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  • 1
    Electronic Resource
    Electronic Resource
    Springer
    Research in engineering design 4 (1992), S. 75-87 
    ISSN: 1435-6066
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Technology
    Notes: Abstract Although many ingenious mechanisms have been designed, the fundamental task of conceptualizing these devices is, to a great extent, still an art. While sophisticated computational tools for dynamic analysis of mechanisms exist, hardly any computational methods exist for generalized synthesis. To develop a computational model for synthesis, a formal foundation for mechanisms design must be laid by rationalizing the process of mechanical synthesis. Rationalization in synthesis implies that complex mechanical motions can be described in terms of primitives or building blocks. In this paper, we present a matrix methodology that forms the basis for a computable approach to design synthesis. In this methodology, the continuous design space of a mechanisms domain is discretized into functional subspaces, and each subspace is represented uniquely by a conceptual building block. The matrix scheme serves as a formal means to (a) represent and reason with the building blocks at different levels of abstraction, (b) generate alternate conceptual design configurations, and (c) facilitate rapid simulation of design concepts by connecting a series of building blocks.
    Type of Medium: Electronic Resource
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  • 2
    Electronic Resource
    Electronic Resource
    Springer
    Research in nondestructive evaluation 4 (1992), S. 37-54 
    ISSN: 1432-2110
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract This paper presents a formalization of the knowledge domain of nondestructive quality control of polymeric composite components. The formalization scheme presented in this paper has been implemented in a prototype knowledge-based expert system (KBES), called NICC for nondestructive inspection of composite components, to help in the quality assurance of these parts. Geometric and bonding characteristics of individual and assembled components are taken into account, as opposed to the better understood evaluation of well-behaved test specimens. The use of nondestructive techniques in the inspection of plastic and polymeric composites is fairly recent and hence, the knowledge required to develop a KBES is still very scattered and not yet fully covered in the literature. This study demonstrates both the feasibility of compiling and representing this knowledge domain and the possibility of translating it into an efficient automated tool capable of giving reliable expert-like advice at low cost. The reasoning process is divided into three stages. In the first stage, a polymetric composite component is completely defined according to features that are relevant for nondestructive inspection. In the second stage, all the discontinuities that may be present in the component are determined. Finally, in the third stage, appropriate nondestructive testing procedures are identified to detect each of the possible discontinuities.
    Type of Medium: Electronic Resource
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  • 3
    Publication Date: 2014-04-15
    Print ISSN: 0036-8733
    Electronic ISSN: 1946-7087
    Topics: Biology , Natural Sciences in General , Physics
    Published by Springer Nature
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  • 4
    Publication Date: 1992-06-01
    Print ISSN: 0934-9839
    Electronic ISSN: 1435-6066
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Technology
    Published by Springer
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  • 5
    Publication Date: 2019-07-13
    Description: The Adaptive Compliant Trailing Edge (ACTE) flap was flown on the National Aeronautics and Space Administration (NASA) Gulfstream GIII testbed at the NASA Armstrong Flight Research Center. This smoothly curving flap replaced the existing Fowler flaps creating a seamless control surface. This compliant structure, developed by FlexSys Inc. in partnership with the Air Force Research Laboratory, supported NASA objectives for airframe structural noise reduction, aerodynamic efficiency, and wing weight reduction through gust load alleviation. A thorough structures airworthiness approach was developed to move this project safely to flight. A combination of industry and NASA standard practice require various structural analyses, ground testing, and health monitoring techniques for showing an airworthy structure. This paper provides an overview of compliant structures design, the structural ground testing leading up to flight, and the flight envelope expansion and monitoring strategy. Flight data will be presented, and lessons learned along the way will be highlighted.
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN24640 , Society of Flight Test Engineers International Annual Symposium; Sep 14, 2015 - Sep 17, 2015; Lancaster, CA; United States
    Format: application/pdf
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  • 6
    Publication Date: 2019-07-13
    Description: A seamless adaptive compliant trailing edge (ACTE) flap was demonstrated in flight on a Gulfstream III aircraft at the NASA Armstrong Flight Research Center. The trailing edge flap was deflected between minus 2 deg up and plus 30 deg down in flight. The safety-of-flight parameters for the ACTE flap experiment require that flap-to-wing interface loads be sensed and monitored in real time to ensure that the structural load limits of the wing are not exceeded. The attachment fittings connecting the flap to the aircraft wing rear spar were instrumented with strain gages and calibrated using known loads for measuring hinge moment and normal force loads in flight. The safety-of-flight parameters for the ACTE flap experiment require that flap-to-wing interface loads be sensed and monitored in real time to ensure that the structural load limits of the wing are not exceeded. The attachment fittings connecting the flap to the aircraft wing rear spar were instrumented with strain gages and calibrated using known loads for measuring hinge moment and normal force loads in flight. The interface hardware instrumentation layout and load calibration are discussed. Twenty-one applied calibration test load cases were developed for each individual fitting. The 2-sigma residual errors for the hinge moment was calculated to be 2.4 percent, and for normal force was calculated to be 7.3 percent. The hinge moment and normal force generated by the ACTE flap with a hinge point located at 26-percent wing chord were measured during steady state and symmetric pitch maneuvers. The loads predicted from analysis were compared to the loads observed in flight. The hinge moment loads showed good agreement with the flight loads while the normal force loads calculated from analysis were over-predicted by approximately 20 percent. Normal force and hinge moment loads calculated from the pressure sensors located on the ACTE showed good agreement with the loads calculated from the installed strain gages.
    Keywords: Aircraft Design, Testing and Performance
    Type: AFRC-E-DAA-TN27065 , SciTech 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-13
    Description: The Adaptive Compliant Trailing Edge (ACTE) flap was flown on the NASA Gulfstream GIII test bed at the NASA Armstrong Flight Research Center. This smoothly curving flap replaced the existing Fowler flaps creating a seamless control surface. This compliant structure, developed by FlexSys Inc. in partnership with Air Force Research Laboratory, supported NASA objectives for airframe structural noise reduction, aerodynamic efficiency, and wing weight reduction through gust load alleviation. A thorough structures airworthiness approach was developed to move this project safely to flight.
    Keywords: Structural Mechanics; Research and Support Facilities (Air); Aircraft Stability and Control; Quality Assurance and Reliability; Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN26324 , SFTE Annual International Symposium; Sep 14, 2015 - Sep 17, 2015; Lancaster, CA; United States
    Format: application/pdf
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