REGULATION SYSTEMS OF THE CYCLONE-4 LV UPPER STAGE MAIN LIQUID ROCKET ENGINE
- Paper number
IAC-10.C4.1.8
- Author
Dr. Vladimir Shnyakin, Yuzhnoye State Design Office, Ukraine
- Coauthor
Mr. Volodymyr Konokh, Ukraine
- Coauthor
Mr. Igor Kalinichenko, Yuzhnoye State Design Office, Ukraine
- Coauthor
Mr. Sergiy Valivakhin, Yuzhnoye State Design Office, Ukraine
- Year
2010
- Abstract
In the framework of the Ukrainian-Brazilian project the Yuzhnoye SDO is devel-oping RD861K liquid propellant engine for the Cyclone-4 LV upper stage. It is an up-graded version of RD861 engine created in 1967 and used until now in the Cyclone-3 LV upper stage. The engine of gas-generator-cycle produces thrust of 8000 kgf at Isp of 330 sec with propellants NTO+UDMH. For meeting the external requirements and provision of the engine reliability the following regulation systems are upgraded or used. 1. System of thrust stabilization. The sensitive element is a pressure indicator at the oxidizer (Ox) pump outlet, the executive one – hydraulic throttle with electro-mechanical actuator in the GG fuel (Fu) line. The accuracy of stabilization is ±4%. 2. Pressure stabilizer of direct action with a membrane sensitive element and ex-ecutive throttle of “nozzle-flapper” type. Being installed in the GG Ox line it provides MR stabilization for GG within ±2%. 3. The engine MR stabilizer (MRS) consisting of pressure stabilizer of indirect action and two flowmeter units with jet amplifiers. The inaccuracy of MR maintenance does not exceed 1%. MRS application has allowed addition of 21 kg to the payload in-jected into a transfer orbit for the geosynchronous one. 4. Pneumo-piloted helium pressure regulator in the line of the turbine spinning up. During startup the turbine inlet pressure is maintained within 2±0.4 MPa at helium flowrate of 0.4 kg/s. 5. Helium pressure regulator in the pneumatic unit controlling the start-cutoff valves. The regulator is provided with relief valve. Helium pressure is maintained at a level of 6±0.4 MPa. The report presents design specificities of all the said control units. By September 2009 all the systems have passed successfully the development phase, 9 engines have been subjected to fire tests. The critical issues of the fire tests were development of the nozzle extension, removal of increased vibrations in the tur-bopump, provision of serviceability and confirmation of the MRS accuracy. The tasks have been solved on steady operation of pressure stabilizer in GG line and helium pres-sure regulator at the turbine inlet. Development of the engine is being continued.
- Abstract document
- Manuscript document
IAC-10.C4.1.8.pdf (🔒 authorized access only).
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