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.

Robust-augmentation nonlinear dynamic inversion control of over-actuated coaxial high-speed helicopter in transition mode

As the elevator and rudder can be used actively for control,in addition to the rotors,Coaxial High-speed Helicopters(CHHs)have the problems of control redundancy and changing control authority in the transition mode.This paper presents a robust-augmentation transitioning flight control design for a CHH under the adverse conditions of parametric uncertainties and external disturbances.First,based on control characteristic analysis,an Adaptive Filtered Nonlinear Dynamic Inversion(AFNDI)controller is proposed for the angular rate to handle the effect of unknown unstructured uncertainties and external turbulence.Theoretical analysis proves that the presented angular rate controller can guarantee steady-state and transient performance.Furthermore,the attitude angle and velocity controllers are also added.Then,an Incremental-based Nonlinear Prioritizing Control Allocation(INPCA)method is designed to take into account control surface transition and changing control authority,which efficiently distributes the required moments between coaxial rotors and aero-surfaces,and avoids the control reversal problem of the yaw channel.In the proposed control architecture,the low-pass filter is introduced to alleviate the adverse influence of time delay and measurement noise.Finally,the effectiveness of the proposed controller is demonstrated through nonlinear numerical simulations,and is compared with existing methods.Simulation results show that the proposed control law can improve both capabilities of disturbance rejection and fast response,and works satisfactorily for the CHH transitioning control characteristic.

A hybrid model of a subminiature helicopter in horizontal turn

A hybrid model of a subminiature helicopter in horizontal turn is presented. This model is based on a mechanism model and its compensated neural network （NN）. First, the nonlinear dynamics of a sub-miniature helicopter is established. Through the linearization of the nonlinear dynamics on a trim point, the linear time-invariant mechanism model in horizontal turn is obtained. Then a diagonal recursive neural network is used to compensate the model error between the mechanism model and the nonlinear model, thus the hybrid model of a subminiature helicopter in horizontal turn is achieved. Simulation results show that the hybrid model has higher accuracy than the mechanism model and the obtained compensated-NN has good generalization capability.

Detection of butt weld of laser-MIG hybrid welding of thin-walled profile for high-speed train

Purpose–This study aims to solve the problem of weld quality inspection,for the aluminum alloy profile welding structure of high-speed train body has complex internal shape and thin plate thickness(2–4 mm),the conventional nondestructive testing method of weld quality is difficult to implement.Design/methodology/approach–In order to solve this problem,the ultrasonic creeping wave detection technology was proposed.The impact of the profile structure on the creeping wave detection was studied by designing profile structural test blocks and artificial simulation defect test blocks.The detection technology was used to test the actual welded test blocks,and compared with the results of X-ray test and destructive test(tensile test)to verify the accuracy of the ultrasonic creeping wave test results.Findings–It is indicated that that X-ray has better effect on the inspection of porosities and incomplete penetration defects.However,due to special detection method and protection,the detection speed is slow,which cannot meet the requirements of field inspection of the welding structure of aluminum alloy thin-walled profile for high-speed train body.It can be used as an auxiliary detection method for a small number of sampling inspection.The ultrasonic creeping wave can be used to detect the incomplete penetration welds with the equivalent of 0.25 mm or more,the results of creeping wave detection correspond well with the actual incomplete penetration defects.Originality/value–The results show that creeping wave detection results correspond well with the actual non-penetration defects and can be used for welding quality inspection of aluminum alloy thin-wall profile composite welding joints.It is recommended to use the echo amplitude of the 10 mm 30.2 mm 30.5 mm notch as the criterion for weld qualification.

Laser-pulsed MIG hybrid welding technology of A6N01S aluminum alloy

Welding research of A6N01S-T5 aluminum alloy profile for high-speed train was done by using laser-MIG hybrid welding and MIG welding individually. And the weld appearance,welding distortion,mechanical properties of the joints and microstructures were analyzed. The test results demonstrated that high-efficient welding for the profile can be achieved by using laser-MIG hybrid welding,the speed of which can be over 3. 0 m/min. The processing had a good gap bridging ability,even if the gap of the butt joint was up to 2. 0 mm,a good weld appearance can also be got. While the hybrid welding speed was greater than 2. 5 m/min,the welding distortion of the laser-tandem MIG hybrid joints was just about 33% of that of the MIG joints,but the welding efficiency was over 3 times of MIG welding. And tensile strength of the hybrid joints was 85% of that of A6N01S-T5 base metal,9% higher than that of the MIG joints. Fatigue properties was tested individually with pulsed tensile fatigue method in the condition of 1 × 10~7 lifetime. The test results demonstrated that the fatigue strength of the joints was a little lower than that of base material,which could be up to 115 MPa. But the fatigue strength of hybrid welding joints was 107. 5 MPa,which was 23% higher than 87 MPa of MIG welding joints.

