Friction coupling vibration characteristics analysis of aviation hydraulic pipelines considering multi factors

As the power transmission system of an aircraft,a hydraulic pipeline system is equivalent to the " blood vessel" of the aircraft. With the development of aircraft hydraulic system to high pressure,high speed and high power ratio,the fluid-structure interaction vibration mechanism of hydraulic pipeline is more complex and the influence of friction coupling on vibration cannot be ignored. The fluid-structure interaction of hydraulic pipeline will lead to system vibration,lower reliability of system operation and even pipeline rupture. Taking a hydraulic pipeline of C919 aircraft wingtip as the research object,a 14-equation model of fluid-structure interaction vibration considering friction coupling effect is established in this paper. The effects of friction and fluid parameters on the pipeline fluid-structure interaction vibration characteristics are studied and verified by experiments. The research results will provide theoretical guidance for the analysis of the pipeline fluid-structure interaction vibration and have important theoretical significance and great engineering value for promoting the localization process of large aircraft.

直线驱动电静液作动器的匹配设计规则

电静液作动器(EHA)是一种高度集成的泵控传动系统,A380和F35等机型已经利用EHA驱动主飞控舵面。但传统的以旋转电机和柱塞泵构成的EHA面临低频响的问题,以一种具有良好动态特性的新原理直线驱动电静液作动器(LEHA)为对象,研究其参数匹配设计问题。LEHA的关键特征在于新型的直线协同配流泵,以及采用直线电机直接驱动泵的吸排油和配流组件。首先,从静态指标匹配性上考虑LEHA的参数设计规则,得到最大空载速度约束条件、最大静态输出力约束条件、系统最高压力约束条件;然后,根据系统模型分析系统各参数对频宽的影响,得到LEHA的动态性能匹配设计规则,具体是指LEHA频宽指标对直线电机振荡频率的约束条件;最后,分析LEHA的功率约束条件,给出了LEHA对惯性负载、弹性负载和黏性阻尼负载在输出力-速度坐标下的功率包络条件,得到LEHA的负载匹配设计约束。LEHA参数设计的6项匹配设计约束条件能够为LEHA的设计过程提供理论依据。

液压元件及系统智能化发展现状及趋势思考

第四次工业革命利用信息化技术促进产业变革,将带我们进入智能化时代。由于液压系统作为核心动力和控制部分,广泛应用于先进制造、航空航天、海洋等重大装备,工业装备的智能化必然会要求液压元件及系统实现智能化。所以,近年来智能液压一直是液压领域的研究热点,推动液压领域进入智能时代,也给液压系统的研究带来新的活力,但也遇到了新的挑战,包括对智能液压系统的理解不一致,缺乏系统综合的研究,成碎片化的点突破等。分析智能液压系统的内涵与演进历程,阐述智能液压系统的架构体系,总结出智能液压系统具有的智能感知、智能调控、智能运维三大特征,并从这三个方面综述国内外的研究进展,揭示智能液压存在的问题和挑战;最后讨论应对挑战的研究路径和发展趋势。

大型飞机电液动力控制与作动系统新体系基础研究

大型飞机的研发制造能力是一个国家航空实力的重要体现,所以国家确定了大型飞机研制重大科技专项,是国家成为航空强国的意志体现。在我国大型飞机重大科技专项计划的大背景下,针对突破核心关键技术,为研制大型客机做好技术储备,国家重点基础研究发展计划(973计划)"大型飞机电液动力控制与作动系统新体系基础研究"项目围绕大型飞机电液动力作动系统新体系的创成与高效服役、高压高速液压系统固液耦合驱动机理与界面效应、功率电传电静液作动系统的能量传输与匹配运行3个方面的关键科学问题开展了深入研究,取得了一系列重要研究成果。本文从项目研究概况、关键研究进展、总结与展望这3个方面进行论述。

