航天推进技术研究院主办
[1]张帆,张会强.DRBCC动力飞行器两级入轨运载特性分析[J].火箭推进,2023,49(05):32-38.
ZHANG Fan,ZHANG Huiqiang.Analysis on transportation capacity of DRBCC-powered two-stage-to-orbit launch vehicle[J].Journal of Rocket Propulsion,2023,49(05):32-38.
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ZHANG Fan,ZHANG Huiqiang.Analysis on transportation capacity of DRBCC-powered two-stage-to-orbit launch vehicle[J].Journal of Rocket Propulsion,2023,49(05):32-38.
DRBCC动力飞行器两级入轨运载特性分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年05期
页码:
32-38
栏目:
目次
出版日期:
2023-10-25
- Title:
- Analysis on transportation capacity of DRBCC-powered two-stage-to-orbit launch vehicle
- 文章编号:
- 1672-9374(2023)05-0032-07
- Keywords:
- DRBCC propulsion system; propulsion performance; transportation capacity; two-stage-to-orbit
- 分类号:
- V412
- 文献标志码:
- A
- 摘要:
- 为发展RBCC动力系统,同时进一步探索推进性能对入轨有效载荷的影响规律,对以DRBCC为动力的两级入轨飞行器运载特性进行了研究。在给定飞行器构型和飞行剖面基础上,开展了该飞行器180 km近地轨道两级入轨设计。结果表明:以DRBCC飞行器作为第一级,配合独立火箭动力的第二级,150 t级飞行器180 km近地轨道的有效载荷为4.773 t; DRBCC的推力和比冲与飞行器飞行状态密切相关,DRBCC在2.5 Ma以下时一直工作在混合模态,而在2.5 Ma以上直接转入亚燃冲压模态; 在亚燃和超燃冲压模态,DRBCC的比冲随马赫数变化较为平缓,而推力出现了波动,且在亚燃冲压模态波动较大; 两级入轨过程中,DRBCC混合模态主要使飞行器完成爬高,亚燃冲压模态同时用来完成爬高和增速,超燃冲压模态主要用来增速。
- Abstract:
- In order to provide a suggestion for developing rocket-based-combined-cycle(RBCC)system, as well as researching the influence of propulsion performance on payload, the transportation capacity of dual-rocket-based-combined-cycle(DRBCC)powered two-stage-to-orbit(TSTO)launch vehicle was studied. The configuration of the TSTO launch vehicle was designed, and the flight profile was given. Then the TSTO transportation capacity to low-earth-orbit at 180 km was calculated. Results show the 150 t-weight TSTO launch vehicle can achieve payload of 4.773 t for equatorial mission to low-earth-orbit at 180 km with a DRBCC-powered first stage and a rocket engine powered second stage. The propulsion performance of DRBCC is tightly coupled to flight states of the launch vehicle. DRBCC works in hybrid mode under 2.5 Ma and then directly turns into ramjet mode. In ramjet and scramjet mode, specific impulse changes gently along with Mach number, but thrust fluctuates, especially in ramjet mode. During orbit-injecting process, hybrid mode is mainly used to raise height, ramjet mode is used to raise both height and speed, and scramjet mode is mainly used to raise speed.
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备注/Memo
收稿日期:2022-10-08; 修回日期:2022-11-06
基金项目:中国博士后科学基金(2018M640140)
作者简介:张帆(1989—),男,博士,工程师,研究领域为飞行器总体设计、组合循环动力。
更新日期/Last Update:
1900-01-01