A trajectory shaping guidance law with field-of-view angle constraint and terminal limits

In this paper, a trajectory shaping guidance law,which considers constraints of field-of-view(FOV) angle, impact angle, and terminal lateral acceleration, is proposed for a constant speed missile against a stationary target. First, to decouple constraints of the FOV angle and the terminal lateral acceleration, the third-order polynomial with respect to the line-ofsight(LOS) angle is introduced. Based on an analysis of the relationship between the looking angle and the guidance coefficient,the boundary of the coefficient that satisfies the FOV constraint is obtained. The terminal guidance law coefficient is used to guarantee the convergence of the terminal conditions. Furthermore, the proposed law can be implemented under bearingsonly information, as the guidance command does not involve the relative range and the LOS angle rate. Finally, numerical simulations are performed based on a kinematic vehicle model to verify the effectiveness of the guidance law. Overall, the work offers an easily implementable guidance law with closed-form guidance gains, which is suitable for engineering applications.

基于偏振干涉成像光谱仪的视场增强和相位热漂移补偿关键技术的研究

偏振干涉成像光谱技术以傅里叶变换光谱学为理论基础,以一系列起偏/检骗器、剪切分束器和延时晶体等双折射晶体材料为主要结构,较之传统光栅式色散型光谱仪具有多通道、图谱合一、大光通量、高信噪比和抗环境振动干扰等一系列优点,并且结合多普勒光谱学相关原理和技术,已被广泛应用在各种天文学和天体物理学测试与计量领域如空间遥感、视向速度、宇航飞行、月球探测等。但是许多前人研究工作中仍然存在两个尚未妥善解决的问题:(1)视场受限。普通型偏振干涉成像光谱仪存在远场条纹的弯曲而使系统视场角限制在±2°以内,严重影响傅里叶变换后的光谱重构精度;(2)相位热漂移。晶体的热胀冷缩和双折射率之差随温度变化的特性导致像面干涉条纹发生随机抖动误差,将严重影响以多普勒频移为原理的视向速度等测量精度。因此,首先引入一块半波片构成增强型的Savart剪切分束器实现主动的视场展宽,可以使增强后的观察视场角达到±10°左右。这一改进不仅提高了傅里叶光谱变换的算法精度,同时也大幅增加光通量从而实现对微光光谱进行高信噪比的探测与标定。另外,为了消除环境温度造成的相位热漂移误差,选用偏硼酸钡(α-BBO)和铌酸锂(LiNbO3)两种晶体进行精密组合匹配。该关键技术利用这两种晶体的双折射率之差随温度变化的相反特性,从而实现相位热漂移误差补偿。实验证明,在实验室环境温度下热相位漂移误差不超过0.02rad。通过这些方案改善偏振干涉成像光谱仪的测试精度,拟实现对天文光梳以及其他大型天文光谱仪器快速而精确的标定与测试。