A high resolution inversion method for fluid factor with dynamic dryrock V_(P)/V_(S) ratio squared

As an important indicator parameter of fluid identification,fluid factor has always been a concern for scholars.However,when predicting Russell fluid factor or effective pore-fluid bulk modulus,it is necessary to introduce a new rock skeleton parameter which is the dry-rock VP/VS ratio squared(DVRS).In the process of fluid factor calculation or inversion,the existing methods take this parameter as a static constant,which has been estimated in advance,and then apply it to the fluid factor calculation and inversion.The fluid identification analysis based on a portion of the Marmousi 2 model and numerical forward modeling test show that,taking the DVRS as a static constant will limit the identification ability of fluid factor and reduce the inversion accuracy.To solve the above problems,we proposed a new method to regard the DVRS as a dynamic variable varying with depth and lithology for the first time,then apply it to fluid factor calculation and inversion.Firstly,the exact Zoeppritz equations are rewritten into a new form containing the fluid factor and DVRS of upper and lower layers.Next,the new equations are applied to the four parameters simultaneous inversion based on the generalized nonlinear inversion(GNI)method.The testing results on a portion of the Marmousi 2 model and field data show that dynamic DVRS can significantly improve the fluid factor identification ability,effectively suppress illusion.Both synthetic and filed data tests also demonstrate that the GNI method based on Bayesian deterministic inversion(BDI)theory can successfully solve the above four parameter simultaneous inversion problem,and taking the dynamic DVRS as a target inversion parameter can effectively improve the inversion accuracy of fluid factor.All these results completely verified the feasibility and effectiveness of the proposed method.

An Improved Nonlinear Dynamic Inversion Method for Altitude and Attitude Control of Nano Quad-Rotors under Persistent Uncertainties

Nonlinear dynamic inversion(NDI)has been applied to the control law design of quad-rotors mainly thanks to its good robustness and simplicity of parameter tuning.However,the weakness of relying on accurate model greatly restrains its application on quad-rotors,especially nano quad-rotors(NQRs).NQRs are easy to be influenced by uncertainties such as model uncertainties(mainly from complicated aerodynamic interferences,strong coupling in roll-pitch-yaw channels and inaccurate aerodynamic prediction of rotors)and external uncertainties(mainly from winds or gusts),particularly persistent ones.Therefore,developing accurate model for altitude and attitude control of NQRs is difficult.To solve this problem,in this paper,an improved nonlinear dynamic inversion(INDI)method is developed,which can reject the above-mentioned uncertainties by estimating them and then counteracting in real time using linear extended state observer(LESO).Comparison with the traditional NDI(TNDI)method was carried out numerically,and the results show that,in coping with persistent uncertainties,the INDI-based method presents significant superiority.

NONLINEAR DYNAMIC INVERSION CONTROL WITH ADAPTIVE COMPENSATION FOR FLIGHT CONTROL SYSTEM

A type of nonlinear dynamic inversion control with adaptive compensation is proposed in order to overcome its over sensitivity to parameter uncertainty and disturbance for flight control system using nonlinear dynamic inversion. This control strategy is different from the general strategy of a nonlinear adaptive control by taking into consideration both parameter uncertainty and external disturbance, the two major uncertain forms in flight control. Finally, an analysis of the stabilily of this control structure is given.

Civil aircraft fault tolerant attitude tracking based on extended state observers and nonlinear dynamic inversion

For the problem of sensor faults and actuator faults in aircraft attitude control,this paper proposes a fault tolerant control(FTC)scheme based on extended state observer(ESO)and nonlinear dynamic inversion(NDI).First,two ESOs are designed to estimate sensor faults and actuator faults respectively.Second,the angular rate signal is reconstructed according to the estimation of sensor faults.Third,in angular rate loop,NDI is designed based on reconstruction of angular rate signals and estimation of actuator faults.The FTC scheme proposed in this paper is testified through numerical simulations.The results show that it is feasible and has good fault tolerant ability.

Trajectory Tracking of Quadrotor Aerial Robot Using Improved Dynamic Inversion Method

This paper presents trajectory tracking control works concerning quadrotor aerial robot with rigid cross structure. The quadrotor consists of four propellers which are two paired clockwise rotate and anticlockwise rotate. A nonlinear dynamic model of the quadrotor is provided, and a controller based on the improved dynamic inverse is synthesized for the purpose of stabilization and trajectory tracking. The proposed control strategy has been tested in simulation that can balance the deviation of model inaccuracy well.

