AKKOYUN AEROSPACE / LAUNCH SYSTEM DEVELOPMENT
Dedicated access to orbit for small missions.
Akkoyun Aerospace is developing a vertically integrated small launch system for satellites that require greater control over launch timing, target orbit, and deployment.
CURRENT DEVELOPMENT
Reusable subscale VTVL flight demonstrator
PURPOSE
Validate propulsion, control, avionics, manufacturing, and integrated vehicle capability before scaling toward orbit.
STATUS
NOT OPERATIONAL — TECHNOLOGY DEVELOPMENT PROGRAM
01 — THE MISSION
Some missions need control over the launch itself.
For many spacecraft, rideshare is the right solution. For missions where timing, destination, or deployment conditions are mission-critical, the launch itself becomes part of the mission architecture.
RIDESHARE
PAYLOAD → AVAILABLE MISSION → SHARED SCHEDULE → PREDEFINED ORBIT → DEPLOYMENT
Efficient and cost-effective when mission requirements match an available flight.
DEDICATED MISSION
PAYLOAD → MISSION-DEFINED LAUNCH → TARGET ORBIT → MISSION-SPECIFIC DEPLOYMENT
Launch timing, orbit, and deployment defined by the mission, not by an available manifest.
02 — THE LAUNCH SYSTEM
Built around the mission.
The long-term objective is a small orbital launch vehicle providing dedicated, mission-specific access to orbit for small satellites and small payloads. The vehicle is a long-term development objective, not an operational launch service. Published specifications will follow confirmed engineering milestones.
FIG. 02 — VEHICLE ARCHITECTURE
DEDICATED SMALL PAYLOAD MISSIONS
MISSION-SPECIFIC ORBITS
CONTROL OVER LAUNCH TIMING
VERTICALLY INTEGRATED DEVELOPMENT
COMPACT GROUND AND LOGISTICS FOOTPRINT
EUROPEAN LAUNCH CAPABILITY
03 — HOW WE GET THERE
Build small. Validate. Scale.
Before scaling an orbital launch vehicle, Akkoyun Aerospace is developing a complete reusable subscale flight vehicle. The demonstrator brings propulsion, propellant systems, thrust-vector control, avionics, guidance, software, structures, and ground systems together in one testable vehicle. The objective is to discover integration problems and validate engineering decisions while iteration remains fast and economically manageable.
The demonstrator is not the destination. It is the development platform used to reach the destination.
04 — VERTICAL INTEGRATION
We build the capability to build the vehicle.
Akkoyun Aerospace does not only design hardware. Much of the manufacturing, tooling, and test capability required to create and validate that hardware is developed internally. This keeps the feedback loop between design, manufacture, test, and iteration short and direct.
DESIGN → MANUFACTURE → TEST → LEARN → ITERATE
MACHINED IN-PROCESS / ALUMINIUM FLIGHT HARDWARE
CNC MACHINED / IN-HOUSE MANUFACTURING
FIG. 05 — DTR ENG-01 / ENGINE CORE, 316L
05 — PROPULSION
DTR ENG-01
COMPACT DEEPLY THROTTLEABLE BIPROPELLANT ROCKET ENGINE
DTR ENG-01 is a compact ethanol–oxygen rocket engine developed for reusable vehicle testing, control-system development and repeated operational testing.
Its architecture focuses on high functional integration with deliberately low manufacturing complexity, while retaining a configuration representative of flight hardware.
316L / 50–130% / 107 N SL / DESIGN POINT
INTEGRATED CONSTRUCTION
The engine core is additively manufactured from 316L stainless steel, allowing the chamber and nozzle structure to be produced as a highly integrated assembly.
The material choice keeps manufacturing robust and comparatively economical while supporting rapid development iterations.
THROTTLEABLE OPERATION
DTR ENG-01 is designed for operation across a 50–130% throttle range.
The internal thermal architecture is designed to maintain effective chamber cooling throughout this operating envelope.
DEVELOPMENT PURPOSE
DTR ENG-01 is intended as a reusable development engine for integrated vehicle testing, propulsion development, control-system development and repeated operational testing. The objective is not simply to produce thrust.
The engine is designed to become part of a complete integrated flight vehicle development program.
TECHNICAL DATA
DESIGN POINT / CALCULATED PERFORMANCE
PROPELLANTS
ETHANOL + GASEOUS OXYGEN
THROTTLE RANGE
50–130%
NOMINAL PRESSURE
15 BAR
SEA-LEVEL THRUST
107 N
VACUUM THRUST
125 N
SEA-LEVEL ISP
213 S
VACUUM ISP
248 S
TOTAL MASS FLOW
51.4 G/S
EFFECTIVE EXHAUST VELOCITY — SEA LEVEL
EFFECTIVE EXHAUST VELOCITY — VACUUM
PRIMARY MATERIAL
TECHNICAL DETAILS
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07 — RCS
RCS THR-01
REACTION CONTROL SYSTEM THRUSTER — ITERATION 01
RCS THR-01 is a compact propane–oxygen reaction-control thruster developed for short-duration, repeatable firing.
Rather than continuous thrust, the system is designed to generate controlled impulse events for vehicle stabilization and attitude correction.
Its compact combustion chamber and nozzle architecture are designed around rapid pulsed operation, with a maximum firing frequency of 10 Hz.
MAXIMUM FIRING FREQUENCY
SHORT-DURATION PULSED OPERATION / 1.0 N SL / 1.4 N VAC
FIG. 07 — RCS THR-01 / HARDWARE
PULSED OPERATION
RCS THR-01 is built for short-duration, high-frequency firing rather than continuous thrust.
This allows controlled impulse generation for vehicle stabilization and attitude correction.
VEHICLE FUNCTION
ATTITUDE CONTROL & STABILIZATION
Provides controlled pulsed thrust for vehicle attitude correction and stabilization.
TECHNICAL DATA
DESIGN POINT / DESIGN PERFORMANCE
PROPELLANTS
PROPANE + OXYGEN
SEA-LEVEL THRUST
1.0 N
VACUUM THRUST
1.4 N
SEA-LEVEL ISP
170 S
VACUUM ISP
232 S
VACUUM EXHAUST VELOCITY
~2.28 KM/S
TOTAL MASS FLOW
~0.6 G/S
NOMINAL CHAMBER PRESSURE
4 BAR
MAXIMUM FIRING FREQUENCY
10 HZ
FIG. 07.2 — NOZZLE / CHAMBER DETAIL
GEOMETRY
COMBUSTION CHAMBER
SINGLE CHAMBER
NOZZLE
PARABOLIC
THROAT DIAMETER
1.81 MM
EXIT DIAMETER
2.09 MM
EXPANSION RATIO
1.34
STATE: DESIGNED / MANUFACTURED
FIG. 07.3 — MACHINED INTERFACES / ASSEMBLY DETAIL
TECHNICAL DETAILS
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08 — COMPANY
About Akkoyun Aerospace.
Founded by Yasin Akkoyun to develop launch capability through vertically integrated hardware development, rapid iteration, and physical testing. The company designs and manufactures much of its flight and test hardware internally, and documents development publicly as it progresses from individual components toward integrated vehicle testing.
FOUNDER
YASIN AKKOYUN
MODEL
VERTICALLY INTEGRATED HARDWARE
BASE
EUROPE
YASIN AKKOYUN / FOUNDER
09 — CONTACT
Work with Akkoyun Aerospace.
For investment, technical partnerships, suppliers, research collaboration, future payload missions, and media inquiries.
INVESTMENT / TECHNICAL PARTNERSHIP / SUPPLIER / RESEARCH / FUTURE LAUNCH / MEDIA