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A e r o s p a c e E n g i n e e r i n g , C h u l a l o n g k o r n U n i v e r s i t y A I A A S t u d e n t B r a n c h 10 20 30 10 20 30 30 20 10 30 20 10 AIAA STUDENT BRANCH AEROSPACE ENGINEERING INTERNATIONAL SCHOOL OF ENGINEERING F L I G H T S I M U L A T I O N R E S E A R C H L A B O R A T O R Y C H U L A L O N G K O R N U N I V E R S I T Y References David Allerton, (2009). Principles of flight simulation (1st edition). Available: No.:629.13252078 AA434P at Center of Academic Resources, Chulalongkorn Uni- versity Use Arial 16pt. bold for title, and Arial 8pt. regular for references. Bandu N. Pamadi, (1998) Performance, Stability, Dynamics, and Control of Air- planes E. Bruce Jackson, (August 7-9, 1995). Results of a Flight Simulation Software Methods Survey. Presented at AIAA Flight Simulation Technologies Conference. [Electronic format]. Available at NASA Technical reports server (NTRS) Document ID: 19970012788 E. Bruce Jackson and Bruce L. Hildreth, Status of the AIAA modeling and simula- tion format standard. [Electronic format] Available at freepatentsonline.com key- word: flight simulation Jon S. Berndt and the JSBSim Development Team (2010) JSBSim An open source, platform-independent, flight dynamics model in C++ [Electronic format] Availble at http://jsbsim.sf.net Michael Basler, Martin Spott, Stuart Buchanan, Jon Berndt, Bernhard Buckel, Cam- eron Moore, Curt Olson, Dave Perry, Michael Selig, Darrell Walisser, and others, (2011) The FlightGear Manual [Electronic format]. Available at http://flightgear.org David R. Miller [email protected] ,(Update edition 4 Mar, 2006) Multiple Monitors in FlightGear: Quick and Dirty [Electronic format] Available at http://www.inkdrop. net/dave/multimon.pdf Tarek Abdunabi, (August 2006) Modelling and Autonomous Flight Simulation of a Small Unmanned Aerial Vehicle [Electronic format] Available at http://jsbsim.sf.net Raksok Khankhampoch 503 13960 21 [email protected] 085 393 5599 Sorasit Thongjeen 503 14359 21 [email protected] 080 595 7849 Advisor: Asst. Prof. Niphon Wansophark Senior Project, Academic Year 2010 Station 1 : Aircraſt Modelling Station 2 : Flight Dyanamic Model Station 3 : Visualization Figure 1: Basic concept and station layout of the flight simualtion system. FLIGHT SIMULATION International School of Engineering(ISE), Faculty of Engineer, Chulalongkorn University. Abstract The flight simulation system in this project was built on basic idea of porting a huge, complexes flight simulation system that need a large support facility to the simplest level that can be handle by consumer level hardware. The system divides into 3 main parts, modeling, flight dynamic (which is heart of the system), and the visual, each setup in separated station. The Digital DATCOM in the first sta- tion (modeling) will calculate the aerodynamic data from the given design geometry, then use those result from Digital DATCOM to assemble the aircraft model configu- ration file by hand. This model now can be moved to the second station (flight dynamic) where it will be subject to the flight dynamic model, and produce the result in from of 6-DOF force and moment. Those force and moment later will be plot into the visual system and produce visual clue for pilot in the third station. Parallel Calculation FlightGear is the scalable systems, which means each of its instances can be configure to do certain job for ex- ample, one FlightGear instance can be configure to take responsible in Flight dynamic model calculation, while another instance is responsible for displaying the envi- ronment. The key concept of configure multi-instance is that use loopback IP-address which will allow computer to ping back to itself to simulate the network transfer data inside one computer. and the network IP-address for seconadry computer. So, for the main instance that will receive input and calculate flight dynamic of aircraft, these two param- eter have to be add before run the instance, with this little modification when running the program. --native-fdm=socket,out,60,127.0.0.1,5500,udp --native-ctrls=socket,out,60,127.0.0.1,5501,udp if we change the IP-address in this command then the multi-computer parallel calculation can be achieved. Objective The objectives of this engineering flight simulation are the following - Be able to build the flight simulation system. - Be able to validate the result of the simulation. - Be able to use the valid system to evaluate the particu- lar system of the desire aircraft. Figure 2(top), 3(middle), and 4(buttom): show the case using to test our result from flight simulation system base on NASA test model of jumbo 747 classic data. the top figure show the configuration of the system, the mid- dle is the result from mathematical modle derived by NASA and the buttom figure is our result produce form simulation. we can see the similarities in the result. along with 2 other case we conclude that the result from this flight simulation system is acceptable. Simulation Result Validation From our platform of flight simulation will be used in any experiment that need to use the simulation of real envi- ronment with the design aircraft so the simulation need to be ensure that it will provide the reasonable and precise to the real environment that aircraft expecting to handle. The method used to test this simulation was to validate the model of the aircraft that run on flight simulation en- vironment program (FlightGear) by compare the data of some flight testing in each condition with the company (Boeing aircraft industry) who construct and testing that aircraft. Validation consists of two forms of model testing, although strictly both are interdependent. Performance tests are, for the most part, based on steady-state measurements, for example, maximum level speed, engine-out climb rate or time to reach V1 from brakes release or sideslip an- gles for rudder input. The other form of tests involve the system dynamics to ensure that the response of the sys- tem to inputs is correct, for example, the pitching moment change caused by a change of engine thrust, response in yaw and roll resulting from an engine failure or pitch rate response with a flight control law. Conclusion and Future work. Flight simulation system is the system that solve the equa- tion of motion (6 degree of freedoms) when the given air- craft model are subject to any flight conditions which is called flight dynamics model, with the visual generation system the result of simulation can be convert and pro- ject into real-time visualization, which helps understand the result from the equation of motion which are the co- efficients of lift, drag, and side forces and roll, pitch, and yaw moments The combination of FlightGear Flight Simulator and JSB- Sim Flight Dynamic model, which are open source pro- jects written in the C++ programming language and used in this project, provided a solid base for building the scal- able simulation environment. This project was intent to build the basic simulation envi- ronment that have potential of holding new feature with- out modifies the core system, Although many challeng- es were faced at the beginning of the project due to the need to investigate different approaches, and the lack of clear documentation for FlightGear, the aims of the pro- ject were met, and the project objectives specified in sec- tion 4 were all achieved. As mention earlier this project was opens the door to the new area of knowledge and new area of learning for aerospace engineering students that wish to continue perform a future work in this project, it is hold unbound potential of developing this system as long as there are basic idea layout for them. Student can further enhance the core system functionality, increase stability of system by decreasing FlightGear resource usage, develop inter- action panel, integrate the control system in to simulation process, implement fully functional avionics system, and even develop the motion system. As for the faculty, the facility from this project give many benefits, it can be used as tool aid the teaching in aircraft design class, avionics class, aircraft stability and control class, and aerospace engineering laboratory class. or if it has been further develop to the certain level (if it could obtain the FAA certificate it would be great). When reach that level this flight simulation facilities can be open as the center and charge for service. 0 20 40 60 80 100 120 140 160 180 200 40 45 50 55 60 65 70 75 80 85 90 Airspeed (kt) Time(sec) counting from when height equal to 0 to 45 ft Airspeed(kt) Airspeed(kt)
