New method for aircraft fuel saving using Flight Management System and its validation on the L-1011 aircraft

16th AIAA Aviation Technology, Integration, and Operations Conference

2016

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The aeronautical industry requires important quantities of fossil fuel to sustain flights. Fuel burn releases pollution particles to the atmosphere such as carbon dioxide. The aeronautical industry has set itself the goal of diminishing CO 2 emissions for the forthcoming years. A way of reducing fuel consumption is by improving en-route operations. For long haul flights, cruise is the flight stage that requires the most fuel consumption. Taking advantage of tailwinds reduces the flight time, thus reducing the fuel requirements. In this paper, an algorithm based on the Ant Colony Optimization was developed to optimize the lateral navigation reference trajectory of a commercial aircraft. Following a constant flight level, the algorithm was able to identify favorable wind areas, and to lead the aircraft to take advantage of these winds to optimize the flight cost. The aircraft model was a numerical performance model constructed from experimental flight data, where weather information was obtained by using information from Weather Canada. Results showed important fuel savings for different long haul flights. NomenclatureCDA = Continuous Descent Approach CDG = Paris Charles De Gaulle International airport (France) CI = Cost Index LNAV = Lateral Navigation NRT = Tokyo Narita International Airport (Japan) Pherom i = Pheromone level at a given path. PDB = Performance Database P i = Waypoint Selection Probability PTP = International Airport of Point à Pitre (Guadeloupe) TOC = Top of climb TOD = Top of decent VNAV = Vertical Navigation WA = Wind Azimuth WS = Wind Speed YUL = Montreal Pierre Eliot Trudeau International Airport (Canada) γ = Pheromone evaporation rate

Section: Introductionmentioning

confidence: 99%

Lateral Reference Trajectory Algorithm Using Ant Colony Optimization

Murrieta-Mendoza

Hamy

16th AIAA Aviation Technology, Integration, and Operations Conference

2016

Self Cite

“…The different ways to achieve such a goal are as diversified as the reduction of weight by use of composite materials, the creation of new generation jet engines or the optimization of the flight trajectories computed by the Flight Management System (FMS). This last particular point has the benefit of not requiring a structural modification for existing aircrafts or specific, heavy maintaining operations [1][2][3]23 .…”

Section: Introductionmentioning

confidence: 99%

Presentation of three methods results comparison for Vertical Navigation VNAV trajectory optimization for the Flight Management System FMS

Beulze

Dancila

15th AIAA Aviation Technology, Integration, and Operations Conference

et al. 2015

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One of the principal axes in the quest for improved aircraft operations, oriented towards attaining the future environmental and economic standards such as fuel consumption and air pollutant emission reduction is the development of flight trajectory optimization algorithms for the Flight Management System. This paper provides a comparative presentation of the algorithms developed and results obtained, at LARCASE, with the purpose of determining an optimized vertical flight trajectory for a given flight plan. The approach considered in the construction of the optimized vertical trajectory navigation plan (VNAV) was purely geometric. The optimization objectives were represented by the minimization of the number of vertical (climb, level-flight or descent) profile segments composing the VNAV trajectory, and the employment of climb and descent trajectories whose gradients are equal, or closest to a specified value which accounts for the aircraft's performances and flying conditions.

“…Morphing wing system o reduce the fuel consumption on aircraft, the aerospace industry must take steps forward in aircraft operation but also in aircraft design. One step taken by the Laboratory of Applied Research in Active Controls, Avionics and Aeroservoelasticity (LARCASE) team in green aircraft technologies is optimizing the trajectories of the aircraft during its flight time [1][2][3] . In terms of aircraft design, one aspect of research focuses on the aircraft modeling based on flight test data 4,5 , and on the implementation of these models in the design of new attitude controllers 6 .…”

Section: Introductionmentioning

confidence: 99%

Systemic modeling and design approach for morphing wing aileron controller using Matlab/Simulink

Vincent

AIAA Modeling and Simulation Technologies Conference

2015

This paper offers an introduction to the concept of system modeling to validate the feasibility of a multidisciplinary actuation solution with the constraints of concrete research applications. To explain the modeling procedure, the case of a morphing wing aileron actuation solution is presented. The requirements and limitations for the design are presented, then a detailed solution is elaborated. Finally the modeling of this solution is developed in the Matlab/Simulink environment to validate its practicality. This approach generates a simple but representative model with a relatively high degree of accuracy without requiring detailed information about the internal system parts. The modeling system is a cornerstone of a morphing wing aileron control project with potential industrial applications. NomenclatureA = Attachment point between the reference body and the linear actuator body B = Attachment point between the linear actuator piston rod end and the lever arm C = Attachment point between the lever arm and the reference body ! = X axis of the reference body ! = Y axis of the reference body ! = X axis of the linear actuator ! = X axis of the lever arm ! = X axis of the aileron = Angle between ! and ! = Angle between ! and ! = Angle between ! and ! = Angle between ! and ! ! = Fixed angle D = Length of the linear actuator body x = Length of the linear actuator protruded piston d = Actuator length (Sum of the length D and x) ! = Distance between B and C ! = Distance between A and C