![]() All improvement measures are discussed with respect to essential aeromechanics aspects and are reflected by critical evaluations on flight test results. Furthermore the main rotor was tuned for low 4/rev vibrations and reduced 4/rev torque amplitudes in the fixed system. The shaft bending moment limit was enhanced to ensure a slope landing capability of the aircraft up to 12° nose up slopes. A hub geometry change from a 2.5° blade droop angle to a central 2.5° hub precone angle was performed to expand the load factor capability by lowering loads in lead-lag bending and in the control system. beginning of testing in 1991, load optimization was necessary to achieve a longer service life of critical parts and to expand the flight envelope. Although the aircraft showed the expected flight properties from the very. Then follows a brief presentation of theoretical tools, as they were used for predictions and simulations during the design phase. First a short description of the helicopter and the main rotor is given. This paper addresses the whole process of load determination during the development of the TIGER main rotor system. To get high performances, the exciting angles are optimized in two different operating modes respectively, and the optimized performances in the motoring mode are given as well. In the end, the performances of the designed SRM are basically verified by simulation. In thermal design stage, a liquid-cooling system is designed based on the thermal analysis of the machine. In electromagnetic design stage, the electromagnetic structure and dimensions of the machine and the number of phase winding turns per pole are obtained the topology and main technical details of the converter are briefly introduced as well. The entire design process is mainly divided into two stages: electromagnetic design and thermal design. Based on these requirements, a high speed switched reluctance machine (SRM) is designed to operate as a starter/generator. ![]() Some important performance requirements for CS/G system are obtained. The combined starter/generator (CS/G) system is introduced as a key technology to enable M/AEA. The basic concepts and advantages of more/all electric aircraft (M/AEA) are briefly addressed.
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