This paper covers a new method of longitudinally controlling an aircraft by changing the horizontal tail arm length, without the conventional control surface called ‘elevator’. The effects of changing horizontal tail arm length from its steady level trimmed condition are determined numerically for the chosen Cessna aircraft. From the numerical calculations, the possibilities of implementing this type of control in the chosen Cessna aircraft are analyzed. At last, some recommendations are suggested for the effective longitudinal control of the Cessna aircraft by changing horizontal tail arm length. Further, it is also suggested that employing both elevator control and tail arm length control together will make an aircraft to meet any kind of longitudinal controllability and stability requirement at any instant. This optimal aircraft configuration can be achieved by proposing a novel configuration and morphing solutions.

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In modern engineering, the rapid growth in the development of unmanned aerial vehicles which deserves the major space in the area of intelligence and surveillance operations. Unlike the conventional aircraft, the number of rotors mounted in an autonomous body that determines the propulsive efficiency as well as the maneuvering capabilities of unmanned aerial vehicles. The main objective of this research reveals that the low cost and an autonomous aerial vehicle with four rotors configuration design to achieve the long endurance flight limit. The developed Quadcopter flying model integrated with Arduino autopilot module which effectively controls the various maneuvering actions during the flight. This paper also reveals the entire hardware structure of the designed Quadcopter and its flight dynamic response characteristics. The remotely operated Quadcopter model was subjected to the flight test and the performance parameters have recorded. The flight test was conducted in an open environment in which stability parameters has been observed during onboard. Pitch angle, the Rotational speed of four rotors and the various attitudes of Quadcopter were changed accordingly to maintain the steady level flight. Findings are plotted with respect to the flight endurance.