ŞİMŞEK System

Türkiye's Independent Access to Space Capability through the ŞİMŞEK Launch Vehicle Family and Space Launch Centers

Orbital Altitude Şimşek-1: 550 km | Şimşek-2: 700 km

Diameter Şimşek-1: 2.7 m | Şimşek-2: 3.7 m

Overall Length Şimşek-1: ~30 m | Şimşek-2: ~40 m

With the goal of achieving independent access to space, research and development activities were initiated in 2012. As a result, the Sounding Rocket was developed, enabling the Türkiye's first successful access to space in 2017. Subsequent sounding rocket missions provided valuable flight heritage and validated critical subsystems and technologies.

Building on these achievements, ROKETSAN was appointed by the Secretariat of Defence Industries as the prime contractor for the Şimşek-1 System Development Project on 29 October 2018. The project aims to develop Türkiye's capability to launch satellites into Low Earth Orbit (LEO). Subsequently, on 29 October 2025, ROKETSAN was also designated as the prime contractor for the Şimşek-2 System Development Project, which aims to establish the capability to place satellites into Sun-Synchronous Orbit (SSO).

Advanced Space Technologies Qualified

To achieve independent access to space, the development of a Domestic Space Launch Center is currently underway. In parallel, infrastructure development for an Overseas Space Launch Center is progressing to enable access to a wider range of orbital destinations and mission profiles.

The planned launch infrastructure includes:

• Payload Processing Facility

• Launch Control Center

• Vehicle Integration Building

• Stage Ignition Test Facility

• Launch Pad

• Propellant Filling, Draining, and Pressurization Systems

• Flame Deflector and Water Deluge System

• Storage Facilities

• Tracking, Telemetry, and Communications Systems

Space Systems Technologies

System and Technical Specifications

Technical Specifications

Mission Şimşek-1: Rideshare launch capability to Low Earth Orbit (LEO) ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ Şimşek-2: Rideshare launch capability to Sun-Synchronous Orbit (SSO)

Payload Capacity Şimşek-1: 400 kg payload → 550 km circular LEO at 42.5°–45° inclination ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎Şimşek-2: 1,500 kg payload → 700 km Sun-Synchronous Orbit (SSO)

Configuration Three-stage liquid-propellant launch vehicle configuration

Diameter Şimşek-1: 2.7 m ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎Şimşek-2: 3.7 m

Height Şimşek-1: ~30 m‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ ‎ Şimşek-2: ~40 m