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  • 42.75
  • Aircraft Stability and Control
  • Industrial Chemistry
  • Inorganic Chemistry
  • Temperatur
  • 2015-2019  (10)
  • 1950-1954
  • 1915-1919
  • 2019  (10)
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  • 2015-2019  (10)
  • 1950-1954
  • 1915-1919
Year
  • 1
    Publication Date: 2019-07-20
    Description: These slides describe a method and technology of modeling flexible aircraft for active control of structural dynamics. Objective: Generate models useful for the design and evaluation of control laws for active structural control and flutter suppression that are able to accurately predict body freedom flutter.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN66921 , Aerospace Control and Guidance Systems Committee (ACGSC) Meeting; Mar 27, 2019 - Mar 29, 2019; Santa Fe, NM; United States
    Format: application/pdf
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  • 2
    Publication Date: 2019-07-20
    Description: A multi-objective optimal control technique is modified to accommodate changing cost function weights and is used to control a flexible wing aircraft model. Variation of the weights is used to adjust the relative importance of each objective according to either a prescribed function of time or of the state. Several techniques for obtaining a practical approximation to the optimal control solution are presented, and stability of a specific weight structure with the optimal controller is demonstrated. Functionality of the multi-objective control design with weight variation is demonstrated in simulation of a flexible wing transport aircraft and is shown to improve performance over the fixed weight version both at a constant flight condition and across changing flight conditions.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN64647 , AIAA SciTech Forum 2019; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 3
    Publication Date: 2019-07-20
    Description: A new 6-DoF aeroservoelastic (ASE) Common Research Model (CRM) provided by The Boeing Company with aspect ratio 13.5 and 17 control surfaces per wing is utilized to demonstrate combined tracking and optimal multi-objective control. The multi-objective controller is derived on the closed loop tracking controller, and utilizes state and gust estimates provided by an extended state observer. Various methods of model reduction useful for control and estimation are presented. A computationally efficient MATLAB/Simulink simulation is presented which includes actuator dynamics, rate and deflection saturation limits, and gust disturbance inputs. The platform is used to demonstrate excellent 6-DoF tracking control performance coupled with the multi-objective controller, which is shown to effectively reduce structural mode movement, wing root bending moment, and drag. State and gust estimation is also shown to perform well, even when derived and/or implemented with significantly fewer states than the original full-sized model.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN271828 , AIAA Science and Technology Forum and Exposition; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 4
    Publication Date: 2019-07-20
    Description: Slides for an invited presentation (as part of a series) at Santa Clara University, invited by prof. Mohammad Ayoubi. The slides are an overview and summary of past and current research projects in the field of envelope protection, upset prevention and stall recovery guidance, with the aim to avoid loss of control accidents and improve safety in air transportation. The overall aim of this presentation series is to inspire students and to show them possible opportunities that they can pursue for their later careers paths.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN52363 , Santa Clara University Invited Lecture Series; Santa Clara, CA; United States
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  • 5
    Publication Date: 2019-09-13
    Description: An extension of model reference adaptive control is presented that accommodates use of a time-varying reference model. Specifically, the reference model is taken to be a time-varying convex combination of two linear, time-invariant models. The design is intended to act as a way to smoothly transition between two different reference models without resorting to a scheduled switch. It also provides the ability to use an interpolated reference model when the plant is operating between design points. The time variation of the combination must satisfy some requirements to ensure stability but is otherwise user choice. Subject to these requirements, bounded tracking error behavior is demonstrated via Lyapunov stability analysis for the single-input, single-output, output feedback case. Tracking error convergence is asymptotic when time variation ceases. The proposed design is demonstrated in simulation of a numerical model.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN66631 , American Control Conference; Jul 10, 2019 - Jul 12, 2019; Philadelphia, PA; United States
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  • 6
    Publication Date: 2019-10-30
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN74004
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  • 7
    Publication Date: 2019-07-13
    Description: This paper verifies a motion cueing strategy for improved pilot stall recovery training in commercial transport simulators. Eight airline transport pilots flew a high-altitude stall recovery task in the NASA B747 level-D-certified full flight simulator under three different motion configurations: no motion, baseline motion, and enhanced motion. For each motion condition, pilots performed the task with both baseline aircraft dynamics and aircraft dynamics enhanced with lateral-directional characteristics of the airplane at angle of attack approaching stall. Motion configuration significantly affected: 1) pilot opinions on the helpfulness of motion in performing the task, 2) the maximum roll angle in the stall maneuver, 3) the minimum load factor in the recovery, 4) the number of secondary stick shakers in the stall recovery, and 5) the maximum airspeed in the recovery. The two different aircraft dynamics significantly affected: 1) pilot opinions on the noticeability of the banking roll off near the stall and 2) the maximum roll angle in the stall maneuver. These results indicate that the relatively minor enhancements to the motion logic of heritage commercial transport simulators presented here can significantly improve pilot performance in simulated stall recoveries, and potentially improve stall recovery training.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN65276 , AIAA SciTech Forum 2019; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 8
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    In:  CASI
    Publication Date: 2019-07-13
    Description: An overview of the flight control work in the Intelligent Systems Division at NASA Ames is presented. The highlight focuses on efforts surrounding performance-adaptive aeroelastic wing shaping for aircraft with flexible wings. Topics covered include aeroservoelastic modeling capabilities, online drag-optimizing control designs, gust and maneuver load alleviation techniques, and related wind tunnel demonstrations.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN67091 , Aerospace Control and Guidance Systems Committee Meeting; Mar 27, 2019 - Mar 29, 2019; Santa Fe, NM; United States
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  • 9
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: JSC-E-DAA-TN69878-2 , AIAA AVIATION Forum and Exposition; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
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  • 10
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: JSC-E-DAA-TN69878-1 , AIAA AVIATION Forum and Exposition; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
    Format: text
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