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.

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。

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.

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.

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。

BOOSTING SPARSE LEAST SQUARES SUPPORT VECTOR REGRESSION (BSLSSVR) AND ITS APPLICATION TO THRUST ESTIMATION

In order to realize direct thrust control instead of conventional sensors-based control for aero-engine, a thrust estimator with high accuracy is designed by using the boosting technique to improve the performance of least squares support vector regression （LSSVR）. There exist two distinct features compared with the conven- tional boosting technique： （1） Sampling without replacement is used to avoid numerical instability for modeling LSSVR. （2） To realize the sparseness of LSSVR and reduce the computational complexity, only a subset of the training samples is used to construct LSSVR. Thus, this boosting method for LSSVR is called the boosting sparse LSSVR （BSLSSVR）. Finally, simulation results show that BSLSSVR-based thrust estimator can satisfy the requirement of direct thrust control, i.e. , maximum absolute value of relative error of thrust estimation is not more than 5‰.

基于冗余执行器的航空发动机推力快速响应控制方法研究

面向飞/推一体化控制需求,开展涡扇发动机推力快速响应控制研究,提出了适用于推力最小相位系统的冗余控制方案。研究内容包括:(1)借鉴阀位控制思想,提出在传统燃油流量(Wf)回路基础上增设尾喷口喉道面积(A8)回路,通过挖掘冗余执行器变化速率潜力,提高推力响应速度,降低了对于燃油泵快速作动的需求,同时该方法可以使喷口在推力响应过程逐渐回中,系统具备持续的推力快速调节能力;(2)分析了A8调节推力的物理机理,指出容腔压力动力学主导的部件间流量匹配过程使得A8对推力具有直馈作用,是提高推力响应速度的有效途径。基于发动机部件级模型的评估结果表明,本文提出的方法在执行机构存在速率限制的情况下,实现了推力10 rad/s闭环带宽和A8回中的设计目标,方法可行、有效。在推力响应过程中,A8直馈作用对推力变化的贡献度最高时超过50%。随着对于推力控制模式和推力响应速度的日趋关注,应对容腔内的压力动态过程给予充分的重视。

双机械臂布局下的电推进位保策略

对于地球同步轨道的电推进卫星,可采用双机械臂式电推布局进行轨道维持控制.本文研究了双机械臂式电推布局的自主位保控制策略,针对南北各一台机械臂,每台机械臂分别配置一台电推力器的布局方式,通过每天1~2次点火,以尽量少的点火指向变动实现东西/南北联合位保控制.在双侧机械臂、电推力器正常情况下研究具有解析形式的在轨位保算法.研究基于单侧矢量调节机构和该侧电推力器的故障位保策略,给出衡量不同矢量机构能力和推力比冲下的位保效率衡量方法.仿真结果表明,正常/故障情况下的位保控制精度均能够满足同步轨道位保控制要求.本算法为解析形式,计算量较小,可以实现多星共轨和定点捕获/轨位漂移,便于量上自主实施.

基于冷流推力的变微过载控制方法研究

针对地面微重力环境下的变微过载控制方法,以不同冷流压力以及二次流入射位置等因素,开展了基于冷流推力的流场仿真,分析了二次射流对主流流场影响。并研制了冷流推力系统,通过测试验证了冷流推力与总压的相互关系。并通过微重力落舱开展了1s微重力环境下的变微过载试验,结果表明通过冷流流场型面设计,以及主流、二次流压力的控制可以控制作用于内舱的推力,从而改变内舱微重力环境下的微重力水平,满足在微重力环境下的变微过载控制能力。

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。

安徽宣城矿集区控矿构造特征及其深部找矿指示意义

宣城矿集区因近年发现了茶亭斑岩型铜金矿、长山热液型铅锌矿等大-中型矿产地而成为长江中下游成矿带较热门矿集区之一。通过详细的野外调查和系统分析,本文厘定了研究区北东向构造格架为一条深大断裂带、两个坳陷盆地、三条逆冲推覆构造带,其中推覆构造带由多个自南东向北西运动的倒转复式褶皱和叠瓦状逆冲岩席组成。根据典型矿床控矿构造解析,明确了江南深大断裂和深部主推覆构造是区内一级控岩控矿构造,北东向断裂带及其次级构造、推覆体上盘倒转褶皱转折端和翼部、层间破碎带、五通组与黄龙-船山组的“硅钙面”、燕山晚期中酸性侵入岩与碳酸盐岩的接触带等为区内重要的控矿、容矿构造,并据此提出了该区下一步深部找矿方向。

新型矢量推力八旋翼飞行器的设计与控制

飞行器在物理交互场景中应用广泛,但现有的飞行器及装置在面对大矢量推力应用时,往往难以满足结构和控制简单的要求。为解决这一问题,设计了一种结构简单可行的矢量推力八旋翼飞行器,利用倾斜共轴转子和铰链—同步带的结构,只需一个额外的执行器,即可控制所有转子的倾转角度,从而实现矢量推力,可在物理交互场景中提供足够的横向推力。基于此,设计了对应的位姿控制器,采用SO(3)上的几何控制方法设计了全局稳定的位姿控制器,使用非线性扰动观测器对外部力和力矩进行估计并补偿,以提高整个控制系统的鲁棒性。在MATLAB/Simscape中,进行了飞行器的5D轨迹跟踪、倾转悬停和扰动估计的仿真实验,实验结果充分验证了该飞行器设计的可行性和相应控制算法的有效性。

