A novel strategy of smart manipulation by micro-scale oscillatory networks of the reactionary zones for enhanced extreme thrust control of the next-generation solid propulsion systems

The main aim of this research is to get a better knowledge and understanding of the micro-scale oscillatory networks behavior in the solid propellants reactionary zones. Fundamental understanding of the micro-and nano-scale combustion mechanisms is essential to the development and further improvement of the next-generation technologies for extreme control of the solid propellant thrust. Both experiments and theory confirm that the micro-and nano-scale oscillatory networks excitation in the solid propellants reactionary zones is a rather universal phenomenon. In accordance with our concept,the micro-and nano-scale structures form both the fractal and self-organized wave patterns in the solid propellants reactionary zones. Control by the shape, the sizes and spacial orientation of the wave patterns allows manipulate by the energy exchange and release in the reactionary zones. A novel strategy for enhanced extreme thrust control in solid propulsion systems are based on manipulation by selforganization of the micro-and nano-scale oscillatory networks and self-organized patterns formation in the reactionary zones with use of the system of acoustic waves and electro-magnetic fields, generated by special kind of ring-shaped electric discharges along with resonance laser radiation. Application of special kind of the ring-shaped electric discharges demands the minimum expenses of energy and opens prospects for almost inertia-free control by combustion processes. Nano-sized additives will enhance self-organizing and self-synchronization of the micro-and nano-scale oscillatory networks on the nanometer scale. Suggested novel strategy opens the door for completely new ways for enhanced extreme thrust control of the solid propulsion systems.

Reduced-dimensional MPC controller for direct thrust control

With the development of the aircraft gas turbine engine, a control system should be able to achieve effective thrust control to gain better operability. The main contribution of this paper is to develop a novel direct thrust control approach based on an improved model predictive control method through a strategy that reduces the dimension of control sequence. It can not only achieve normal direct thrust control tasks but also maximize the thrust level within the safe operation boundaries. Only the action of switching the objective functions is required to achieve the switch of these two thrust control modes while there is no modification to the control structure. Besides,a shorter control sequence is defined for multivariable control by updating only one control variable at every simulation time instant. Therefore, the time requirement for the solving process of the optimal control sequence is reduced. The proposed controller is implemented to a twin-spool engine.Simulations are conducted in the wide flight envelope, and results show that the average timeconsumption can be reduced up to 65% in comparison with the standard model predictive control,and the thrust can be increased significantly when maximum thrust mode is implemented by using engine limit margins.

Direct thrust control for multivariable turbofan approach

A novel turbofan Direct Thrust Control(DTC)architecture based on Linear ParameterVarying(LPV)approach for a two-spool turbofan engine thrust control is proposed in this paper.Instead of transforming thrust command to shaft speed command and pressure ratio command,the thrust will be directly controlled by an optimal controller with two control variables.LPV model of the engine is established for the designing of thrust estimator and controller.A robust LPV H∞filter is introduced to estimate the unmeasurable thrust according to measurable engine states.The thrust estimation error system is proved to be Affinely Quadratically Stable(AQS)in the whole parameter box with a prescribed H∞performance indexγ.Due to the existence of overdetermined equations,the solving of controller parameters is a multi-solution problem.Therefore,Particle Swarm Optimization(PSO)algorithm is used to optimize the controller parameters to obtain satisfactory control performance based on the engine’s LPV model.Numerical simulations show that the thrust estimator can acquire smooth and accurate estimating results when sensor noise exists.The optimal controller can receive desired control performance both in steady and transition control tasks within the engine working states above the idle,verifying the effectiveness of the proposed DTC architecture’s application in thrust direct control problem.

Neural network-based model predictive control with fuzzy-SQP optimization for direct thrust control of turbofan engine

A nonlinear model predictive control method based on fuzzy-Sequential Quadratic Programming(SQP)for direct thrust control is proposed in this paper for the sake of improving the accuracy of thrust control.The designed control system includes four parts,namely a predictive model,rolling optimization,online correction,and feedback correction.Considering the strong nonlinearity of engine,a predictive model is established by Back Propagation(BP)neural network for the entire flight envelope,whose input and output are determined with random forest algorithm and actual situation analysis.Rolling optimization typically uses SQP as the optimization algorithm,but SQP algorithm is easy to trap into local optimization.Therefore,the fuzzy-SQP algorithm is proposed to prevent this disadvantage using fuzzy algorithm to determine the initial value of SQP.In addition to the traditional three parts of model predictive control,an online correction module is added to improve the predictive accuracy of the predictive model in the predictive time domain.Simulation results show that the BP predictive model can reach a certain degree of predictive accuracy,and the proposed control system can achieve good tracking performance with the limited parameters within the safe range。

