TY - JOUR
T1 - Study on payload mass of rocket/dual-mode scramjet combined propulsion powered cruise vehicle
AU - Lv, Xiang
AU - He, Guo Qiang
AU - Liu, Pei Jin
AU - Qin, Fei
PY - 2014/8/1
Y1 - 2014/8/1
N2 - For rocket/dual-mode scramjet(RDMSJ) combined propulsion powered cruise vehicle operating in near space, vehicle mass was divided into several components utilizing the"from top to bottom"mass assessment method, and payload mass assessment model was established. Under the system requirements of takeoff mass of 3 000 kg, cruise range of 1 500 km, some factors affecting the payload mass were investigated, including gas pressure /turbo pump feeding system, liquid hydrogen /JP-10 fuel, thrust to weight ratio of vehicle, and cruise range. Response surface models were established for payload mass and propulsion system mass responding to cruise range. The investigation results show that, for JP-10 fueled vehicle with gas pressure feeding system, the payload mass is 313 kg; if the vehicle is fueled by liquid hydrogen with neither feeding system, it can not carry any payload. The maximum cruise range of JP-10 fueled vehicle is 2270 km without any payload on board. The thrust to weight ratio of RDMSJ powered vehicle should be greater than 1.2 to maintain a lower level of propellant consumption.
AB - For rocket/dual-mode scramjet(RDMSJ) combined propulsion powered cruise vehicle operating in near space, vehicle mass was divided into several components utilizing the"from top to bottom"mass assessment method, and payload mass assessment model was established. Under the system requirements of takeoff mass of 3 000 kg, cruise range of 1 500 km, some factors affecting the payload mass were investigated, including gas pressure /turbo pump feeding system, liquid hydrogen /JP-10 fuel, thrust to weight ratio of vehicle, and cruise range. Response surface models were established for payload mass and propulsion system mass responding to cruise range. The investigation results show that, for JP-10 fueled vehicle with gas pressure feeding system, the payload mass is 313 kg; if the vehicle is fueled by liquid hydrogen with neither feeding system, it can not carry any payload. The maximum cruise range of JP-10 fueled vehicle is 2270 km without any payload on board. The thrust to weight ratio of RDMSJ powered vehicle should be greater than 1.2 to maintain a lower level of propellant consumption.
KW - Hypersonic vehicle
KW - Near space
KW - Payload
KW - Rocket/dual-mode scramjet combined propulsion
UR - http://www.scopus.com/inward/record.url?scp=84907931017&partnerID=8YFLogxK
U2 - 10.7673/j.issn.1006-2793.2014.04.002
DO - 10.7673/j.issn.1006-2793.2014.04.002
M3 - 文章
AN - SCOPUS:84907931017
SN - 1006-2793
VL - 37
SP - 442
EP - 447
JO - Guti Huojian Jishu/Journal of Solid Rocket Technology
JF - Guti Huojian Jishu/Journal of Solid Rocket Technology
IS - 4
ER -