Galaxy Roket'le
Geleceğe Roketle!
Since 2019 we have built sounding rockets, microsatellites and the original subsystems that make them possible. Our rockets have flown at the ROKETSAN Hisar Test Range, and every new platform learns from the flight data of the one before. Today we are developing our 100 N liquid rocket engine and our liquid-engine sounding rocket.
We design and analyse our own liquid-propellant rocket engines and verify them on our test setup on campus. Our 100 N class engine is being developed for the TEKNOFEST 2025 B3 category, and our 1200 N class engine for our sounding rocket targeting an apogee of 4,452 metres.
From 1,500 metres on our first flight to the 18,000 feet we are targeting for TEKNOFEST 2025: the altitudes we reached and the ones we aim for.
Altitude data for the Göktürk rocket is not in our records. 1,500 m ≈ 4,921 ft.
Real dimensions taken from our team's CAD model. Drag to rotate, switch the view or take the rocket apart.
Drawn from our team's CAD file at its real dimensions. Tap a part or take the rocket apart.
The first part to meet the air. Its pointed profile reduces drag; it slides into the body on a shoulder, which shows when you explode the rocket.
The rocket's main structure. The section view shows its thin wall and how the nose shoulder sits inside it.
Keep the rocket pointing straight in flight. Three fins sit 120° apart around the body; explode the rocket to see the tabs that go into the body.
Every rocket of ours, from our first flight to the liquid-engine sounding rocket we are developing today, with its key technical data.
02A sounding rocket that will fly on our own liquid-propellant rocket engine, targeting an apogee of 4,452 metres. 320 cm long, 15 cm in diameter and weighing 29 kg, it will carry a 4 kg scientific payload to the target altitude with an original 1200 N class liquid-propellant engine delivering 11,990 N·s of total impulse.
03Our 12,000-ft mid-altitude sounding rocket is being developed for the TEKNOFEST 2025 Rocket Competition, with a composite airframe, an in-house separation mechanism and a 5 kg payload capacity.
04Our 14,000-ft rocket carried the 4 kg Polaris microsatellite and featured advanced avionics including a live video downlink. Successfully launched on 18 August 2023 at the ROKETSAN Hisar Test Range.
05Developed for the TEKNOFEST 2022 mid-altitude category, capable of carrying a 5 kg payload to 10,000 ft. Its flight computer and recovery system were designed entirely in-house.
06Built by our second in-house team, launched successfully with a complete recovery. It made us one of the few teams to fly two rockets in a single season.
07Launched on 3 September 2021, carrying a 5 kg payload to 1,500 m with GSM-equipped avionics and strong aerodynamic performance.
08Our very first rocket reached 1,500 meters carrying a 4 kg payload, the platform where our story began.
We design our own liquid-propellant rocket engines, their test systems and a sounding rocket that will fly on one of them. Below is a technical summary of two of these projects.
A sounding rocket that will fly on our own liquid-propellant rocket engine, targeting an apogee of 4,452 metres. 320 cm long, 15 cm in diameter and weighing 29 kg, it will carry a 4 kg scientific payload to the target altitude with an original 1200 N class liquid-propellant engine delivering 11,990 N·s of total impulse.
The rocket will be recovered on its own two parachutes and the payload on a separate parachute of its own, in line with the CONOPS. Our work focuses on the thermodynamic optimisation of the liquid-propellant (N₂O and Jet-A1) engine, thrust chamber sizing, characterisation of the mixture ratio (O/F) and integrating all of these into the aerodynamic airframe within a mass budget that keeps the flight stable.
Developed for the TEKNOFEST 2025 Rocket Competition B3 – Original Liquid-Propellant Rocket Engine Development category, the engine is designed to produce 100 N of thrust with gaseous oxygen and Jet-A1, burn stably for 10 seconds at a chamber pressure of 10 bar and reach a vacuum specific impulse of at least 260 seconds.
The project is a multidisciplinary engineering effort covering propellant selection, combustion chamber and nozzle design, performance prediction with thermochemical calculations, dynamic simulations in a mathematical modelling environment, structural material analyses and the safe operation of the system. The goal is to design and analyse the engine and verify it through testing.
| Subsystem | Parameter | Value |
|---|---|---|
| General engine data | Engine type | Liquid propellant |
| Fuel · Oxidiser | Jet-A1 · Gaseous oxygen | |
| Total impulse | 1,000 N·s | |
| Peak thrust | 100 N | |
| Burn time | 10 s | |
| General performance | Thrust (sea level) | 100 N |
| Specific impulse (Isp) | 260 s | |
| Chamber pressure | 10 bar | |
| Mixture ratio (O/F) | 3.45 | |
| Combustion chamber | Material | CuCrZr |
| Injector system | Injector type | Swirl |
| Material | CuCrZr | |
| Nozzle | Material | CuCrZr |
Summary flight data for the rockets we have launched.
| Rocket | Year | Altitude | Payload | Outcome |
|---|---|---|---|---|
| Ceren Özdemir | 2020 | 1,500 m | 4 kg | First flight |
| Şehit Şenay Aybüke Yalçın | 2021 | 1,500 m | 5 kg | Successful |
| SES | 2022 | 10,000 ft | 5 kg | TEKNOFEST 2022 |
| Göktürk | 2022 | — | — | Successful launch and recovery |
| Şehit Eren Bülbül | 2023 | 14,000 ft | Polaris · 4 kg | Successful · live video |
The original payloads, control systems and avionics architectures that make our rockets possible.
Our 4 kg Micro Atmospheric Measurement and Observation Satellite carried a sensor suite for temperature, pressure, humidity and particulate readings, flown aboard the Eren rocket and streaming live data to our ground station.
Our in-house control system corrects the vehicle's attitude in flight through thrust vectoring. Actuator mechanics, control algorithm and embedded software are all developed by the team.
Our solid motor systems and liquid-fuel rocket engine project cover combustion chamber, injector design, cooling and feed line development.
Our modular avionics architecture combines flight computer, telemetry, power distribution and recovery triggering in one capsule, working alongside our 35 km+ communication module.
A payload that records strain and vibration data on the airframe during flight, used to validate structural design and optimise the mass of future vehicles.
We fly our rockets at the launch site near Lake Tuz in Aksaray. We modelled the area in 3D from satellite imagery and elevation data, from the integration tent to the launch rail and on to the ground station. Drag to rotate, or pick a point to look closer.
713 m2.9 km
Drag to rotate · Ctrl + wheel to zoomDrag to rotate · Pinch to zoom
The concrete platform where teams assemble their rockets one last time in their tents, pass pre-launch checks and wait for their launch slot.
Open in Google MapsWhere the rocket is loaded onto the rail and ignited. It lies 3.6 km from the integration area as the crow flies.
Open in Google MapsWhere the flight is tracked and our ground station receives live telemetry, 713 m from the rail.
Open in Google MapsImagery: contains modified Copernicus Sentinel-2 data (June–September 2026, composite of 8 passes) · Elevation: Copernicus DEM GLO-30
41 frames from our launch days: the integration platform, the launch rails and the tracking station.
