Analytical and a numerical ground resonance analysis of a conventionally articulated main rotor helicopter

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dc.contributor.advisor Van Niekerk, J. L.
dc.contributor.author Eckert, Bernd en_ZA
dc.contributor.other University of Stellenbosch. Faculty of Engineering. Dept. of Mechanical and Mechatronic Engineering.
dc.date.accessioned 2007-11-16T08:54:15Z en_ZA
dc.date.accessioned 2010-06-01T08:51:11Z
dc.date.available 2007-11-16T08:54:15Z en_ZA
dc.date.available 2010-06-01T08:51:11Z
dc.date.issued 2007-03 en_ZA
dc.identifier.uri http://hdl.handle.net/10019.1/2522
dc.description Thesis (MScEng (Mechanical and Mechatronic Engineering))--University of Stellenbosch, 2007.
dc.description.abstract The helicopter is a prime example of a nonlinear multi-body dynamic system that is subjected to numerous forces and motions to which the system must react. When a helicopter, with a conventionally articulated rotor head, is resting on the ground with its rotor spinning, a condition called ground resonance can develop. Ground resonance is a specific self-excited oscillation of the helicopter and is caused by the interaction between the main rotor blades and the fuselage structure. Inertia forces of the blades perform an out-of-phase lagging motion, which reacts with the elastic landing gear of the helicopter. For certain values of the main rotor angular velocity, the frequency of these inertia forces coincides with a natural vibration frequency of the fuselage structure. If this occurs, the inertia forces of the lagging blades produce oscillations of the fuselage, which then further excite the lagging motion of the blades. This interaction is responsible for an instability of conventionally articulated main rotor helicopters, which is called ground resonance. The ground resonance phenomenon is investigated by means of a classical analytical approach in which the ground resonance equations are derived from Euler-Bernoulli beam theory and verified with results in literature. These equations are required to discuss ground resonance stability in further detail and determine the specific regions in which the phenomenon occurs. These results are incorporated in a simplified numerical model using an elastic multiple-body dynamics analysis program called DYMORE to simulate the South African Rooivalk Combat Support Helicopter. DYMORE is a program that offers nonlinear multi-body dynamic analysis code, using the finite element method, which was specifically developed for helicopter modelling. The complexity of helicopter modelling generally requires large amounts of computing power to ensure reasonable processing time. In order to prevent excessive computational time, the numerical model will be simplified in terms of aerodynamic and structural aspects. The scope of the numerical investigation is, therefore, limited to the ground resonance phenomenon without the effect of aerodynamic forces and representing the fuselage as multi-body beam structures of specified stiffness. en_ZA
dc.format.extent 4137428 bytes en_ZA
dc.format.mimetype application/pdf en_ZA
dc.language.iso en en_ZA
dc.publisher Stellenbosch : University of Stellenbosch
dc.subject Dissertations -- Mechanical engineering en
dc.subject Theses -- Mechanical engineering en
dc.subject Resonant vibration en
dc.subject Rotors (Helicopters) en
dc.title Analytical and a numerical ground resonance analysis of a conventionally articulated main rotor helicopter en_ZA
dc.type Thesis en_ZA
dc.rights.holder University of Stellenbosch


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