Motion control of thrust system for shield tunneling machine

The thrust hydraulic system of the prototype shield machine with pressure and flow compound control scheme was introduced. The experimental system integrated with proportional valves for study was designed. Dynamics modeling of multi-cylinder thrust system and synchronous control design were accomplished. The simulation of the synchronization motion control system was completed in AMESim and Matlab/Simulink software environments. The experiment was conducted by means of master/slave PID with dead band compensating flow and conventional PID regulating pressure. The experimental results show that the proposed thrust hydraulic system and its control strategy can meet the requirements of tunneling in motion and posture control for the shield machine, keeping the non-synchronous error within ±3 mm.

塔里木盆地西北缘沙井子断裂带的构造特征与形成演化

塔里木盆地西北缘的沙井子断裂带,位于塔北隆起的温宿凸起和北部坳陷的阿瓦提凹陷之间。它是塔里木盆地的一条一级断裂带,由沙井子断裂、英雄断裂、温宿断裂和沙南断裂组成。其中沙井子断裂是主干断裂,其它3条是其分支断裂。本轮研究新发现温宿分支断裂,并将沙南断裂解释为英雄断裂前缘的反冲断层,归属沙井子断裂带。沙井子断裂带的雏形形成于奥陶纪末—志留纪初,在泥盆纪末—石炭纪、二叠纪末—三叠纪初、侏罗纪末—白垩纪初、白垩纪末—古近纪初和新近纪—第四纪发生过多期冲断作用和新近纪末—第四纪初的张扭性构造变形后,才最终定型。沙井子断裂带是一条断控油气富集区带,温宿油田、托探1油藏、沙南1油藏、新苏地1油气藏等都受其控制。

基于推力矢量分配的ROV姿态控制技术研究

针对遥控水下机器人(ROV:Remote Operated Vehicle)在水下作业时,传统滑膜控制(SMC:Sliding Mode Control)方法存在抖振、稳定性差等问题,提出一种新型协同控制律,并设计出一种基于推力矢量分配的ROV姿态控制器。首先,建立ROV运动学和动力学模型,并解耦动力学模型;然后,提出了一种新型协同控制律,通过构造适当的宏变量使其呈指数收敛,从而为ROV姿态控制系统提供连续的控制律,达到消除ROV姿态控制系统抖振的目的;最后,采用新型协同控制律设计出基于推力矢量分配的ROV姿态控制器。通过Matlab/Simulink进行仿真,结果表明,所提出的新型协同控制律可提高ROV姿态控制系统的控制精度与稳定性。该控制策略为ROV姿态控制提供了一种新的可行方案。

基于直接推力控制的直驱波浪发电系统功率优化

为提升系统波能捕获能力,分析浮子受力,以状态空间法近似拟合辐射力,建立直驱式波浪发电系统数学模型。基于最优控制理论,以系统捕获波能为目标函数,在S域求解Hamilton方程,计算奇异最优控制率,经拉氏逆变换后得到理想电磁力信号。结合直接推力控制,设计二阶滑模控制方案,保证电机推力与初级磁链的跟踪效果。仿真结果表明,所提最优功率方案下系统捕获功率高,滑模控制器跟踪误差小、动态性能好,可提高波能转化率,有效降低推力与初级磁链脉动,增强系统鲁棒性。

基于改进LADRC的矢量推力双旋翼飞行器姿态控制

针对矢量推力双旋翼无人机姿态控制过程中存在强耦合、模型不精确的问题,提出了一种改进型的线性自抗扰姿态控制(linear active disturbance rejection controller,LADRC)方法。该方法利用改进线性扩张状态观测器(linear extended state observer,LESO)提高对总扰动的实时观测精度,根据姿态角的误差及其变化率引入模糊控制思想对线性状态误差反馈控制律进行在线参数整定,最后以矢量推力双旋翼飞行器为研究对象,对比PID和常规LADRC对外界扰动的抗扰效果,仿真试验验证了该方法能够较好估计补偿系统的总扰动,具有更好的抗扰性能和收敛速度。

