一种适用于攻击地面固定目标的最优再入机动制导律

本文运用飞行力学原理和现代控制理论，对攻击地面固定目标的飞行器的再入机动制导方法进行了研究。在考虑飞行器命中目标时有落地速度和速度角要求的条件下，推导出了一种适用于攻击地面固定目标的最优再入机动导引律。并通过模拟计算分析论证了该制导规律的正确性。     

Integrated Entry Guidance for Reusable Launch Vehicle

A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.     

基于变结构控制理论的导弹平滑导引律研究

针对导弹采用变结构导引律攻击机动目标时,容易引起视线角速率的抖动现象,基于变结构控制理论,提出了一种设计简单、具有较好鲁棒性及准确性的平滑导引律。该导引律设计主要通过引入双曲正切函数,消除了攻击导弹的视线倾角增量变化律的抖动现象。通过仿真结果说明:在相同的攻击时间内,对比于比例导引律、变结构导引律,该导引律明显地减小攻击导弹的脱靶量,验证了该导引律的有效性。     

超音速反舰导弹突防的三维制导建模研究

三维变轨制导律的设计是超音速反舰导弹提高突防能力的有效方法。为了深入研究超音速反舰导弹变轨突防的三维制导规律,针对反舰导弹、拦截弹和目标舰艇之间相对运动的特点,分别建立了三维空间中反舰导弹与拦截弹和反舰导弹与目标舰艇的相对运动矢量方程及其视线速率方程,为超音速反舰导弹变轨突防的三维制导规律研究与仿真提供了基础和前提。     

某型产品振动试验目标零位调整时间缩短的分析与实现

针对制导舱振动试验过程中遇到的目标零位调整时间过长的问题,对调零过程进行分析,发现目标模拟发射器在每枚产品振动试验时都要进行调整,才能符合产品振动试验的要求.而工作现场目标模拟发射器支架与目标模拟发射器之间不是刚性连接结构,使得整个振动试验因为需要目标调零而变得时间过长.改造升级现有支架和目标模拟发射器之间的连接座成为...     

高校毕业设计（论文）环节存在问题及对策研究

分析高校毕业设计（论文）教学环节存在的8个方面的问题,提出“建立毕业设计（论文）规范、制度”“加强毕业设计（论文）工作监控”“进行高校毕业设计（论文）工作的量化考核创新毕业设计（论文）指导模式推行毕业设计（论文）管理和指导网络化”和“毕业设计（论文）融入信息素质教育”6个方面的对策,简略介绍西安航空学院在毕业设计（论文）环节教改研究方面取得的主要成果和今后研究的主要问题。     

基于MPSP的次优滑模制导律

针对导弹拦截机动目标的问题,提出了一种能满足多终端约束的次优滑模制导律(Sub-OSMG).该算法将模型预测静态规划(MPSP)与滑模控制(SMC)相结合,解决了MPSP在系统模型不精确时由于依赖模型预测而导致的控制量发散问题;基于三自由度相对运动方程建立所提出的制导律,其鲁棒性通过Lyapunov稳定性理论进行了证明;在滑模控制的设计中引入一种较为新颖的滑模面,巧妙地继承了两种方法的优点,其区别于传统扩展比例导引(APN),在仅知机动幅值的情况下,能精确地击中目标.仿真结果表明,所提出的Sub-OSMG能够有效地抵消外部扰动,具有更高的精度、更好的鲁棒性、更小的控制代价.     

Advanced high-order nonlinear chirp scaling algorithm for high-resolution wide-swath spaceborne SAR

Spaceborne Synthetic Aperture Radar (SAR) is a well-established and powerful imaging technology that can provide high-resolution images of the Earth’s surface on a global scale. For future SAR systems, one of the key capabilities is to acquire images with both high-resolution and wide-swath. In parallel to the evolution of SAR sensors, more precise range models, and effective imaging algorithms are required. Due to the significant azimuth-variance of the echo signal in High-Resolution Wide-Swath (HRWS) SAR, two challenges have been faced in conventional imaging algorithms. The first challenge is constructing a precise range model of the whole scene and the second one is to develop an effective imaging algorithm since existing ones fail to process high-resolution and wide azimuth swath SAR data effectively. In this paper, an Advanced High-order Nonlinear Chirp Scaling (A-HNLCS) algorithm for HRWS SAR is proposed. First, a novel Second-Order Equivalent Squint Range Model (SOESRM) is developed to describe the range history of the whole scene, by introducing a quadratic curve to fit the deviation of the azimuth FM rate. Second, a corresponding algorithm is derived, where the azimuth-variance of the echo signal is solved by azimuth equalizing processing and accurate focusing is achieved through a high-order nonlinear chirp scaling algorithm. As a result, the whole scene can be accurately focused through one single imaging processing. Simulations are provided to validate the proposed range model and imaging algorithm.     

地球大气边缘高超声速飞行再入点调整方法

分析环境波动对地球大气边缘高超声速飞行的影响,论证了利用微弱气动力实现再入点调整的可能性。提出神经网络I-PIDA姿态控制策略,控制力矩由脉宽调制驱动的反作用推力器实现,利用模糊预测制导的方法实现再入点的精确调整。仿真算例说明该方法可以实现姿态跟踪和再入点的位置调整,并具有较强的鲁棒性。     

考虑目标安全性的最优协同拦截制导律研究

针对目标和其发射的拦截弹对来袭攻击弹进行协同拦截问题,设计了一种最优协同拦截制导律。建立描述目标、攻击弹和拦截弹三者相对运动关系的模型,引入零控脱靶量对模型进行降阶处理。考虑拦截弹对攻击弹的拦截精度、拦截末端时目标的安全性以及目标、拦截弹的控制能量问题,基于攻击弹-拦截弹零控脱靶量、攻击弹-拦截弹终端横向相对运动速度零控脱靶量、目标-攻击弹零控脱靶量以及目标和拦截弹的加速度,建立了性能指标函数,同时考虑目标和拦截弹加速度的有限性,基于极小值原理设计了最优协同拦截制导律。仿真结果表明,相比目标和拦截弹独立飞行的情况,采用协同拦截制导律,在考虑了目标安全性的前提下,机动性较弱的拦截弹能够以较平直的弹道成功拦截攻击弹。