General Equations of Motion for a Damaged Asymmetric Aircraft

Bacon, Barton J.; Gregory, Irene M.

doi:10.2514/6.2007-6306

Cited by 88 publications

(66 citation statements)

References 1 publication

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“…offsets are appropriately modeled and accounted for. Some recent research activities have addressed this aspect 14 . From an aerodynamic modeling standpoint, many assumptions of symmetry may no longer be valid due to the off-axis influences of damage, and new aerodynamic contributions will need to be modeled.…”

Section: Modeling Issuesmentioning

confidence: 99%

Aerodynamic Effects and Modeling of Damage to Transport Aircraft

Shah

2008

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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A wind tunnel investigation was conducted to measure the aerodynamic effects of damage to lifting and stability/control surfaces of a commercial transport aircraft configuration. The modeling of such effects is necessary for the development of flight control systems to recover aircraft from adverse, damage-related loss-of-control events, as well as for the estimation of aerodynamic characteristics from flight data under such conditions. Damage in the form of partial or total loss of area was applied to the wing, horizontal tail, and vertical tail. Aerodynamic stability and control implications of damage to each surface are presented, to aid in the identification of potential boundaries in 'recoverable' stability or control degradation. The aerodynamic modeling issues raised by the wind tunnel results are discussed, particularly the additional modeling requirements necessitated by asymmetries due to damage, and the potential benefits of such expanded modeling. Nomenclature

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Section: Modeling Issuesmentioning

confidence: 99%

Aerodynamic Effects and Modeling of Damage to Transport Aircraft

Shah

2008

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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“…Inertial effects, including center of gravity shift and change to the aircraft mass properties, have not been modeled but may be incorporated following the approach outlined in Ref. 26.…”

Section: Lifting Surface Damage Effectsmentioning

confidence: 99%

Aircraft Flight Envelope Determination Using Upset Detection and Physical Modeling Methods

Keller

McKillip

Kim

2009

AIAA Guidance, Navigation, and Control Conference

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The development of flight control systems to enhance aircraft safety during periods of vehicle impairment or degraded operations has been the focus of extensive work in recent years. Conditions adversely affecting aircraft flight operations and safety may result from a number of causes, including environmental disturbances, degraded flight operations, and aerodynamic upsets. To enhance the effectiveness of adaptive and envelope limiting controls systems, it is desirable to examine methods for identifying the occurrence of anomalous conditions and for assessing the impact of these conditions on the aircraft operational limits. This paper describes initial work performed toward this end, examining the use of fault detection methods applied to the aircraft for aerodynamic performance degradation identification and model-based methods for envelope prediction. Results are presented in which a model-based fault detection filter is applied to the identification of aircraft control surface and stall departure failures/upsets. This application is supported by a distributed loading aerodynamics formulation for the flight dynamics system reference model. Extensions for estimating the flight envelope due to generalized aerodynamic performance degradation are also described.

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“…To address this problem, recently in Refs. [57] and [58], models of aircraft systems in the presence of damage and failures have been developed for investigating effects of damage and simultaneous failure-and damage-tolerance. These models in [58] were derived assuming that nominal flight (with zero steady-state angular velocities) is still achievable with feedback control, after damage and failures, which suggests that the models can be linearized at zero angular velocity for the purpose of controller design.…”

Section: Aircraft Dynamics Under Failures and Damagementioning

confidence: 99%

Direct Adaptive Control of Systems with Actuator Failures: State of the Art and Continuing Challenges

Tao

Joshi

2008

AIAA Guidance, Navigation and Control Conference and Exhibit

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In this paper, the problem of controlling systems with failures and faults is introduced, and an overview of recent work on direct adaptive control for compensation of uncertain actuator failures is presented. Actuator failures may be characterized by some unknown system inputs being stuck at some unknown (fixed or varying) values at unknown time instants, that cannot be influenced by the control signals. The key task of adaptive compensation is to design the control signals in such a manner that the remaining actuators can automatically and seamlessly take over for the failed ones, and achieve desired stability and asymptotic tracking. A certain degree of redundancy is necessary to accomplish failure compensation. The objective of adaptive control design is to effectively use the available actuation redundancy to handle failures without the knowledge of the failure patterns, parameters, and time of occurrence. This is a challenging problem because failures introduce large uncertainties in the dynamic structure of the system, in addition to parametric uncertainties and unknown disturbances. The paper addresses some theoretical issues in adaptive actuator failure compensation: actuator failure modeling, redundant actuation requirements, plant-model matching, error system dynamics, adaptation laws, and stability, tracking, and performance analysis. Adaptive control designs can be shown to effectively handle uncertain actuator failures without explicit failure detection. Some open technical challenges and research problems in this important research area are discussed.

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General Equations of Motion for a Damaged Asymmetric Aircraft

Cited by 88 publications

References 1 publication

Aerodynamic Effects and Modeling of Damage to Transport Aircraft

Aerodynamic Effects and Modeling of Damage to Transport Aircraft

Aircraft Flight Envelope Determination Using Upset Detection and Physical Modeling Methods

Direct Adaptive Control of Systems with Actuator Failures: State of the Art and Continuing Challenges

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