无人机短距着陆控制技术研究

研究固定翼无人机短距着陆性能具有十分重要的现实意义。基于对象无人机三种襟翼构型中的着陆襟翼构型,分析以固定油门为基础的传统着陆控制方式存在的缺陷性问题,从动力学角度分析近地段在低速、大姿态状态下各项着陆指标间的相互制约关系,并得出“空速为影响着陆性能的主导诱因”这一重要结论,从动力学角度提出油门速度闭环控制方案。在控制律设计过程中,创新性地采用线性化理论分析和半物理非线性仿真相结合的手段,充分结合工程实践经验,突出了油门速度控制的特殊性与有效性,使着陆性能得到前所未有的提升。

三摆臂式扰流片矢量气动力数值仿真研究

为适应智能可控弹药发动机喷口愈来愈小的发展趋势,针对三摆臂式扰流片矢量控制形式开展了气动力数值仿真。研究三摆臂式扰流片推力和侧向力调节能力。结果表明:推力随着主推角的增加而降低,最大推力损失仅与主推角有关;当主推角大于36°,扰流片间的气动干扰增强;侧向力随着侧向角和入口压力的增加而增大;当3个扰流片均位于发动机尾流中,前后方向和左右方向侧向力调节干扰小,且侧向力调节对推力影响小。

Thrust estimator design based on least squares support vector regression machine

In order to realize direct thrust control instead of traditional sensor-based control for aero-engines,it is indispensable to design a thrust estimator with high accuracy,so a scheme for thrust estimator design based on the least square support vector regression machine is proposed to solve this problem. Furthermore,numerical simulations confirm the effectiveness of our presented scheme. During the process of estimator design,a wrapper criterion that can not only reduce the computational complexity but also enhance the generalization performance is proposed to select variables as input variables for estimator.

基于喷管二次流控制的推力矢量特性研究

通过控制二次流喷口相对位置和宽度来改变喷管出口燃气流动方向是实现推力矢量控制的方法之一。为掌握落压比(NPR)、二次流压比(SPR)以及二次流喷口相对位置(X_(j))和宽度(d)对推力矢量性能的影响,通过数值计算分析了发动机推力矢量角(δ)、推力系数(C_(f))变化规律。结果表明,随着落压比的减小,喷管可以获得更大的推力矢量角度,但推力损失更大;主流落压比不同时,喷管推力矢量效率的最小值所对应的二次流压比不同;随着二次流喷口宽度的增加,喷管的推力矢量角度逐渐增大且随着二次流压比的增大其增幅也随之变大;推力矢量效率在SPR≤0.6时,随着二次流喷口宽度的增大而减小;SPR=0.8后随着二次流喷口宽度的增大先下降后上升,SPR=1.2时随着二次流喷口宽度的增大而增大;随着二次流喷口位置向喷管出口的移动,推力矢量角仅在喷口后的气流分离由闭式变为开式时发生一次突增,而推力系数发生一次突减;随着二次流喷射角度的增大,喷管的推力矢量角度不断增大,喷管的推力系数呈现不断减小的趋势。

利用径向力平衡飞行控制的航天器高精度轨道捕获方法

为实现对探测器轨道形状与高度的精准调整,提出一种径向力平衡飞行的航天器连续推力控制新方法。建立连续推力平衡飞行的动力学极坐标模型,并推导出特殊条件下的解析轨道解,进一步分析边值条件,给出连续推力的控制律。利用这一平衡飞行控制理论,构建轨道捕获的最优控制策略。考虑推力器的推力水平,通过一次或多次的控制过程,实现对轨道形状、轨道高度及轨道相位的综合调整。数值仿真表明:利用平衡飞行的轨道控制方法,配置微小推力器的空间引力波探测器可以实现高精度的轨道捕获;该方法具有控制过程可解析、计算量小、简便、实用等特点。

