船闸闸室灌泄水过程非稳定渗流特性

为了研究船闸闸室在非均质成层地基、灌泄水条件下的非稳定渗流特性,根据渗流基本理论,将渗流分为固结渗流与瞬时稳定渗流。以工程实例为依托,利用有限元软件ABAQUS建立二维渗流模型,模拟船闸灌泄水过程,考虑流固耦合,分析非稳定渗流特性及影响。结果表明,随着灌泄水的周期性变化,测压管水位存在周期性、衰减性与滞后性;在灌泄水过程中,存在泄水、灌水速度零点;泄水末期,非稳定渗流计算的渗透应力沿高程均大于低水稳定渗流计算值,渗透稳定系数降低,发生渗透破坏的可能性加大。因此,在船闸防渗设计中应充分考虑非稳定渗流场的影响。     

旋转弹引信用卫星定位接收信号旋转解调方法

为解决旋转弹飞行中的高旋转、高动态条件会造成卫星定位接收系统无法正常定位的问题,针对旋转、动态环境开展了旋转弹卫星定位接收信号旋转解调方法的研究.详细分析了旋转条件对卫星定位信号接收的影响,并针对旋转特性设计了旋转跟踪解调环,用于对旋转的跟踪与解调,给出了旋转弹卫星定位信号接收系统的设计方案,基于Simulink实现了旋转弹卫星定位信号接收系统的仿真,并给出了相应的仿真与实验结果.结果表明,设计的以旋转跟踪环为核心的旋转弹卫星定位信号接收系统,在中心频率为200 Hz的情况下跟踪范围可达到±40 Hz,较好地满足了转速在200转/s左右的旋转弹信号接收要求.      

水下航行器附连水质量的理论及实验研究

以二维无限长圆柱在水下的垂向振动为例,对其有限区域的不可压缩流场进行分析;通过数值计算并借鉴刘易斯法,分析了水域宽度比、水深比和浸没深度比等无量纲参数对刚体附连水质量的影响;提出了水下航行器附连水质量的快速预测公式.结果表明:刚性壁面可使刚体的附连水质量增大,但当刚体与壁面的距离增加到一定程度(截面半径的5倍)时,刚性壁面的影响可以忽略;自由表面可使刚体的附连水质量减小,当刚体与自由表面的距离达到截面半径的6倍时,可以忽略自由表面的影响;当刚体的垂向运动频率较高或刚体与自由表面的距离较大时,可以认为自由表面的速度势为零.     

实现船舶稳性的多油舱自适应调度算法及仿真

针对油舱对船舶浮态与稳性的影响，研究了保持船舶稳性的多油舱自适应调度控制算法，并用WinCC (Windows Control Center)组态软件编写了船舶自动浮态调整仿真系统。在系统架构上，采用布尔逻辑表构建了油舱、泵、管路之间的连通关系，并根据浮态方程计算出舱群之间的调驳油量，再根据多变量多约束的自适应优化调度算法实现了油舱驳油过程中浮态的平衡。仿真结果表明调度算法可以对船舶的浮态进行有效调整，并保持船舶稳性，避免了由油舱油量分布不均给船舶带来的不利影响，保障了航行安全。     

基于区间证据推理的不确定性航线配船方法

为弥补不确定性航线配船模拟算法的不足,提出一种基于区间证据推理的航线配船解析算法.该方法以证据推理理论为基础,以船舶公司期望效用最大化为目标,考虑航线特征及船舶属性等因素,构建出一个多航线、多船型的航线配船模型.与目前的模拟算法相比,该方法具有稳定性好、准确性高、可以处理模糊数据等优点.最后,通过算例验证了模型的可行性和方法的有效性.     

