基于密切曲锥的乘波构型一体化飞行器设计方法研究

描述了基于密切曲锥的乘波构型一体化飞行器设计方法。其特点是采用曲面乘波压缩前体,前体进气道压缩面基准流场由激波和等熵压缩波轴对称流场组成,三维乘波面采用密切曲锥方法由前缘线各点流线跟踪拟合构成流面;前体上表面由变半径轴对称特征线法生成基准流场并流线跟踪构成流面;尾喷管根据发动机燃烧室出口参数构造特征线流场并流线跟踪得到膨胀型面。快速的分析工具采用工程计算、一维燃烧室计算与经验公式相结合的方法对飞行器性能进行初步评估。所设计的三米量级一体化模型飞行器通过数值计算和风洞试验对性能进行了验证,结果表明,飞行器在设计状态基本达到设计要求,发动机正常点火工作,飞行器得到正推力,采用的气动性能快速分析估算方法对气动力的预测较为准确。

复合曲锥对旋流器分离性能的影响

常规旋流器锥段为直线型锥或单一曲线型锥,在生产中伴有不同程度的底流夹细和溢流跑粗,分离精度有待提高。综合2种曲线锥各自的特征和优点,提出了一种复合曲锥旋流器,其上锥段向轴心内凹,下锥段由轴心向外凸。采用数值模拟的方法对比分析了直线型锥和复合曲锥旋流器流场及分离性能的变化,发现随着曲率指数n由1增加到3,在上锥段切向速度和外旋流轴向速度增加,在下锥段切向速度和外旋流轴向速度降低,促进了密度层更合理的分布,分离粒度由19.38μm增加到24.91μm,分离精度由0.517提高到0.649,其中5μm颗粒的底流回收率由6.98%降低到2.40%,改进效果明显。

曲锥前体/内转进气道一体化设计与试验研究

介绍了曲锥前体/内转进气道一体化的设计方法,针对进气道侧壁外扩角这一设计因素,设计了具有不同捕获形状的两套一体化构型,并完成了两套模型在马赫数Ma=6.0、0°迎角状态下的风洞试验及数值模拟对比。结果表明,基于该一体化设计方法,曲锥前缘产生的初始入射激波在设计状态下能够完全封闭进气道唇罩,进而起到抑制唇罩溢流和提高一体化构型流量捕获能力的效果。在设计条件下,进气道侧壁外扩角的增加有助于减少侧壁产生的溢流,从而提高一体化构型的流量捕获能力。同时,外扩角的增大将导致下游反压前传速度加快,从而恶化进气道的内部流场并降低一体化构型的反压特性。因此,设计此类一体化构型时,需要考虑外扩角对捕获流量和进气道出口性能的综合影响,选择合适的进气道侧壁外扩角度以达到设计需求。

关于曲锥体积的计算

曲锥是一种形体,有关体积计算的资料上均没有列出曲锥体积的计算公式。作者建立了曲锥截面圆半径的函数,通过两次积分,解决了曲锥体积计算问题。它对曲锥类零件成形工艺(锻造、铸造、冲压、焊拼)的计算具有重要意义。 一、曲锥体积的计算公式 1.两个有关的定义 (1)曲锥的定义 曲锥是中心线为圆弧,在经过中心线所在圆弧圆心的截平面上的截面为圆。

球铁曲轴缩松缺陷分析与解决

曲轴作为汽车发动机中的关键零部件,对缩松的要求很高,而潮模砂与覆膜砂等工艺相比,型砂强度偏低,缩松倾向偏大。本文合理设计了减轻缩松缺陷的铸造工艺,采用铸造模拟软件MAGMA对曲轴的铸造过程进行了模拟,同时采用工艺出品率较高的曲锥冒口工艺,来提高冒口对曲轴的补缩能力。并通过增强孕育效果,最终在潮模砂生产线上生产出符合缩松标准甚至无缩松的曲轴。

内镜辅助下后鼓室微创手术入路的临床解剖学研究

目的为内镜辅助下后鼓室微创手术入路提供解剖学基础。方法利用成人15例(30侧)头部标本,解剖并测量后鼓室及其与周围结构之间的位置关系。结果面神经锥段中点分别到水平半规管最凸点、鼓室窦前缘中点、卵圆窗中点、圆窗中点、岬小桥下端、岬后脚下端的距离是(3.21±0.41)、(2.79±0.25)、(3.97±0.37)、(6.48±0.53)、(4.85±0.39)、(6.21±0.57)mm;砧骨窝中点至锥隆起顶端、面神经锥段中点、镫骨头中点、圆窗中点、卵圆窗中点、匙突顶点的距离分别为(4.43±0.36)、(3.10±0.28)、(6.55±0.55)、(9.56±0.82、(6.67±0.65)、(4.63±0.39)mm;鼓室窦的深度、横截面短径、横截面长径分别是(3.10±0.27)、(1.05±0.10)、(1.89±0.19)mm;后鼓室窦深度、横截面长径、横截面短径分别是(1.15±0.10)、(0.83±0.29)、(0.63±0.51)mm;外侧鼓室窦横截面近似椭圆型,其深度、上下径、左右径分别是(1.63±0.12)、(0.36±0.03)、(0.74±0.09)mm;面隐窝外侧气房直径(0.28±0.13)mm。结论后鼓室解剖结构精细复杂,对其解剖结构的精准定位有利于彻底清除病变和防止术后并发症的发生。

