共查询到18条相似文献,搜索用时 359 毫秒
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测控系统是航天发射任务中不可缺少的支持保障系统,为适应未来我国新一代大型运载火箭的发射任务,本文提出建立一个低成本、高效率的运载火箭发射测控系统,其作用为运载火箭发射任务提供测控支持服务,这样将大大增强运载火箭发射的灵活性,降低发射成本,并且对这一发射测控系统组成结构和体制提出了初步构想。 相似文献
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承担此次嫦娥三号探测器发射任务的长征三号乙改进型运载火箭,为捆绑式三级液体运载火箭。与承担嫦娥二号发射任务的火箭相比,这枚火箭采用了多项新技术,进行了多项技术状态更改,突破了多轨道、窄窗口发射和高精度入轨技术,可靠性和安全性也得到进一步提高。 相似文献
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针对交会对接任务对发射窗口的轨道日照角、光学导航测量设备阳光抑制角和轨道共面等多项约束,建立了交会对接发射窗口计算数学模型,给出了交会对接发射窗口计算方法与流程,分析了各种约束对交会对接发射窗口的影响。计算并构建了交会对接任务目标飞行器和追踪飞行器的年度日照发射窗口集合。按照2种任务规划思路分别给出了确定目标飞行器和追踪飞行器年度共面窗口集合的方法,为多约束交会对接年度发射窗口的日窗口和时刻窗口的分析和规划提供了清晰的结果。仿真结果验证了交会对接年度发射窗口集合的正确性和有效性,模型、方法和结果可作为交会对接任务发射窗口分析和规划的依据。
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《中国航天(英文版)》2017,(1)
The Long March 5(LM-5) launch vehicle is China's new generation heavy-lift rocket with the largest payload capacity,representing the highest standard of China's current launchers.It took 10 years to develop the LM-5 launch vehicle.On November 3,2016,the LM-5 carrier rocket blasted off from the Wenchang satellite launch center on Hainan Island,achieving a successful maiden flight.During the development of the LM-5 rocket,the engineering team accumulated abundant experience on developing heavy-lift cryogenic rockets and established a thorough research and development system for new generation launch vehicles,which significantly raised the ability for launcher RD. 相似文献
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Multistage rockets are commonly employed to place spacecraft and satellites in their operational orbits. Performance evaluation of multistage rockets is aimed at defining the maximum payload mass at orbit injection, for specified structural, propulsive, and aerodynamic data of the launch vehicle. This work proposes a simple method for a fast performance evaluation of multistage rockets. The technique at hand is based on three steps: (i) the flight-path angle at each stage separation is guessed, (ii) the spacecraft velocity is maximized at the first and second stage separation, and (iii) for the last stage the thrust direction is obtained through the particle swarm optimization technique, in conjunction with the use of the Euler–Lagrange equations and the Pontryagin minimum principle. The coast duration at the second stage separation is optimized as well. The method at hand is extremely simple and easy-to-implement, but nevertheless it proves to be capable of yielding near-optimal ascending trajectories for a multistage launch vehicle with realistic structural, propulsive, and aerodynamic characteristics. The solutions found with the technique under consideration can be employed either for a rapid evaluation of the multistage rocket performance or as guesses for more refined optimization algorithms. 相似文献