Sensitivity Analysis of Finite-Lag Receivers

This paper presents the sensitivity analysis of a class of receivers called finite-lag receivers, introduced by the authors in [1] through [3]. Since these receivers are based on the use of fixed-lag smoothing techniques, algorithms for the calculation of large-scale and small-scale sensitivities of fixed-lag smoothing are derived using a state augmentation approach. Steady-state analysis of these algorithms shows that an explicit relation can be obtained between sensitivity coefficients of fixed-lag smoothing and filtering. The specific case of sensitivity to variations in the measurement (channel) noise is considered as an example. These results are applied to study the sensitivity performance of the finite-lag receivers for analog communication. It is shown, for example, that finite-lag receivers for AM signals, besides being superior in performance [1]-[3], [11], in terms of output SNR or error variance, are also much less sensitive to the additive noise power level, compared to zero-lag receivers.     

Ni基超合金强化相的电子结构和层错能的计算

为了控制和调整合金中位错分解方式，最终达到控制蠕变机制和提高合金持久寿命的目的。应用实空间Recursion方法，计算了Ni3Al强化相中[111]层错的电子结构及加入微合金化元素Co的效应。建立了Ni3Al中沿[111]方向生长的晶体模型和产生层错后的晶体模型，给出了体元的电子态密度，费米能级和层错能。通过计算得到了以下结论：(1)在Ni3Al晶胞中Al对于总态密度的贡献在整个能量范围内较小，总态密度主要来自过渡金属Ni。(2)用Co原子代替Ni3Al中Al原子可以降低Ni3Al层错能。     

In-Flight Alignment and Calibration of Inertial Measurement Units?Part II: Experimental Results

This is the second part of a two-part paper which summarizes work pursued by the author in 1967 [2]. The paper describes the application of minimum-variance estimation techniques for in-flight alignment and calibration of an inertial measurement unit (IMU) relative to another IMU and/or some other reference. The first paper [1] formulates the problem, and this paper reports numerical results and analyses. The approach taken is to cast the problem into the framework of Kalman-Bucy estimation theory, where velocity and position differences between the two IMU's are used as observations and the IMU parameters of interest become part of the state vector. Instrument quantization and computer roundoff errors are considered as measurement noise, and environmental induced random accelerations are considered as state noise. In this paper, numerical results for three important IMU error parameter configurations are presented and discussed. The main results of the paper determine the effects of state and observation noise levels and the nominal trajectory on the identifications of the errors for these configurations. A discussion of the minimum number of trajectory maneuvers and of the optimal trajectory maneuvering is given.     

A. M. Hubert and C. Jaschek (eds.), B[e] Stars

The B[e] stars are early type stars with hydrogen emission lines, forbidden [FeII] and [OI] emission lines, and with an IR excess due to circumstellar dust. These properties may occur in stars of quite different evolutionary stages. In fact, the group of B[e] stars is very inhomogeneous, and contains pre-main sequence stars, supergiants with disks, compact planetary nebulae, symbiotic stars, and a group of stars with unclear evolutionary phase. The book gives the proceedings of a workshop in Paris in 1997 in which the properties and evolutionary phases of the B[e] stars are discussed. It contains chapters on: (1) the definition of B[e] stars, (2) distances, kinematics and the distribution in our Galaxy, (3) spectroscopy, (4) infrared properties, (5) photometry, polarimetry and variability, (6) models for winds and disks, (7) evolutionary stages, (8) revised classification of B[e] stars. The book ends with an object list of all B[e] stars. The book is very useful for students and researchers of hot star winds and gives nice overviews of the observations and theories and remaining puzzles of these strange objects with winds and outflowing dust-forming disks. This revised version was published online in August 2006 with corrections to the Cover Date.     

In-Flight Alignment and Calibration of Inertial Measurement Units?Part I: General Formulation

This is the first part of a two-part paper which summarizes work pursued by the author in 1966 [1]. The paper describes the application of minimum-variance estimation techniques for in-flight alignment and calibration of an inertial measurement unit (IMU) relative to another IMU and/or some other reference. The first part formulates the problem, and the second part [2] reports numerical results and analyses. The approach taken is to cast the problem into the framework of Kalman-Bucy estimation theory, where velocity and position differences between the two IMU's are used as observations and the IMU parameters of interest become part of the state vector. Instrument quantization and computer roundoff errors are considered as measurement noise, and environmental induced random accelerations are considered as state noise. Typical applications of the technique presented might include the alignment and calibration of IMU's on aircraft carriers, the initialization of rockets or rocket airplanes which are launched from the wing of a mother ship, the alignment and calibration of IMU's which are only used in the latter phases of rocket flight, and for the initialization/updating of SST guidance systems.     

Comments on "on Probability of Error in Decision Feedback Equalizer"

The above-mentioned paper [1] derives bounds on the error probability of a decision feedback equalizer (DFE) which are claimed to be significantly tighter than the earlier upper bound of [2]. Unfortunately, [1] makes an unsupportable assumption which reddars the conclusions incorrect. We show that valid bounds can be obtained by the methods of [1], but that for the numerical example of [2] , the resulting upper bound is never tighter than, and sometimes significantly weaker than, that derived in [2]. Similarly, a lower bound derived by the method of [1] is shown for the same numerical example to be very close to the error-free past lower bound previously known.     