Output Feedback for Stochastic Nonlinear Systems with Unmeasurable Inverse Dynamics

This paper considers a concrete stochastic nonlinear system with stochastic unmeasurable inverse dynamics. Motivated by the concept of integral input-to-state stability （iISS） in deterministic systems and stochastic input-to-state stability （SISS） in stochastic systems, a concept of stochastic integral input-to-state stability （SiISS） using Lyapunov functions is first introduced. A constructive strategy is proposed to design a dynamic output feedback control law, which drives the state to the origin almost surely while keeping all other closed-loop signals almost surely bounded. At last, a simulation is given to verify the effectiveness of the control law.

Dynamic mechanical behavior and nonlinear hyper-viscoelastic constitutive model of SiO_(2) particle-reinforced silicone rubber composite:experimental and numerical investigation

SiO_(2)-particle reinforced silicon rubber composite(SP-RSRC)is a widely utilized material that offers shock absorption protection to various engineering structures in impact environments.This paper presents a comprehensive investigation of the mechanical behavior of SP-RSRC under various strain rates,employing a combination of experimental,theoretical,and numerical analyses.Firstly,quasi-static and dynamic compression tests were performed on SP-RSRC utilizing a universal testing machine and split Hopkinson pressure bar(SHPB)apparatus.Nonlinear stress-strain relationships of SP-RSRC were obtained for strain rates ranging from 1×10^(−3) to 3065 s^(−1).The results indicated that the composite showed evident strain rate sensitivity,along with nonlinearity.Then,a nonlinear visco-hyperelastic constitutive model was developed,consisting of a hyperelastic component utilizing the 3rd-order Ogden energy function and a viscous component employing a rate-dependent relaxation time scheme.The model accurately characterized the dynamic mechanical response of SP-RSRC,effectively mitigating the challenge of calibrating an excessive number of material parameters inherent in conventional viscoelastic models.Furthermore,the simplified rubber material(SRM)model,integrated within the LS-DYNA software,was chosen to depict the mechanical properties of SP-RSRC in numerical simulations.The parameters of the SRM model were further calibrated based on the strain-stress relationships of SP-RSRC,as predicted by the developed nonlinear visco-hyperelastic constitutive model.Finally,an inverse ballistic experiment using a single-stage air gun was conducted for SP-RSRC.Numerical simulations of SHPB experiments and the inverse ballistic experiment were then performed,and the reliability of the calibrated SRM model was verified by comparing the results of experiments and numerical simulations.This study offers a valuable reference for the utilization of SP-RSRC in the realm of impact protection.

基于增量非线性动态逆的导弹解耦控制设计

针对导弹大迎角机动存在强耦合动力学特点,提出了一种基于增量非线性动态逆的解耦控制方法,将自动驾驶仪分为高带宽的快变角速率内回路和低带宽的慢变角回路控制,用部分逆近似求解的方法分别设计了增量形式的动态逆控制律对消不同的耦合项,实现控制解耦的目的。典型工况数字仿真结果表明,所设计的导弹增量非线性动态逆控制解耦律大大改善了强耦合动力学下的稳定控制性能。相比传统PID控制,它能够完全消除过载响应的低频振荡和超调量,同时还使得滚转角响应能够准确跟踪指令。

INVERSION OF A NONLINEAR DYNAMICAL MODEL FROM THE OBSERVATION

A technique for inversion of a nonlinear dynamical model from the observations has been developed, and examined by using the Lorenz system. The results show that the Lorenz system can be accurately inversed by using the observation data set. This technique will be broadly used in establishing the nonlinear dynamical model from an actual data set.