New rapid transfer alignment method for SINS of airborne weapon systems

Transfer alignment is an effective alignment method for the strapdown inertial navigation system （SINS） of airborne weapon systems. The traditional transfer alignment methods for large misalignment angles alignment use nonlinear transfer align- ment models and incorporate nonlinear filtering. A rapid transfer alignment method with linear models and linear filtering for ar- bitrary misalignment angles is presented. Through the attitude quaternion decomposition, the purpose of transfer alignment is converted to estimate a constant quaternion. Employing special manipulations on measurement equation, velocity and attitude linear measurement equations are derived. Then the linear trans- fer alignment model for arbitrary misalignment angles is built. An adaptive Kalman filter is developed to handle modeling errors of the measurement noise statistics. Simulation results show feasibili- ty and effectiveness of the proposed method, which provides an alternative rapid transfer alignment method for airborne weapons.     

Self-alignment of full skewed RSINS：observability analysis and full-observable Kalman filter

Traditional orthogonal strapdown inertial navigation sys-tem （SINS） cannot achieve satisfactory self-alignment accuracy in the stationary base： taking more than 5 minutes and al the iner-tial sensors biases cannot get ful observability except the up-axis accelerometer. However, the ful skewed redundant SINS （RSINS） can not only enhance the reliability of the system, but also improve the accuracy of the system, such as the initial alignment. Firstly, the observability of the system state includes attitude errors and al the inertial sensors biases are analyzed with the global perspective method： any three gyroscopes and three accelerometers can be assembled into an independent subordinate SINS （sub-SINS）;the system state can be uniquely confirmed by the coupling connec-tions of al the sub-SINSs;the attitude errors and random constant biases of al the inertial sensors are observable. However, the ran-dom noises of the inertial sensors are not taken into account in the above analyzing process. Secondly, the ful-observable Kalman filter which can be applied to the actual RSINS containing random noises is established; the system state includes the position, ve-locity, attitude errors of al the sub-SINSs and the random constant biases of the redundant inertial sensors. At last, the initial self-alignment process of a typical four-redundancy ful skewed RSINS is simulated： the horizontal attitudes （pitch, rol ） errors and yaw error can be exactly evaluated within 80 s and 100 s respectively, while the random constant biases of gyroscopes and accelero-meters can be precisely evaluated within 120 s. For the ful skewed RSINS, the self-alignment accuracy is greatly improved, mean-while the self-alignment time is widely shortened.     

一种有效估计着陆引导信号多径时延的方法

利用导航信号收发已知且具有周期性的特点,提出了一种对着陆引导信号多径时延进行有效估计的方法。该方法首先计算相关函数,而后对相关函数进行二次微分,对时延值进行初步估计。最后通过直线拟合算法和比例拟合算法提高估计精度。通过计算机仿真,验证了算法的有效性。该算法具有在低采样率的条件下,估计精度高的特点。     

GPSNISNAV integrated relative navigation and attitude determination system for ultra-close spacecraft formation flying

For the improvement of accuracy and better fault-tolerant performance, a global position system (GPS)/vision navigation (VISNAV) integrated relative navigation and attitude determination approach is presented for ultra-close spacecraft formation flying. Onboard GPS and VISNAV system are adopted and a federal Kalman filter architecture is used for the total navigation system design. Simulation results indicate that the integrated system can provide a total improvement of relative navigation and attitude estimation performance in accuracy and fault-tolerance.     

船体复杂外板成型评价方法

船体复杂外板的成型评价是曲面外板成型加工的必要环节,能为外板的二次加工提供依据.结合水火弯板加工工艺,提出了一种成型评价方法.该方法先通过三维空间变换,实现目标曲面与检测曲面的匹配.然后,利用多项式拟合与参数分解方法,实现检测曲面偏差量的分解.最后,给出了成型率的计算方法,实现对检测曲面成型度的评价.实验结果表明,本方法能对复杂外板加工过程中的横向、纵向以及扭向成型情况进行客观的评价,而且本方法的评价指标与加工工艺紧密结合,可作为曲面外板加工参数的推理依据.