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  • 1
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    Development of a flutter suppression control law by use of Linear Quadratic Gaussian and constrained optimization design techniques (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A control law is developed to suppress symmetric flutter for a mathematical model of an aeroelastic research vehicle. An implementable control law is attained by including modified LQG (Linear Quadratic Gaussian) design techniques, controller order reduction, and gain scheduling. An alternate (complementary) design approach is illustrated for one flight condition wherein nongradient-based constrained optimization techniques are applied to maximize controller robustness.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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  • 2
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    Application of optimization techniques to the design of a flutter suppression control law for the DAST ARW-2 (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design of a candidate flutter suppression (FS) control law for the symmetric degrees of freedom for the DAST ARW-2 aircraft is discussed. The results illustrate the application of several currently employed control law design techniques. Subsequent designs, obtained as the mathematical model of the ARW-2 is updated, are expected to employ similar methods and to provide a control law whose performance will be flight tested. This study represents one of the steps necessary to provide an assessment of the validity of applying current control law synthesis and analysis techniques in the design of actively controlled aircraft. Mathematical models employed in the control law design and evaluation phases are described. The control problem is specified by presenting the flutter boundary predicted for the uncontrolled aircraft and by defining objectives and constraints that the controller should satisfy. A full-order controller is obtained by using Linear Quadratic Gaussian (LQG) techniques. The process of obtaining an implementable reduced-order controller is described. One example is also shown in which constrained optimization techniques are utilized to explicitly include robustness criteria within the design algorithm.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 1; 17 p
    Format: application/pdf
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  • 3
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    Development of a flutter suppression control law by use of linear quadratic Gaussian and constrained optimization design techniques (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A control law to suppress symmetric flutter for a mathematical model of an aeroelastic research vehicle is developed. An implementable control law is attained by including modified linear quadratic Gaussian design techniques, controller order reduction, and gain scheduling. A complementary design approach for a flight condition wherein nongradient-based constrained optimization techniques are applied to maximize controller robustness is illustrated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: DGLR The 2nd International Symposium on Aeroelasticity and Structural Dynamics; p 297-308
    Format: text
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  • 4
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    Active control - A look at analytical methods and associated tools (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A review of analytical methods and associated tools for active controls analysis and design problems is presented. Approaches employed to develop mathematical models suitable for control system analysis and/or design are discussed. Significant efforts have been expended to develop tools to generate the models from the standpoint of control system designers' needs and to develop the tools necessary to analyze and design active control systems. Representative examples of these tools are discussed. Examples where results from the methods and tools have been compared with experimental data are also presented. Finally, a perspective on future trends in analysis and design methods is presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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  • 5
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    Tools for active control system design (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Efficient control law analysis and design tools which properly account for the interaction of flexible structures, unsteady aerodynamics and active controls are developed. Development, application, validation and documentation of efficient multidisciplinary computer programs for analysis and design of active control laws are also discussed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA Aircraft Controls Research, 1983; p 263-279
    Format: application/pdf
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  • 6
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    STABCAR: A program for finding characteristic root systems having transcendental stability matrices (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: STABCAR can be used to determine the characteristic roots of flexible, actively controlled aircraft, including the effects of unsteady aerodynamics. A modal formulation and a transfer-matrix representation of the control system are employed. Operable in either a batch or an interactive mode, STABCAR can provide graphical or tabular output of the variation of the roots with velocity, density, altitude, dynamic pressure or feedback gains. Herein the mathematical model, program structure, input requirements, output capabilities, and a series of sample cases are detailed. STABCAR was written for use on CDC CYBER 175 equipment; modification would be required for operation on other machines.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TP-2165 , L-14861 , NAS 1.60:2165
    Format: application/pdf
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  • 7
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    Fitting aerodynamic forces in the Laplace domain: An application of a nonlinear nongradient technique to multilevel constrained optimization (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique which employs both linear and nonlinear methods in a multilevel optimization structure to best approximate generalized unsteady aerodynamic forces for arbitrary motion is described. Optimum selection of free parameters is made in a rational function approximation of the aerodynamic forces in the Laplace domain such that a best fit is obtained, in a least squares sense, to tabular data for purely oscillatory motion. The multilevel structure and the corresponding formulation of the objective models are presented which separate the reduction of the fit error into linear and nonlinear problems, thus enabling the use of linear methods where practical. Certain equality and inequality constraints that may be imposed are identified; a brief description of the nongradient, nonlinear optimizer which is used is given; and results which illustrate application of the method are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86317 , NAS 1.15:86317
    Format: application/pdf
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  • 8
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    Program Structure Combines Segmentation and Dynamic Storage (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Programing techniques incorporate advantages of overlaying into segmented loads while retaining all dynamic load advantages of segmentation, employing those capabilities that best suit mode of operation, whether batch or interactive. User is allowed to load a program automatically in a variable manner, based solely on a single data input to the program, to maintain minimal field lengths for interactive use.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-12830 , NASA Tech Briefs (ISSN 0145-319X); 6; 2; P. 236
    Format: text
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  • 9
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    Segmentation, dynamic storage, and variable loading on CDC equipment (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques for varying the segmented load structure of a program and for varying the dynamic storage allocation, depending upon whether a batch type or interactive type run is desired, are explained and demonstrated. All changes are based on a single data input to the program. The techniques involve: code within the program to suppress scratch pad input/output (I/O) for a batch run or translate the in-core data storage area from blank common to the end-of-code+1 address of a particular segment for an interactive run; automatic editing of the segload directives prior to loading, based upon data input to the program, to vary the structure of the load for interactive and batch runs; and automatic editing of the load map to determine the initial addresses for in core data storage for an interactive run.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-3315
    Format: application/pdf
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  • 10
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    Design of a candidate flutter suppression control law for DAST ARW-2 (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A control law is developed to suppress symmetric flutter for a mathematical model of an aeroelastic research vehicle. An implementable control law is attained by including modified LQG (linear quadratic Gaussian) design techniques, controller order reduction, and gain scheduling. An alternate (complementary) design approach is illustrated for one flight condition wherein nongradient-based constrained optimization techniques are applied to maximize controller robustness.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2221
    Format: text
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