RESEARCH ON SCHEME OF HIGH-SPEED ROTOR／WING TRANSITION HELICOPTER RD15

To analyze the existing schemes of high-speed rotorcrafts and some new technologies, a new conceptual sketch of the high-speed rotor/wing transition helicopter RD15 is proposed. The overall layout of the RD15 is given out and the transition process from the helicopter mode to the airplane mode is designed. The lift system consists of a circular disk-wing with four retractable blades. The technology of individual blade control is adopted for flight control in hover and low speed flight. The tail is a vectored thrust duct propeller. It can provide the anti-torque in hover, and offer the multi-directional controls and propulsion drive for the airplane mode flight. The aerodynamic characteristics and key technologies in the transition process for this layout, including the nose up angle of disk-wing, the length of the blade, rotation speed, pitch angle and other parameters, are theoretically ana lyzed and experimentally tested. Calculation and experiments show that the shift process of the lift, the power and controls are smooth, and the designed scheme is feasible.

The effects of corrugation and wing planform on the aerodynamic force production of sweeping model insect wings

The effects of corrugation and wing planform （shape and aspect ratio） on the aerodynamic force production of model insect wings in sweeping （rotating after an initial start） motion at Reynolds number 200 and 3500 at angle of attack 40℃ are investigated, using the method of computational fluid dynamics. A representative wing corrugation is considered. Wing-shape and aspect ratio （AR） of ten representative insect wings are considered; they are the wings of fruit fly, cranefly, dronefly, hoverfly, ladybird, bumblebee, honeybee, lacewing （forewing）, hawkmoth and dragon- fly （forewing）, respectively （AR of these wings varies greatly, from 2.84 to 5.45）. The following facts are shown. （1） The corrugated and flat-plate wings produce approximately the same aerodynamic forces. This is because for a sweeping wing at large angle of attack, the length scale of the corrugation is much smaller than the size of the separated flow region or the size of the leading edge vortex （LEV）. （2） The variation in wing shape can have considerable effects on the aerodynamic force; but it has only minor effects on the force coefficients when the velocity at r2 （the radius of the second ：moment of wing area） is used as the reference velocity; i.e. the force coefficients are almost unaffected by the variation in wing shape. （3） The effects of AR are remarkably small： whenAR increases from 2.8 to 5.5, the force coefficients vary only slightly; flowfield results show that when AR is relatively large, the part of the LEV on the outer part of the wings sheds during the sweeping motion. As AR is increased, on one hand, the force coefficients will be increased due to the reduction of 3-dimensional flow effects; on the other hand, they will be decreased due to the shedding of part of the LEV; these two effects approximately cancel each other, resulting in only minor change of the force coefficients.

Wing kinematics measurement and aerodynamics of free-flight maneuvers in drone-flies

The time courses of wing and body kinematics of two free-flying drone-flies, as they performed saccades, were measured using 3D high-speed video, and the morpho- logical parameters of the wings and body of the insects were also measured. The measured wing kinematics was used in a Navier-Stokes solver to compute the aerodynamic forces and moments acting on the insects. The main results are as following. （1） The turn is mainly a 90° change of heading. It is made in about 10 wingbeats （about 55 ms）. It is of interest to note that the number of wingbeats taken to make the turn is approximately the same as and the turning time is only a little different from that of fruitflies measured recently by the same approach, even if the weight of the droneflies is more than 100 times larger than that of the fruitflies. The long axis of body is about 40° from the horizontal during the maneuver. （2） Although the body rotation is mainly about a vertical axis, a relatively large moment around the yaw axis （axis perpendicular to the long axis of body）, called as yaw moment, is mainly needed for the turn, because moment of inertial of the body about the yaw axis is much larger than that about the long axis. （3） The yaw moment is mainly pro- duced by changes in wing angles of attack： in a right turn, for example, the dronefly lets its right wing to have a rather large angle of attack in the downstroke （generally larger than 50°） and a small one in the upstroke to start the turn, and lets its left wing to do so to stop the turn, unlike the fruitflies who generate the yaw moment mainly by changes in the stroke plane and stroke amplitude.

