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航天器近距离小推力抵近轨迹优化方法
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作者 侯锐 唐蕊 +1 位作者 韩宏伟 黄攀峰 《宇航学报》 2025年第8期1555-1564,共10页
近年来,随着在轨卫星数量的急剧增加,面向空间目标在轨服务的抵近操作成为航天器操控任务的重要阶段。同时,随着电推进技术的迅速发展,高效能小推力机动逐渐成为当前轨道机动的主要形式。针对空间目标近距离抵近交会/飞越任务需求,提出... 近年来,随着在轨卫星数量的急剧增加,面向空间目标在轨服务的抵近操作成为航天器操控任务的重要阶段。同时,随着电推进技术的迅速发展,高效能小推力机动逐渐成为当前轨道机动的主要形式。针对空间目标近距离抵近交会/飞越任务需求,提出了基于凸优化的小推力抵近轨迹快速优化设计方法。首先,针对近距离小推力抵近过程中的非线性动力学,通过模型假设和参数近似来线性化。然后,针对推力矢量带来的二阶等式约束,给出了基于参数正则策略实现约束边界激活,从而实现了无损凸化。之后,为了增强小推力轨迹优化问题的收敛性,构建了基于终端约束松弛的罚函数项,提升了轨迹优化算法的鲁棒性。最后,分别给出了面向目标交会和飞越任务的抵近轨迹数值仿真结果,验证了该算法的有效性。此方法可以快速得到最优小推力抵近轨迹,能够应用于未来空间目标在轨服务中在线决策与制导开环设计。 展开更多
关键词 空间目标抵近 小推力机动 凸优化 无损凸化
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Ignition characteristics and combustion performances of a LO_2/GCH_4 small thrust rocket engine 被引量:2
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作者 ZHANG Jia-qi LI Qing-lian SHEN Chi-bing 《Journal of Central South University》 SCIE EI CAS CSCD 2018年第3期646-652,共7页
A 500 N model engine filled with LO2/GCH4 was designed and manufactured.A series of ignition attempts were performed in it by both head spark plug and body spark plug.Results show that the engine can be ignited but th... A 500 N model engine filled with LO2/GCH4 was designed and manufactured.A series of ignition attempts were performed in it by both head spark plug and body spark plug.Results show that the engine can be ignited but the combustion cannot be sustained when head spark plug applied as the plug tip was set in the gaseous low-velocity zone with thin spray.This is mainly because flame from this zone cannot supply enough ignition energy for the whole chamber.However,reliable ignition and stable combustion can be achieved by body spark plug.As the O/F ratio increases from 2.61 to 3.49,chamber pressure increases from 0.474 to 0.925 MPa and combustion efficiency increases from 57.8%to 95.1%.This is determined by the injector configuration,which cannot produce the sufficiently breakup of the liquid oxygen on the low flow rate case. 展开更多
关键词 LO2/GCH4 small thrust rocket engine ignition characteristic combustion performance
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