TY - JOUR
T1 - Mass estimation method and its application for horizontal takeoff horizontal landing two stage to orbit system
AU - Jiang, Yazhong
AU - Jiang, Chongwen
AU - Gao, Zhenxun
AU - Lee, Chunhian
PY - 2014/4
Y1 - 2014/4
N2 - Aiming at transportation missions to low global orbit, a mass estimation method was proposed for horizontal takeoff horizontal landing two stage to orbit (TSTO) transportation systems considering thrust-drag characteristics in different flight stages and specific impulse variations in different engine modes. Three schemes of turbine based combined cycle-reusable rocket (TBCC-RR), rocket based combined cycle-reusable rocket (RBCC-RR), and reusable rocket-reusable rocket (RR-RR) were designed and compared for a mission to deliver 8 t payloads to a 200 km orbit. Influences of several parameters on design results were analyzed, including the separation point, throat-drag ratio and structure mass fraction of the first stage vehicle. The position of separation point has a great influence on TSTO schemes. If a RBCC vehicle is used as the first stage, it's recommended that the separation take place when the scramjet is turn off. Though TBCC-RR scheme leads to a smaller gross takeoff mass, RBCC-RR scheme has a smaller structure mass. The most effective way for gross mass reduction is to cut down the structure mass fraction and another approach is to improve throat-drag ratio of the vehicle.
AB - Aiming at transportation missions to low global orbit, a mass estimation method was proposed for horizontal takeoff horizontal landing two stage to orbit (TSTO) transportation systems considering thrust-drag characteristics in different flight stages and specific impulse variations in different engine modes. Three schemes of turbine based combined cycle-reusable rocket (TBCC-RR), rocket based combined cycle-reusable rocket (RBCC-RR), and reusable rocket-reusable rocket (RR-RR) were designed and compared for a mission to deliver 8 t payloads to a 200 km orbit. Influences of several parameters on design results were analyzed, including the separation point, throat-drag ratio and structure mass fraction of the first stage vehicle. The position of separation point has a great influence on TSTO schemes. If a RBCC vehicle is used as the first stage, it's recommended that the separation take place when the scramjet is turn off. Though TBCC-RR scheme leads to a smaller gross takeoff mass, RBCC-RR scheme has a smaller structure mass. The most effective way for gross mass reduction is to cut down the structure mass fraction and another approach is to improve throat-drag ratio of the vehicle.
KW - Conceptual design
KW - Mass estimation
KW - Rocket based combined cycle
KW - Turbine based combined cycle
KW - Two stage to orbit
UR - https://www.scopus.com/pages/publications/84901190995
U2 - 10.13700/j.bh.1001-5965.2013.0299
DO - 10.13700/j.bh.1001-5965.2013.0299
M3 - 文章
AN - SCOPUS:84901190995
SN - 1001-5965
VL - 40
SP - 473
EP - 478
JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
IS - 4
ER -