涡轴-涡扇变循环发动机方案及性能匹配设计研究

针对旋转机翼式垂直起降高速巡航飞行器,提出了一种新概念结构形式的涡轴-涡扇变循环(TSFVCE)发动机,能够分别在涡轴和涡扇两种模态工作。首先对涡轴-涡扇变循环发动机的结构及工作模式进行了介绍,并建立基于变比热的部件级性能仿真模型;然后通过循环分析,确定发动机第二涵道比为3,Flade外涵风扇压比为1.98,第一涵道比为0.11,完成发动机设计点性能方案设计;最后分析了核心机驱动风扇(CDFS)可调机构对发动机性能影响机理,得出CDFS放气阀对发动机涡扇模态下的推力与涡轴模态下的功率影响较大,对涡扇模态的推力影响最大为61.5%,对涡轴模态的功率影响最大为33.3%,可利用此特性实现发动机在涡扇和涡轴模态下推力和功率输出的匹配。

WZ-1 直升机旋翼桨叶的设计

从气动、动力学和结构设计三个方面介绍了直升机旋翼桨叶设计的一般要求，分析了桨叶扭转角、平面形状、桨尖形状等参数对直升机性能、旋翼气动特性和动力学特性的影响，并结合ＷＺ－１无人驾驶直升机的使用要求对其旋翼桨叶进行了初步设计，给出了桨叶的构形和“共振图”。本文的设计和分析方法可用于指导其他直升机的旋翼桨叶设计。

AN IMPROVED MODEL OF CURVED VORTEX ELEMENT FOR ROTOR WAKE ANALYSIS

This paper describes an improved model of curved vortex element on the circular arc (CVEC) for rotor wake analysis.As the key of the paper,two approximate formulas are derived by the series of limited terms to replace the Legendre incomplete elliptical integrals from the Biot-Savart integration,and the analytical solution of the induced velocity for the CVEC is obtained, which is more efficient in the complex rotor free wake calculation. Furthermore,the approximate formulas with the chosen factors are selected to avoid sigularity and give finite result of the induced velocity on the Vortex line,and an equivalent viscous vortex core radius might be evaluated.As examples, the induced velocity calculations on the vortex ring and two turns of a skew vortex helix are performed, and the comparisons between the circular-arc vortex element and the conventional straightline vortex element (SLVE) are given.It is shown that this curved vortex element model is advantageous over the SLVE model and is suitable for the rotor wake analysis.

西黄胶囊联合TP方案对晚期非小细胞肺癌患者血清Foxp3、Ang-2水平的影响

目的探讨西黄胶囊联合TP方案治疗晚期非小细胞肺癌患者的临床疗效。方法选取2017年6月—2019年6月期间新乡医学院第一附属医院收治的晚期非小细胞肺癌患者86例,采用随机摸球法分为对照组和治疗组,每组各43例。对照组采用TP方案化疗,治疗组在此基础上加用西黄胶囊治疗。两组患者均连续治疗42 d后,观察两组患者近期疗效及不良反应发生情况,同时观察两组患者治疗前后中医证候症状积分、血清叉头翼状螺旋转录因子3(Forkhead or winged helix transcription,Foxp3)、血管生成素-2(Angiopoietin-2,Ang-2)、美国东部肿瘤协作组体能状况(Eastern cooperative oncology group performance status,ECOGPS)评分变化。结果治疗后治疗组有效率为46.51%、疾病控制率为83.72%,与对照组有效率25.38%、疾病控制率65.12%比较,差异有统计学意义(P<0.05)。治疗后,两组患者咳嗽、气短、胸闷、出汗、乏力、畏寒肢冷、腰膝酸软积分及总分较治疗前均降低,差异有统计学意义(P<0.05);且治疗组低于对照组,差异有统计学意义(P<0.05)。治疗后两组患者血清Foxp3、Ang-2水平较治疗前明显降低,差异有统计学意义(P<0.05);且治疗组低于对照组,差异有统计学意义(P<0.05)。治疗后两组ECOGPS评分均较治疗前降低,差异有统计学意义(P<0.05);且治疗组低于对照组(P<0.05)。治疗组发热(30.23%)、恶心呕吐(30.23%)、血小板减少(34.88%)、白细胞减少(41.86%)及肝肾功能损伤(30.23%)发生率与对照组(53.49%、60.47%、55.81%、48.84%、44.19%)比较,差异有统计学意义(P<0.05)。结论西黄胶囊联合TP方案治疗NSCLC的效果显著,能明显改善患者临床症状及体能状况,减轻化疗毒副反应,并降低血清Foxp3、Ang-2表达水平发挥抗癌作用。

