弹用涡扇发动机数字电子控制器设计

【作者】 王海泉；

【导师】 郭迎清；

【作者基本信息】 西北工业大学 ， 航空宇航推进理论与工程， 2006， 硕士

【摘要】 为保证航空发动机安全、高效的工作,满足复杂控制理论应用的需要,发动机控制系统的电子化、数字化已成为航空推进系统控制发展的方向,发动机数字电子控制系统必将使航空推进系统控制技术进入一个新的发展阶段。 本文就是针对某弹用涡扇航空发动机的特性设计其数字式电子控制器(DEEC),以实现对推进系统的较好控制。 在进行电子控制器设计前,本论文首先结合该型发动机的特性,针对测得的实验数据,使用不同的辩识方法对发动机的数学模型进行辩识,选用辩识效果最好的方法来得到发动机模型。同时,还讨论了对原始数据进行插值、零均值化等数据预处理方法后对辨识结果的影响。 其次针对建立的发动机数学模型,利用不同的PID参数整定方法设计推进系统的PID控制器。通过对仿真结果的分析比较,精调的Ziegler-Nichols整定PID控制器能使整个系统超调量和调节时间都较好的满足控制要求。 然后针对该型航空发动机的工作原理和控制要求,结合嵌入式技术对双余度数字式电子控制器的总体进行软硬件设计,主要介绍了嵌入式双冗余结构的硬件选型、硬件组合及软件编程实现,包括硬件的故障诊断、数据采集和数据通讯等。 最后,初步设计控制系统的半物理实时仿真平台,以完成对设计出的涡扇航空发动机数字式电子控制器的性能验证,包括实现控制器和仿真机之间的数据传输和初步完成仿真机接收到数据的曲线实时显示。更多还原

【Abstract】 Because of the implementation of complex control theory and safety, efficient work of aero-engine, it has been the trend that the digital electronic control system substitutes the traditional hydraulic control system.Based on the theory of turbofan aero-engine used as cruise missile, this paper designed its digital electronic controller in order to achieve the control mission to the system.Before designing the digital electronic engine controller, depending on the basic theory of system identification, as well as the main structure and the experiment data of aero-engine, this paper first used different identification method to set up the engine model, and chose the method which had the highest fitting degree to build the model. Mean while, influences of some data pretreatment method, for instance, interpolation and zero-mean, were discussed.Second, based on the engine model having set up, paper used several different methods of PID control to designed system’s PID controller, by comparing simulation result, the precision adjust Ziegler-Nichols PID controller can reduce the engine system’s overshoot and shorten the control time to meet the require of system better than other methods of PID controller which were designed.Then, based on the structure and control request of the aero-engine system, by using the technology of embedded system, digital electronic engine controller which had double redundancy was designed from two aspects of hardware and software, introduced several key techniques such as the selection of embedded system’s hardware, hardware connection and software compiling to achieve the system structure of double redundancy, including hardware fault diagnostic approach, the timing collection of engine data, data communicated between two systems and so on .Last, in order to evaluate the digital electronic engine controller which was designed for the aero-engine system, designed the primary control system hardware-in-the-loop simulation system, included how to transfer data between thecontroller and the simulate computer, how to show the data curve on the computer.更多还原