Search results

Acc to @SavunmaSanayiST.com, CDR of Hurjet is in December 2020 or January 2021. Four different Hürjet configuration will be revealed.

Truck - Seyit produced by Anadolu Isuzu ! Radar - Aselsan with a range more than 500km. Bye bye Man

MAYAK The Mayak launch vehicle family provides spacecraft launches into low and medium orbits, including sun-synchronous. The launch vehicles use environmentally friendly propellants: liquid oxygen and kerosene. The Mayak family is derived from the existing Zenit and Cyclone launch vehicles...

DNEPR Lightweight tandem launch vehicle The Dnepr launch vehicle is used for efficient and highly accurate injection of a single or multiple spacecraft into 300-900 km orbits inclined at 50.5°, 64.5°, 87.3°, 98°. The launch vehicle burns hypergolic storable liquid propellants. Using multiple...

ZENIT-3SLBF Medium-lift tandem launch vehicle The Zenit-3SLBF Integrated Launch Vehicle is designed to deliver medium-weight spacecraft into mean and high circular and elliptical near-earth orbits, including geosynchronous transfer and geostationary orbits, as well as escape trajectories...

ZENIT-3SLB Medium-lift tandem launch vehicle The Zenit-3SLB launch vehicle delivers medium-weight payloads into medium and high circular and elliptical orbits, including geostationary transfer and geostationary orbits, and escape trajectories. The Zenit-3SLB rocket is a part of the Zenit...

ZENIT-3SL Medium-lift tandem launch vehicle The Zenit-3SL Integrated Launch Vehicle is designed to deliver heavy spacecraft into mean and high circular and elliptical near-earth orbits, geosynchronous transfer and geostationary orbits, as well as escape trajectories with orbit inclination...

ZENIT-2SLB Medium-lift tandem launch vehicle The Zenit-2SLB launch vehicle delivers medium-weight payloads into low Earth orbits, including sun-synchronous and polar orbits. The Zenit-2SLB rocket is a part of the Zenit family, which uses environmentally friendly propellants: liquid oxygen and...

CYCLONE-4M Class of launch-vehicle: medium-lift Staging: tandem Cyclone-4M LV is a two-staged monoblock medium-lift LV produced to satisfy the growing demand for commercial launch missions to LEO and SSO (including SC constellations). The first stage of the Cyclone-4M LV is developed basing on...

CYCLONE-4 Lightweight tandem launch vehicle BASIC SPECIFICATIONS Number of stages 3 Dimensions, mm Length Stage diameter Fairing diameter 40190 3000 4000 Launch mass, tons 198,25 Propellants Oxidizer Fuel NTO UDMH Thrust, ton-force Stage 1 Stage 2 Stage 3 313 102 8...

CYCLONE-1M The Cyclone-1M is a lightweight liquid-propellant launch vehicle designed to deliver payloads into low Earth orbits, including sun-synchronous orbits. The Cyclone-1M will be launched both from a space launch center located in Ukraine and from foreign space launch centers. FEATURES...

AMMONIA JET PROPULSION SYSTEMS The ammonia propulsion system (APS) is designed for correction of SC injection error in orbital period and orbital period keeping during active lifetime. AMMONIA PROPULSION SYSTEM FOR SICH-2M SC BASIC SPECIFICATIONS Total thrust pulse, N·s (kgf·s): in...

HALL-ENGINE-BASED ELECTRIC JET PROPULSION SYSTEM The Hall-engine-based Electric Jet Propulsion System (EJPS) is designed for spacecraft orbit correction, stabilization, and interplanetary flights. BASIC SPECIFICATIONS Working medium - xenon Maximum bottle pressure at 50°С, MPa 13...

SOLID-PROPELENT SPECIAL ENGINES PULSED CONTROL SRM Usage of micro SRM provides short-time control pulses along the yaw and pitch channels Basic characteristics: Propellant composite, high-energy Operating time, s 0.045 … 0.05 Thrust, kgf up to 500 Case high-strength steel...

SOLID-PROPELLANT MAIN ENGINES MAIN SOLID ROCKET MOTORS The main functions are: thrust application; producing control force along the yaw and pitch channels with rotating control nozzle (RCN); performance of all SRM characteristics under the specified external influences in every phase of...

LIQUID-PROPELLANT THRUSTERS LOW-THRUST Liquid-propellant thrusters are incorporated in liquid-propellant jet propulsion systems and generate thrust by propellant exhaust through a supersonic nozzle. Cyclone-3 Rocket 100 N Thruster Cyclone-3 Rocket 30 N Thruster...

RD-880 The engine is dual-chamber, two-mode, single firing, with turbopump propellant feed system, made according to oxidizing generator gas afterburning scheme. The engine is developed on the basis of Zenit LV proven technologies. RD880.1 single-chamber engine with thrust 500 tf can be...

RD-815 Main engine with turbopump propellant feed system, made according to generator gas afterburning scheme. The engine is developed on the basis of Zenit LV proven technologies. The engine has high mass-energy characteristics. This engine is designed for the use in most advanced LV of...