GEOMETRIC MODELING OF GENERATING-MANUFACTURED SPIRAL BEVEL GEARS BASED ON CUTTING SIMULATION

A geometric modeling method for generating-manufactured spiral bevel gears（SBGs） is proposed. It consists of two steps： （1） creating a reference model by simulating the process of cutting spiral bevel gear,（2） reconstructing the final solid model by collecting data points from the reference model and fitting these points into NURBS surfaces. In this method,cutting simulation avoids abstruse mathematical theories and complex methods,thus making it convenient to obtain data points on the complex tooth surface before the gear is manufactured and efficient to increase the accuracy of the solid model. Also,the representations of tooth surfaces of the final model is unified as a NURBS surface function. The NURBS surface is continuous and smooth,thus it is available for wide applications in CAD/CAE. The experiment proves that the method can be used to establish an accurate pair of SBG models,thus providing a feasible and effective way for CAD/CAE modeling.

直线对{axy+byz+czx=0 Ax+By+Cz=0的性质及应用

对给出所给直线对的两个性质定理进行了证明,并讨论了它的应用。

曲锥前体/三维内转进气道一体化设计与分析

对圆锥流场在不同攻角条件下的气动特征进行分析,以流线追踪技术为基础,发展了一种曲锥前体/三维内转进气道一体化设计方法,获得了三个几何参数对一体化方案外形和性能的影响规律。研究发现,三维内转进气道侧壁外扩角对进气道流量捕获系数影响明显,而捕获形状圆心角对进气道的影响主要表现在几何特征上。此外,进气道流量捕获系数随外压缩段总长度的增大而减小。基于对捕获形状的研究,设计了一种曲锥前体/三维内转进气道,并通过数值模拟对该方案进行研究。结果表明:在设计点来流马赫数为6.0时,该方案进气道流量捕获系数能够达到0.93,且具有0.61的总压恢复系数;在非设计点来流马赫数为5.0时,流量捕获系数能够保持在0.86,总压恢复系数为0.77。

On a Fixed Value Theorem for Directed Areas in Conic Circumscribed Polygons and Applications

Using polar equations for conic sections, we research conic circumscribed n-sided polygons（n ≥ 4） deeply on the basis of papers[1-3]. We obtain a general fixed value theorem for directed areas of some triangles in conic circumscribed n-sided polygons and derive as many as n（n - 3） concurrent points of three lines and some other collinear, equiareal results in conic circumscribed n-sided polygons（n ≥ 4）. So the results of papers[1-3] are unified.

Analysis of 3D curve expansion of conical cam with oscillating tapered roller follower

This paper focuses on the analysis of running conditions and machining processes of conical cam with oscillating follower. We point out the common errors existing in the design and machining of the widely used plane expansion method of conical cam trough-out line. We show that the motion can be divided into two parts, i.e. the oscillating motion of oscillating bar and the rotary motion of oscillating bar relative to the conical cam. By increasing the rotary motion of oscillating bar, the motion path of tapered roller on oscillating bar (i.e. contour surface of conical cam) can be expanded on the cylinder. Based on these analyses, we present a creative and effective designing and machining method for 3D curve expansion of conical cam with oscillating follower.

Finite element simulation and microstructure of two-pass inner spinning process of curved-generatrix cone cylindrical parts with annealing/quenching

A two-pass annealing/quenching internal spinning process with small-end rotations is proposed to form a curved generatrix conical thin-walled shell.That is,annealing at 360°C for 2 h followed by the 1st pass spinning,and finally quenching in ice water after holding for 1 h at 498°C followed by the 2nd pass spinning.ABAQUS finite element software is used to simulate the internal spinning process of the products formed under different forming parameters.The distribution laws of spinning force,the stress and strain under different forming processes were compared and analyzed.The mechanical properties and microstructure of the products are subsequently analyzed.The results show that the strain and the residual stress in the skin area of the formed products under two-pass spinning process more uniform,and the hardness and the mechanical performance are improved.The microstructure of the products formed with the 0.15 mm thickness reduction at the 2nd pass is excellent.And the second phase grain size distributed uniformly in the range of 36μm.Whereas,the second phase particles are broken seriously and the size distribution inhomogeneity is increased when the thickness reduction in the skin area is greater than 0.20 mm at the 2nd pass spinning process.

Study on the Splicing Principle of the Air Splicer for Auto-coner

The shaping form of an untwisted yarn-end for the air splicer is analyzed and then a cosine curve form which will have practically good splicing effect is proposed. The yarn motion in the splicing nozzle by applying hydrodynamics and the splicing principle of the air splicer are also studied.

