火箭推进

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。

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.

引言
1 计算模型
2 DRBCC动力系统及其性能
3 结果与分析
4 结论

图1 两级入轨飞行器示意图<br/>Fig.1 Layout of the two-stage-to-orbit launch vehicle

图1 两级入轨飞行器示意图
Fig.1 Layout of the two-stage-to-orbit launch vehicle

表1 预燃室产生的富燃预燃气<br/>Tab.1 Fuel-rich gas produced by pre-chamber of rocket engine

表1 预燃室产生的富燃预燃气
Tab.1 Fuel-rich gas produced by pre-chamber of rocket engine

图2 DRBCC动力系统示意图<br/>Fig.2 Layout of the DRBCC system

图2 DRBCC动力系统示意图
Fig.2 Layout of the DRBCC system

图3 DRBCC混合模态和纯引射模态性能<br/>Fig.3 Performance of DRBCC hybrid and pure ejector mode

图3 DRBCC混合模态和纯引射模态性能
Fig.3 Performance of DRBCC hybrid and pure ejector mode

图4 DRBCC亚燃冲压模态性能<br/>Fig.4 Performance of DRBCC ramjet mode

图4 DRBCC亚燃冲压模态性能
Fig.4 Performance of DRBCC ramjet mode

图5 DRBCC超燃冲压模态性能<br/>Fig.5 Performance of DRBCC scramjet mode

图5 DRBCC超燃冲压模态性能
Fig.5 Performance of DRBCC scramjet mode

图6 两级入轨飞行轨迹<br/>Fig.6 Flight trajectory of orbit-injecting process

图6 两级入轨飞行轨迹
Fig.6 Flight trajectory of orbit-injecting process

表2 两级入轨计算结果<br/>Tab.2 Calculation results for two-stage-to-orbit

表2 两级入轨计算结果
Tab.2 Calculation results for two-stage-to-orbit

图7 DRBCC在第一和第二飞行阶段时的性能<br/>Fig.7 Performance of DRBCC during phase 1 and phase 2

图7 DRBCC在第一和第二飞行阶段时的性能
Fig.7 Performance of DRBCC during phase 1 and phase 2

图8 混合模态助推系数变化<br/>Fig.8 Boost coefficient during hybrid mode

图8 混合模态助推系数变化
Fig.8 Boost coefficient during hybrid mode

表3 两级入轨过程各阶段飞行时间、推进剂消耗、速度增量和高度增量<br/>Tab.3 Flight time,propellant consumption,spead and altitude increment during orbit-injecting process

表3 两级入轨过程各阶段飞行时间、推进剂消耗、速度增量和高度增量
Tab.3 Flight time,propellant consumption,spead and altitude increment during orbit-injecting process

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备注

引言

1 计算模型

2 DRBCC动力系统及其性能

3 结果与分析

4 结论

期刊信息