A Note on Satellite Dynamics

It is demonstrated here that inertial differentiation of angular momentum-is independent of the choice of the moving reference coordinate system. The results agree with Greensite [1] and contradict Sen's results [2] by indicating a basic error in his derivation. However, Sen's step [2] is correct.     

多向铺层碳/环氧复合材料特性及声发射分析

 本文对六种多向铺层的碳纤维增强环氧复合材料的拉伸破坏性能进行了研究,并采用声发射技术监测其损伤扩展过程,分析了它们的破坏机理。 新型的高性能碳纤维增强环氧复合材料应用于宇航、机械及体育器具等,由于工作条件及受力情况是复杂的,采用多向铺层才能满足受拉、压、弯、剪、扭等不同载荷的分别组合,具体铺层设计要针对主要承力情况来确定。多向铺层复合材料的损伤破坏比单向铺层的情况复杂,更需要采用试验的手段来研究它们的力学性能和破坏机理。在非破坏性测试中声发射技术的特点在于能够配合加载装置在进行试验过程中检测并记录复合材料的破坏过程,而且不移动探头的位置即可监测材料的较大区域,因此应用愈来愈多。声发射技术是利用材料或构件受力变形或损伤过程中应变释放产生弹性波这一原理来检测材料的缺陷、退化和破坏,评定材料的性能。声发射技术可以检测复合材料的剪切破坏及拉伸屈服破坏、分层及纤维断裂、粘接强度等。 本工作对六种多向铺层碳/环氧复合材料（包括0/90、±45°、30/60和三种碳布）进行拉伸试验,确定了它们的强度、模量、最大应变率及泊松比,给出六种不同铺层的应力应变关系以及声发射信号量的关系。采用声发射技术配合显微镜观测手段分析不同铺层的碳/环氧材料的声发射表征     

碳纤维复合材料层压板低速冲击试验研究

为研究复合材料不同铺层结构的抗冲击性能,采用碳纤维预浸料制备了单向[0°]8和正交[0/90]2s铺层2种不同结构的碳纤维复合材料层压板,并使用Instron 9250落锤冲击测试仪测试其低速冲击性能,得到了载荷-时间曲线,分析了2种不同铺层方式的复合材料层压板的低速冲击加载力学性能,得到复合材料层压板的破坏形态来分析其破坏方式。结果表明:2种铺层方式产生了不同的破坏模式,正交[0/90]2s的复合材料层压板的抗低速冲击能力要优于单向[0°]8铺层的。     

Comments on "Computationally Efficient Bank of Rectangular Digital Filters"

In [1] a scheme for forming a rectangular FIR filter bank is described using only a few percent of the number of multiplications required by straightforward procedures. The sidelobe level suffers degradation. Attention is drawn to a different scheme published in [2] and [3] which needs even fewer multiplications without degradationvof the sidelobe level.     

某型燃气涡轮发动机风车状态内阻力的计算

由于很多燃气涡轮发动机都缺乏计算风车特性必需的低转速状态的部件特性，给计算发动机风车状态的特性带来了很大的困难。但是，风车特性是燃气涡轮发动机设计和使用过程中必须考虑的，因此，本文参考尤．阿．李特维诺夫提出的计算发动机风车特性的方法，计算了燃气涡轮发动机风车状态时的内阻力。从计算结果分析，该方法不依赖于部件特性，非常适合燃气涡轮发动机的风车特性计算。     

Al-Cu-Mg合金中时效相S′的二次衍射效应研究

本文利用透射电镜研究了Al-Cu-Mg合金中S′相及S相在铝基体基本带轴上的复合衍射花样。选区衍射表明,由S′相相对于铝基体存在的12种变体及其二次衍射效应构成了复合衍射图。铝基体[112]带轴的近似三等分点是由S′相的[914]带轴及二次衍射造成,并与S’相的<101>、<110>强衍射构成了复合衍射花样;铝基体[111]带轴主要由S′相的<514>强衍射构成;铝基体[111]带轴主要由S′相的<013>和<021>强衍射构成。     

Effect of hygrothermal aging on moisture diffusion and tensile behavior of CFRP composite laminates

