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  • 1
    Electronic Resource
    Electronic Resource
    Approximate solutions to idealized structural dynamic optimization problems (1975)
    Springer
    Journal of optimization theory and applications 16 (1975), S. 119-133 
    Details
    ISSN: 1573-2878
    Keywords: Structural optimization ; minimum-weight design ; control theory ; distributed parameter problems ; two-point boundary-value problems
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mathematics
    Notes: Abstract This paper presents an application of two solution methods to the least-weight optimization of a simple sandwich beam with a frequency constraint. The first method, an adaptation of a numericalshooting technique used in optimal control, is found to give good results if unknown initial conditions can be reasonably approximated. The second method, a perturbation method used widely in theoretical mechanics and aerodynamics, yields approximate analytical expressions. These expressions can be used in turn to estimate starting values for the numerical technique. Converged numerical results are presented for a least-weight cantilever beam with fixed fundamental frequency and for a beam on simple supports with fixed fundamental frequency.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00935627
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Optimum design of composite structures (1989)
    Chichester [u.a.] : Wiley-Blackwell
    International Journal for Numerical Methods in Engineering 27 (1989), S. 437-448 
    Details
    ISSN: 0029-5981
    Keywords: Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mathematics , Technology
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/nme.1620270214
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  • 3
    Electronic Resource
    Electronic Resource
    An experimental and analytical investigation of the rail shear-test method as applied to composite materials (1980)
    Springer
    Experimental mechanics 20 (1980), S. 273-279 
    Details
    ISSN: 1741-2765
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract This report presents the results from an experimental and analytical investigation of the stress distributions occurring in a rail shear test. The effects of nonuniform stresses induced by differential thermal expansion, rail flexibility and specimen aspect ratio on measured shear modulus and ultimate strength of composite laminates are shown. A two-dimensional linearly elastic finite-element model was used to analytically determine how various geometric parameters influenced the magnitude and distribution of inplane normal and shear stresses in a tensile-rail-shear specimen. Rail shear tests were conducted at room temperature and 589 K (600°F) on selected graphite-polyimide composite laminates using two titanium rail configurations. The analysis and test methods are discussed, and the results of the effects of the various parameters on shear modulus and ultimate strength are presented.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF02328411
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  • 4
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    An experimental and analytical investigation of the rail shear-test method as applied to composite materials (1980)
    Springer
    Details
    Publication Date: 1980-08-01
    Print ISSN: 0014-4851
    Electronic ISSN: 1741-2765
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 5
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    Approximate solutions to idealized structural dynamic optimization problems (1975)
    Springer
    Details
    Publication Date: 1975-07-01
    Print ISSN: 0022-3239
    Electronic ISSN: 1573-2878
    Topics: Mathematics
    Published by Springer
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    PAPER CURRENT
  • 6
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    Integrated structure/control design - Present methodology and future opportunities (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Attention is given to current methodology applied to the integration of the optimal design process for structures and controls. Multilevel linear decomposition techniques proved to be most effective in organizing the computational efforts necessary for ISCD (integrated structures and control design) tasks. With the development of large orbiting space structures and actively controlled, high performance aircraft, there will be more situations in which this concept can be applied.
    Keywords: CYBERNETICS
    Format: text
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  • 7
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    On the track of practical forward-swept wings (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Structural laminates which comprise wing-cover skins for forward swept winged aircraft are examined. The laminates are themselves composed of lamina arranged in a symmetrical and unbalanced fashion. The fibers are oriented so that no fiber has a counterpart in the same ply which is at an exact anti-angle to itself. The laminate orientation creates a wash-out in a forward swept wing and alleviates aeroelastic loading. Further discussion is devoted to center-of-pressure movement, flutter behavior, aeroelasticity and aeroelastic divergence, and wind tunnel testing of aerodynamically tailored wings. It is found that rotating the laminate to increase the divergence dynamic pressure decreases strain under aerodynamic loading. Flight tests with three models are reported, and it is concluded that divergence can be avoided by the use of an efficient composite structure.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 20; Jan. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Integrated aeroservoelastic tailoring of lifting surfaces (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An approach to the integration of two design activities, structural design and active control design, for a highly idealized aeroservoelastic system is presented. The particular design goal for this study is the maximization of the stable airspeed envelope of an idealized model of an aeroservoelastic system through rational and systematic variation of structural and control design parameters. The steady-state linear quadratic regulator is used to model the control subsystem; the structural subsystem is assigned characteristic design parameters, such as shear center position. The application of the procedure described here produces optimally controlled structures with stability characteristics superior to those of open-loop and initial closed-loop designs.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 86-1005
    Format: text
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  • 9
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    Vibration tailoring of advanced composite lifting surfaces (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 141-147
    Format: text
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  • 10
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    Aeroelastic optimization of a panel in high Mach number supersonic flow. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Solution for a least-weight skin thickness distribution for a panel with a flutter parameter constraint. This panel weighs less than any similar constant thickness panel, but has the same critical supersonic panel flutter parameter. The panel rests on simple supports and is of sandwich construction. The span to chord ratio is large enough that the inertial, elastic, and aerodynamic behavior is one-dimensional. The Mach number is great enough that the aerodynamic forces acting on the upper panel surface may be accurately described by quasi-steady, linearized, supersonic aerodynamic theory. The final optimum design is obtained from theoretical and numerical methods adapted from optimal control theory. The results of this investigation show that the optimal panel thickness distribution is symmetric about the panel chord midpoint. Compared to a reference panel with constant thickness, optimum panels are found to be nearly 12% lighter.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft; 9; Sept
    Format: text
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