Development of A Flight Dynamics Model For A UH-1H Helicopter Simulator

2007-09-10

Suggestions

Development of a sabot design tool for aeroballistic range testing
Kafdağlı, Karaca Efe; Kayran, Altan; Department of Aerospace Engineering (2006)
The aim of this thesis is to investigate the general design and analysis principles of sabots and to develop a sabot design tool. Structures which support and align the models in gun bore, and separate without disturbing the flight path of models are called sabots. In the scope of this study, structurally critical regions and loads acting on sabots due to acceleration in the gun are determined. To calculate the loads acting and to size the sabots, approximate relations are derived by the help of strength of...
Development of a 3D Grain Burnback Simulation Tool for Solid Rocket Motors
Ata, Yusuf; Kurtuluş, Dilek Funda; Arkun, Ö. Uğur (2018-01-01)
Development of a micro-fabrication process simulator for micro-electro-mechanical systems(mems)
Yıldırım, Alper; Dölen, Melik; Department of Mechanical Engineering (2005)
The aim of this study is to devise a computer simulation tool, which will speed-up the design of Micro-Electro-Mechanical Systems by providing the results of the micro-fabrication processes in advance. Anisotropic etching along with isotropic etching of silicon wafers are to be simulated in this environment. Similarly, additive processes like doping and material deposition could be simulated by means of a Cellular Automata based algorithm along with the use of OpenGL library functions. Equipped with an inte...
Development of a high-fideliity transient aerothermal model for a helicopter turboshaft engine for inlet distortion and engine deterioration simulations
Novikov, Yaroslav; Uzol, Oğuz; Kutay, Ali Türker; Department of Aerospace Engineering (2012)
Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass i...
Development of a rotorcraft time domain system identification software
Aslandoğan, Ongun Hazar; Yavrucuk, İlkay; Gürsoy, Gönenç; Department of Aerospace Engineering (2023-1-03)
A system identification software to identify stability and control derivatives for rotorcraft in hover and forward flight conditions is developed in this thesis. To demonstrate the identification procedure, a high fidelity nonlinear model of the H135 helicopter is used. Frequency sweep, 3211 and 2311 type inputs are given to the nonlinear helicopter model to generate test data. The procedure is carried out by identifying a state space model structure in time domain using output error method with Levenberg-M...
Citation Formats
İ. Yavrucuk, “Development of A Flight Dynamics Model For A UH-1H Helicopter Simulator,” 2007, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/81620.