Aircraft Loss-of-Control Accident Prevention: Switching Control of the GTM Aircraft with Elevator Jam Failures

The nonlinear dynamics of a large transport aircraft are analyzed to determine how the natural stability of the aircraft could be used for stall and spin recovery. The analysis is performed using the wide-envelope nonlinear simulation model for the Generic Transport Model (GTM). A bifurcation analysis is performed with respect to elevator to find the desirable stable equilibria of the aircraft inside the aerodynamic envelope, and to check for undesirable stable equilibria outside the envelope. For control surface deflections near zero, only one stable equilibrium branch is found, corresponding to the aircraft gliding with the steady-state angle of attack and sideslip angle well within the envelope. For excessive elevator deflections, two stable branches are found corresponding to stall and spin conditions. Simulations are performed to confirm the results of the bifurcation analysis and to analyze the transient behavior during the stall and spin departure and recovery. The results confirm that the aircraft enters stall and spin when excessive elevator is commanded, and recovers from stall and spin when the elevator is returned to zero deflection. The stall and spin recovery of a large transport aircraft can therefore be performed by setting the throttle to idle, returning the control surfaces to their neutral values, and relying on the aircraft's natural stability. The natural rate damping of the aircraft is sufficient to quickly recover the aircraft from spin, and the natural tendency of the aircraft to point its nose into the airstream is sufficient to recover the aircraft from stall. Nomenclature α = angle of attack, rad β = sideslip angle, rad P = roll rate, rad/s Q = pitch rate, rad/s R = yaw rate, rad/s AirSTAR = Airborne Subscale Transport Aircraft Research GTM = Generic Transport Model LOC = Loss-of-Control QLC = Quantitative Loss-of-Control Criteria UAV = Unmanned Aerial Vehicle

Section: The Generic Transport Modelmentioning

confidence: 99%

Bifurcation Analysis and Simulation of Stall and Spin Recovery for Large Transport Aircraft

Jaa

2012

“…Most of the development work on the GTM thus far has been aimed at Fault Tolerant Control 19,20 and modelling of damage to the physical aircraft 18,31 Recently, there has been work on LOC prevention and envelope protection utilising the GTM [32][33][34] . Research is also being done on various adaptive control methods for creating robust controllers meant to handle failures or upsets which push the aircraft beyond the normal flight envelope [35][36][37] .…”

Section: The Generic Transport Modelmentioning

confidence: 99%

“…The GTM was specifically developed for research into nonlinear flight domains and is modelled throughout an extensive range of flight conditions. The GTM is reviewed in more detail in the following section, but the focus of the research on the GTM thus far has been on Fault Tolerant Control (FTC) [18][19][20] .…”

Section: Introductionmentioning

confidence: 99%

Bifurcation Analysis of the Generic Transport Model with a view to Upset Recovery

Jaa

2012

There is a trend developing in research focusing on commercial aircraft safety, especially with respect to upset recovery and loss-of-control. In seeking to address the upset recovery problem from a control perspective and owing to the fact that upsets involve flight outside the regular flight envelope, the requirement for a wide-envelope non-linear model arises, along with the requirement for non-linear analysis techniques. These needs are addressed by NASA's Generic Transport Model (GTM) and bifurcation theory respectively, with the latter having been used extensively in the analysis of non-linear flight dynamics of military aircraft operating in broad flight envelopes. This paper focuses on the application of bifurcation theory to the GTM and includes an analysis of the initial results thereof. It covers the difficulties involved in combining the two tools, especially the changes that need to be made to the GTM simulation in order to make it compatible with the mathematics performed in bifurcation analysis. Bifurcation theory is applied primarily to the longitudinal dynamics of the aircraft to investigate the effects of the aircraft elevator and throttle on the aircraft behaviour. The results agree with other research that suggests the classical role these controls play in established upset recovery doctrine is effective, but often not correctly executed. The paper also investigates the coupling between the longitudinal and lateral dynamics of the aircraft, highlighting how aerodynamic stall negatively affects the lateral dynamics. NomenclatureGTM Generic Transport Model LOC Loss-of-Control UAV Unmanned Aerial Vehicle FTC Fault Tolerant Control V velocity magnitude α angle of attack β sideslip angle P x body-axis relative angular rate Q y body-axis relative angular rate R z body-axis relative angular rate Φ Euler 321 roll attitude angle Θ Euler 321 pitch attitude angle Ψ Euler 321 yaw attitude angle δ e absolute elevator deflection angle δ a absolute aileron deflection angle δ r absolute rudder deflection angle δ t absolute throttle percentage * PhD Student, Department of Electrical and Electronic Engineering, sjpauck@sun.ac.za. † Senior Lecturer, Department of Electrical and Electronic Engineering, jengelbr@sun.ac.za, AIAA Senior Member.

“…It allows the development of control laws that can be implemented on the GTM in-flight model. The majority of GTM research has been on the development of controllers 8,9 to help control upset scenarios and for implementing into the Aircraft Integrated Resilient Safety Assurance and Failsafe Enhancement (AIRSAFE) concept where resilient control is integrated with flight safety assessment and management; an overview is given in Ref. [10] .…”

Section: Introductionmentioning

confidence: 99%

Bifurcation Analysis of the NASA GTM with a View to Upset Recovery

Gill¹,

Lowenberg²,

Krauskopf

et al. 2012

The loss of control in-flight of civil airliners is a matter of great concern to the aviation industry. Loss of control in-flight often involves so called 'upset' conditions and, hence, the ability to recover from upset will reduce the frequency of loss of control incidents. This paper presents the use of bifurcation analysis, complemented by time-history simulations, to understand the flight dynamics of the open loop NASA Generic Transport Model with a view to identifying the attractors of the dynamical system that underlie upset behaviour. A number of drivers for potential upset conditions have been discovered which include non-oscillatory spirals and oscillatory spins. Time-histories of the upset conditions yield the response characteristics associated with these upset scenarios.