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  • AIRCRAFT STABILITY AND CONTROL  (12)
  • 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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    NASA TECHNICAL REPORTS
  • 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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    NASA TECHNICAL REPORTS
  • 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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    NASA TECHNICAL REPORTS
  • 4
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    Active control - A look at analytical methods and associated tools (1984)
    In:  Other Sources
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    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
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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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    SPINEQ: A program for determining aircraft equilibrium spin characteristics including stability (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program, SPINEQ, is described which can algebraically solve the nonlinear equations of motion for equilibrium spin conditions. Linear characteristics of the airplane about the equilibrium points are also determined. The theoretical basis of the program is outlined, computational flow is shown, the functions of major subroutines are described, and key parameters directing the computations are identified. Program input and output are described and illustrated by means of a test case. The program is available from COSMIC.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-78759 , L-12328
    Format: application/pdf
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  • 7
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    A Digital Program for Calculating the Interaction Between Flexible Structures, Unsteady Aerodynamics and Active Controls (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer program, ISAC, is described which calculates the stability and response of a flexible airplane equipped with active controls. The equations of motion relative to a fixed inertial coordinate system are formulated in terms of the airplane's rigid body motion and its unrestrained normal vibration modes. Unsteady aerodynamic forces are derived from a doublet lattice lifting surface theory. The theoretical basis for the program is briefly explained together with a description of input data and output results.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-80040
    Format: application/pdf
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  • 8
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    Control law design to meet constraints using SYNPAC-synthesis package for active controls (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Major features of SYNPAC (Synthesis Package for Active Controls) are described. SYNPAC employs constrained optimization techniques which allow explicit inclusion of design criteria (constraints) in the control law design process. Interrelationships are indicated between this constrained optimization approach, classical and linear quadratic Gaussian design techniques. Results are presented that were obtained by applying SYNPAC to the design of a combined stability augmentation/gust load alleviation control law for the DAST ARW-2.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-83264 , NAS 1.15:83264 , Joint Automatic Control Conf.; Jun 17, 1981 - Jun 19, 1981; Charlottesville, VA; United States
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  • 9
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    Eigenspace design of an active flutter suppression system (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An active control system is designed for the suppression of wing flutter in a flight test vehicle. Eigenvalue placement is used to synthesize a full state controller which satisfies performance specifications on control surface activity and which exhibits excellent gain and phase margins. The use of limited state feedback is examined; however, it is found that a simple frequency response matching technique can be used to design a realizable compensator which reproduces the feedback properties of the full state controller. The performance of the control system using this compensator is evaluated at various flight conditions and found to be satisfactory. In addition eigenvector shaping is used to enhance the gust load alleviation capabilities of the flutter control system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 84-1867
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  • 10
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    Design of a candidate flutter suppression control law for DAST ARW-2 (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    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 LQC (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
    Type: NASA-TM-86257 , NAS 1.15:86257 , AIAA PAPER 83-2221 , AIAA Guidance and Control Conf.; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN; United States
    Format: application/pdf
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