Design evaluation of the performance capabilities and schematic for the LOx/LNG liquid-propellant rocket engine
- Paper number
IAC-23,C4,IPB,6,x77916
- Author
Dr. Volodymyr Shulha, Yuzhnoye State Design Office, Ukraine
- Coauthor
Mr. Alexandr Prokopchuk, Yuzhnoye State Design Office, Ukraine
- Coauthor
Mr. Sergey Shokod'ko, Yuzhnoye State Design Office, Ukraine
- Coauthor
Mr. Dmytro Khromiuk, Yuzhnoye State Design Office, Ukraine
- Year
2023
- Abstract
Specialists of Yuzhnoye State Design Office are developing a number of advanced LOX/kerosene liquid-propellant rocket engines. In parallel, their interest is turning to the use of methane as a propellant for space launch vehicles, spurred by the new trends and approaches to launch vehicle development, which bring forward requirements such as launch services cost reduction, launch site environmental safety, as well as the desire of space technology developers to have reusable rockets to deliver payloads into space. Liquefied natural gas (LNG) containing up to 98% methane can substitute methane. The paper defines the engine performance capability requirements and discusses possible engineering solutions for their implementation. In particular, the performance and balance calculations are shown for the following solutions, with afterburning of – oxidizer-rich generator gas, – fuel-rich generator gas, – both propellants gasified in the combustion chamber. The conclusion compares the performance capabilities and the LRE reliability enhancement capabilities for LOx/LNG and LOx/kerosene configurations.
- Abstract document
- Manuscript document
(absent)