抑郁症治疗的新靶点-mTOR信号通路

近年临床研究表明,单次注射低剂量谷氨酸N-甲基-D-天门冬氨酸(NMDA)受体拮抗剂氯胺酮可以在2小时内缓解抑郁症状,药效持续长达一周,引发抑郁症治疗领域的高度关注,但氯胺酮的快速起效抗抑郁机制至今尚不明确。最近李楠欣等人研究发现氯胺酮能快速激活哺乳动物的雷帕霉素靶点(mTOR)途径,从而导致大鼠前额皮质突触信号蛋白增多及棘突触数量增加。NMDA受体的其他拮抗剂,如CP-101606(曲索罗地)等也能产生与氯胺酮类似的抗抑郁作用,激活mTOR信号通路。这些研究表明,mTOR信号通路很有可能是一种新型快速起效抗抑郁药治疗的靶点。

A PREDICTION OF THE VORTEX-RING STATE BOUNDARY BASED ON MODEL TESTS

To understand the vortex-ring state and to develop an approach for predicting its boundary, a series of model rotor tests of vertical descent and oblique descent have been conducted on a newly-built test apparatus - the Whirling Beam. The test results showed some unsteady aerodynamic behavior of the model rotor operating in the vortex-ring state. A very irregular variation of the rotortorque at low rate-of-descent was observed here for the first time. We considered it to be the start of the 'power settling' and determined the critical descent velocity according to this observation. A previous criterion for the vortex-ring state was modified to give a semi-empirical method for predicting the entire vortex-ring state boundary. The computed boundary shows a good correlation with the model test results and the flight experiences.

浅谈纵横无人机CW-10在山区测图中的应用

近年来,无人机行业在测绘领域迅速发展并广泛应用,市场上以单纯的固定翼或旋翼类型无人机居多,本文以纵横公司固定翼加旋翼组合的CW10无人机为搭载平台,以贵州铜仁某处山区地形为例,进行实际应用,测试其在地形起伏较大的区域执行测绘任务的能力。文中设定了不同飞行高度,测试其在不同成图比例尺下的成图精度,同时考虑电池的续航里程,找出最优执行方案设计、航线设计等注意事项,方便实际操作人员高效完成现场航测任务规划,合理利用电池电量,并保障无人机安全顺利完成作业。

Optically Powered Temperature Measuring Instrument for Big Rotor

Abstract: A micro - power consumption non - contact temperature measuring instrument for big rotor is introduced. As it solves very well the signal coupling under high speed rotation and power supply problem for probe, the instrument can realize persistent on - line temperature measurement for big rotor drived by the ordinary light transmitted by optical fiber under the room light.

Aerodynamic efficiency enhancement effect of the energy capture technique on a flyable flapping wing rotor system

To date,no experimental study has been done on eliminating the energy consumption of the flapping wing rotor(FWR;caused by inertial force)based on an energy capture mechanism(such as a spring).Also,the effect of the variation amplitude of the twist angles on the FWR remains unknown.In this study,a 19.2-g FWR model is designed and manufactured.Three different kinds of springs are then selected and assembled onto the FWR to reduce the energy consumption caused by the inertial forces.Afterward,a motion capture system and a lift measurement system are built to test the aerodynamic and kinematic performance of the FWR.Then,the influence of the variation range of the twist angles and the dimensions of the spring on the motion parameters and lift efficiency of the FWR is analyzed.If the rigid twist angle variation range is set to 10°–70°instead of 10°–50°,the FWR can generate 3 to 10 g of greater average lifts under the same input voltage.In most cases,the introduction of the spring also improves the average lifting rate by 1-4 g.The lift enhancement effect induced by the spring is more pronounced when the main frequency with the maximum amplitude is close to or coincides with the resonant frequency of the FWR structure.If the main frequency is greater than the resonance frequency of the FWR structure,the lift enhancement effect is hardly observed.In conclusion,according to experimental analyses,both the selection of 10°-70°preset twist angles and the application of springs can improve the lift efficiency of FWR and overcome the weight of the FWR system(37.8 g)assembled with a flight control system.Free-flight test results show that the FWR system(including the 19.2-g FWR model and an 18.6-g flight control system)has sufficient lifting margin to successfully perform a take-off mission and achieve a stable hovering action.

