Hybrid Engine and General Information
The Anadolu rocket was developed in the third year of hybrid engine research. The hybrid engine named TONGA was integrated into the rocket, aiming to participate in the competition with a hybrid-propelled rocket for the first time.
Paraffin was used as solid fuel and N2O as oxidizer in the rocket. With an instantaneous thrust of 1.1 kN/s and a burn time of 10 seconds, a total impulse of 11.075 N.s is achieved. The maximum speed of the rocket is calculated as 0.76 Mach.
Mechanical Features
The rocket body and fins were produced from aluminum, while the nose cone was made of carbon fiber material. The rocket is equipped with a CO2-based separation mechanism and is designed to carry a payload of 10 lb to an altitude of 10,000 feet.
Ripstop fabric was used for the rocket's parachute. The nose cone has a Haack Von Karman profile, with a wall thickness of 1 mm and a diameter of 160 mm. The first 65 mm section was manufactured from aluminum.
The rocket has an inner diameter of 156.4 mm and an outer diameter of 160 mm. It consists of 4 separate bodies, each 700 mm in length.
Electronics and Avionics
The rocket is equipped with an RF communication system operating at 433 MHz frequency and 500 mW output power. This system, compatible with all known serial communication protocols, provides high performance in data transmission.
The avionics unit supports 8 channels and is compatible with 2S or 3S LiPo batteries in the power line. This feature provides long-lasting and reliable power supply.
