Bifurcation Analysis of a Highly Augmented Aircraft Model

Avanzini, Giulio; Matteis, G. De

doi:10.2514/2.4108

Cited by 58 publications

(30 citation statements)

References 5 publications

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“…It is then possible to find ϕ α using Equation (13) because ∂ϕ q /∂α can be determined numerically as a result of the second relationship in Equation (24).…”

Section: Dynamic Gain Scheduling With the Feedback Statementioning

confidence: 99%

“…An analysis of the open-loop models was carried out using the AUTO continuation software. Figure 2 shows the bifurcation diagrams (23)(24)(25)(26) for the second order open-loop model with the pitch flap (PF) deflection as the continuation parameter (µ). Solid lines indicate stable branches while dotted lines indicate unstable branches.…”

Section: Open-loop Ice Modelmentioning

confidence: 99%

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Dynamic gain-scheduled control of the ICE 101-TV

2005

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This paper shows the theoretical development and application of dynamic gain scheduled control -a novel method for the control of nonlinear systems -to an aircraft model. The idea behind this method is to schedule the control law gains with a fast varying state variable rather than with a slow varying state or an input parameter. This is advantageous as it is then possible to schedule the gains with a state variable that is dominant in the mode that we are most interested in controlling. The use of this type of gain scheduling is shown to improve the transient response of the aircraft model when stepping between trim conditions and to overcome some of the problems associated with conventional gain scheduled controllers (such as control surface position limit saturation). 'Hidden coupling terms' that introduce unwanted dynamics when scheduling gains with a fast state (rather than the input design parameter) are eliminated directly by applying a transformation to the classical parameter-scheduled gain distributions which are calculated using eigenstructure assignment. A second order longitudinal model and a 5th order longitudinal/lateral model of the ICE 101-TV tailless delta-wing aircraft configuration are used to demonstrate the design process. AbbreviationsAMT all-moving tip AMTact all-moving tip actuator AMTL all-moving tip (left) AMTLact all-moving tip (left) actuator THE AERONAUTICAL JOURNAL DECEMBER 2005 593

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“…It is then possible to find ϕ α using Equation (13) because ∂ϕ q /∂α can be determined numerically as a result of the second relationship in Equation (24).…”

Section: Dynamic Gain Scheduling With the Feedback Statementioning

confidence: 99%

Section: Open-loop Ice Modelmentioning

confidence: 99%

Dynamic gain-scheduled control of the ICE 101-TV

2005

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“…Further examples along this line of research can be found in (Jahnke and Culick, 1994) and (Liaw et al, 2003). The bifurcation analysis of the controller augmented aircraft was considered in (Avanzini and Matteis, 1997) and (Gibson et al, 1998). The ultimate goal of all the above research is to design control systems that circumvent or alleviate the undesirable nonlinear phenomena.…”

Section: Introductionmentioning

confidence: 99%

Bifurcation Analysis of Flight Control Systems

Thomas

Kwatny

Chang

2005

IFAC Proceedings Volumes

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“…Mehra [11], a wide history of use in military aircraft flight dynamics and control problems [12][13][14][15]. With regards to the loss-of-control of civil aircraft, bifurcation analysis has been applied, in open-loop form, to the GTMds [10] and the model created for the 'Simulation of UPset Recovery in Aviation' (SUPRA) research programme [16], which have both revealed the existence of spiral dives and steep spins.…”

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confidence: 99%

Impact of Controller Delays on the Nonlinear Dynamics of Remotely Piloted Aircraft

Gill

Lowenberg

Neild

et al. 2016

Journal of Guidance, Control, and Dynamics

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Time delays arise in most feedback systems and have specific relevance for remotely piloted vehicles with ground-based pilots and controllers. NASA's test facility for flight dynamics and control research using sub-scale vehicles, AirSTAR, has developed the remotely piloted Generic Transport Model (GTM). Analysis of a numerical model of this has previously provided insight into open-loop upset dynamics and the impact of flight controllers. However, to date, studies have not considered the effect of time delay on the system's stability. Current developments at the AirSTAR facility are aimed at testing a sub-scale generic airliner model during loss-of-control conditions over extended distances and altitudes compared to the GTM. In developing controllers for such a remotely piloted vehicle it is helpful to understand the effect of delay in the communication links and protocols. This paper utilises bifurcation analysis to evaluate the effect of delay on the closed-loop stability for the GTM numerical model with a linear quadratic regulator controller with proportional and integral components (LQR-PI). The impact of time delays in both fixed-gain and gain-scheduled versions of the controller are presented in terms of the stability of nominal and off-nominal solutions. This is followed by a discussion of stability maps, again generated by bifurcation analysis, which can be used to assess, over a wide

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Bifurcation Analysis of a Highly Augmented Aircraft Model

Cited by 58 publications

References 5 publications

Dynamic gain-scheduled control of the ICE 101-TV

Dynamic gain-scheduled control of the ICE 101-TV

Bifurcation Analysis of Flight Control Systems

Impact of Controller Delays on the Nonlinear Dynamics of Remotely Piloted Aircraft

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