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双语推荐:纵向运动

穿浪双体船在海洋中高速航行时,纵向运动会对其性能造成不利影响,产生的垂向加速度使乘员晕船,设备短期失效。为了解决此问题,首先建立穿浪双体船纵摇和垂荡运动模型,然后运用切片理论求解运动方程中的水动力系数,将随机海浪作为外界干扰,以T型水翼为纵向运动稳定装置,进而建立带T型水翼的穿浪双体船纵向运动模型。最后以90 m长的穿浪双体船为研究对象,利用状态反馈H∞控制策略设计控制器,对船体的纵摇和垂荡进行仿真实验。结果表明:状态反馈H∞控制器可有效地减小船舶纵向运动,降低晕船率,为减小高速船纵向运动提供可靠实用的方法。
When wave piercing catamaran sails at high speed in the sea, longitudinal motion has a harmful influence on its performance. The vertical acceleration makes crew seasickness and equipments out of work in a short term. In order to solve this problem, pitching and heaving motion model of wave piercing catamaran is established. Then strip theory is used to solve hydrodynamic coefficients of motion equation. Considering random ocean wave as external interference and T-foil as stability device of longitudinal motion, the longitudinal motion model of wave piercing catamaran with T-foil is established. The pitching and heaving motion is experimenting with the 90 -meters wave piercing catamaran using state-feedback H∞algorithm as controller. The results show that state-feedback H∞ controller could reduce the longitudinal motion of the ship and the rate of seasickness effectively. This paper has provided a reliable and practical method to reduce the longitudinal motion of wave pierc
为有效抑制果园钢索牵引悬挂式货运系统吊重的纵向偏摆,该文采用根轨迹校正法设计了系统纵向运行稳定性控制器。在忽略侧向运动影响的前提下,利用拉格朗日方程建立了线性化的纵向动力学模型。通过在左半复平面添加2个零点,对系统的根轨迹进行了校正。仿真和试验结果表明:所提出的只考虑吊重在纵向平面内运动的数学模型能够表述原系统运动特性,设计的控制器可快速衰减纵向偏摆,抑制吊重纵向摆动角度在±1.5°以内,将摆角角速度幅度极值减小至10%。该研究为悬挂货运系统的纵向稳定性控制提供了参考依据。
A cable-driven hanging transport system has the characteristics of labor saving, economic efficiency and good revenue, along with good prospect for increasing orchard utilization. Compared with the wheeled carrier and crawler, it can meet the demand of the complex mountainous topography. Both during and after transfer, the load motion of the hanging system can cause load swings, which is undesirable especially in the variations of acceleration. The longitudinal oscillations may lead to the instability of system and damage of agricultural goods. The aim of this paper is to develop an effective control method for the load motion that produces short travel time with suppressed load swing and satisfies operational constraints. Due to the nonlinearities of spatial three-dimensional motion of transferred load, the dynamics of the cable-driven hanging transport system showed complexity with coupled motion of load. In fact, the lateral movement had little effect on the longitudinal s
提出了一种包含侧向和纵向运动控制模块的路径跟随策略,搭建了基于微分平坦理论的侧向运动控制模块,把非线性车辆模型反馈线性化.通过极点配置实现了对车辆行驶轨迹的闭环控制。搭建了双闭环纵向运动控制模块,外环对车辆的行驶距离进行控制,内环对车辆的纵向车速进行控制。实车试验结果表明,该控制策略能把跟随误差限制在7cm内。
A following strategy of a fully-automatic parking assist system comprising lateral and longitudinal motion control module is presented in this paper. The lateral motion control module based on differential flatness theory is established. After linearizing the non-linear vehicle model feedback, closed loop of vehicle traveling track is realized through pole placement. Dual closed-loop longitudinal motion control module is established, with the outer closed-loop controls the distance traveled of the vehicle, while the inner-loop controls the longitudinal velocity. Field test results show that with this control strategy, following error can be limited within 7 centimeters.

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基于非线性动力学理论,分析了飞机大迎角纵向机动的稳定性及混沌行为。根据纵向机动的动力学模型,分析了飞机在大迎角状态下的飞行稳定性,通过 Lyapunov 稳定性原理,给出了不同参数匹配条件下飞机的纵向机动稳定域;以升降舵偏角和质量为系统参数,利用Melnik-ov方法,研究了飞机纵向机动的混沌运动,得到通向混沌的道路;通过数值仿真得出不同条件下的飞机纵向运动的Lyapunov指数,分析实验结果并对理论推演进行了验证。结果表明:大攻角机动情况下,飞机极易进入混沌状态,造成飞行不稳定甚至导致飞行事故。
Based on nonlinear dynamics theory,this paper analyzes the stable field and roads led to chaos of aircraft vertical maneuvering at high angles of attack,analyzes flight stability of aircraft at the high angle state and puts forward the stable field of vertical maneuvering under various matching parameter on the ba-sis of aircraft vertical maneuvering equation.Regarding rudder angle and quality as variable parameters, the chaos movement is analyzed by developing the heteroclinic orbit based on Melnikov method.This pro-vides a theory foundation for the control of aircraft vertical maneuvering at high angles of attack under va-rious conditions.