新型双旋翼洞穴勘探无人机设计与实现

针对传统洞穴勘探作业难度高、工作人员面临安全隐患大的问题,设计了一款能够搭载多种探测设备的勘探无人机,适用于洞内勘探、救援及矿洞作业等诸多领域,为传统无人机技术的应用与整体架构带来创新性功能拓展,有望在地理环境、资源开发、灾害救援等方面发挥重大作用。

无人机摄影测量在矿山测量中的应用分析

对使用无人机进行矿井摄影测量的优点进行了说明,从无人机摄影测量的像控点布置、无人机的航迹规划、空中三角测量等几个角度对无人机摄影测量技术进行了详细的描述,并将多旋翼无人机与固定翼无人机进行了比较,给出了无人机摄影测量技术在矿井中的应用场景,并与其使用场景的特征进行了比较,从而为无人机摄影测量技术在类似矿井测量场景的应用提供了一定的参考。

利用旋翼机和固定翼飞机的空气动力学理论综合估算电动垂直起降飞行器的飞行性能

根据旋翼机和固定翼飞机的气动理论开发了一个综合方法过程用于估算电动垂直起降(Electric vertical takeoff and landing, e VTOL)飞行器的飞行性能。这种飞机通常采用多旋翼垂直飞行,螺旋桨和机翼的不同组合方式实现飞行。其中,对旋翼和螺旋桨的气动性能采用传统动量理论分析和旋翼元素分析。本文利用此综合理论研究了12架e VTOL飞行器的飞行性能,包括多旋翼飞行器、矢量推进飞行器和升力巡航飞行器。计算了悬停、爬升和下降以及巡航水平飞行,不同飞行状态时驱动电机、旋翼和机身的飞行特性。据此,可以进一步确定电力推进系统的性能指标,以匹配螺旋桨或旋翼,从而满足飞行任务。

电力行业无人机典型应用的服务模式和创新研究

对包括多旋翼无人机、垂起固定翼无人机和无人直升机在内的3种主要应用类型的无人机在我国电网中的应用现状进行分析,探讨出无人机服务于我国电网电力巡检、电力应急、物资运输等典型应用场景的服务模式和创新方式,提出了搭建无人机电网作业服务云平台这一思路。云平台的构想和搭建,对提升电力系统内部工作效率、电力系统外部服务质量等方面都有着绝对的积极作用,并将会提升电力行业无人机应用的智能性、灵活性和可持续发展性,为无人机应用推动电力行业高质量发展提供重要的智力支撑。

直升机技术发展现状与展望

简单回顾了直升机技术发展的历程和技术特点 ,介绍了直升机的技术进展 。

旋转机翼悬停气动特性研究

鸭式旋转机翼(CRW)是一种先进的高速直升机方案,旋翼同时也是机翼,是其最关键气动部件之一。采用结构分区拼接网格技术进行空间离散,分区建立参考系,通过求解多重参考系下的N-S方程来计算旋翼流场,首先以传统的Caradonna-Tung实验旋翼的亚、跨声速悬停流场分析为例验证该方法的可靠性,进而采用该方法对旋转机翼悬停流场进行了数值计算,旋翼拉力计算值和地面实验值吻合较好,结果分析表明旋转机翼的悬停流场有着不同于传统旋翼的流场特性。

齿轮旋翼传动系统动态固有特性识别

通过对齿轮旋翼传动系统进行理论分析，在运转的条件下进行实验测定和在线识别，指出由于旋翼的非线性耦合作用，使得带有旋翼的齿轮传动系统具有不同于其它齿轮系统的特有特性，即动态特性随转速的不同而发生变化，并得到了其变化规律。

飞行器智能结构系统研究进展与关键问题

飞行器智能结构是由传感器、驱动器、控制元件和基体结构组成的集成系统,它具有承载、检测、判断与动作等功能,可显著提升飞行器的性能。根据国内外飞行器智能结构系统研究的最新进展,论述了飞行器结构动力响应主动控制、智能机翼、旋翼以及飞行载荷谱监测与结构损伤诊断等的基本原理与技术问题;指出了飞行器智能结构系统研究在埋入式功能元件、复杂非线性多场耦合系统的动力学建模与控制以及智能结构系统中的损伤和失效问题等方面所面临的关键技术问题和挑战。