Carbon Fiber Reinforced Polymer (CFRP) composites are widely used in aircraft structures, because of their superior mechanical and lightweight properties. CFRP composites are often exposed to hygrothermal environments in service. Temperature and moisture can affect the material properties of composites. In order to make clear the moisture diffusion behavior and the properties degradation of composites, the TG800/E207 composite laminates with four stacking sequences [0]₁₆, [90]₁₆, [±45]_4s, and [(+45/0/0/–45)_s]_s are designed and manufactured. Moisture absorption tests are carried out at 80 ℃, 90 %RH. It is shown that the moisture absorption curves of composite laminates present a three-stage. A modified Fickian model was proposed to capture the diffusion behavior of TG800/E207 composite laminates. The relationships among the non-Fickian parameters, the environmental parameters and the stacking sequences of CFRP were correlated and compared. Results showed that the modified Fickian curve is sensitive to the diffusivity of Stage I and Stage II. Compared with unaged specimens, the maximum tensile stress for [0]₁₆, [90]₁₆, [±45]_4s, and [(+45/0/0/–45)_s]_s decreased by 14.94 %, 28.15 %, 11.96 %, and 26.36 %, respectively. The strains at failure for [0]₁₆, [90]₁₆, [±45]_4s, and [(+45/0/0/–45)_s]_s decreased by 55.38 %, 62.65 %, 46.41 %, and 31.71 %, respectively. The elastic modulus for [0]₁₆, [90]₁₆, [±45]_4s, and [(+45/0/0/–45)_s]_s increased by 90.93 %, 94.57 %, 49.22 %, and 8.22 %, respectively. [90]₁₆ sample has the minimum saturated moisture content and the maximum strength degeneration.     

计算航空器起落架起转、回弹载荷的解析方法

本文是对文献[1]的补充。文献[1]中给出的公式,仅适用于t_p≤t_(max)情况。对于t_p>t(max),需另行推导计算公式。本文在文献[1]的假设及公式基础上,导出了适用于t_p>t_(max)的公式,并对其应用及有关问题进行了讨论。最后给出了算例结果。     

固体推进剂药浆适应期的研究

本文研究了抑制剂乙酰丙酮(HAA)对硝酸酯增塑的端羟基共聚醚和多异氰酸酯固化反应的影响.通过改变〔HAA〕/〔FeAA〕和〔HAA〕/〔T-12〕的摩尔比,可以有效地调节其固化反应的适应期.在固体含量为70～75%的配方中,采用HAA/T-12固化催化体系,药浆的适应期得以延长,并给出合格的固化样品.     

基于筏化的镍基单晶合金高温蠕变模型

采用应力法以及界面能法对不同取向的镍基单晶合金在950℃下的筏化类型进行了预测.上述两种方法的筏化预测结果一致,[001]取向为N型筏化,[011]取向为P型筏化,[111]取向不筏化.进一步,根据筏化预测结果以及晶体滑移理论,结合Kachanov-Robotnov（K-R）损伤演化公式,建立了一个镍基单晶合金蠕变模型,采用该模型并结合商用有限元软件Abaqus的用户材料子程序（UMAT）二次开发接口,对[001],[011]和[111]取向下的CMSX-4镍基单晶合金,在950℃,180~450MPa应力条件下的蠕变变形行为进行了模拟.该模型能够准确预测镍基单晶合金的筏化类型以及滑移系开动规律,更加符合材料的蠕变变形物理机制,因此模型可以对镍基单晶合金的高温蠕变曲线的第2,3阶段进行很好的模拟,并得到了试验的验证.      

非对称铺层复合材料板室温形状的非线性有限元分析

由于一般铺层复合材料板壳存在拉伸-弯曲、拉伸-扭转等耦合效应,在温度变化时将出现垂直于中面方向的翘曲变形,给工程使用和理论分析带来了极大的不便。但另一方面,利用非对称铺层复合材料板壳可以有效地减轻结构的重量,并可能提供利用平面模具制造曲面层合壳的新工艺。     

剩余柔度模态与附着模态在模态综合法中的等价性

在早期的模态综合法中,引起计算误差的主要原因是由于截去了高阶模态。文献[1～4]从不同角度揭示,剩余柔度模态和附着模态可以有效地补偿这种截断误差。在此基础上,已派生出两类新的自由界面模态综合法。第一类方法的特点是将子结构位移用自由界面模态与剩余柔度模态来表示,第二类方法的特点是用自由界面模态与附着模态来表示子结构位移。本文将指出,这两类方法是等价的。其等价性表现在剩余柔度模态与附着模态可以相互替换而不影响模态综合的最终结果。本文将以文献[4]提出的方法为例来证明该等价性,并在文末给出一个数值算例。     

晶体取向对第四代单晶高温合金DD15高周疲劳性能的影响

在定向炉中分别采用籽晶法制备了[001]、[011]和[111]3种不同取向的第四代单晶高温合金DD15,在800℃研究了不同取向的高周疲劳性能,分析了合金不同取向的显微组织、疲劳断口形貌和疲劳断裂组织.结果表明:在凝固方向横截面上不同取向合金的铸态枝晶和热处理γ′相组织明显不同.合金800℃的高周疲劳性能存在各向异性...     

进气总压总温畸变对压气机稳定性的影响

本文对 Melick提出的进口总压周向稳态畸变对压气机稳定性裕度损失的估算方法作了改进 ,并加以推广应用于进口总温周向稳态畸变的情况。在此基础上 ,本文提出了总温和总压组合畸变下压气机稳定性裕度损失的预测方法。以某型双轴涡喷发动机为例作了某些具体的计算。