应对风切变的四旋翼轨迹跟踪几何控制方法

针对存在风切变环境的四旋翼轨迹跟踪问题,提出了结合增量非线性动态逆的几何控制方法。首先,建立了基于SO(3)群的风切变扰动四旋翼动力学模型,并建立风场模型,引入风切变效应。其次,利用四旋翼的微分平坦特性将轨迹跟踪问题转换为状态跟踪问题,并依据微分平坦特性推导参考高阶状态量实现前馈控制。在控制器设计部分,姿态控制采用几何控制,使姿态具有全局不存在奇异点的特性。对于风场扰动带来的阻力与气动力矩,使用增量非线性动态逆方法进行补偿,实现线加速度和角加速度的控制。最后,基于Simulink在多种风速场景中对不同航迹进行了仿真实验,仿真结果验证了所提方法相较传统方法在面对风切变干扰情况下的有效性。

基于终端滑模的F-16固定翼飞行器有限时间编队控制

以F-16固定翼飞行器为研究对象,采用终端滑模控制方法,实现了六自由度固定翼飞行器的有限时间编队控制。首先,根据奇异摄动理论,将固定翼飞行器十二阶微分运动方程按照响应速度快慢分为外环位置编队控制系统和内环姿态跟踪控制系统。外环应用有限时间稳定性理论和非线性滑模控制方法设计了分布式控制器,实现多固定翼飞行器系统的有限时间编队控制。然后,将外环分布式控制器产生的控制信号转换为内环单架固定翼飞行器的姿态跟踪参考信号,内环应用非线性动态逆(nonlinear dynamic inversion,NDI)控制和增量非线性动态逆(incremental nonlinear dynamic inversion,INDI)控制在可能存在执行器故障的情况下实现单架固定翼飞行器姿态的跟踪控制。最后,通过仿真实例验证了该控制方法的有效性。

Survey on nonlinear reconfigurable flight control

An overview on nonlinear reconfigurable flight control approaches that have been demonstrated in flight-test or highfidelity simulation is presented. Various approaches for reconfigurable flight control systems are considered, including nonlinear dynamic inversion, parameter identification and neural network technologies, backstepping and model predictive control approaches. The recent research work, flight tests, and potential strength and weakness of each approach are discussed objectively in order to give readers and researchers some reference. Finally, possible future directions and open problems in this area are addressed.

Output regulation of nonaffine nonlinear systems using singular perturbation theory

A control synthesis method for output regulation based on singular perturbation theory combined with inverting design is considered for a class of nonaffine nonlinear systems. The resulting control signal is defined as a solution to ＂fast＂ dynamics which inverts a series error model, whose state is exponentially stable. It is shown that, under sufficient conditions being consistent with the assumptions of singular perturbation theory, this problem is solvable with （ε） tracking error if and only if a set of first-order nonlinear partial differential equations are solvable. The control law can be easily constructed and the simulations show the feasibility and effectiveness of the controller.

Nonlinear Accelerator Beam Transport Operator

This paper deals with the theory of nonlinear accelerator beam transport op-erator.For nonautonomous accelerator dynamics,a theorem of finding the inversenonlinear beam transport operator is developed.Several concrete examples are workedout in detail to show the practical applications of this theory.

基于动态逆控制的高超声速飞行器飞/发一体化控制方法研究

为了减小高超声速飞行器飞/发耦合效应对自身的影响,开展了高超声速飞行器飞/发一体化控制研究。建立面向控制的高超声速飞行器飞/发一体化数学模型。分别采用非线性动态逆控制与增量非线性动态逆控制方法,设计了姿态慢变外回路、角速率快变内回路控制算法。基于包含高超声速飞行器飞/发耦合特性的在线本体模型,以操纵交联的形式设计了高超声速飞行器姿态与发动机的耦合控制方案。在非线性动态逆控制器中引入参考模型、误差控制、在线估计等模块,保证了高超声速飞行器的飞行品质和鲁棒性要求。仿真实验结果表明,采用了非线性动态逆控制设计的飞/发耦合控制方案达到了预期的控制性能。

四旋翼无人机非线性轨迹跟踪控制

针对四旋翼轨迹跟踪在高频情况下易出现系统不稳定的问题,设计一种基于动态逆技术(Dynamic Inverse,DI)的轨迹跟踪方法。由于四旋翼是典型的欠驱动系统,本文考虑双闭环设计,通过各种数值实验验证在低频率与高频率情况下控制器的追迹性能,并与PID控制器进行比较。仿真结果表明,频率为0.6πrad/s时本文方法的位置跟踪均方误差比PID方法的误差小0.0514 m,当频率大于1.15πrad/s时PID控制方法使得系统出现不稳定,而本文方法仍可以完成较好的轨迹跟踪。