基于Hybrid State A^(*)与增强安全管道的直升机低空航迹规划

直升机低空突防已逐渐成为现代空战察打任务的核心,而低空航迹规划算法是实现该技术的关键。尽管现有的航迹规划算法已经被应用于实际低空突防任务,但基于“前端-后端”式的传统航迹规划算法依然存在规划航迹机动执行性差与复杂动态场景下易碰撞的缺陷。针对上述问题,本文提出一种基于Hybrid State A^(*)与增强安全管道的改进算法。首先,基于Hybrid State A^(*)算法的联合轨迹优化,可以在状态空间中完成兼顾直升机机动特性的初始航迹高效搜索,有效保证直升机航迹的可达性。其次,基于初始航迹膨胀的增强安全管道,将后端航迹优化参数限制在安全的可行域内,进而有效提升复杂动态场景下规划航迹的安全性。在实验环节,本研究结合ROS机器人仿真环境与Rviz数据可视化工具完成仿真验证,通过算法间的综合对比实验,论证了本研究所提算法对规划的航迹机动性与安全性有明显的提升。

用于直升机舱内降噪的智能周期撑杆研究

直升机主减速器内的齿轮啮合引起的中高频振动是直升机舱内噪声的主要来源之一,通过设计具有隔振性能的减速器撑杆可以有效抑制传递到机体的振动,进而减小齿轮啮合诱发的舱内噪声。基于压电叠堆/橡胶周期结构,提出了一种适用于直升机舱内降噪的主动/被动混合振动控制的智能周期撑杆,在满足强度与刚度要求的同时,具有优良的多频与宽频减振能力。压电叠堆与橡胶材料周期排列组成周期结构,其在特定频率范围内具有“机械滤波”特性;同时,通过调节驱动压电叠堆的电压与电流,改变压电叠堆的动刚度,可实现主动减振的功能。为了对智能周期撑杆的主动/被动混合振动控制性能进行分析,建立了基于传递矩阵形式的智能周期撑杆的机电耦合动力学模型,并使用多物理场仿真软件验证了模型的正确性。进一步基于该模型分析了在驱动电压与电流有限的条件下的智能周期撑杆的最优隔振性能:在智能周期撑杆一端固支、一端受到10N的激振力时,最大驱动电压为20V、最大驱动电流为1A的电学边界限制下,该智能周期撑杆具有将692Hz以上的振动完全衰减的能力,对692Hz以下的振动有一定程度的控制效果。此外,还研究了材料参数与力学边界条件对主动控制的影响,即橡胶材料的阻尼、激振力对进行主动控制时需要的驱动电压与电流的影响。使用有限元模型校核了智能周期撑杆的强度与刚度,验证了所提出的智能周期撑杆方案的工程可行性。使用压电叠堆作动器与聚酯乙烯杆件组成一个三周期的压电叠堆周期撑杆作为智能周期撑杆的简化模型,验证了主动/被动混合振动控制性能,分析了力学边界条件对隔振性能的影响,以及进行主动控制时的驱动电压和电流与最优驱动电压和电流的关系。

基于BFO-FPA参数寻优无人直升机轨迹跟踪自抗扰控制

为解决小型无人直升机轨迹跟踪控制受系统数学模型精度、自身低成本微机电系统(MEMS)姿态测量误差及飞行环境干扰的内外扰动影响问题,设计了一种基于线性/非线性混合自抗扰控制(ADRC-LADRC)的无人直升机轨迹跟踪控制器,并提出了一种基于细菌觅食优化-花授粉算法(BFO-FPA)的控制器参数整定方法,提高了BFO算法的收敛速度,增强了FPA算法的全局搜索能力。最后,通过ALIGN无人直升机锁尾螺旋爬升飞行试验,验证了BFO-FPA算法参数寻优后自抗扰轨迹跟踪控制器能有效克服无人直升机受内外扰动的影响,提高了控制器轨迹跟踪精度和鲁棒性。

复合式常规旋翼高速直升机机身气动布局风洞试验研究

复合式常规旋翼高速直升机是国内外高速直升机重点发展的几种构型之一。本文首先简要介绍了某300kg复合式常规旋翼高速直升机的机身气动布局形式,针对该机设计并加工了1∶1.5机身风洞试验模型,在4m×3m风洞开展了机身气动特性风洞试验。通过对比不同机身部件组合状态在不同迎角、侧滑角条件下的气动力及纵横向气动导数,获得了全机及各部件气动性能。根据风洞试验结果,结合已建立的旋翼气动力模型和螺旋桨气动力模型,建立了全机飞行力学模型,并分析了不同飞行速度下全机的静稳定性,验证了该复合式高速直升机具有合理的机身气动布局,研究结果可为复合式常规旋翼高速直升机的进一步发展提供参考。

