Name: Name: | U-1250 | U-1250 |
Original Name: Original Name: | У-1250 | |
Category: Category: | liquid-fueled rocket engine | |
Manufacturer: Producer: | M.V.Khrunichev State Scientific and Production Center Государственный научно-производственный центр имени М.В.Хруничева | |
Period of manufacture: Production Period: | XX.XX.1945- XX.XX.1946 | |
Units produced: Number of Produced: | ? | |
Prototype produced: Prototype Built: | XX.XX.1945 | |
Use: Use: | Test and development rocket engine | |
Specifications: Technical Data: | | |
Number of combustion chambers: Number of combustion chambers: | 1 | |
Weight: Weight: | 59 kg | 130.07 lb |
Overall length: Overall Length: | 800 mm | 2 ft 7.5 in |
Overall Width / Maximum Diameter: Overall Width / Maximum Diameter: | ? mm | ? ft in |
Thrust control: Thrust control: | yes | yes |
Fuel feed: Fuel feed: | pressurized cycle | pressurized cycle |
Cooling: Cooling: | regenerative cooling | regenerative cooling |
Injector type: Injector type: | shower head type | shower head type |
Number of nozzles: Number of jets: | 69 fuel 52 for oxidizer | 69 for fuel 52 for oxidant |
Ignition: Ignition: | xylidine | xylidine |
Fuel: Driving fuel: | liquid double-component | liquid double-component |
Fuel: Fuel: | kerosene | kerosene |
Oxidizer: Oxidant: | AK (nitric acid) | AK (nitric acid) |
Fuel/Oxygenant ratio: Proportion fuel / oxidant: | ? | |
Performance and operating values: Performance and operational values: | | |
Maximum thrust: Maximum Thrust: | 1300 N 01) | 292.25 lbf 01) |
Specific Impulse: Specific impulse: | 212 Ns/kg 01) | 47.96 lbfs/lb 01) |
Discharge rate: Efflux velocity: | ? m/s | ? ft/s |
Combustion chamber pressure: Pressure in combustion chamber: | ? Pa | ? bar |
Combustion chamber temperature: Temperature in combustion chambre: | ? °C | ? °F |
Thrust-to-weight ratio: Proportion thrust / weight: | ? | |
Lifetime: Lifetime: | ? | |
Note: Note: | - multiple use - Maximum continuous working time: 44 s 01) - at sea level 02) - in the air | - multiple using - maximum continuous labour time: 44 s 01) - at sea level 02) - at vacuum |
Sources: Sources: | Liquid fuel rocket engines - http://www.lpre.de Isaev, A.M. - First Steps to Space Engines, Mashinostroyenie Publishing House, Moscow 1978 State Scientific and Production Center of M.V.Khrunichev - http://www.khrunichev.ru/main.php?id=19&nid=16 |