An unmanned aerial vehicle (UAV) has found its applications in dangerous combat applications. Their lightweight feature has attracted them in civilian, agricultural, and medical assistance as well. The necessity to increase these UAVs' thrust, payload capacity, and endurance is rising tremendously day by day. Therefore, there is a requirement to develop better propulsion systems. Dual Powered Penta-copter needs to be developed, which consists of both engine and motor. The engine is placed in the centre, and four motors take up the corners. The thrust, payload and endurance of the aircraft are higher when compared to a conventional quadcopter. The rotation of the propeller creates an equal and opposite torque on the aircraft. The reaction torque of the engine in DPP remains unbalanced. The unbalanced reaction torque will rotate the aircraft in the opposite direction. Hence suitable torque balance mechanism has to be suggested. The engine's torque should equal the torque of four motors while satisfying the required total thrust at all conditions. This study aims to develop a suitable mechanism for the same. The thrust requirement for a quadcopter varies in a mission. Take-off requires higher thrust when compared to hover and forward flight. If temporary thrust is provided during take-off, then it is possible to downsize the engine. Nitromethane is a fuel additive that can be used to enhance the thrust temporarily. Apart from enhancing thrust, nitromethane blend addition creates thermal management issues because of its higher combustion temperature. Heat transfer analysis will be carried out to maintain lower engine material temperature when nitromethane will be used. The fuel additive method into DPP will satisfy the mission criteria.