Relative intensity noise in high-speed hybrid square-rectangular lasers

Relative intensity noise(RIN) and high-speed modulation characteristics are investigated for an Al Ga In As/In P hybrid square-rectangular laser(HSRL) with square side length, rectangular length, and width of 15,300, and 2 μm, respectively. Single-mode operation with side-mode suppression larger than 40 dB has been realized for the HSRL over wide variation of the injection currents. In addition, the HSRL exhibits a 3 dB modulation bandwidth of 15.5 GHz, and an RIN nearly approaches standard quantum shot-noise limit 2 hv∕P=-164 dB∕Hz at high bias currents due to the strong mode selection of the square microcavity. With the increase of the DC bias current of the Fabry–Perot section, significantly enhanced modulation bandwidth and decreased RIN are observed.Furthermore, intrinsic parameters such as resonance frequency, damping factor, and modified Schawlow–Townes linewidth are extracted from the noise spectra.

A New Hybrid Control Scheme for an Integrated Helicopter and Engine System

A new hybrid control scheme is presented with a robust multiple model fusion control（RMMFC） law for a UH-60 helicopter and an active disturbance rejection control（ADRC） controller for its engines.This scheme is a control design method with every subsystem designed separately but fully considering the couplings between them.With three subspaces with respect to forward flight velocity,a RMMFC is proposed to devise a four-loop reference signal tracing control for the helicopter,which escapes the closed-loop system from unstable state due to the extreme complexity of this integrated nonlinear system.The engines are controlled by the proposed ADRC decoupling controller,which fully takes advantage of a good compensation ability for unmodeled dynamics and extra disturbances,so as to compensate torque disturbance in power turbine speed loop.By simulating a forward acceleration flight task,the RMMFC for the helicopter is validated.It is apparent that the integrated helicopter and engine system（IHES） has much better dynamic performance under the new control scheme.Especially in the switching process,the large transient is significantly weakened,and smooth transition among candidate controllers is achieved.Over the entire simulation task,the droop of power turbine speed with the proposed ADRC controller is significantly slighter than with the conventional PID controller,and the response time of the former is much faster than the latter.By simulating a rapid climb and descent flight task,the results also show the feasibility for the application of the proposed multiple model fusion control.Although there is aggressive power demand in this maneuver,the droop of power turbine speed with an ADRC controller is smaller than using a PID controller.The control performance for helicopter and engine is enhanced by adopting this hybrid control scheme,and simulation results in other envelope state give proofs of robustness for this new scheme.

Efficient Helicopter-Satellite Communication Scheme Based on Check-Hybrid LDPC Coding

When implementing helicopter-satellite communications, periodical interruption of the received signal is a challenging problem because the communication antenna is intermittently blocked by the rotating blades of the helicopter. The helicopter-satellite channel model and the Forward Error Control（FEC） coding countermeasure are presented in this paper. On the basis of this model, Check-Hybrid（CH） Low-Density Parity-Check（LDPC）codes are designed to mitigate the periodical blockage over the helicopter-satellite channels. The CH-LDPC code is derived by replacing part of single parity-check code constraints in a Quasi-Cyclic LDPC（QC-LDPC） code by using more powerful linear block code constraints. In particular, a method of optimizing the CH-LDPC code ensemble by searching the best matching component code among a variety of linear block codes using extrinsic information transfer charts is proposed. Simulation results show that, the CH-LDPC coding scheme designed for the helicopter-satellite channels in this paper achieves more than 25% bandwidth efficiency improvement, compared with the FEC scheme that uses QC-LDPC codes.

Performance of High-Speed Grease Lubricated Hybrid Ceramic Ball Bearing

To simplify the lubricating system for high-speed bearings and improve its reliability, grease lu-bricated high-speed hybrid ceramic bearings were theoretically and experimentally researched. Bearings with an outer race of 62 mm and eleven 9.525-mm balls were investigated. Traction coefficient and flash temperature between the bearing races and the balls were calculated and the results show that the traction coefficient of Si3N4 hybrid ceramic bearings is 74% that of the steel AISI 440B ones at 30 000 r/min and 1750 N, and the flash temperature of the hybrid bearings is 49% that of steel ones. Simulating the high-speed bearing rotational conditions, the grease lubricated hybrid ceramic ball bearings were tested and the results show that the power consumption of hybrid ceramic bearing lubricated by grease D at 24 000 r/min and axial load 1750 N is 80% that of steel ones.

