基于等基因序列双重随机遗传算法的复合材料铺层优化

复合材料铺层优化中常用的各种遗传算法，较难同时综合考虑表面45°、分层比例、连续铺层数限制等复杂工程约束问题，基于此，提出一种针对复合材料层压板的等基因序列双重随机遗传算法，在交换和突变算子中引入双重随机算法以保证优化迭代中基因序列的严格相等，基于SABRE 软件实现该优化算法，并通过算例验证算法的正确性。结果表明：该算法可满足均衡性、对称性、表面45°、连续铺层数限制、铺层比例等复杂工程约束，有较高的可靠性与工程适用性。     

基于参考航迹的地面测控站站址规划算法研究

当使用地面测控站接力手段对飞航式导弹进行测控时,就存在测控站的布站问题。结合地理信息系统GIS,建立一种基于参考航迹的测控站站址规划算法,可以为布站规划提供有效的计算机辅助手段。     

考虑减摆器非线性特性的前起落架摆振分析

飞机的前起落架摆振通常在飞机起飞或降落滑跑的过程中发生，对飞机的稳定性和操纵性产生危害，是一种严重的飞机故障。针对某型号无人机，基于动量矩定理，建立考虑起落架侧弯、扭转的摆振数学模型，讨论使用传统油液阻尼减摆器和电磁阻尼减摆器时不同的动力学模型。对于传统油液阻尼减摆器，采用等效线性模型，得到摆振临界稳定阻尼曲线的上下边界；而对于电磁阻尼减摆器的非线性模型，使用分岔分析理论确定系统的摆振稳定区域。结果表明：过大的减摆阻尼对摆振无法起到抑制的作用，得到控制参数平面上摆振的稳定区域，可为后续的起落架减摆设计提供参考。     

Space object material identification method of hyperspectral imaging based on Tucker decomposition

Space object material identification method based on Tucker decomposition is proposed and demonstrated experimentally. Space target generally has a low spatial resolution because of the limitation in detection distance. Hyperspectral imaging (HSI) technology can capture the image from visible light to shortwave infrared continuously while providing the spatial and spectral information of the target, thereby introducing a new space target detection and identification approach. However, the data obtained by the HSI system often contain mixed pixels, thereby causing difficulties in target material identification. In this work, a material identification method of hyperspectral data based on Tucker decomposition is proposed by combining mixed spectral theory with tensor decomposition. The feasibility of the method is verified by using satellite model hyperspectral data with different spatial resolutions compared with the endmember obtained from the non-negative matrix decomposition (NMF), independent component analysis (ICA), tensor singular value decomposition (t-SVD). The average CORR of NMF, ICA, t-SVD and the proposed method is 0.2694, 0.5818, 0.6397 and 0.937, correspondingly. Therefore, the proposed method has demonstrated a more remarkable performance in terms of material identification, the analysis results of the material abundance distribution that used the proposed method.     

SIMULATION OF LARGE CIVIL AIRCRAFT LANDING RESPONSE UNDER CONSIDERATIONS OF FLEXIBLE AIRFRAME

To evaluate the landing response of the large civil aircraft in the conceptual design phase , a method for simulating aircraft landing is given.The model for the shock absorber is investigated.The flexible airframe model is established using finite element model ( FEM ) to analyze its modes.Then , the whole aircraft model with flexible airframe is made for the multibody simulation.Tail-down , two-point , three-point and sideslip landing scenarios are studied.The influence on the landing performance considering mode superposition of the flexible airframe is analyzed.Both longitudinal and spanwise positions of the main landing gear are changed to research the influence on the landing performance.Results show that the method is feasible.The shock absorber axial force of the main landing gear with the flexible airframe is smaller than that of rigid airframe.The number of mode superposition and the position of main landing gear can influence the landing response.     

横截面形状对超声速磁流体发生器性能的影响

通过三维数值模拟研究了不同横截面形状的磁流体(MHD)发生器的热、电磁流动特性,发生器入口采用超声速来流条件,旨在应用于磁流体旁路超燃冲压发动机推进系统。数值模拟采用低磁雷诺数下磁流体五方程模型,通过熵条件格式和超松弛迭代(SOR)法联合算法分别求解Navier-Stokes方程组和电势方程。研究表明在电极壁面上电场、电流以及洛伦兹力等电磁场参数呈周期性变化,由于电极端点效应,电磁场参数在电极端点出现周期性的极值,而在管道中心电极端点效应对电流影响并不大,沿着流向电流保持连续变化。对不同管道横截面形状的发生器的数值模拟表明:由于涡电流和二次流效应的影响,形状参数较小的发生器焦耳热较为严重,二次流较弱;而形状参数较大的发生器焦耳热较小,二次流增强。因此,当形状参数α=0.8时可获得较好的焓提取率和电效率。     

液体火箭发动机有无隔板的热态解数值模拟

用数值方法模拟了液体火箭发动机燃烧室内有无隔板两种情况的热态解。气相控制方程用欧拉坐标系下的Navier-Stokes方程组描述,液相控制方程在Lagrangian坐标系下进行描述。      

起落架油气式缓冲器设计中压缩比的选取

从理论上探讨缓冲器压缩比的选择范围。提出当缓冲器压缩比(静态对全伸展之比q_(so)、全压缩对静态之比q_(ms))的取值范围为2.5～4.5时,既可以较大限度地减少缓冲器体积,又可以把起落架的动载荷限制在较低的范围内,并为以往经验地选取压缩比提供理论基础。     

CAD／CAM技术在模具设计与制造中的应用

ＣＡＤ／ＣＡＭ技术的出现和应用，对传统的模具设计与制造方法有着重大影响。本文以刀柄为例介绍了它的模具结构设计、加工方案，以及应用ＣＡＤ／ＣＡＭ技术解决刀柄模具型腔的曲面造型及数控加工编程的过程。     

弹性飞机地面滑行随机最优控制

将主动控制缓冲器应用于飞机地面滑行减振。建立了飞机在随机跑道激励下,考虑机身俯仰运动与弹性振动的非线性随机动力学模型。采用统计线性化方法,使模型在平衡点附近线性化。加入前置线性滤波器将随机路面高斯激励转换成高斯白噪声激励。基于随机最优控制理论,设计了线性二次型高斯(LQG)控制器。由Monte-Carlo法模拟了路面随机过程,得到了飞机的动响应。通过主动控制缓冲器与被动控制缓冲器的仿真比较可以看出,主动控制缓冲器能够有效提高飞机地面滑行的舒适性与减振性。