飞机防滑刹车控制技术研究综述综述

机轮刹车系统是飞机上最重要的着陆减速系统,关系到飞机的安全起降,其核心是防滑刹车控制技术。飞机刹车过程包含了众多在控制领域具有挑战的问题(不确定性、强非线性和强时变性),如何在刹车过程中有效克服着陆中所涉及的地面摩擦、刹车盘力矩波动、起落架载荷变化和阵风等具有复杂非线性特征的干扰,实现对地面结合力的可控利用,将对提高飞机地面安全发挥重要作用。本文对飞机防滑刹车控制技术进行综述。简述了飞机机轮防滑刹车系统的作用、发展、基本控制原理和典型架构;从应用需求出发归纳了关键评价指标;以数学模型的形式描述了系统内的典型非线性环节和着陆环境中的扰动;按照飞机防滑控制技术发展的顺序,依次介绍讨论了开关式防滑控制、偏压调制式防滑控制、自适应防滑控制和智能防滑控制中具有代表性的方法。从刹车控制律验证角度介绍了全数字仿真和试验方法。最后,结合刹车控制系统研制所存在的问题与挑战对本领域所涉及的技术研究重点进行了展望。

飞机新原理电液自馈能刹车系统设计与优化

当前,传统飞机液压刹车系统普遍采用集中式的机载液压源作为动力,液压能通过能源管路传输到刹车作动器,整个系统零部件数目众多,管路布局复杂,由此带来的管路振动、液压油泄漏等问题突出,限制了飞机刹车系统可靠性和可维护性的提升。近年来,一种飞机新原理电液自馈能刹车系统被提出,将模块化的"自馈能装置"安装在机轮附近,回收机轮着陆时的旋转动能,并将其转换成液压能,用于刹车作动。提出了一种利用波浪曲面进行取能的专用取能机构,设计了自馈能系统紧凑型专用取能机构,研制了高可靠、低能耗、高抗污染的自馈能刹车系统原理样机,完全实现了自馈能,即使飞机失去全部动力也能正常完成刹车功能,使抗污染等级从NAS6级提升到NAS10级,可靠性和可维护性优于传统液压刹车。

大流量压电式高速开关阀设计与仿真测试

针对目前高速开关阀快速性的不足及大流量的需求,利用压电晶体响应快速的特点,设计一种压电直动式高速开关阀,采用压电执行器直接驱动锥阀式阀芯结构,控制开关阀开启和关闭。设计桥式位移放大结构,放大压电执行器的输出位移,提高开关阀的控制流量。为补偿锥阀式阀芯结构开启、关闭过程中的液动力波动,提出锥阀+滑阀的组合式阀芯结构,建立其液动力模型,分析开关阀启闭过程中的负载力变化。建立压电直动式高速开关阀的数学模型,结合AMESim仿真软件分析、优化影响其性能的设计参数。搭建压电高速开关阀静态流量及动态启闭特性的试验测试平台,测试开关阀流量特性、启闭时间等性能指标,分析PWM控制载波频率及占空比与开关阀静态、动态流量之间的关系。基于设计参数仿真和实物样机试验测试结果表明,设计的压电式开关阀在压力10MPa下,输出流量17.4L/min,开启时间1.05ms,关闭时间0.85ms,实现大流量与快速性的要求。研究工作可为高速开关阀精确流量控制提供理论基础,对于拓展数字液压技术的应用具有重要意义。

Adaptive Nonlinear Optimal Compensation Control for Electro-hydraulic Load Simulator

Directing to the strong position coupling problem of electro-hydraulic load simulator (EHLS), this article presents an adaptive nonlinear optimal compensation control strategy based on two estimated nonlinear parameters, viz. the flow gain coefficient of servo valve and total factors of flow-pressure coefficient. Taking trace error of torque control system to zero as control object, this article designs the adaptive nonlinear optimal compensation control strategy, which regards torque control output of closed-loop controller converging to zero as the control target, to optimize torque tracking performance. Electro-hydraulic load simulator is a typical case of the torque system which is strongly coupled with a hydraulic positioning system. This article firstly builds and analyzes the mathematical models of hydraulic torque and positioning system, then designs an adaptive nonlinear optimal compensation controller, proves the validity of parameters estimation, and shows the comparison data among three control structures with various typical operating conditions, including proportion-integral-derivative (PID) controller only, the velocity synchronizing controller plus P1D controller and the proposed adaptive nonlinear optimal compensation controller plus PID controller. Experimental results show that systems' nonlinear parameters are estimated exactly using the proposed method, and the trace accuracy of the torque system is greatly enhanced by adaptive nonlinear optimal compensation control, and the torque servo system capability against sudden disturbance can be greatly improved.

