Hybrid Engine and General Information
ISTIKBAL was developed using hybrid engine technology, utilizing paraffin as solid fuel and N2O as the oxidizer.
Mechanical Features
The rocket body and nose cone are made of carbon fiber. The first 50 mm of the nose cone is reinforced with aluminum. The fins are also made of aluminum.
The rocket weighs approximately 32 kg, has a total length of 3.1 meters, and a diameter of 150 mm. The nose cone has a Haack Von Karman shape and is 600 mm in length.
The rocket body consists of 3 parts with respective lengths of 750 mm, 1130 mm, and 700 mm. The body has a wall thickness of 2.5 mm.
The rocket features a CO₂-based separation mechanism.
The rocket uses a single parachute system, designed to deploy at apogee.
Electronics and Avionics
The rocket includes a dual-directional valve system controllable via Mosfets and Relays.
It features an avionics system capable of heating 3 igniter wires simultaneously and triggering separation through an electronic igniter.
The power line is supplied by a 12V 3S Lithium-Polymer battery, which is stepped down to 5V using a Buck Converter and to 3.3V using an LDO.
