Test and development of efficient blades for use in VTOL aircraft

Abstract

The Phoenix LR Type 2 mod 1system shows the necessity for further testing using a variety of set ups wth respect to blade and gears. Further, during the course of writing this report, numerous design changes to the blade to lighten the structure was developed which will help with the required performance of the rotor. By limiting the weight of the components, the blade would have to lift less weight and thus draw less power from the power supply to remain airborne. However, making a craft too light and sacrificing strength is also not advisable as well as there is a possibility of blade failure before the full lift capacity of the blade has been tested. These interplay of factors contribute to making the design of a high efficient long endurance aircraft an especially difficult task. This of course has not factored in the added complexity of balancing energy supply weight and airframe integrity. This balancing act is important as carrying more energy in the form of batteries increases the weight of the aircraft while requiring the blades to generate more lift. This added required lift again requires more energy to overcome the generated corresponding drag. Therefore, finding the most optimal layout and settings is crucial in this particular problem.