考虑推力陷阱的组合动力飞行器切换控制方法研究

针对组合动力飞行器动力切换时的推力陷阱问题,提出了一种考虑推力陷阱的组合动力飞行器切换控制方法。首先,针对组合动力飞行器正常飞行控制需求,基于超螺旋滑模控制方法,设计了正常飞行控制器,从而实现飞行器受扰动情况下的有限时间稳定跟踪参考指令;其次考虑组合动力飞行器动力切换引起的推力损失带来的控制约束,设计了输入约束控制器,实现模态转换阶段跟踪误差有限时间收敛的同时减小推力需求;然后考虑正常情况及模态转换阶段控制器的结合,设计了组合发动机软切换控制方法;最后通过仿真验证了所设计的控制器能够有效规避推力损失现象,并且能够有效保障切换控制系统的稳定性及鲁棒性。

基于卡尔曼滤波算法的风电机组动态推力消减控制策略

随着变桨变速式风电机组叶片的大型化发展趋势,风电机组在额定风速区域运行时,由于尖峰推力导致的极限荷载问题越来越突出。为此,在风电机组基本控制策略基础上提出了一种基于卡尔曼滤波算法的动态推力消减控制策略,根据风电机组能量传递关系,以测量转矩、桨距角和风轮转速为输入量,对轮毂风速进行估计,经过推力消减控制器的最优桨距角计算实现动态变桨,以降低风电机组整体的轴向推力水平;最后以某5.0MW风电机组为例,搭建了半实物仿真实验平台,对提出的控制策略进行了实验验证。实验结果表明:该控制策略能够有效降低风电机组轴向推力,减小风电机组极限荷载。

直线电机分段供电协同控制策略

针对多个变流器交替为长定子直线电机多个定子段分段供电存在的问题,该文提出一种电流协同控制策略来减小推力波动。首先,优化电机电路连接拓扑,将由同一变流器供电的定子段的中性点连接在一起,采用电流过零开通的切换策略,使得电流由一个定子段切换至另一个定子段的过程中,变流器的电流连续无畸变。然后,建立电机单个定子段(简称单元电机)的电压和推力方程。根据单元电机的状态方程,得出2个单元电机的电流之和、电流之差对应的状态方程及推力表达式,设计相应的电流协同控制器。通过2个单元电机的电流之和来控制系统输出推力、2个单元电机的电流之差来控制推力波动。该电流控制策略减少了动子过分段时产生的推力波动,实现推力与电流偏差导致的推力波动之间的解耦控制。仿真和实验结果验证了所提电流协同控制策略的有效性。

Novel TPN control algorithm for exoatmospheric intercept

A novel control algorithm with fixed pulse thrust, based on true proportional navigation（TPN）, is proposed for exoatmospheric intercept.According to the TPN guidance law and pulse thrust characteristics, the principle of control command is presented, the control stability and precision are analyzed.With the help of the TPN guidance law, the algorithm can automatically modulate the turn-on time and duration of the thrust, which could effectively limit the impact of measure noise of the line-of-sight（LOS） angle and rate on the interception miss-distance.At last, the number-theoretic method（NTM） is introduced to acquire the relation between control algorithm and miss-distance, even as it simulates the intercept process with initial state noise.And the reliability of the algorithm is demonstrated with the simulation result.

考虑疲劳载荷分布的海上风电机组出力优化控制

针对海上风电场疲劳载荷分布不均衡、各机组维护频次不同步而导致运维成本高的问题,提出了一种考虑疲劳载荷分布的海上风电机组出力优化控制策略。基于风机最小推力系数控制策略有效降低风电场的尾流效应,以疲劳载荷分布均衡为目标优化各机组的疲劳载荷,使各机组维护频次同步,进而降低运维成本。仿真结果表明:与风机最大功率点跟踪控制策略相比,所提策略在实现风电场疲劳载荷均衡分布的同时,使得风电场年发电量提高4.20%。

Numerical Investigation of Plasma Active Flow Control

Based on the theory of EHD （electronhydrodynamic）, a simplified volume force model is applied to simulation to analyze the traits of plasma flow control in flow field, in which the cold plasma is generated by a DBD （dielectric-barrier-discharge） actuator. With the para- electric action of volume force in electric field, acceleration characteristics of the plasma flow are investigated for different excitation intensities of RF （radio frequency） power for the actuator. Furthermore, the plasma acceleration leads to an asymmetric distribution of flow field, and hence induces the deflection of jet plume, then results in a significant deflection angle of 6.26° thrustvectoring effect. It appears that the plasma flow control technology is a new tentative method for the thrust-vectoring control of a space vehicle.