SFR0 LAUNCH
SFR0 is a solid-propellant sounding rocket developed between September and December 2024 as a technology demonstrator to support the development of the team’s main project, SFR1, a hybrid-propellant launch vehicle scheduled for flight in 2025.
While SFR0 shares the same structure as SFR1, it uses a COTS (Commercial Off-The-Shelf) solid motor instead of the in-house hybrid propulsion system, enabling in-flight testing of all SFR1 subsystems except propulsion. The rocket features modular aluminum flange connections, a lightweight composite airframe and a dual avionics system: an in-house unit for data acquisition and a COTS unit for pyro ejection control.
With a height of 2.7 meters and a diameter of 150 mm, SFR0 is composed of cylindrical sections connected by aluminum flanges. It reuses parts of the SFR1 structure, including a water-filled tank for mass balancing and apogee reduction. Powered by a Cesaroni Pro98 3G solid motor with two grains, the motor is mounted using a custom clamping system for stability and easy removal. The rocket’s skin is primarily made of carbon fiber, with a fiberglass OBE bay for radio transmission and composite nosecone and fins produced using custom molds.
On May 5th, 2025, we successfully launched SFR0 from Roccaraso, Abruzzo, becoming the first student rocketry team from northeastern Italy to reach this milestone. SFR0 reached an apogee of 1250 m and a maximum speed of Mach 0.44 (approximately 150 m/s).
Ignition was achieved remotely, with a very short transient as expected. The rocket accelerated along the launch rail and lifted off around T+1 s. During powered flight, it gained speed and remained passively stabilized by its rear fins. The motor burned out at approximately T+3.5 s, after which the rocket continued coasting upward, reaching apogee at T+16 s.
At this point, aerodynamic forces decreased and the rocket’s angle increased until it peaked at the apogee. Around T+45 s, at 450 m altitude, the drogue was disconnected from the recovery bay, initiating the deployment of the main parachute. Once fully deployed, the main further reduced the descent speed to approximately 6 m/s. The rocket touched down safely at T+146 s, and recovery operations began.
The goal of the launch was to test the avionics, aerodynamic and structural stability and the recovery system, all of which were successfully validated.
We would like to thank Professor Daniele Pavarin, the University of Padua and the Department of Industrial Engineering for supporting us from the very beginning. We are also grateful to all our sponsors who provided us with materials, components, sensors and access to laboratories, making it possible for us to achieve this milestone.