Practical compensation for nonlinear dynamic thrust measurement system

The real dynamic thrust measurement system usually tends to be nonlinear due to the complex characteristics of the rig, pipes connection, etc. For a real dynamic measuring system, the nonlinearity must be eliminated by some adequate methods. In this paper, a nonlinear model of dynamic thrust measurement system is established by using radial basis function neural network （RBF-NN）, where a novel multi-step force generator is designed to stimulate the nonlinearity of the system, and a practical compensation method for the measurement system using left inverse model is proposed. Left inverse model can be considered as a perfect dynamic compensation of the dynamic thrust measurement system, and in practice, it can be approximated by RBF-NN based on least mean square （LMS） algorithms. Different weights are set for producing the multi-step force, which is the ideal input signal of the nonlinear dynamic thrust measurement system. The validity of the compensation method depends on the engine＇s performance and the tolerance error 0.5%, which is commonly demanded in engineering. Results from simulations and experiments show that the practical compensation using left inverse model based on RBF-NN in dynamic thrust measuring system can yield high tracking accuracy than the conventional methods.

级联式预设性能动态逆解耦直接升力着舰控制

为在下滑着舰过程中,克服“反区”操纵特性,减轻飞行员操纵负担,提升着舰精度和安全性,将直接升力方法引入着舰控制律设计,发挥其响应速度快、控制精度高、解耦性能好等优点。采用预设性能的非线性动态逆方法和控制分配算法相结合的控制架构设计了两层级联式综合直接升力着舰控制器,既可以实现纵向轨迹和姿态控制间的解耦,还可以实现横航向控制与纵向运动间的解耦。首先,建立了舰载机全量六自由度非线性模型作为研究对象;然后,通过设置虚拟中间控制量将动态逆与控制分配环节有机地衔接,通过预设误差向量约束方程的方法提升动态逆控制环节的综合控制性能,据此设计出级联式纵、航向综合解耦的直接升力控制器;最后,仿真验证所设计的直接升力控制器可以在保持迎角和速度稳定的情况下调整飞行轨迹高度,实现纵向轨迹控制和姿态控制的解耦;还可以在对中控制的时候,保持纵向高度稳定,实现横航向运动和纵向运动的解耦。研究表明,采用直接升力控制可以实现飞行员操纵到控制变量间的逐一对应,显著减轻操纵负担并提升下滑着舰控制精度。

基于稳定逆的生化过程操作曲线求取方法

针对生化过程中操作曲线的求取问题,提出一种非线性稳定逆的近似求解方法。该方法根据过程动力学模型,利用改进的稳定逆算法来求解对应生产输出目标的操作曲线。并针对稳定逆算法计算量过大的问题,通过对稳定逆原理中的内动态进行离散化处理,将原本利用非线性系统内动态方程求解内动态解析解的过程,利用递推公式转化成求解内动态的离散数值解,从而加快稳定逆算法的计算速度。最后以化学反应器为例进行操作曲线设计的仿真,验证了所提方法的可行性。

一种基于增量式动态逆的涡轴发动机抗扰综合控制方法

针对全包线内涡轴发动机转速抗扰控制效果一致性与鲁棒性难以保证的问题,提出一种基于增量式动态逆的综合抗扰控制方法。结合涡轴发动机的转子动力学特性,提出一种基于增量式动态逆的主控回路设计方法。针对传统负载扭矩估计方法需要大量数据支撑的问题,提出一种基于非线性观测器的发动机端负载扭矩在线估计方法。基于主控回路动态逆算法和负载扭矩估计方法,创新性地将动态逆输入与输出的定量关系和转子加速度扰动变化量结合,提出了一种负载扭矩扰动全补偿前馈控制方法,并从理论上推导了该方法,能够使得由于负载扭矩导致的转子加速度扰动得到全补偿。基于倾转旋翼机/发动机综合非线性仿真模型,针对倾转旋翼机不同飞行的模式,进行抗扰控制效果仿真验证。结果表明:在频域上,基于增量式动态逆的综合抗扰控制方法能保证全包线的频域性能的一致性;在时域上,相比于具有相同带宽下的PID控制器,基于增量式动态逆的综合抗扰控制方法能够在全包线内使动力涡轮转速跟踪的调节时间降低1s,并可有效降低动力涡轮转速的下垂量至1%以内,具有优越的抗扰效果。