Finite element analysis of contact fatigue and bending fatigue of a theoretical assembling straight bevel gear pair

The aim of this work is to propose a 3D FE model of a theoretical assembling straight bevel gear pair to analyze the contact fatigue on the tooth surface and the bending fatigue in the tooth root. Based on the cumulative fatigue criterion and the stress-life equation, the key meshing states of the gear pair were investigated for the contact fatigue and the bending fatigue. Then, the reliability of the proposed model was proved by comparing the calculation result with the simulation result. Further study was performed to analyze the variation of the contact fatigue stress and the bending fatigue stress under different loads. Furthermore, the roles of the driving pinion and the driven gear pair were evaluated in the fatigue life of the straight bevel gear pair and the main fatigue failure mode was determined for the significant gear. The results show that the fatigue failure of the driving pinion is the main fatigue failure for the straight bevel gear pair and the bending fatigue failure is the main fatigue failure for the driving pinion.

Tooth surface geometry optimization of spiral bevel and hypoid gears generated by duplex helical method with circular profile blade

In order to effectively improve meshing performance of spiral bevel and hypoid gears generated by the duplex helical method, the effects of straight lined and circular cutting edges profile on meshing and contact of spiral bevel and hypoid gears were investigated analytically. Firstly, a mathematical model of spiral bevel and hypoid gears with circular blade profile was established according to the cutting characteristics of the duplex helical method. Based on a hypoid gear drive, the tooth bearings and the functions of transmission errors of four design cases were analyzed respectively by the use of the tooth contact analysis(TCA), and the contact stresses of the four design cases were analyzed and compared using simulation software. Finally, the curvature radius of the circular profile blade was optimized. The results show that the contact stresses are availably reduced, and the areas of edge contact and severe contact stresses can be avoided by selecting appropriate circular blade profile. In addition, the convex and concave sides are separately modified by the use of different curvature radii of inside and outside blades, which can increase the flexibility of the duplex helical method.

NC Machining of Spiral Bevel Gear and Hypoid Gear Based on Unity Transformation Model

A unity transformation model (UTM) was presented for flexible NC machining of spiral bevel gears and hypoid gears. The model can support various machining methods for Gleason spiral bevel gears and hypoid gears, including generation machining and formation machining for wheel or pinion on a universal five-axis machining center, and then directly produce NC codes for the selected machining method. Wheel machining and pinion machining under UTM were simulated in Vericut 6.0 and tested on a five-axis machining center TDNC-W2000 with NC unit TDNC-H8. The results from simulation and real-cut verify the feasibility of gear machining under UTM as well as the correctness of NC codes.

展向截断曲面乘波压缩进气道气动布局

描述了所设计的展向截断曲面乘波压缩进气道.其特点是采用曲面乘波压缩前体,前体进气道压缩面基准流场由等熵压缩波轴对称流场组成,三维乘波面采用密切曲锥方法由前缘线各点流线跟踪拟合构成流面.乘波面根据飞行器和发动机的宽度要求进行了截断.数值计算和风洞试验结果表明:与相同几何收缩比的四波系压缩进气道相比,在马赫数为4.5时,曲面乘波压缩进气道流量系数提高12%,总压恢复系数提高39%;在马赫数为6时,曲面乘波压缩进气道流量系数提高4%,总压恢复系数提高50%.超然冲压发动机性能明显提高.

Point return orbit design and characteristics analysis for manned lunar mission

Point return orbit(PRO) of manned lunar mission is constrained by both lunar parking orbit and reentry corridor associated with reentry position.Besides,the fuel consumption and flight time should be economy.The patched conic equations which are adaptive to PRO are derived first,the PRO is modeled with fuel and time constraints based on the design variables of orbit parameters with clear physical meaning.After that,by combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed.Simulation example indicates that the method has excellent convergence performance and precision.According to a great deal of simulation results by the method,the PRO characteristics such as Moon centered orbit parameters,Earth centered orbit parameters,transfer velocity change,etc.are analyzed,which can supply references to the manned lunar mission orbit scheme.

A new method to determine the elastoplastic properties of ductile materials by conical indentation

Based on load-displacement curves,indentation is widely used to extract the elastoplastic properties of materials.It is generally believed that such a measure is non-unique and a full stress-strain curve cannot be obtained using plural sharp and deep spherical indenters.In this paper we show that by introducing an additional dimensionless function of A/A (the ratio of residual area to the area of an indenter profile) in the reverse analysis,the elastoplastic properties of several unknown materials that exhibit visually indistinguishable load-displacement curves can be uniquely determined with a sharp indentation.

Associative Cones and Integrable Systems

Abstract We identify R^7 as the pure imaginary part of octonions. Then the multiplication in octonions gives a natural almost complex structure for the unit sphere S^6. It is known that a cone over a surface M in S^6 is an associative submanifold of R^7 if and only if M is almost complex in S^6. In this paper, we show that the Gauss-Codazzi equation for almost complex curves in S^6 are the equation for primitive maps associated to the 6-symmetric space G2/T^2, and use this to explain some of the known results. Moreover, the equation for S^1-symmetric almost complex curves in S^6 is the periodic Toda lattice, and a discussion of periodic solutions is given.