Design and analysis of the hybrid excitation rail eddy brake system of high-speed trains

Compared to the current eddy braking patterns using a single magnetic source,hybrid excitation rail eddy brakes have many advantages,such as controllability,energy saving,and various operating models.Considering the large braking power consumption of the high-speed train,a hybrid excitation rail eddy brake system,which is based on the principle of electromagnetic field,is proposed to fulfill the needs of safety and reliability.Then the working processes of the mechanical lifting system and electromagnetic system are demonstrated.With the electromagnetic system analyzed using the finite element method,the factors such as speed,air gap,and exciting current have influences on the braking force and attractive force.At last,the structure optimization of the brake system is discussed.

一种新型共轴式直升机操纵机构运动学分析

提出一种新型共轴式少自由度混联机构,可以模拟三桨叶共轴式直升机操纵机构的运动,由下操纵3-SPS+PS+RRS并联机构和上操纵混联机构串联而成,整体机构结构简单紧凑,所以可应用于三桨叶共轴式无人机。机构对旋转盘的约束等效为一个PS约束支链,上操纵混联机构等效为几个并联机构后,运用螺旋理论分析上操纵机构的自由度,证明上下倾斜盘运动姿态一致,结合下操纵机构得出整个机构满足三桨叶共轴直升机操纵机构所需的自由度。对上操纵机构中的倾斜盘的姿态角和运动支链的位置进行分析,并得出了在下操纵机构一定倾斜姿态下变距转动角的变化规律。通过PRO/E仿真查看整体机构的运行情况。

适于直升机配平计算的混合遗传算法

结合传统的数值计算如拟牛顿法的局部快速收敛特性,以及遗传算法的全局收敛与群体搜索的优点,发展出一种新的混合遗传算法,使之具备全局快速收敛特性。通过两个算例及某型直升机在前进比为0.2状态下的配平,验证了该算法的可行性及高效性,从而为直升机的配平计算提供了一种新的成功的算法,同时也在传统数值分析方法和现代智能进化算法之间的有效结合做了一次比较成功的尝试。

直升机旋翼气弹动力学优化策略(Ⅱ)——多目标优化解法研究

在旋翼气弹动力学模型基础上进行了多目标优化问题的描述和分类,定义了多目标优化问题及其解,讨论了多目标优化问题的解法,提出了直升机旋翼气弹动力学多目标优化问题的解法。使用改进的遗传模拟退火算法、加权系数法、全局准则法相结合的混合式解法进行旋翼气弹动力学多目标优化问题的求解。算例结果表明:使用混合法的多目标优化解法设计变量变化平缓;同时设计目标函数的3次/转、4次/转、5次/转谐波振动载荷和桨叶总质量分别比初始设计减少13.4%、31.5%、20.9%和7.36%,优化效果明显。由本文的研究可知,在直升机旋翼气弹动力学多目标优化问题中,使用混合式多目标优化问题解法能使旋翼气弹动力学多目标优化收敛到Pareto最优解,同时可提高多目标优化问题解质量和结果的鲁棒性。

直升机操纵稳定性优化设计

为了提高直升机操纵稳定性,建立了适合直升机总体设计的操纵稳定性分析模型,通过优化设计选择合适的总体参数和布局参数,以获得优良的直升机操纵稳定性。以UH-60A直升机为算例,结果表明该直升机操纵稳定性优化设计方法是可行和有效的;同时对比经典数值优化算法、智能优化算法和混合优化算法,发现混合优化算法更适合直升机操纵稳定性优化设计模型的求解。

一种新PSO混合算法在直升机配平中的应用

直升机配平计算是动力学分析的基础,其实质是求解高维复杂的非线性方程组。针对经典算法与智能算法的特点与不足,提出了一种求解非线性方程组的新粒子群方法。在粒子群(Particle swarm optimization,PSO)算法的基础上,根据模拟退火(Simulated annealing,SA)思想,引入了嵌入式LM(Levenberg-marquardt)优化算子。该方法充分发挥了3种算法的优势,克服了LM算法初值敏感性,PSO算法易陷入局部极值等问题。通过UH-60A直升机实例配平计算,验证了本文算例模型的准确性。在此基础上,针对某一前飞状态下的配平算例,在收敛可靠性和计算效率上通过与其他算法进行对比,表明该算法具有可靠的收敛性和较高的计算效率,进一步验证了该算法在配平问题上的可信度与实用性,为直升机飞行动力学问题的处理提供了一种新的有效方法。

杂交水稻制种人工授粉方法研究

介绍人工授粉对杂交水稻制种质量和产量的重要影响,分析现有杂交水稻制种人工授粉方法的原理、发展历程、优缺点、效益及国内外发展现状,为提高杂交水稻的制种质量及减轻农民的劳动强度提供有益参考。