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  • 1
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    Design of a flutter suppression system for an experimental drone aircraft (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 380-386
    Format: text
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  • 2
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    Analysis and flight data for a drone aircraft with active flutter suppression (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 12, p. 1935, Accession no. A81-29495)
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 3
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    New and existing techniques for dynamic loads analyses of flexible airplanes (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 340-347
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  • 4
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    Design of the flutter suppression system for DAST ARW-IR (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The design of the flutter suppression system for a remotely-piloted research vehicle is described. The modeling of the aeroelastic system, the methodology used to synthesized the control law, the analytical results used to evaluate the control law performance, and ground testing of the flutter suppression system onboard the aircraft are discussed. The major emphasis is on the use of optimal control techniques employed during the synthesis of the control law.
    Keywords: CYBERNETICS
    Type: NASA-TM-84642 , NAS 1.15:84642 , AIAA/ASME/ASCE/AHS 24th Struct., Struct. Dyn. and Mater. Conf.; May 02, 1983 - May 04, 1983; Lake Tahoe, NV; United States
    Format: application/pdf
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  • 5
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    Response of the Alliance 1 Proof-of-Concept Airplane Under Gust Loads (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This report presents the work performed by Lockheed Martin's Langley Program Office in support of NASA's Environmental Research Aircraft and Sensor Technology (ERAST) program. The primary purpose of this work was to develop and demonstrate a gust analysis method which accounts for the span-wise variation of gust velocity. This is important because these unmanned aircraft having high aspect ratios and low wing loading are very flexible, and fly at low speeds. The main focus of the work was therefore to perform a two-dimensional Power Spectrum Density (PSD) analysis of the Alliance 1 Proof-of-Concept Unmanned Aircraft, As of this writing, none of the aircraft described in this report have been constructed. They are concepts represented by analytical models. The process first involved the development of suitable structural and aeroelastic Finite Element Models (FEM). This was followed by development of a one-dimensional PSD gust analysis, and then the two-dimensional (PSD) analysis of the Alliance 1. For further validation and comparison, two additional analyses were performed. A two-dimensional PSD gust analysis was performed on a simplet MSC/NASTRAN example problem. Finally a one-dimensional discrete gust analysis was performed on Alliance 1. This report describes this process, shows the relevant comparisons between analytical methods, and discusses the physical meanings of the results.
    Keywords: Structural Mechanics
    Type: NASA/CR-2001-210649 , NAS 1.26:210649
    Format: application/pdf
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  • 6
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    Design of the flutter suppression system for DAST ARW-1R - A status report (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the design of the flutter suppression system for a remotely-piloted research vehicle. The modeling of the aeroelastic system, the methodology used to synthesize the control law, the analytical results used to evaluate the control law performance, and ground testing of the flutter suppression system onboard the aircraft are discussed. The major emphasis is on the use of optimal control techniques employed during the synthesis of the control law.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-0990 , Structures, Structural Dynamics and Materials Conference; May 02, 1983 - May 04, 1983; Lake Tahoe, NV
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  • 7
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    Comparison of analysis and flight test data for a drone aircraft with active flutter suppression (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper presents a comparison of analysis and flight test data for a drone aircraft equipped with an active flutter suppression system. Emphasis is placed on the comparison of modal dampings and frequencies as a function of Mach number. Results are presented for both symmetric and antisymmetric motion with flutter suppression off. Only symmetric results are presented for flutter suppression on. Frequency response functions of the vehicle are presented from both flight test data and analysis. The analysis correlation is improved by using an empirical aerodynamic correction factor which is proportional to the ratio of experimental to analytical steady-state lift curve slope. In addition to presenting the mathematical models and a brief description of existing analytical techniques, an alternative analytical technique for obtaining closed-loop results is presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-0640 , Conference on Structures, Structural Dynamics and Materials; Apr 06, 1981 - Apr 08, 1981; Atlanta, GA
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  • 8
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    The application of active controls technology to a generic hypersonic aircraft configuration (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analytical methods are described for the prediction of aerothermoelastic stability of hypersonic aircraft including active control systems. Thermal loads due to aerodynamic heating were applied to the finite element model of the aircraft structure and the thermal effects on flutter were determined. An iterative static aeroelastic trim analysis procedure was developed including thermal effects. And active control technology was assessed for flutter suppression, ride quality improvement, and gust load alleviation to overcome any potential adverse aeroelastic stability or response problems due to aerodynamic heating. A generic hypersonic aircraft configuration was selected which incorporates wing flaps, ailerons, and all moveable fins to be used for active control purposes. The active control system would use onboard sensors in a feedback loop through the aircraft flight control computers to move the surfaces for improved structural dynamic response as the aircraft encounters atmospheric turbulence.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101689 , NAS 1.15:101689 , National Aero-Space Plane Technology Symposium; Oct 01, 1989; Cleveland, OH; United States
    Format: application/pdf
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  • 9
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    Comparison of analysis and flight test data for a drone aircraft with active flutter suppression (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A drone aircraft equipped with an active flutter suppression system is considered with emphasis on the comparison of modal dampings and frequencies as a function of Mach number. Results are presented for both symmetric and antisymmetric motion with flutter suppression off. Only symmetric results are given for flutter suppression on. Frequency response functions of the vehicle are presented from both flight test data and analysis. The analysis correlation is improved by using an empirical aerodynamic correction factor which is proportional to the ratio of experimental to analytical steady-state lift curve slope. The mathematical models are included and existing analytical techniques are described as well as an alternative analytical technique for obtaining closed-loop results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-83145 , AIAA PAPER 81-0640 , AIAA Dynamics Specialist Conf.,; Apr 08, 1981 - Apr 11, 1981; Atlanta, GA; United States
    Format: application/pdf
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  • 10
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    Dynamic loads analyses of flexible airplanes - New and existing techniques (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper reviews existing techniques for calculating dynamic loads for flexible airplanes and presents a new technique. The new technique involves the summation-of-forces method of writing dynamic loads equations. Until now this form of the dynamic loads equations has been formulated in the frequency domain. The new technique uses s-plane approximation methods (previously applied only to the equations of motion) to transform the dynamic loads equations from a second-order frequency-domain formulation with frequency-dependent coefficients into a linear-time-invariant state-space formulation. Several numerical examples demonstrate the usefulfness of the new technique and the high quality of the results. In addition, a convergence investigation establishes that the summation-of-forces method converges more quickly (that is, with fewer modes) than does the mode displacement method.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 85-0808 , Structures, Structural Dynamics, and Materials Conference; Apr 15, 1985 - Apr 17, 1985; Orlando, FL
    Format: text
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