基于时间累计法的工时定额评估数学模型的建立

采用时间累计法对基本维修作业建立数学模型，解决了表格式工时定额数据多、误差大、使用不便和管理复杂等问题。而且，通过设计和建立数学模型数据库系统，为计算机辅助制定工时定额创造了条件。以基本维修作业为研究对象，系统地分析了基本维修作业划分和量化的方法及步骤，包括模型确定的方法和系数求解公式，并对基于累计法的基本维修作业数学模型进行了深入的研究，从而得到了工时定额评估的一般方法。     

测控应答机下行调制度问题的技术分析

针对应答机采用不同的接收信号功率控制方式，对下行测距调制度、残留遥控调制度以及转发噪声调制度的情况进行了理论分析，得到了各种情况下的调制度数学模型，可供读者在航天工程的测控链路设计及应答机设计时参考。     

一种利用极化信息的HRRP-ATR方法

在研究了单极化条件下高分辨率距离像的目标识别后，给出一种利用目标全极化信息的投票识别方法。实验结果表明，该方法具有较高的识别率。     

模糊模式识别方法在最后进近排序中的应用

介绍了美国正在研究的最后进近间隔工具(FAST)的排序思想,利用该排序思想,讨论了模糊模式识别排序理论在最后进近中的具体应用,并进行了仿真.仿真结果表明,该方法能很好地模拟管制员的决策过程,使到达飞机流快速而有序地进入机场着陆.     

正确认识德育内涵--构建适合人才发展的德育教育新模式

从探讨长期困扰人们的德育内涵入手 ,历史的剖析了德育内涵对人才素质教育的意义 ,期望通过粗浅的理论分析 ,明晰现代社会实施德育教育的方法 ,从而构建适合人才发展的德育教育新模式。     

A unified accretion–ejection paradigm for Black Hole X-ray binaries

We present a unified accretion–ejection picture that explains the different spectral state of Black Hole X-ray binaries (BHXrB) from radio to X/γ-rays. In this view, the central region of BHXrB has a multi-flow configuration which consists in (1) an outer standard accretion disc, (2) an inner magnetized accretion disc driving, (3) a self-collimated electron–proton MHD jet, surrounding and (4) a relativistic electron–positron beam when adequate conditions are met. This picture provides a simple and unified explanation to the various canonical spectral states of BH X-ray binaries, by varying the transition radius r_J between the inner disc driving jets and the outer standard disc. In this framework, large r_J correspond to Quiescent and Hard states while small r_J correspond to Thermal Dominant ones. In between these two extremes, r_J can reach values that switches on the pair cascade process giving birth to a relativistic electron–positron beam. This would correspond to the bright intermediate state.     

基于复合推进系统动态模型-状态变量模型的航空发动机直接推力预测控制

直接推力控制可以有效改善推力控制的品质,针对航空发动机直接推力控制问题,进行了模型预测控制(Model Predictive Control, MPC)研究。为了提升航空发动机推力控制的精度,提出了基于复合推进系统动态模型-状态变量模型(Compact Propulsion System Dynamic Model-State Variable Model-State Variable Model, CPSDM-SVM)的航空发动机直接推力预测控制方法。CPSDM实时估计出不可测参数（推力、喘振裕度等）的基准值,SVM则根据未来输入实时预测发动机未来响应。由于CPSDM将发动机分为进气道、核心机、喷管、喘振裕度、推力等进行建模,在兼顾精度的同时,提高机载模型的实时性。CPSDM-SVM作为MPC算法中的预测模型,具有较高的精度和实时性。仿真结果表明,在与基于分段线化模型的传统模型预测控制方法实时性基本相同的情况下,所提出方法控制效果有明显的提升,调节时间减小了1.17s。所提出方法稳态控制精度为0.08%,传统方法稳态精度为2.58%。因此,所提出方法在保证实时性的条件下,提升了控制精度和控制效果。     

Sub-optimal fixed-finite-horizon spacecraft configuration control on SE(3)

For achieving the desired configuration of spacecraft at the desired fixed time, a sub-optimal fixed-finite-horizon configuration control method on the Lie group SE(3) is developed based on the Model Predictive Static Programming (MPSP). The MPSP technique has been widely used to solve finite-horizon optimal control problems and is known for its high computational efficiency thanks to the closed-form solution, but it cannot be directly applied to systems on SE(3). The methodological innovation in this paper enables that the MPSP technique is extended to the geometric control on SE(3), using the variational principle, the left-invariant properties of Lie groups, and the topology structure of Lie algebra space. Moreover, the energy consumption, which is crucial for spacecraft operations, is considered as the objective function to be optimized in the optimal control formulation. The effectiveness of the designed sub-optimal control method is demonstrated through an online simulation under disturbances and state measurement errors.     

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.     

交会对接成像敏感器的光点筛选改进

首先介绍了交会对接成像敏感器图像光点匹配算法.基于对在轨图像光点动态特性的研究,为解决交会对接过程中目标误识别、误匹配,以及匹配、适配过程严重耗时的缺陷,提出了光点形状筛选和光点大小分组2套匹配改进算法,并设计了基于光点形状大小动态特性改进的光点匹配算法.该方法以交会对接走廊中不同相对距离时目标光斑大小的最大差别为依据,针对每一个光点,仅将光斑大小与其在同一合理范围内的其他光点一起进行目标匹配.实验结果表明,该方法杜绝误匹配等异常错误的同时,极大地提高了运算效率.该方法可以成为在轨交会对接末段制导实时测算的重要保障,目前已在众多航天器在轨交会对接、空间交会逼近试验中使用.