Theoretical study of flow ripple for an aviation axial-piston pump with damping holes in the valve plate

Based on the structure of a certain type of aviation axial-piston pump＇s valve plate which adopts a pre-pressurization fluid path （consisting a damping hole, a buffer chamber, and an orifice） to reduce flow ripple, a single-piston model of the aviation axial-piston pump is presented. This sin- gle-piston model comprehensively considers fluid compressibility, orifice restriction effect, fluid resistance in the capillary tube, and the leakage flow. Besides, the instantaneous discharge areas used in the single-piston model have been calculated in detail. Based on the single-piston model, a multi-piston pump model has been established according to the simple hydraulic circuit. The sin- gle- and multi-piston pump models have been realized by the S-function in Matlab/Simulink. The developed multi-piston pump model has been validated by being compared with the numerical result by computational fluid dynamic （CFD）. The effects of the pre-pressurization fluid path on the flow ripple and the instantaneous pressure in the piston chamber have been studied and opti- mized design recommendations for the aviation axial-piston pump have been given out.

Nonlinear Adaptive Robust Force Control of Hydraulic Load Simulator

This paper deals with the high performance force control of hydraulic load simulator. Many previous works for hydraulic force control are based on their linearization equations, but hydraulic inherent nonlinear properties and uncertainties make the conven- tional feedback proportional-integral-derivative control not yield to high-performance requirements. In this paper, a nonlinear system model is derived and linear parameterization is made for adaptive control. Then a discontinuous projection-based nonlin- ear adaptive robust force controller is developed for hydraulic load simulator. The proposed controller constructs an asymptoti- cally stable adaptive controller and adaptation laws, which can compensate for the system nonlinearities and uncertain parame- ters. Meanwhile a well-designed robust controller is also developed to cope with the hydraulic system uncertain nonlinearities. The controller achieves a guaranteed transient performance and final tracking accuracy in the presence of both parametric uncer- tainties and uncertain nonlinearities; in the absence of uncertain nonlinearities, the scheme also achieves asymptotic tracking performance. Simulation and experiment comparative results are obtained to verify the high-performance nature of the proposed control strategy and the tracking accuracy is greatly improved.

Modeling and Optimal Design of 3 Degrees of Freedom Helmholtz Resonator in Hydraulic System

Three degrees of freedom （3-DOF） Helmholtz resonator which consists of three cylindrical necks and cavities connected in series （neck-cavity-neck-cavity-neck-cavity） is suitable to reduce flow pulsation in hydraulic system. A novel lumped parameter model （LPM） of 3-DOF Helmholtz resonator in hydraulic system is developed which considers the viscous friction loss of hy- draulic fluid in the necks. Applying the Newton＇s second law of motion to the equivalent mechanical model of the resonator, closed-form expression of transmission loss and resonance frequency is presented. Based on the LPM, an optimal design method which employs rotate vector optimization method （RVOM） is proposed. The purpose of the optimal design is to search the reso- nator＇s unknown parameters so that its resonance frequencies can coincide with the pump-induced flow pulsation harmonics respectively. The optimal design method is realized to design 3-DOF Helmholtz resonator for a certain type of aviation piston pump hydraulic system. The optimization result shows the feasibility of this method, and the simulation under optimum parame- ters reveals that the LPM can get the same precision as transfer matrix method （TMM）.

