物理仿真

• Pointing to the data obtained from semi - physical simulation of certain helicopter which mainly has low - frequency noise , a data - processing method of depressing and filtering noise from the signal , using the pagoda - structure re - constructing arithmetic and the wavelet transform principle , is proposed
  摘要针对直升机半物理仿真测量数据主要是低频噪声的特点，提出利用小波变换、塔式结构重构算法，对信号进行降噪滤波处理的方法。
• Base on the design of monitoring system for integrated flight / propulsion control simulation platform , this paper studies three levels of closed loop simulation experimental schemes for an engine control system , the feasibilities of which are validated by different means
  本文在进行飞/推综合控制半物理仿真平台监控系统设计的基础上,针对某型发动机控制系统,研究了三个层次的闭环仿真试验方案,并且通过不同的方式论述了方案的可行性。
• Last of article , uniting the concrete situation of the laboratory , a modification means to simulate the systematic unit of diesel engine power station more clearly is put forward ; along with utilizes fuzzy + pi ' s double model to lift the laboratory physics imitation system control performance means
  在文章的最后，结合实验室具体情况提出了实现进一步逼真模拟柴油机电站系统装置的改进方法；以及利用模糊+ pi双模控制，提高实验室物理仿真系统控制性能的方法。
• The antenna pointing control accuracy can satisfy the design specification and it is validated to be appropriate and effective . at last , the designed user satellites complex control system is simulated based on xpc target which is used for hardware - in - the - loop simulation
  4 .基于xpc实时仿真平台,充分利用实验室条件,搭建了用户星天线样机在回路中的半物理仿真实验,将天线指向控制系统和星体姿态稳定控制系统联合起来,组成中继卫星复合控制系统进行近一步的验证。
• The electro - hydraulic load simulator of fin stabilizer is physical half - objective simulative system . its function is to simulate , under laboratory conditions , different kinds of hydrodynamic force exerted on the fin stabilizer so as to detect technical performance index of the driving system of fin stabilizer . thus the classical self - destructing all - objective experiment will be converted to half - objective forecasting experiment in laboratory to achieve the aims such as shortening lead time , saving developing funds , enhancing reliability and success proportion
  减摇鳍电液负载仿真台是一种半实物物理仿真系统，其功能是在实验室的条件下，模拟船舶航行过程中减摇鳍所受的海浪水动力载荷谱，从而检测减摇鳍驱动系统的技术性能指标，将经典的自破坏全实物实验转化为在实验室条件下的半实物预测性实验，以达到缩短研制周期、节约研制经费、提高可靠性和成功率的目的。
• The test requirements of ifpc system are analyzed firstly , and the general scheme of hardware - in - loop simulation test platform for ifpc is proposed . base on the scheme , the monitoring system architecture is designed , signal conditioner , signal interfacing emulator and software design of the monitoring system are discussed in detail . finally , the monitoring system developed is validated by a closed - loop simulation test system with aero - engine model and digital controller arithmetic
  论文首先分析了发动机控制系统以及飞推综合控制系统试验需求，提出飞推综合控制半物理仿真试验平台的总体方案；根据此方案，确定了仿真平台监控系统的体系结构，设计了信号调理电路和接口信号仿真器，并进行了监控软件开发；最后，利用发动机数学模型和数字控制器构成闭环仿真测试环境，以验证所开发的监控系统的有效性。
• Designs the framework of the 3d scene graph system based on the real - time simulation environment , introduces the multigen creator , vegaprime and the modeling method of the uav and the terrain , explains the model motion , the control of the angle of view and the data communication , summarizes the character of the scene graph system
  在总体框架设计一章中设计了具有三维视景仿真的无人机半物理仿真系统结构,介绍了模型构造工具multigencreator和三维系统开发环境vegaprime ,阐述了无人机建模和地形建模的方法,说明了模型运动、视点控制和数据通信的实现方式,并概括了该系统的特点。
• A temperature signal physical simulation method is proposed in this paper . the temperature simulation system is constructed and its controller is designed . the experiment results indicate that the temperature simulation system can meet the requirement of the matter - in - loop simulation of aero - engine control system
  本文提出涡轮出口气体温度信号的物理模拟方法,构建了温度模拟系统,设计了温度模拟系统控制器,进行了温度模拟系统试验,试验结果表明温度模拟系统基本满足航空发动机控制系统半物理仿真的需求。
• Because it is impossible to adjust the air bearing absolutely balance , the difference between mass center and rotation center must lead to a notable gravity disturbance torque . in the process of identification , modeling and identification of gravity disturbance torque is considered , and an extended kalman filter is educed for identifying air bearing inertia matrix and gravity disturbance torque , and then the algorithm is validated
  由于气浮台平衡调试方法和手段的限制,实验过程中气浮台质心与转动中心有一定的位置偏差,必将导致较大的重力干扰力矩,在辨识算法的推导过程中,重点考虑了重力干扰力矩的建模和参数辨识问题,推导了气浮台的转动惯量和重力干扰力矩辨识的扩展卡尔曼滤波算法,并对算法进行了数学仿真和全物理仿真验证。