【作者】 刘欣；

【导师】 杨涛；

【作者基本信息】 国防科学技术大学 ， 航空宇航科学与技术， 2012， 博士

【摘要】 助推-滑翔式飞行器以其增加射程、提高突防能力的独特优势正成为当前的研究热点。本文以解决助推-滑翔式飞行器弹道优化与再入制导关键技术为目标，系统研究了全弹道基本特性、弹道优化技术、再入弹道在线生成和跟踪制导、弹道在线优化与预测制导等问题，主要研究成果如下：基于平面再入运动模型，对助推-滑翔式飞行器的全弹道特性进行了分析。分析了平衡滑翔弹道特性，得到了高度、倾角、射程等弹道参数与升阻比、滑翔速度的关系；分析了助推-滑翔式飞行器被动段射程与主动段终点参数的关系并与弹道导弹的相关结果进行比较；根据飞行器任务进行了火箭助推方案设计，完成了主动段弹道的分析与设计。建立了再入弹道优化问题的数学模型，阐述了Gauss伪谱方法求解最优控制问题的基本框架，并应用Gauss伪谱方法对助推-滑翔式飞行器的飞行性能进行了分析，计算了针对全弹道的最大射程弹道、针对给定再入点的飞行器目标覆盖范围、考虑禁飞区约束的最优弹道。对再入滑翔弹道的在线生成与跟踪制导方法进行了研究，将再入制导分为纵向和侧向制导，纵向采用在线生成与跟踪制导的方式，侧向则采用方位误差走廊控制弹道。主要做了两方面的研究工作：一是提出了基于高度-速度(H-V)飞行剖面的再入弹道在线生成方法，在再入走廊内将整个滑翔段弹道设计为二段三次H-V曲线，根据待飞射程的要求确定H-V曲线，基于反馈线性化方法设计了弹道跟踪制导律，通过跟踪H-V曲线获得其他弹道参数，引入射程更新技术，实现了高精度的再入制导；二是改进了基于平衡滑翔弹道的再入弹道在线生成方法，利用平衡滑翔条件建立了弹道参数间的近似关系，并将弹道约束转换为控制量约束，建立攻角的参数化模型，根据待飞射程要求迭代确定攻角曲线，利用弹道参数间的近似关系，得到其他纵向弹道参数，采用线性二次调节器方法计算弹道跟踪的最优增益系数，通过弹道跟踪实现了高精度的再入制导。针对目前数值预测-校正制导方法的局限性，提出了基于伪谱法弹道在线优化的预测制导技术。较系统的讨论了以伪谱法进行弹道在线优化来进行预测-校正的可行性和实现方法，通过对控制更新时间间隔以及在线优化计算节点数的合理选择，保证了较高制导精度和在线计算效率，为实现数值预测-校正制导的应用提供了一条可行的途径。采用一种满足落角约束的最优导引律来解决滑翔式飞行器下压段制导问题，并进行仿真验证。本文工作是最优控制理论在助推-滑翔式飞行器弹道设计与再入制导技术上的一次创新性应用，所作工作能对发展未来新型助推-滑翔式飞行器及相关技术问题的进一步研究提供有益的理论依据和技术支持。更多还原

【Abstract】 Based on augmenting the range and excellent penetration ability, the boost-glidevehicle becomes one of the focuses currently. For the purpose of developingtrajectory optimization and reentry guidance technology of the boost-glide vehicle,this dissertation studies the properties of the whole trajectory, trajectory optimizationmethod, on-board trajectory generation and tracking guidance, trajectory onlineoptimization and predictor-corrector guidance. The main work and results achieved inthis dissertation are summarized as follows:Based on the planar reentry dynamic model, the rudimentary properties of theboost-glide trajectory are studied. The characteristics of the equilibrium glidetrajectory are analyzed. The influences of burnout trajectory parameters on range areanalyzed comparing with ballistic vehicle. Based on two stage rocket-boost launchingmode, booster parameter is evaluated for mission; the trajectory of boost phase isdesigned.A trajectory optimization approach using Gauss Pseudospectral Method (GPM)for boost-glide vehicle is developed. The optimization models for the boost-glidetrajectory are presented and the principle of GPM is described. Then the GPM isapplied to compute the optimal trajectory of Max range of whole trajectory, theattainable region of reentry flight and the optimal trajectory considering the restrictionof “no-fly zone”.A scheme of reentry trajectory on-board generation and tracking guidance forboost-glide vehicle is discussed. The reentry guidance is divided into longitudinalguidance and lateral guidance, the vehicle’s longitudinal motion is controlled bytrajectory on-board generation and tracking guidance, lateral motion is controlled byheading error corridor. The main contributions of this research are:1. A method ofheight vs velocity(H-V) profile online generation is proposed. The trajectory isdesigned to two segments of cubic curve in reentry corridors, the curve is determinedby terminate range constraint. A nonlinear tracking law is designed using thefeedback linearization method. The reference trajectory is obtained by trajectorytracking, with the range updating method, the H-V profile generation and trackingguidance performed well.2. An improved equilibrium glide trajectory generationmethod is proposed. The equilibrium glide condition is presented and utilized toestablish the approximate relationship between trajectory parameters and convert allpath constraints to the constraints of control variables. The control variables areparameterized, the parameters of control variable and longitudinal reference trajectorycan be solved with terminate range constraint. The corresponding tracking law is designed using linear quadratic regulator theory. Then the3DOF trajectory iscompleted by longitudinal trajectory tracking control and the heading error corridorcontrol in lateral motion. The equilibrium glide trajectory generation and LQRtracking guidance can overcome the disturbances of initial states and aerodynamicsparameters.To improve the performances of conventional numerical predictor-correctorguidance, a pseudospectral-based online trajectory optimization and feedbackguidance algorithm has been developed and evaluated. The feasibility of using onlinetrajectory optimization to predict the trajectory instead of using numerical integrationis discussed. The good performance is obtained by reasonably choose of the controlupdating period and the number of nodes in optimization calculation. This canprovide an approach for apply the numerical predictor-corrector guidance.The guidance laws with terminal angular constraint in dive phase are studied.The research of this dissertation is an innovative application of optimal controltheory on trajectory design and reentry guidance of Boost-Glide vehicle, which willprovide theoretical support for the overall design and key technology development ofthis kind of vehicle.更多还原