Enhanced Self-Spacing Algorithm for Three-Degree Decelerating Approaches

Prins, Johan De; Schippers, Kristof; Mulder, Max; Veld, Alexander in 't; Clarke, John‐Paul

doi:10.2514/6.2005-6140

Cited by 4 publications

(2 citation statements)

References 6 publications

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“…The resulting acceleration along the flight path x .. is then integrated in time to yield the predicted speed and distance profiles. A more elaborate treatment of this method can be found in De Prins et al (2007).…”

Section: Own Trajectory Predictionmentioning

confidence: 99%

Pilot Support Interface for Three-Degree Decelerating Approach Procedures

Veld

Mulder

Clarke

2009

The International Journal of Aviation Psychology

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Previous research on aircraft noise abatement has resulted in some promising flight procedures to mitigate noise impact, such as the three-degree decelerating approach (TDDA). A problem with decelerating approaches, however, is that they typically lead to increased spacing, which in turn results in a significant reduction of runway landing capacity. A possible solution to this problem might be to delegate the task of separating the aircraft during the approach to the pilot. To aid the pilot, an algorithm has been developed that predicts the trajectory of the preceding aircraft and optimizes the flap schedule based on this prediction. Offline simulations indicate that using this system runway throughput numbers of up to 98% of the capacity of a conventional instrument landing system (ILS) approach can be achieved (Ren & Clarke, 2003). To assess practical implementation issues and to investigate pilot appreciation, a piloted experiment was conducted, for which a pilot support interface has been developed that presents the future separation information in an intuitive fashion. The experiment showed that it is indeed possible for pilots to perform the spacing task while flying a TDDA. The pilot support interface significantly reduces pilot workload when compared to a baseline display. Also the effects of off-nominal lead pilot behavior on pilot performance are reduced by the use of online flap schedule optimization and separation prediction.

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Section: Own Trajectory Predictionmentioning

confidence: 99%

Pilot Support Interface for Three-Degree Decelerating Approach Procedures

Veld

Mulder

Clarke

2009

The International Journal of Aviation Psychology

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“…When the aircraft performs a time constrained descent in idle thrust, the descent is conceived assuming a hypothetical 4D trajectory, where the Air Traffic Controller imposes the aircraft to fly through a specific waypoint at a specific time. In case of a Closed Path trajectory with constant Flight Path Angle, for example, whether it is a Constant-Descent Final Approach (CDFA), a Three-Degree Decelerating Approach (TDDA) 22,23 or an Advanced Continuous Descent Approach (ACDA) 24 , the FMS function can be seen as a tool that computes a reference airspeed, for an assigned flight path angle, to select the appropriate autopilots and feed them with the reference signals to match. The calculated trajectory is thus tailored to the specific airplane and requires advanced flight management on board, as well as strong interaction with the ground air traffic management, which consider local traffic, flight scheduling, weather, and capabilities of every the single aircraft.…”

Section: A Constrained Idle Descent In Cdomentioning

confidence: 99%

Analysis of the Impact of Performance Model Accuracy on 4D Trajectory Optimization

Battipede

Sirigu

Cassaro

et al. 2015

AIAA Modeling and Simulation Technologies Conference

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4D trajectory optimization can be conceived as a non-linear optimization problem, where the mathematical formulations adopted to generate and evaluate trajectories are purposely selected to meet the specific operational requirements, which are recognized as primary for each mission phase. Among the mathematical tools, the choice of the optimization technique and the objective function is always thoroughly addressed in literature. Among the available aircraft mathematical models, the more attractive solutions for trajectory optimization are the so called performance models, due to their great accuracy in describing the real aircraft behavior conjugated with the possibility of being integrated in the mathematical tool in a very straightforward way. This paper aims to investigate how a trajectory optimization problem is affected by the accuracy of the employed model in terms of resulting velocities, accelerations and angles demanded. NomenclatureC = path constraint D = differentiation matrix E = East direction coordinate f = state vector derivative function FF = fuel flow g = gravitational acceleration h = altitude J = cost function L = cost function Lagrange term m = aircraft mass N = North direction coordinate N c = number of control variables N p = interpolating polynomial order N s = number of state variables P = waypoint s = actual aircraft position SEP = specific excess power T = thrust t = time u(t) = control function V TAS = true air speed w = Clenshaw-Curtis weights x(t) = state variables γ = path angle ε = waypoint error η = boundary condition * Associate Professor, Mechanical Aeronautical and Space Dept., manuela.battipede@polito.it, AIAA Member. 2 λ = longitude μ = thrust specific fuel consumption Π = thrust lever ρ = air density τ = Chebyshev-Gauss-Lobatto point Φ = cost function Mayer term ϕ = bank angle φ = latitude χ = Lagrange interpolating polynomials ψ = heading angle Subscripts 0 = initial time f = final time I = i-th waypoint l = lower bound u = upper bound

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Investigation of a Three-Degree Decelerating Approach of a Twin-Engined Jet Aircraft under Actual Flight Conditions

Mulder

2005

AIAA Guidance, Navigation, and Control Conference and Exhibit

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Enhanced Self-Spacing Algorithm for Three-Degree Decelerating Approaches

Cited by 4 publications

References 6 publications

Pilot Support Interface for Three-Degree Decelerating Approach Procedures

Pilot Support Interface for Three-Degree Decelerating Approach Procedures

Analysis of the Impact of Performance Model Accuracy on 4D Trajectory Optimization

Investigation of a Three-Degree Decelerating Approach of a Twin-Engined Jet Aircraft under Actual Flight Conditions

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