刚柔耦合系统神经网络跟踪控制方法研究

针对刚柔耦合系统的姿态跟踪及振动抑制问题,采用一次近似动力学模型,提出了一种神经网络控制方法.典型刚柔耦合系统由一个中心刚体和带有末端质量块的柔性附件组成,假设系统参数未知并且截断模型具有任意的有限维.该方法利用多层神经网络补偿系统非线性项及未建模动态,利用其自学习和自适应能力,降低不确定性因素对系统产生的影响;并且控制器只利用姿态角和角速度信息进行反馈控制,不需要知道柔性附件振动信息.理论分析和实验结果表明该方法使闭环系统所有信号一致最终有界,能有效地使系统完成姿态跟踪,而且能显著地减少柔性结构的弹性振动.     

Plume aerodynamic effects of cushion engine in lunar landing

 During the second period of China "Tanyue" Project, the explorer will softland on the moon. The cushion engines are used to decelerate the explorer and reduce the impact on the lunar ground. It is necessary to study its plume effects on the explorer component. The self-developed PWS (Plume WorkStation) software based on direct simulation Monte Carlo (DSMC) method is used to simulate the plume effects of two 150 N engines. Due to the complex structure of the explorer, PWS uses a decoupling method to treat the boundary mesh, which mainly interacts with simulation particles, and has no relation with the computational grids. After the analytical expressions of plane surfaces and curved surfaces of each boundary block are given, the particle position within or without the boundary blocks can be easily determined. Finally the 3D plume field of two 150 N engines is simulated. The pressure, temperature and velocity distributions of plume field are clearly presented by three characteristic slices. The aerodynamic effects on the explorer bottom, the landfall legs and antenna are separately shown. The compression influence on the plume flow of four landfall legs can be observed.     

Impact vibration reduction for flexible manipulators via controllable local degrees of freedom

When performing operation tasks, the interaction between a flexible manipulator and a grasped object usually results in an impact. In this paper, a new way is suggested to alleviate impact vibration of a flexible manipulator via its structural characteristic when capturing a moving object. Controllable local degrees of freedom are introduced to the topological structure of the flexible manipulator, and used as an effective tool to combat impact vibration through dynamic coupling. A corresponding method is put forward to reduce impact vibration responses of the flexible manip- ulator via the controllable local degrees of freedom. By planning motion of the controllable local degrees of freedom, appropriate control force can be constructed to increase the modal damping and stiffness and eliminate the exciting force simultaneously, thereby reducing impact vibration responses of the flexible manipulator. Simulations are conducted and results are shown to prove the presented method.     

Adaptive modification of turbofan engine nonlinear model based on LSTM neural networks and hybrid optimization method

An accurate and reliable turbofan engine model which can describe its dynamic behavior within the full flight envelop and lifecycle plays a critical role in performance optimization, controller design and fault diagnosis. However, due to the performance differences caused by the tolerance of engine manufacturing and assembly, and performance degradation during continuously stringent environmental regulations, the model accuracy is severely reduced. In this paper, an adaptive modification method of turbofan engine nonlinear Component-Llevel Model (CLM) based on Long Short-Term Memory (LSTM) Neural Network (NN) and hybrid optimization algorithm is pro-posed. First, a dynamic compensator with a combined LSTM NN architecture is constructed to compensate for the initial error between the experimental data and CLM of a turbofan engine under health condition. Then, a sensitivity analysis approach based on the entropy coefficient and technique for order preference by similarity to an ideal solution integrated evaluation is developed to choose the unmeasurable health parameters to be adjusted. Finally, a parallel hybrid optimization algorithm is developed to complete the adaptive model modification when the performance degrades. The proposed method is verified on a military low-bypass twin-spool turbofan engine, and the experimental results show the effectiveness of the proposed method.     

Adaptive sensitive frequency band selection for VMD to identify defective components of an axial piston pump

The underlying study investigates single valued neutrosophic entropy based adaptive sensitive frequency band selection for variational mode decomposition(VMD) for the purpose of identifying defective components in an axial pump. The proposed methodology is applied in the following steps. First, VMD is applied for decomposing vibration signals into various frequency bands, called as modes. After computing energy of each VMD, the lower(minimum) and upper(maximum) bounds from these energy readings ...     

采用BP网络辨识航空发动机数学模型

运用ＢＰ网络和实测数据作为学习样本，对某型航空发动机的数学模型进行了辨识研究。辨识模型输出的结果与实测数据比较误差较小。这种方法收敛速度快、精度高，结果表明用ＢＰ网络辨识方法能够得到比较精确的发动机数学模型。     

电子回旋共振推力器C/C复合材料栅极的力学性能

为了研究电子回旋共振推力器在搭载火箭升空过程中,过载和振动环境对栅极带来的影响,采用有限元分析软件建立了10 cm C/C复合材料栅极的有限元分析模型,计算分析了不同C/C复合材料栅极的力学性能、频率响应和振动模态。结果表明:20g过载下,栅极的最大变形量为6.12×10-4mm;在5~800 Hz激振下,栅极频率响应的最大位移为2.3×10-6mm;过载对栅极的影响要大于振动对它的影响,但是这两个值都在安全门限内;综合分析栅极频响和模态分析的计算结果,栅极仅在其第一阶模态处于外界激振发生共振。     

发动机构型分析与评价软件的设计与实现

在发动机初步设计阶段,要根据对发动机的构型方案进行分析与评价,来选择发动机主要设计参数,并从多个发动机方案中选择最佳方案。作者以液体推进剂火箭发动机为研究对象,建立了一个发动机构型分析与评价软件IRE/CAA。本文阐述了软件LRE/CAA的设计思想,介绍了软件所包括的模块和各个模块的功能,并说明了在软件实现过程中一些问题的处理方法。     

液体火箭发动机燃烧室的一种分区模型

发展了燃烧室的分区模型 :将燃烧室分为两个区 ,一个是燃烧区 ,采用时滞燃烧瞬时均匀混合模型 ,另一个是流动区 ,连同喷管一起 ,采用一维理想气体流动的有限元状态变量模型。给出了一个利用该模型计算发动机起动过程的一个算例 ,计算结果表明该模型可较好地描述液体火箭发动机燃烧室的建压及非稳态流动过程。模型采用状态方程形式 ,具有形式简单、计算简便的特点 ,适用于液体火箭发动机的控制与仿真     

弹用涡喷发动机振动故障诊断技术探讨

简要地论述了弹道涡喷发动机振动故障诊断的理论基础，介绍了弹用涡喷发动机振动故障的一些特点，设计一套弹用涡喷发动机振动故障诊断系统，探讨了弹用涡喷发动机振动故障诊断的方法。