INFO DAYS FP7 2nd Call

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1 Rzeszow, Integrated Design Flight Mechanics performance optimization Andrzej MAJKA

2 Integrated design of personal aircrafts fleet (multidisciplinary problem) Problems: Problem formulation in multipurpose and multitask depiction. Regional and personal aircraft fleet optimization characteristics on the stages of personal airplanes requirements (specifications) forming. Optimum division of tasks set between individual aircraft types of example air transport system (determination of optimum specialization fields). Economical, ecological and social evaluation of air transport system. Efficiency criterions analysis of the local air transport in local (European) conditions - effectiveness factors. Optimum structure of personal aircraft fleet. Rational structures of parks of small transport aircrafts for different criteria.

3 Integrated design of personal aircrafts fleet (multidisciplinary problem) Methods and tools: Mathematical model of aircraft fleet (multitask system ) function and task division. Software to created models. Numerical systems for optimization (CAD programs). The realization of calculations and finding the optimum division of tasks set between individual aircraft types of air transport system. Analysis of model tasks solution of system optimization and creation of system structure optimization tool.

4 Mathematical model of aircraft Geometry Weights Aerodynamics Power unit Performance Flight model Transport possibilities

5 Cruise profile (task model)

6 Computer systems for optimization of light transport aircrafts

7 Computer systems for optimization of UAV s

8 Flight Mechanics performance optimization with flight constraints Problems: Flight profile optimisation of transport aircraft (optimum cruise conditions, maximum range conditions, minimum cost flight path, minimum time-to-climb path etc.). Flight manoeuvres optimization. Takeoff and landing manoeuvres optimization. Mission requirements for various ranges and sizes of payload and various types of airplanes. Required performance aircrafts characteristics others

9 Flight Mechanics performance optimization with flight constraints Example results for light jest aircraft Payload Fuel Weight [kg] Lz [km] Payload (fuel)-range diagram Hcruise [m] Wfuel=274 Wfuel=374 Wfuel=474 Wfuel=574 Wfuel=674 Wfuel=741 Wfuel/npax/Lz [kg/pax/km] Lz [km] Range-cruise altitude dependence for constant fuel weights Lz [km] Fuel weight per pax per km

10 Flight Mechanics performance optimization with flight constraints Example results for light jest aircraft 0.40 Wfuel/npax/Lz [kg/pax/km] BPR = 2.8 BPR = 5 BPR = Lz [km] Bypass ratio influence to SFC dependence of seating capacity (payload)

11 Experience of scientific personnel of Department of Aircrafts and Aircraft Engines Participation in R & D projects (e.g. UAV as a demonstrator of modern technological solutions in aerospace applications). Participation in European projects (EPATS). Cooperation with industries (cooperation in designing of aeroplanes: M-15, M-16, M-18, M-19, M-24, M-30 (Mk-1), I-22).

12 Contact: Department of Aircrafts and Aircraft Engines Faculty of Mechanical Engineering and Aeronautics Rzeszow University of Technology Address: ul. Powstancow Warszawy Rzeszow, POLAND phone: mobile: web: andemajk@prz.edu.pl

13 Thank You for your attention

THE MULTI-OBJECTIVE OPTIMIZATION OF THE AIR TRANSPORTATION FLEET STRUCTURE

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