| A Helicopter is a mechanical flying device that uses rotating wings to achieve lift. Rotary wing is key components of helicopter and major factor of the performance of helicopter. As key technology, the rotary wing technology is developing by the nations of the world.Aerodynamic characteristics of helicopter rotor are the deciding factor of performance and quality of helicopter. The rotor is also the main source of vibration and noise. Accidents which caused by rotary wing failures are major part of helicopter accidents. For reasons above, it is necessary to build an effective experimental platform to guarantee the quality of rotors. Dynamic balancing experimental platform of helicopter is mainly used in the research of aerodynamics of rotary wings. By testing, the platform can also guarantee the dynamic balance of rotor.The theme of this paper is structure design of dynamic balancing experiment platform of helicopter under the influence of loads, temperature and so on and the associated computer-aided analysis. The analysis is mainly about deformation of structure, vibration and response characteristics of platform, relations between load and deformation under the influence of temperature. It is able to provide information for further improving and optimizing.
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