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  • 1
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    Comparison of equivalent plate and finite element analysis of a realistic aircraft structural configuration (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a comparison study to assess how well a realistic aircraft structure can be represented with an equivalent plate model. A wing box and full wing structure of a high-speed civil transport aircraft configuration are analyzed. Static and vibration results from the equivalent plate analysis are compared with results from a finite element model. The results from these comparisons show that, for the simpler wing box models, the static displacements and first vibration frequency agree to within 1.5 percent. The full wing models only agree to within 10 percent, for both models, the higher frequencies vary by as much as 26 percent. These differences are due to inadequate refinement of the equivalent plate model.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-3293
    Format: text
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  • 2
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    Multilevel decomposition approach to the preliminary sizing of a transport aircraft wing (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A multilevel/multidisciplinary optimization scheme for sizing an aircraft wing structure is described. A methodology using nonlinear programming in application to a very large engineering problem is presented. This capability is due to the decomposition approach. Over 1300 design variables are considered for this nonlinear optimization task. In addition, a mathematical link is established coupling the detail of structural sizing to the overall system performance objective, such as fuel consumption. The scheme is implemented as a three level system analyzing aircraft mission performance at the top level, the total aircraft structure as the middle level, and individual stiffened wing skin cover panels at the bottom level. Numerical show effectiveness of the method and its good convergence characteristics.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-4296 , NAS 1.26:4296
    Format: application/pdf
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  • 3
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    A new algorithm for general multiobjective optimization (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described is a new technique for converting a constrained optimization problem to an unconstrained one, and a new method for multiobjective optimization based on that technique. The technique transforms the objective functions into goal constraints. The goal constraints are appended to the set of behavior constraints and the envelope of all functions in the set is searched for an unconstrained minimum. The technique may be categorized as a SUMT algorithm. In multiobjective applications, the approach has the advantage of locating a compromise minimum without the need to optimize for each individual objective function separately. The constrained to unconstrained conversion is described, followed by a description of the multiobjective problem. Two example problems are presented to demonstrate the robustness of the method.
    Keywords: MATHEMATICAL AND COMPUTER SCIENCES (GENERAL)
    Type: NASA-TM-100536 , NAS 1.15:100536 , AIAA PAPER 88-2434
    Format: application/pdf
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  • 4
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    Aircraft design for mission performance using non-linear multiobjective optimization methods (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new technique which converts a constrained optimization problem to an unconstrained one where conflicting figures of merit may be simultaneously considered has been combined with a complex mission analysis system. The method is compared with existing single and multiobjective optimization methods. A primary benefit from this new method for multiobjective optimization is the elimination of separate optimizations for each objective, which is required by some optimization methods. A typical wide body transport aircraft is used for the comparative studies.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-2078
    Format: text
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  • 5
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    Aircraft design for mission performance using nonlinear multiobjective optimization methods (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new technique which converts a constrained optimization problem to an unconstrained one where conflicting figures of merit may be simultaneously considered was combined with a complex mission analysis system. The method is compared with existing single and multiobjective optimization methods. A primary benefit from this new method for multiobjective optimization is the elimination of separate optimizations for each objective, which is required by some optimization methods. A typical wide body transport aircraft is used for the comparative studies.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-4328 , NAS 1.26:4328
    Format: application/pdf
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  • 6
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    An indirect method for numerical optimization using the Kreisselmeir-Steinhauser function (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique is described for converting a constrained optimization problem into an unconstrained problem. The technique transforms one of more objective functions into reduced objective functions, which are analogous to goal constraints used in the goal programming method. These reduced objective functions are appended to the set of constraints and an envelope of the entire function set is computed using the Kreisselmeir-Steinhauser function. This envelope function is then searched for an unconstrained minimum. The technique may be categorized as a SUMT algorithm. Advantages of this approach are the use of unconstrained optimization methods to find a constrained minimum without the draw down factor typical of penalty function methods, and that the technique may be started from the feasible or infeasible design space. In multiobjective applications, the approach has the advantage of locating a compromise minimum design without the need to optimize for each individual objective function separately.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-4220 , NAS 1.26:4220
    Format: application/pdf
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  • 7
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    Integrating aerodynamics and structures in the minimum weight design of a supersonic transport wing (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An approach is presented for determining the minimum weight design of aircraft wing models which takes into consideration aerodynamics-structure coupling when calculating both zeroth order information needed for analysis and first order information needed for optimization. When performing sensitivity analysis, coupling is accounted for by using a generalized sensitivity formulation. The results presented show that the aeroelastic effects are calculated properly and noticeably reduce constraint approximation errors. However, for the particular example selected, the error introduced by ignoring aeroelastic effects are not sufficient to significantly affect the convergence of the optimization process. Trade studies are reported that consider different structural materials, internal spar layouts, and panel buckling lengths. For the formulation, model and materials used in this study, an advanced aluminum material produced the lightest design while satisfying the problem constraints. Also, shorter panel buckling lengths resulted in lower weights by permitting smaller panel thicknesses and generally, by unloading the wing skins and loading the spar caps. Finally, straight spars required slightly lower wing weights than angled spars.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-107586 , NAS 1.15:107586 , AIAA/ASCE/ASME/AHS/ASC 33rd Structures, Structural Dynamics and Materials Conference; Apr 13, 1992 - Apr 15, 1992; Dallas, TX; United States
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  • 8
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    A new algorithm for general multiobjective optimization (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes a new technique for converting a constrained optimization problem to an unconstrained one, and a new method for multiobjective optimization based on that technique. The technique transforms the objective functions into goal constraints. The goal constraints are appended to the set of behavior constraints, and the envelope of all functions in the set is searched for an unconstrained minimum. The technique can be categorized as a SUMT algorithm. In multiobjective applications, the approach has the advantage of locating a compromise minimum without the need to optimize for each individual objective function separately. The constrained to unconstrained conversion is described, followed by a description of the multiobjective problem. Two example problems are presented to demonstrate the robustness of the method.
    Keywords: SYSTEMS ANALYSIS
    Type: AIAA PAPER 88-2434 , Structures, Structural Dynamics and Materials Conference; Apr 18, 1988 - Apr 20, 1988; Williamsburg, VA; United States
    Format: text
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  • 9
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    Application of multidisciplinary optimization methods to the design of a supersonic transport (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An optimization design method is discussed. This method is based on integrating existing disciplinary analysis and sensitivity analysis techniques by means of generalized sensitivity equations. A generic design system implementing this method is described. The system is being used to design the configuration and internal structure of a supersonic transport wing for optimum performance. This problem combines the disciplines of linear aerodynamics, structures, and performance. Initial results which include the disciplines of aerodynamics and structures in a conventional minimum weight design under static aeroelastic constraints are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104073 , NAS 1.15:104073 , North Atlantic Treaty Organization-AGARD Structures and Materials Panel Meeting; May 01, 1991 - May 02, 1991; Bath
    Format: application/pdf
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  • 10
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    DB90: A Fortran Callable Relational Database Routine for Scientific and Engineering Computer Programs (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report describes a database routine called DB90 which is intended for use with scientific and engineering computer programs. The software is written in the Fortran 90/95 programming language standard with file input and output routines written in the C programming language. These routines should be completely portable to any computing platform and operating system that has Fortran 90/95 and C compilers. DB90 allows a program to supply relation names and up to 5 integer key values to uniquely identify each record of each relation. This permits the user to select records or retrieve data in any desired order.
    Keywords: Computer Programming and Software
    Type: NASA/CR-2005-213524
    Format: application/pdf
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