Friction compensation for low velocity control of hydraulic flight motion simulator: A simple adaptive robust approach

Low-velocity tracking capability is a key performance of flight motion simulator （FMS）, which is mainly affected by the nonlinear friction force. Though many compensation schemes with ad hoc friction models have been proposed, this paper deals with low-velocity control without friction model, since it is easy to be implemented in practice. Firstly, a nonlinear model of the FMS middle frame, which is driven by a hydraulic rotary actuator, is built. Noting that in the low velocity region, the unmodeled friction force is mainly characterized by a changing-slowly part, thus a simple adaptive law can be employed to learn this changing-slowly part and compensate it. To guarantee the boundedness of adaptation process, a discontinuous projection is utilized and then a robust scheme is proposed. The controller achieves a prescribed output tracking transient performance and final tracking accuracy in general while obtaining asymptotic output tracking in the absence of modeling errors. In addition, a saturated projection adaptive scheme is proposed to improve the globally learning capability when the velocity becomes large, which might make the previous proposed projection-based adaptive law be unstable. Theoretical and extensive experimental results are obtained to verify the high-performance nature of the proposed adaptive robust control strategy.

Modeling of reliability and performance assessment of a dissimilar redundancy actuation system with failure monitoring

Actuation system is a vital system in an aircraft, providing the force necessary to move flight control surfaces. The system has a significant influence on the overall aircraft performance and its safety. In order to further increase already high reliability and safety, Airbus has imple- mented a dissimilar redundancy actuation system （DRAS） in its aircraft. The DRAS consists of a hydraulic actuation system （HAS） and an electro-hydrostatic actuation system （EHAS）, in which the HAS utilizes a hydraulic source （HS） to move the control surface and the EHAS utilizes an elec- trical supply （ES） to provide the motion force. This paper focuses on the performance degradation processes and fault monitoring strategies of the DRAS, establishes its reliability model based on the generalized stochastic Petri nets （GSPN）, and carries out a reliability assessment considering the fault monitoring coverage rate and the false alarm rate. The results indicate that the proposed reli- ability model of the DRAS, considering the fault and redundancy degradation process and identify monitoring, can express its fault logical relation potential safety hazards.

A practical nonlinear robust control approach of electro-hydraulic load simulator

This paper studies a nonlinear robust control algorithm of the electro-hydraulic load simulator （EHLS）. The tracking performance of the EHLS is mainly limited by the actuator＇s motion disturbance, flow nonlinearity, and friction, etc. The developed controller is developed based on the nonlinear motion loading model. The problems of the actuator＇s disturbance and flow nonlinearity are considered. To address the friction problem, the friction model of the loading motor is identified experimentally. The friction disturbance is compensated using the obtained friction model. Therefore, this paper considers the main three factors comprehensively. The developed algorithm is easy to apply since the controller can be obtained just with one step back-stepping design. The stability of the developed algorithm is proven via Lyapunov analysis. Both co-simulation and experiments are performed to verify the effectiveness of this method.

Aircraft-on-ground path following control by dynamical adaptive backstepping

The necessity of improving the air traffic and reducing the aviation emissions drives to investigate automatic steering for aircraft to effectively roll on the ground. This paper addresses the path following control problem of aircraft-on-ground and focuses on the task that the aircraft is required to follow the desired path on the runway by nose wheel automatic steering. The proposed approach is based on dynamical adaptive backstepping so that the system model does not have to be transformed into a canonical triangular form which is necessary in conventional backstepping design. This adaptive controller performs well despite the lack of information on the aerodynamic load and the tire cornering stiffness parameters. Simulation results clearly demonstrate the advantages and effectiveness of the proposed approach.

An experimental study of the dual-loop control of electro-hydraulic load simulator (EHLS)

This paper investigates motion coupling disturbance（the so called surplus torque）in the hardware-in-the-loop（HIL）experiments.The＇＇velocity synchronization scheme＇＇was proposed by Jiao for an electro-hydraulic load simulator（EHLS）in 2004.In some situations,however,the scheme is limited in the implementation for certain reasons,as is the case when the actuator＇s valve signal is not available or it is seriously polluted by noise.To solve these problems,a＇＇dual-loop scheme＇＇is developed for EHLS.The dual-loop scheme is a combination of a torque loop and a position synchronization loop.The role of the position synchronization loop is to decouple the motion disturbance caused by the actuator system.To verify the feasibility and effectiveness of the proposed scheme,extensive simulations are performed using AMESim.Then,the performance of the developed method is validated by experiments.