微牛级高精度直流离子推进系统的推力调节特性

为了研究将微型直流离子推力器用于航天器超高精度控制任务的可行性,设计了一个微牛级直流离子推力器并为其配备了碳纳米管中和装置。对推力器进行了实验测试,评估了其在150~490 V电压范围内可实现的推力范围和推力分辨率,并计算了5、25、50μN推力水平下的噪声。在上述电压范围内,使用氙气和氩气作为工质时,推力器的推力范围分别为5.75~50.83μN和5.93~47.63μN,最大推力噪声为0.12μN/√(Hz)和0.05μN/√(Hz)。此外,对碳纳米管中和器进行了性能测试,实现了最大1.22 mA的引出电流,能够满足氙气工况下0~37.37μN、氩气工况下0~16.50μN的束流中和需求。实验结果表明,该推进系统可以用于引力波探测等高精度空间测量任务所需的无拖曳控制,且使用氩气更有利于实现高精度和低噪声的推力输出。

“天问一号”探测器轨道确定及精度评估

“天问一号”是我国首个自主火星探测任务,高精度轨道确定是圆满完成工程任务和科学数据分析的基础。针对“天问一号”不同飞行阶段的轨道特性、力学环境及测量水平,本文采用不同策略进行轨道确定并评估精度,在地火转移阶段轨道精度优于4 km,环火停泊阶段轨道精度优于1 km,中继通信阶段轨道精度优于100 m;双程测距数据精度约为0.5 m,1 s积分双程测速数据精度约为0.2 mm/s,VLBI时延数据精度约为0.3 ns。“天问一号”定轨精度主要受到太阳光压和姿控模型误差影响,在定轨过程中求解光压系数和经验加速度十分必要。“天问一号”探测器光压系数与经验加速度存在一定程度的耦合,需要添加先验约束信息。

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。

短刺针法结合旋颈调枢法治疗颈源性头痛的临床疗效观察

目的:探究短刺针法结合旋颈调枢法治疗颈源性头痛的临床疗效及安全性。方法:随机选取黑龙江中医药大学附属第三医院推拿科2022年1月—2023年1月就诊的颈源性头痛患者100例纳入本研究。采用随机数字表法将其随机分为对照组和观察组,每组50例。对照组给予口服安普洛治疗,60 mg/次,3次/d,治疗2周;观察组给予短刺针法结合旋颈调枢法治疗,隔日1次,每周治疗3次,治疗2周。比较两组患者治疗前后视觉模拟疼痛量表(VAS)、颈椎活动度评分(ROM)、测量寰齿侧间隙两侧差值、枢椎棘突中心点到齿状突中线的垂直距离差值及其安全性评价。结果:治疗2周后,两组患者的VAS评分较治疗前均明显下降(P<0.01),且观察组的VAS评分明显低于对照组(P<0.01)。治疗2周后,两组患者的颈椎关节活动度(ROM)较治疗前均显著升高(P<0.01),且观察组的ROM评分明显高于对照组(P<0.01)。治疗2周后,观察组患者寰齿侧间隙两侧差值和棘突中点到齿状突中线的垂直距离差值较治疗前均显著降低(P<0.01),而对照组无明显差异(P>0.05),且观察组的寰齿侧间隙两侧差值和棘突中点到齿状突中线的垂直距离差值较对照组均显著降低(P<0.01)。观察组的总有效率为91.1%(41/45),对照组为68.2%(30/44),观察组的临床疗效显著优于对照组(P<0.01)。结论:短刺针法结合旋颈调枢法治疗颈源性头痛与口服安普洛相比疗效更佳。

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。

自适应循环发动机快速推力变化过渡过程性能初步研究

自适应循环发动机是基于变循环发动机设计理念基础并充分考虑飞发一体化设计、热管理等综合性能的面向未来飞行平台的先进动力装置,可通过诸多可调机构实现发动机涵道比、增压比、流量以及工作模式的灵活改变,从而适应不同飞行任务的复杂任务剖面需求,获得更大飞行包线内的性能优化。本文基于自适应循环发动机的性能计算仿真模型,在相关研究基础上结合模式转换和加减速过程实现快速推力变化过程,根据模式转换与加减速控制规律设计,开展典型算例下的快速推力变化过渡过程性能分析并验证其控制规律设计方法可行性,在亚声速巡航工况下,发动机在以M3模式叶尖风扇最小角度状态下,低压转子相对物理转速从0.6加速至1.0,最大可使终止推力增大32.4%,相较于单一模式加减速过渡过程,推力变化范围更宽,加速时间更短,转速变化范围更小。

宽范围微牛顿量级场致发射电推力器设计

针对空间引力波探测任务卫星无拖曳控制对微牛顿量级场发射电推力器的宽、稳、准、快、久指标要求,需突破宽范围可调与分辨率和推力噪声之间的相互限制,从场发射推力产生的原理出发,并利用高精度单摆对模型精度进行标定,建立了基于流量、电压主动调节策略的推力调控模型,结合调控分辨率与响应速度的需求,提出的反馈控制策略使推力器在更宽推力范围内维持低推力噪声水平。最后对研制的推力器样机开展了性能表征,实现了0.86~83.54μN、<0.1μN的推力分辨率、在毫赫兹频段<0.1μN/Hz^(1/2)的推力噪声和定工质流量下<10 ms的推力响应时间。

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。