu, John Y., Langley Research Center.|
|The Physical Object|
Advanced Control Concepts.. Multivariable Control Active Clearance Control. Active Stall and Surge Control Active Combustion Control. Operational Envelopes and Standard Atmosphere .. Basic Thermodynamics of Perfect Gas .. Total Properties and Mass Flow Parameter. Aircraft Model The aircraft (Figure 1) is called the Vireo and is com prised only of a wing and a fuselage. This aircraft was originally built by Sentera, LLC and is currently main-tained and operated by the University of Minnesota. The fully integrated aircraft has a gross mass of kg, a wing span of m, and a fuselage length.
get your aircraft to a safe ﬂying attitude. SAFE Flight Modes Beginner Mode t Envelope limit: Pitch (nose up and down) and Roll (wing tips up and down) angles are limited to help you keep the aircraft airborne t Self-leveling: when the pitch and roll controls are returned to neutral, the aircraft . OPERATING ENVELOPE. It is a graphic. representation of the operating envelope of the aircraft. Velocity is plotted on the horizontal in either. indicated airspeed (KIAS) or indicated Mach number (IMN). The vertical is plotted in either acceleration FAILURE. VELOCITY INCREASE. 0. Figure ENVELOPE DIAGRAM. Page 9 () Original.
Aircraft - describe the number and type of aircraft, any flight critical systems, payload requirements, any special maintenance or stowage requirements driving design requirements, identify deck movement envelopes and fueling requirements, identify launch and recovery systems. expanded company knowledge of the unique aspects of flight control laws in a fly by wire aircraft that employed coaxial rotors, and the RAH Comanche, which developed expertise in composite rotors and advanced transmission design.  The X2 first flew on. 27 August from Schweizer Aircraft's facility at Horseheads, New York.
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Expanded Envelope Concepts for Aircraft Control-Element Failure Detection and Identification Jerold John Y. Hsu ALPHATECH, Inc. Burlington, Massachusetts June Prepared for Langley Research Center Under Contract NAS National Aeronautics and Space Administration Langley Research Center Hampton, Virginia Get this from a library.
Expanded envelope concepts for aircraft control-element failure detection and identification. [Jerold L Weiss; John Y Hsu; Langley Research Center.].
An integrated artificial immune system-based scheme that can operate over extended areas of the flight envelope is proposed in this paper for the detection and identification of a variety of aircraft sensor, actuator, propulsion, and structural failures/ by: Expanded envelope concepts for aircraft control-element failure detection and identification.
The purpose of this effort was to develop and demonstrate concepts for expanding the envelope of failure detection and isolation (FDI) algorithms for aircraft-path failures.
An algorithm which uses analytic-redundancy in the form of aerodynamic Author: Jerold L. Weiss and John Y. Hsu. " A Preliminary Design of a Failure Detection Filter for Detecting and Identifying Control Element Failures in a Transport Aircraft, " NASA TMJuly Aircraft Icing Detection System Jan.
One of the key steps of this approach is determining the structural damage of the state of the aircraft by using the identification, detection, and classification methods presented in this paper. The first works concerning OFC detection have been published by Besch, Giesseler, and Schuller () and describe several combinations of linear methods and signal processing called oscillatory failure identification system (OFIS) where one method corresponds practically to one fault scenario.
However, in real-time industrial implementation it. The research presented in this paper focuses on the effects of structural failures on the safe flight envelope of an aircraft, which is the set of all the states in which safe maneuver of the aircraft can be assured.
Nonlinear reachability analysis based on an optimal control formulation is performed to estimate the safe flight envelope using actual aircraft control surface inputs. Lloyd R. Jenkinson, James F. Marchman III, in Aircraft Design Projects, Stability and control. The aircraft control surfaces were initially sized using conventional design methods 1 and by comparison with current land and amphibious general aviation aircraft.
All controls are conventional with the possible exception of the horizontal stabilizer on which a fully movable stabilizer. One of the key steps of this approach is determining the structural damage of the state of the aircraft by using the identification, detection, and classification methods presented in this paper.
The estimated damage cases will lead to structural damage indices in the database corresponding to those safe flight envelopes that are “closest. • role and expectations of pilot in automated aircraft • improved failure detection, identification and isolation • envelope protection Generalized integrated lateral directional control concept was developed under DARPA/Boeing Condor program (), resulting in.
Don't show me this again. Welcome. This is one of over 2, courses on OCW. Find materials for this course in the pages linked along the left. MIT OpenCourseWare is a free & open publication of material from thousands of MIT courses, covering the entire MIT curriculum.
No enrollment or registration. • An FHA should be conducted at the Aircraft level and the System level. the rationale for its classification.
• FHA should provide the following information: – Identification of related failure conditions. – Identification of the effects of the failure conditions.
A concept that minimizes the likelihood of common. The manual summarizes experience of teaching aircraft designing disciplines in SSAU.
The second edition comprises the significant corrections for the purpose of increasing the accuracy of project estimations and taking into account current achievements of the world aircraft industry. Aircraft Flight Envelope Determination using Upset Detection and Physical Modeling Methods The development of flight control systems to enhance aircraft safety during periods of vehicle impairment or degraded operations has been the focus of extensive work in recent years.
Conditions adversely affecting aircraft flight operations and safety may result from a number of causes, including.
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This research paper describes the methodology applying indicial function. expanded the need for large quantities of reliable aircraft. Used mostly for reconnaissance, stacked-wing tail draggers with wood and metal truss frames with mostly fabric skin dominated the wartime sky.
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Verification of the displayed data with a chart accomplishes three functions: 1. Provides you practice for retention of your map reading.
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The objective is to present a top level view of the systems, from regulatory requirements to the. system senses a failure, it automatically selects the best pre-computed solution from a set of control laws loaded into the aircraft's flight control computer.
On the initial demonstration flight, NASA research pilot James Smolka, flying at Machpurposely locked the aircraft's right horizontal stabilator to represent a failure of hydraulic or. aircraft’s function or a critical failure must be less than per flight hour. The paper is organized as follows: Section I presents flight control systems.
Section II and III provide the fundamental concepts and definition of dependability. Sections IV and V describe basic architecture of Airbus and Boeing fault tolerance flight computer.The upgrade added a data transfer unit and a radar altimeter.
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Although vibration analysis is commonly used in the diagnosis of rolling bearings, it is possible that the failure of such bearings might be detected earlier by an acoustic emission (AE) technique.
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