Space-Based Nonlinear Dynamic Inversion Control for Aircraft Continuous Descent Approach

Bouadi, Hakim; Mora‐Camino, Félix

doi:10.1109/eais.2012.6232823

Cited by 5 publications

(4 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…First, it is necessary replace the aerodynamic forces and moments into the state equation. The dynamics of flight-path angle are written as [11,12]:…”

Section: Control Of the Flight Path Anglementioning

confidence: 99%

Flight-Path Tracking Control of an Aircraft Using Backstepping Controller

Chrif

Kada

Tahar

2015

TIJEE

View full text Add to dashboard Cite

For transportation aircraft, the primary control objective for an autopilot system engaged during approach and landing is relative to the flight path tracking on the basis of highly simplified linear models of flight dynamics. The dynamics governing the flight path of an aircraft are in general highly nonlinear and involve complex physics for which no accurate models are available. In this paper a nonlinear model describing the longitudinal equations of motion in strick feedback form is derived. Backstepping is utilized for the construction of a globally stabilizing controller with a number of free parameters. It is implemented a controller with an internal loop controls involving the pitch rate of the aircraft and an external loop which includes angle of attack, path angle and pitch angle. Finally, nonlinear simulation results for a longitudinal model of a transportation aircraft are displayed and discussed.

show abstract

“…First, it is necessary replace the aerodynamic forces and moments into the state equation. The dynamics of flight-path angle are written as [11,12]:…”

Section: Control Of the Flight Path Anglementioning

confidence: 99%

Flight-Path Tracking Control of an Aircraft Using Backstepping Controller

Chrif

Kada

Tahar

2015

TIJEE

View full text Add to dashboard Cite

show abstract

“…The desired vertical trajectory ( ) x z d is supposed to be a smooth function of x (in the considered application x is the distance to touchdown) while considering expressions (17), (18) and (19) d air V is supposed to be a piecewise smooth function of x .…”

Section: Space-based Nli Tracking Controlmentioning

confidence: 99%

“…A new representation of aircraft vertical guidance dynamics is developed according to this spatial variable. Then a nonlinear inverse control law based-on this new proposed spatial representation of guidance dynamics is established to make the aircraft follow accurately a vertical profile and a desired airspeed [17,18]. The desired airspeed is then regulated to meet two main constraints related to the stall speed and the maximum operating speed and to make the aircraft overfly different waypoints according to a planned time-table.…”

Section: Introductionmentioning

confidence: 99%

Aircraft time-2d longitudinal guidance based on spatial inversion of flight dynamics

Bouadi

Choukroun

Mora‐Camino

2012

2012 IEEE/AIAA 31st Digital Avionics Systems Conference (DASC)

Self Cite

View full text Add to dashboard Cite

With the growth of civil aviation traffic capacity, safety and environmental considerations urge today for the development of guidance systems with improved accuracy for spatial and temporal trajectory tracking. This should induce increased capacity by allowing safe operations at minimum separation standards. Also, at take-off and landing, trajectory dispersion should be reduced resulting in controlled noise impacts on airport surrounding communities. Current civil aviation guidance systems operate with real time corrective actions to maintain the aircraft trajectory as close as possible to the planned trajectory. In this paper, we consider the problems of designing new longitudinal guidance control laws for an autopilot so that accurate vertical tracking and overfly time are better insured. Instead of using time as the independent variable to describe the guidance dynamics of the aircraft, we adopt distance to land, which can be considered today to be available online with acceptable accuracy and availability. A new representation of aircraft longitudinal guidance dynamics is developed according to this spatial variable. Then a nonlinear inverse control law based-on this new proposed spatial representation of guidance dynamics is established to make the aircraft follow accurately a vertical profile and a desired airspeed. The desired airspeed is then regulated to make the aircraft overfly different waypoints according to a planned timetable. Then simulations experiments with different wind conditions are performed for a transportation aircraft performing a general descent approach for landing. These simulation results are compared with those obtained from a classical time-based guidance control law.

show abstract

“…A different representation of aircraft vertical guidance dynamics is developed according to this spatial variable where the overfly time becomes a controlled variable. Then a nonlinear inverse control law based-on 4 this new proposed spatial representation of guidance dynamics is established to make the aircraft follow accurately a vertical profile and a desired airspeed [12][13][14]. This leads to regulate on a spaceindexed basis the desired airspeed to meet constraints related to the stall speed and the maximum operating speed while making the aircraft to overfly different waypoints according to a planned time-table.…”

mentioning

confidence: 99%

Space-Indexed Control for Aircraft Vertical Guidance with Time Constraint

Bouadi

Mora‐Camino

Choukroun

2014

Journal of Guidance, Control, and Dynamics

Self Cite

View full text Add to dashboard Cite

International audienceWith the growth of civil aviation traffic capacity, safety and environmental considerations urge today for the development of guidance systems with improved accuracy for spatial and temporal trajectory tracking. This should induce increased practical capacity by allowing timely operations at minimum separation standards while at takeoff and landing and trajectory dispersion should be reduced, resulting in better controlled noise impacts on airport surrounding communities. Current civil aviation guidance systems operate with real-time corrective actions to maintain the aircraft trajectory as close as possible to a space-indexed planned trajectory while the flight management system copes indirectly with overfly time constraints. In this paper, the design of new longitudinal guidance laws is considered so that accurate vertical tracking is achieved while overfly time constraints are satisfied. Here, distance to land is adopted as the independent variable for the aircraft flight dynamics since it is today available onboard aircraft with acceptable accuracy. A representation of aircraft longitudinal guidance dynamics is developed according to this spatial variable, and a space-indexed nonlinear inverse control law is established to make the aircraft follow accurately a vertical profile and a desired airspeed. The desired airspeed is defined by an outer space-indexed control loop to make the aircraft overfly different waypoints according to a planned timetable. Numerical simulation experiments with different wind conditions for a transportation aircraft performing a descent approach for landing under this new guidance law are described. The resulting guidance performances are compared with those obtained from a classical time-based guidance control law

show abstract

Space-Based Nonlinear Dynamic Inversion Control for Aircraft Continuous Descent Approach

Cited by 5 publications

References 11 publications

Flight-Path Tracking Control of an Aircraft Using Backstepping Controller

Flight-Path Tracking Control of an Aircraft Using Backstepping Controller

Aircraft time-2d longitudinal guidance based on spatial inversion of flight dynamics

Space-Indexed Control for Aircraft Vertical Guidance with Time Constraint

Contact Info

Product

Resources

About