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针对小波方法对自主式水下机器人(AUV)纵向速度进行外部随机干扰抑制时存在的过抑制问题,提出一种AUV纵向速度信号故障特征增强与外部随机干扰抑制方法,采用自适应随机共振方法实现AUV纵向速度信号的随机共振,以达成外部随机干扰能量向故障信号能量的转移;针对AUV纵向速度信号的非周期特性,基于AUV纵向速度信号与周期信号驱动下双稳系统输出信号实验数据,分析AUV纵向速度信号驱动下布朗粒子运动状态。水池实验结果表明:所提方法相对小波方法故障信号特征增强效果为70.66%,避免了过抑制问题,且布朗粒子仅在负势阱内运动
With respect to over-attenuation caused by wavelet decomposition, when attenuating the external stochas-tic disturbance for longitude velocity of autonomous underwater vehicle ( AUV) , a novel algorithm was proposed to enhance fault feature and attenuate stochastic disturbance for AUV longitude velocity. The stochastic resonance of longitude velocity was obtained based on adaptive stochastic resonance, thereby transmitting the energy of external disturbance to that of fault signal. Based on experiment data from outputs of bistable system driven by the non-peri-odic longitude velocity signal and periodic signal, respectively, the motion state of Brownian particle driven by the longitude velocity was analyzed. The pool experiment results showed that in comparison with wavelet method, the enhancement of fault feature was improved by 70.66% without over-attenuation based on the proposed method, the Brownian particle just moved in negative potential well.
针对滑行艇高速运行下出现的海豚运动,研究了周期变推力对滑行艇纵向运动的控制。通过仿真,对不同艇体参数下发生海豚运动的风险进行了评估。开环仿真验证了周期变推力控制海豚运动原理,并得到了周期变推力影响滑行艇纵向运动的规律。通过检测滑行艇纵摇角信息,反馈给周期变推力形成闭环控制,使周期变推力施加的时机更精确,进而优化了减纵摇的效果。利用柴油机变转速控制仿真,验证了变推力控制海豚运动的应用性。仿真结果验证了所提方法的有效性,周期变推力控制能够有效抑制海豚运动,同时不损失滑行艇运行速度,保证了滑行艇运行的安全性和高效性。
This paper focused on periodic force control for vertical motion of planing vessels, according to porpoising of planning vessels running at high speed. The risk of porpoising was evaluated based on simulation of different pa-rameters. The open-loop simulation of periodic force control was shown to verify its rationality, and several rules a-bout how periodic force affects the pitch motions were obtained. The planning vessel'' pitch angle was tested and then the information was feed back to the periodic force control in a closed-loop, which made the time of applying periodic force more accurate, thus made the mitigation of porpoising more effective. A changeable-speed control sys-tem simulation of a diesel engine was proposed to verify its application. The simulation results demonstrate the effec-tiveness of the suggested approach. Periodic force control has effective mitigation for porpoising without loss of run-ning speed, which ensures safety and high effectiveness of the vessels.

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针对高超声速滑翔飞行器再入轨迹规划问题,提出了一种基于微分平坦理论的三自由度轨迹生成方法。在分析纵向运动简化模型的微分平坦属性基础上,将纵向参考轨迹规划问题映射到平坦输出空间,消除微分动力学约束的同时降低系统设计的维数,进而提高求解效率;采用全局插值多项式参数化平坦输出函数,将问题转换为非线性规划问题求解;设计比例-微分反馈控制律跟踪纵向参考轨迹,同时采用航向角误差走廊控制侧向运动,实现三自由度轨迹生成。仿真分析表明所提出的方法能够较快生成满足多种约束且性能优化的飞行轨迹。
For the trajectory planning problem in hypersonic glide vehicle,a differential flatness based three-degree-of-freedom trajectory generation approach is proposed.Based on the flatness analysis of the simplified longitudinal motion model,the reference longitudinal trajectory planning problem was mapped into the flat output space to improve the solving efficiency by eliminating the dynamical constraints and reducing the design dimension.Then the initial problem was transformed into a nonlinear programming problem utilizing global polynomial approximations to the flat outputs.To compensate for the effects of the earth rotation and external disturbances,a Proportion-Differentiation control based reference trajectory tracking controller was designed with good convergence capability.By integrating the lateral motion determined by the error corridor of heading angle based bank angle revision,the three-degree-of-freedom gliding trajectory was ultimately generated.Numerical simulations were cond

