重复使用运载器初期再入段制导技术研究

发布时间：2018-04-15 14:16

本文选题：重复使用运载器 + 再入制导　；参考：《南京航空航天大学》2013年硕士论文

【摘要】：重复使用运载器再入环境复杂，在保证飞行安全的同时又要满足飞行任务需求，这对初期再入制导提出了严峻挑战。本文对重复使用运载器初期段再入段的标称轨迹设计和制导律设计方法展开研究。为了准确描述重复使用运载器初期再入段的运动状态，给出了考虑地球自转的球面三自由度运动模型。对重复使用运载器的气动参数和升阻比特性进行分析，为标称轨迹设计和制导律设计提供了依据。本文形成了基于阻力加速度-速度剖面的初期再入标称轨迹设计方法并给出了标称轨迹参数的计算方法。通过分析迎角对总体约束的影响，设计了再入迎角剖面。为了保证再入安全，将总体约束转化为阻力加速度剖面内的再入走廊，分析了再入走廊的鲁棒性。根据初期再入段的机动能力和飞行任务，将标称轨迹分为5段，在再入走廊内分段设计了标称轨迹剖面的形状和大小，并对气动参数不确定下的轨迹鲁棒性进行验证。根据初期再入段的任务要求，设计了纵横向综合制导方案。纵向通过控制滚转角的大小来跟踪标称轨迹，横向通过控制滚转角的方向来控制航向偏差。采用迎角补偿策略，，通过调整迎角来补偿滚转角反转时带来的纵向跟踪误差。设计了末端航程修正方案，根据待飞距离选择航程合适的过渡段轨迹，以满足再入航程要求。最后，本文在Matlab/Simulink环境下建立了非线性仿真环境，在考虑气动不确定性和存在常值风的条件下，进行初期再入段全过程飞行仿真验证。仿真结果表明了再入制导系统任务管理逻辑的正确性、制导逻辑的合理性和制导系统的鲁棒性。
[Abstract]:The reentry environment of the reusable launch vehicle is complex, which not only ensures the flight safety but also meets the mission requirements, which poses a severe challenge to the initial reentry guidance.In this paper, the nominal trajectory design and guidance law design of the initial reentry section of the reusable launch vehicle are studied.In order to accurately describe the motion state of the initial reentry phase of the reusable launch vehicle, a three degree of freedom spherical motion model considering the rotation of the earth is presented.The aerodynamic parameters and lift-to-drag ratio characteristics of the reusable launch vehicle are analyzed, which provides the basis for the nominal trajectory design and guidance law design.In this paper, the initial re-entry nominal trajectory design method based on drag acceleration velocity profile is developed and the calculation method of nominal trajectory parameters is given.The reentry angle of attack profile is designed by analyzing the influence of angle of attack on the overall constraint.In order to ensure the safety of reentry, the overall constraint is transformed into the reentry corridor in the resistance acceleration profile, and the robustness of the reentry corridor is analyzed.According to the maneuverability and mission of the initial reentry section, the nominal trajectory is divided into five sections. The shape and size of the nominal trajectory profile are designed in the reentry corridor, and the trajectory robustness under the uncertainty of aerodynamic parameters is verified.According to the mission requirements of the initial reentry section, a comprehensive longitudinal and horizontal guidance scheme is designed.Longitudinal control of roll angle to track the nominal trajectory and lateral control of the direction of roll angle to control the course deviation.The angle of attack compensation strategy is used to compensate the longitudinal tracking error when the roll angle is reversed by adjusting the angle of attack.In order to meet the requirements of reentry range, the terminal range correction scheme is designed to select the appropriate transition trajectory according to the distance to be flown.Finally, a nonlinear simulation environment is established under the Matlab/Simulink environment. Under the condition of considering the aerodynamic uncertainty and the constant wind, the flight simulation of the initial re-entry stage is carried out.The simulation results show the correctness of mission management logic, the rationality of guidance logic and the robustness of guidance system.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2013
【分类号】：V448

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