Papers by Keyword: Flight Simulator

Abstract: In this paper, the geometrical model of a guiding device mechanism of a parallel topology robot proposed as a flight simulator is presented. For the operation simulation, the input parameters are the relative displacements of driving kinematical joints links versus time. The displacements of 2 characteristic points on the mobile platform are determined, as well as their velocity and acceleration variations. Also, the variations of kinematic and potential energy of human operator geometrical model and the variation of power consumption for different operating conditions are accomplished. For geometrical modeling and dynamic simulation, SolidWorks software is used.

Abstract: Aiming at the problems existing in maintenance of flight simulator, considering characteristics of expert system, the architecture and fault diagnosis methods of flight simulator, the structure and key realization technology for flight simulator fault diagnosis expert system are studied; the flight simulator fault diagnosis expert system design proposal is completed. Research on transforming from fault tree pattern to rule and diagnosis knowledge representing are emphasized, expert system knowledge base is constructed by means of frame plus production knowledge representing method, then certainty and rule based backward chaining inference engine with depth-first and heuristic search mechanism is designed, the system diagnosis flow and inferring flow are also developed in this paper. Finally the expert system is tested by a fault solving demonstration.

Abstract: In order to improve the dynamic performance of a piloted flight simulator hexapod, a study was carried out to quantify the effects of payload mass and inertia properties on hexapod dynamic performance. Based on the Lagrange-Euler formulation, a dynamics model of hexapod parallel mechanism including the payload mass characteristics was built, and then analyzed with the real hexapod through experiments. According to a large amount of experiment datum, the influence of payload mass and inertia properties on a piloted flight simulator hexapod dynamic performance was obtained, and these results are significant for the high speed and high acceleration control of the hexapod mechanism.

Abstract: A 3($P$) parallel manipulator with three degrees of mobility may be used in different purposes, such as a spatial flight simulator. The same equations but with different unknowns characterize its direct and inverse positional model. By adopting the Euler angles for the mobile platform the inverse positional model is simplified. There are determined the parameters of the linear actuators, which are verified for different situations by graphical simulation in a suitable environment.

Abstract: In the field of professional pilot training, flight simulator is becoming increasingly important, which draws more and more attention nowadays. For effectively guiding and assessing the training quality of pilots while being trained, the system needed to record the video of the flight data from monitors without bringing any changes to the flight simulator. The system extracted the frames from the video and then the images would be processed through binarization. So we could easily recognize the flight data from the binarization images by using the pattern recognition technology. Thus the flight track could be reconstructed in three dimension based on the OpenGL API, which will be very beneficial to the training. Altogether, the system can take advantage of the resources to guide and assess the training process of pilots more efficiently as well as developing the pilot training industry.

Abstract: Through simulating the feelings of vision, hearing, motion and force during flight, the flight simulator can build a realistic flight environment on the ground. Therefore, Flight simulators have an important role in pilot training field. Audio simulation system is a key component of the flight simulator, it has direct impact on the realism and immersion of flight simulation. In this paper, we introduced the development procedure of audio simulation system shortly. Software implementation and its key development technology were mainly focused for expressing the necessity of extracting sound sources from original cockpit recordings. Based on the development method and practical recording conditions, we dicussed sound short-time Fourier analysis and synthesis technology, and sound linear prediction analysis and synthesis technology in detail. The objective of using these technologies was to extract sound sources from original recordings and this was also the preparation step of sound simulation.

Abstract: During last few years avionics system research platform was invented at the Military University of Technology. This modular simulator allows user to design and verify avionics system software using hardware-in-the-loop technique. Mathematical model of an airplane under tests is implemented on a high-performance computer which response to all control signals and environmental disturbances. Environment is simulated on a separate computer which can also visualize orientation and movement of the airplane. Plane structure and aerodynamic features as well as control data can be modified accordingly to user needs. The third PC is used as an interface unit between research platform and main computational unit of the avionics system. This device can send and receive information in real-time using various data protocols and interfaces depending on sensors and actuators that are planned to be used in real system. Those three computers work in a local area network and exchange data using Gigabit Ethernet standard. Possibility to simulate behavior of an UAV controlled by the developed avionics system implemented on an embedded computer working in hardware-in-the-loop mode on the platform, allows software developer to debug any part of the application in various environment conditions very close to reality. Research platform gives also the possibility to modify algorithm and adjust its parameters in real-time to verify suitability of the implemented avionics system software for the particular UAV. The avionics system software developed using this simulation method minimize expensive in-flight tests and assure failsafe performance after first successful flight

Abstract: A hydraulic Control Loading System (CLS) based on velocity-loop was developed and installed on our flight simulator earlier days, but the CLS cannot keep stable in some conditions. This problem is discussed in this paper. The mathematical model of velocity-loop-based CLS is firstly developed with the method of transfer function block diagram. Then, system’s stability conditions are put forward using Roth criterion based on the system model developed. At last, the experiments proves the stability

Abstract: Flight simulation is a simulation of flight and various aspects of the flight environment. Flight simulation is used for a variety of reasons, including aircraft development and flight training. The engineering flight simulator is used for a certain commercial transport aircraft development. The aircraft adopts fly-by-wire flight control technology. The engineering flight simulator was mainly used as a platform to test flying quality of the aircraft. The simulator has actual aircraft cockpit with wide-field visual system mounted on large six degree of freedom(DOF) motion platform that feature comprehensive flight and systems models. In order to demonstrate the flying quality of the aircraft, Flying quality verification experiments were carried out on the simulator. This test provided a means by which one may evaluate flight characteristics for fly-by-wire flight control commercial transport aircraft. Experiment results were evaluated .

Abstract: In the mechanical design process for continuous overload high dynamic flight simulator, a large centrifugal force will be generated, if the arm is very heavy, the motor driving force and energy consumption will be high, so the design objective is minimization of the volume meeting the strength of selected material, this paper established the admissible design domain according to the initial model with the UG. The design variables are the volumetric densities of material in the admissible design domain for the structure. it's very small compared with centrifugal force for gravity, so the influence of gravity is negligible, with the Saint-Venant's principle to simplify constraints. Importing the model into hyperworks software, meshing with hypermesh module, Designing with topology optimization of optistruct module, got the best structure of a flight simulator's arm, and finally designed the actual structure of the arm based on the best structure. Conclusion: topology optimization of the arm flight simulator with hyperworks can reduce design cycle, and reduce weight, resulting in better dynamics.