Fuzzy robust nonlinear control approach for electro-hydraulic flight motion simulator

A fuzzy robust nonlinear controller for hydraulic rotary actuators in flight motion simulators is proposed. Compared with other three-order models of hydraulic rotary actuators, the proposed controller based on first-order nonlinear model is more easily applied in practice, whose control law is relatively simple. It not only does not need high-order derivative of desired command,but also does not require the feedback signals of velocity, acceleration and jerk of hydraulic rotary actuators. Another advantage is that it does not rely on any information of friction, inertia force and external disturbing force/torque, which are always difficult to resolve in flight motion simulators. Due to the special composite vane seals of rectangular cross-section and goalpost shape used in hydraulic rotary actuators, the leakage model is more complicated than that of traditional linear hydraulic cylinders. Adaptive multi-input single-output（MISO） fuzzy compensators are introduced to estimate nonlinear uncertain functions about leakage and bulk modulus. Meanwhile, the decomposition of the uncertainties is used to reduce the total number of fuzzy rules. Different from other adaptive fuzzy compensators, a discontinuous projection mapping is employed to guarantee the estimation process to be bounded. Furthermore, with a sufficient number of fuzzy rules, the controller theoretically can guarantee asymptotic tracking performance in the presence of the above uncertainties, which is very important for high-accuracy tracking control of flight motion simulators.Comparative experimental results demonstrate the effectiveness of the proposed algorithm, which can guarantee transient performance and better final accurate tracking in the presence of uncertain nonlinearities and parametric uncertainties.

Matching design of hydraulic load simulator with aerocraft actuator

This paper intends to provide theoretical basis for matching design of hydraulic load simulator （HLS） with aerocraft actuator in hardware-in-loop test, which is expected to help actuator designers overcome the obstacles in putting forward appropriate requirements of HLS. Traditional research overemphasizes the optimization of parameters and methods for HLS controllers. It lacks deliberation because experimental results and project experiences indicate different ultimate performance of a specific HLS. When the actuator paired with this HLS is replaced, the dynamic response and tracing precision of this HLS also change, and sometimes the whole system goes so far as to lose control. Based on the influence analysis of the preceding phenomena, a theory about matching design of aerocraft actuator with HLS is presented, together with two paired new concepts of ＂Standard Actuator＂ and ＂Standard HLS＂. Further research leads to seven important conclusions of matching design, which suggest that appropriate stiffness and output torque of HLS should be carefully designed and chosen for an actuator. Simulation results strongly support that the proposed principle of matching design can be anticipated to be one of the design criteria for HLS, and successfully used to explain experimental phenomena and project experiences.

A fault-tolerant triple-redundant voice coil motor for direct drive valves:Design, optimization, and experiment

A direct drive actuator （DDA） with direct drive valves （DDVs） as the control device is an ideal solution for a flight actuation system. This paper presents a novel triple-redundant voice coil motor （TRVCM） used for redundant DDVs. The TRVCM features electrical/mechanical hybrid triple-redundancy by securing three stators along with three moving coils in the same frame. A permanent magnet （PM） Halbach array is employed in each redundant VCM to simplify the system structure. A back-to-back design between neighborly redundancies is adopted to decouple the magnetic flux linkage. The particle swarm optimization （PSO） method is implemented to optimize design parameters based on the analytical magnetic circuit model. The optimization objective function is defined as the acceleration capacity of the motor to achieve high dynamic performance. The optimal geometric parameters are verified with 3D magnetic field finite element analysis （FEA）. A research prototype has been developed for experimental purpose. The experimental results of magnetic field density and force output show that the proposed TRVCM has great potential of applications in DDA systems.