Abstract:The horizontal take-off and horizontal landing (HTHL) aerospace vehicle is an important means for future space rapid response and low-cost space transportation. Combined cycle power has full envelope flight capability, and uses air as an oxidant in the atmosphere to greatly enhance the specific impulse of the engine. Therefore, it is the preferred engine system for future HTHL aerospace vehicle. This paper reviews the development history and status of the combined cycle powered aerospace vehicles at home and abroad, and describes the advantages and disadvantages of various types of takeoff and landing. The advantages of HTHL and the requirements for the vehicle and engine are clarified. By comparison of RBCC and rocket for aerospace vehicle, the application advantage of combined cycle engine in HTHL aerospace vehicle is confirmed.
[1] Chase R L,Tang M H. A history of the NASP program from the formation of the joint program office to the termination of the HySTP scramjet performance demonstration program[C]//6th AIAA International Aerospace Planes and Hypersonic Technologies Conference. Chattanooga:AIAA, 1995.
[2] 康开华, 丁文华. 英国未来的SKYLON可重复使用运载器[J]. 导弹与航天运载技术, 2010(6):53-56.
[3] Joyce P J, Pomroy J B. The Hyper-X launch vehicle:Challenges and design considerations for hypersonic flight testing[C]//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies. Capua:AIAA, 2005.
[4] Mercier R A, Ronald T M F. Hypersonic technology (HyTech) program overview[C]//8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Norfolk:AIAA, 1998.
[5] Joseph M H, James S M, Richard M. The X-51A scramjet engine flight demonstration program[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Dayton:AIAA, 2008.
[6] Bowcutt K G, Smith T R, Kothari A P, et al. The hypersonic space and global transportation system:A concept for routine and affordable access to space[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. San Francisco:AIAA, 2011.
[7] Dissel A F, Kothari A P, Lewis M J. Investigation of twostage-to-orbit air-breathing launch vehicle configurations[C]//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies. Capua:AIAA, 2005.
[8] Kothari A P, Livingston J W, Tarpley C, et al. Rocket based combined cycle hypersonic vehicle design for orbital access[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. San Francisco:AIAA, 2011.
[9] Kothari A P, Livingston J W, Tarpley C, et al. A reusable, rocket and airbreathing combined cycle hypersonic vehicle design for access-to-space[C]//AIAA SPACE 2010 Conference & Exposition. Anaheim:AIAA, 2010.
[10] Flaherty K W, Andrews K M, Liston G W. Operability benefits of airbreathing hypersonic propulsion for flexible access to space[J]. Journal of Spacecraft and Rockets, 2010, 47(2):280-287.
[11] Mehta U, Aftosmis M, Bowles J, et al. Skylon aerodynamics and SABRE plumes[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Glasgow:AIAA, 2015.
[12] Hellman B M, Bradford J, German B St, et al. Two stage to orbit conceptual vehicle designs using the SABRE engine[C]//AIAA Space Forum. California:AIAA, 2016.
[13] Steelant J. Sustained hypersonic flight in Europe:technology drivers for LAPCAT Ⅱ[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Bremen:AIAA, 2009.
[14] 苏鑫鑫. 盘点日本的高超声速计划[J]. 飞航导弹, 2008(5):26-31.
[15] 周建兴, 佘文学. HIFiRE项目进展概述及其飞行试验特点分析[J]. 战术导弹技术, 2015(6):11-20.
[16] Boyce R R, Tirtey S C, Brown L, et al. Scramspace:Scramjet-based access-to-space systems[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. San Francisco:AIAA, 2011.
[17] 何国强, 秦飞, 魏祥庚, 等. 火箭冲压组合发动机燃烧的若干基础问题研究[J]. 试验流体力学, 2016, 30(1):1-13.
[18] 张留欢, 杜泉, 张蒙正. RBCC发动机火箭-冲压模态理想热力循环优化分析[J]. 火箭推进, 2016, 42(3):21-32.
[19] 向先宏, 钱战森, 张铁军. TBCC进气道模态转换气动技术研究综述[J]. 航空科学技术, 2017, 28(1):10-18.
[20] 韦宝禧, 凌文辉, 冮强, 等. TRRE发动机关键技术分析及推进性能探索研究[J]. 推进技术, 2017, 38(2):298-305.
[21] Gong C L, Chen B, Gu L X. Design and optimization of RBCC powered suborbital reusable launch vehicle[C]//19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Atlanta:AIAA, 2014.
[22] Gong C L, Chen B, Gu L X. Comparison study of RBCC powered suborbital reusable launch vehicle concepts[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Glasgow:AIAA, 2015.