Two proposals of manned lunar-landing propulsion system were discussed.The structure and basic parameters of propulsion system for existed heavy lift launch vehicles were analyzed.The structure and task requirements were proposed to meet the manned lunar-landing demand.Considering the performance
economics
technical difficulties
working reliability
a scheme of the first stage engine system for heavy lift launch vehicle was proposed.A heavy lift vehicle(HLV) system and a HLV series were estableshed
and their payload capability was calculated.Based on integrative analysis
the lunar launch vehicle is suggested to be 3 stage with 4 boosters
and two 50t liquid oxygen/liquid hydrogen are used for the third stage
while liquid oxygen/kerosene stage combustion cycle engines about 5000kN are used for all other stages.
Basic parameters analysis of first stage engine system for heavy lift vehicle
Forced start-up procedure of a staged combustion cycle engine
Study on the characteristics of bipropellant-fueled pulse rocket engine with high combustion chamber pressure
Optimization of liquid propellants rocket engine based on genetic algorithm
Ground Ignition Test of an Orbit Maneuver H/OThruster Based on Gas Dynamic Resonance Igniter
Related Author
CHEN Jian-hua
LIU Hong-jun
CHEN Hong-yu
WANG Hai-xing
QIN Li-zi
LIANG Shu-qiang
TANG Jia-peng
DUAN Na
Related Institution
National Key Laboratory of Science and Technology on Liquid Rocket Engines, Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation
School of Astronautics, Beijing University of Aeronautics and Astronautics
College of Mechanical and Electronic Engineering North University of china
Beijing Aerospace Propulsion Institute
Air Materiel Department,Air Force Equipment Command