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高空长航时大展弦比无人机机翼结构刚度小,在飞行中变形幅度大且特征频率低,与无人机飞行动力学响应耦合,改变了无人机的飞行动力学特性。为研究其影响,对大展弦比机翼结构进行空间梁假设,利用Hodges本征梁动力学模型,结合大展弦比气动力片条理论和准定常假设对无人机进行建模,计算配平状态下无人机的静变形。机翼柔性改变了无人机的纵向静稳定性,在不同推力分布下,计算并比较柔性无人机纵向静稳定性变化。计算不同飞行高度、结构刚度和有效载荷挂载情形下的无人机的纵向飞行品质,结果显示由于静弹性变形改变无人机配平状态下的俯仰转动惯量,导致无人机的纵向短周期频率减小,阻尼增大。由于机翼柔性的影响,无人机纵向长周期运动与结构弯曲变形运动发生耦合。
The high aspect ratio wing of the High Altitude Long Endurance ( HALE) UAV is flexible, causing the UAV to have large structural deformation .Adopting the spatial beam assumption of the high aspect ratio wing , this paper studies the flight dynamics of the UAV uses Hodges intrinsic beam dynamics model combined with aerody -namic strip theory and quasi-steady assumption , uses this method , computes the static deformation in trim state , analyzes the stability in different thrust distribution , calculates the flying qualities in different altitudes , structural rigidities and payload distributions .The results and their analysis show preliminarily that:( 1) the flexible high as-pect ratio wing changes the longitudinal static stability and the pitch inertia of the UAV , resulting in decreased short cycle frequency and increased damping;( 2) the phugoid motion couples with structure bending motion .

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车辆的横向偏移现象在现实的交通流中广泛存在,交通瓶颈处的横向偏移现象往往更加显著。车辆间横纵向运动相互干扰,使得瓶颈交通流组织十分混乱,通行能力受到显著影响。为了研究瓶颈处车辆横纵向行为规律及其对交通流的影响,提出一个考虑横向偏移特征的车辆行为模型:通过引入目标转向角概念,并结合经典优化速度模型,给出了用于描述车辆的横纵向运动规律的运动方程,同时通过分析车辆横向偏移特征,制定了基于车辆行驶状态划分的目标转向角确定规则集。数值模拟结果表明:车辆的横向偏移会对交通流的运行产生影响,在一定的横向偏移反应阈值下,瓶颈处横向干扰于交通流的影响随着密度的增加而增加;同时观察到了实际城市交通瓶颈的宏观及微观现象,验证了模型的有效性。
Microscopic traffic models are developed to simulate traffic phenomena. However, current models are usually based on the fact that vehicles travel in the middle of a single lane and make a lateral movement only when the driver wants to change lane. They are incapable of describing driving behavior in a complex traffic environment with a lot of lateral separations which may cause traffic flow to be unstable on a single lane. In order to solve the problem, in this paper we first build up the equations of motion based on target steering angle (TSA) and then establish a series of rules for determining TSA by considering the lateral separation characteristics between the follower and the leader. Finally a new vehicular behavior model is developed. The properties of the model are investigated by simulating two scenarios. It is found that the proposed model is capable of describing complex phenomena which cannot be described by existing models and explaining the perturbation caused by bus nea

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研究反鱼雷鱼雷( anti-torpedo torpedo, ATT)与目标鱼雷纵向运动关系,推导ATT与目标鱼雷视线高低角状态方程,采用变结构控制方法设计控制器,将ATT与目标鱼雷视线高低角控制在零角度,通过Lyapunov稳定性理论证明了视线高低角能够控制在零角度。仿真分析表明,在所设计的变结构拦截导引律作用下, ATT与目标鱼雷在纵向的视线高低角稳定趋于零, ATT在纵向可精确命中目标。
A state equation of the sight elevation angle between an anti-torpedo torpedo ( ATT) and a target torpedo is deducted according to the moving relation between the ATT and the target torpedo. Based on the state equation,a variable structure controller is designed to ensure that the sight elevation angle between the ATT and the target torpe-do is zero, which can be proved by Lyapunov stability theory. Simulation analyses show that the sight elevation angle between the ATT and the target torpedo converges to zero stably and the ATT hits the target precisely by taking the advantage of the longitudinal intercepting guidance law generated by the proposed variable structure controller.

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