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  • the design and development of a medium-scale liquid commercial launch vehicle named zq-2 based on liquid oxygen and liquid methane propulsion system

    Paper number

    IAC-19,D2,IP,2,x54580

    Author

    Dr. GENG HAO, China, LandSpace Technology

    Coauthor

    Ms. LEI ZHANG, China, LandSpace Technology

    Coauthor

    Mr. YAWEI XU, China, LandSpace Technology

    Year

    2019

    Abstract
    Liquid oxygen and liquid methane (LOX+LCH4), with the characteristics that are clean, non-pollution, low-cost and high specific impulse, are considered as the next generation liquid rocket engine propellant. The research and engineering development of liquid rocket engine based on LOX+LCH4 propellant has recently become one main research direction. Studies on the launch vehicle design concept based on LOX+LCH4 engines are still necessary to maximize the utilization of these technical advantages of LOX+LCH4 propellants. This paper introduces the design, engineering development and implementation of a medium commercial liquid launch vehicle ZQ-2, based on LOX+LCH4 propulsion system. ZQ-2 and the corresponding series of LOX+LCH4 based liquid rocket engines named TQ are independently developed by Beijing Landspace Space Technology Co., Ltd. ZQ-2 is a two stage launch vehicle, with four (4) 80t-thrust-level LOX+LCH4 LRE engines named TQ in cluster configuration on the first stage to improve the stability in the transonic Mach regime. The total length of ZQ-2 launcher is 50m and the diameter is 3.35m. TQ-13 system is composed of 4 TQ-12 main engines with overall 2630kN thrust with their accessories mounted at the bottom of the first stage. Each TQ-12 main engine can achieve a ground specific impulse of 283s. TQ-16 system provides the propulsion for the second stage, with a total trust 775.9kN and the specific impulse 333s in vacuum. Research shows that the carrying capacity of 500km Sun-Synchronous Orbit (SSO) can reach 1,500kg for the ZQ-2 launch vehicle system, which makes it the largest private commercial launcher in China.
    Abstract document

    IAC-19,D2,IP,2,x54580.brief.pdf

    Manuscript document

    IAC-19,D2,IP,2,x54580.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.