| 1. | Dissimilar redundant flight control computer system
非相似余度飞控计算机 |
| 2. | The paper studies the project of improving the reliability of flight control computer by using the dual cpu hot - redundancy technology
本文主要对利用双机热备份技术来提高飞控计算机可靠性这一方案进行了前期研究。 |
| 3. | The method can be used for many flight control computers easily . the dual cpu hot - redundancy technology became a method to improve the reliability of flight control computer
该方法实施简单，易移植和工程化，具有较好的通用性，为提高飞控计算机可靠性提供了一种途径。 |
| 4. | The system hardwire includes : flexible vehicle management system architectures , fiber optic cable plants , active hand controllers , primary flight control computers , optical mechanizations and smart actuators
同时还介绍了一单通道主飞控系统的地面演示和一副翼配平控制系统的飞行演示。 |
| 5. | Focusing on the advance research of the flight control computer system of some type of a high altitude , long endurance unmanned aerial vehicles , this paper analyzes and research its staicture in techniques of redundancy fault - tolerance
本文针对某型号预研高空长航时无人机飞行控制计算机系统的可靠性要求，运用冗余容错技术对其进行了设计研究。 |
| 6. | We implement the dual cpu hot - redundancy technology into the common uav which used pc / 104 in our country . the reliability of flight control computer can be improved rapidly only if we increase a little hardware and software by the dual cpu hot - redundancy technology
该技术在我国无人机普遍使用的pc 104体系结构作为平台的飞控计算机上实施，只需增加少量的硬件资源和软件模块就可以大大提高飞控计算机的可靠性。 |
| 7. | The modern unmanned helicopter flight control system is generally composed of the flight control computer , the servo driving mechanism , the sensor , and the ground monitor control system etc . in this thesis the research to the helicopter flight characteristics was conducted at first , and its flight dynamic model was preliminary discussed , especially the mathematic model under hung - stop condition was formulated and the algorithm of the controller was designed in detail
现代无人直升机飞行控制系统一般由飞行控制计算机、伺服驱动机构、传感器、地面监测控制等分系统组成。本文首先对直升机的飞行特性进行了研究,并且对飞行动力数学模型做了初步探讨,尤其对在悬停状态下的数学模型做了较为详尽的公式推导和控制器的算法设计。 |
| 8. | Firstly discussing basic type of computer redundant structure and characteristic of the systems , the self - monitoring dual redundancy computer systems is brought forward as the design scheme for the required flight control computer system . the redundant structure is researched about reliability by using markor model and is carefully designed
首先分析了计算机冗余结构的基本类型以及本次设计的要求特点，选择了自监控二冗余飞行控制计算机系统的设计方案，运用马尔科夫模型对此冗余系统的可靠性进行了计算研究，并且对此冗余结构进行了详细地描述及设计。 |
| 9. | Focusing on the flight control computer system of some type of airplane , this paper first analyzes the advantage and disadvantage of the structures of many kinds of fault tolerant flight control computer systems and their ability in tolerating fault , followed by summarizing the key design technology . the dual similar redundancy fault tolerant computer system is brought forward as the design scheme for the required flight control computer . also brought forward is the particular system design
本文以某型号飞机飞控计算机系统为研究对象，首先分析了各种类型容错飞控计算机体系结构的优缺点及容错能力，总结了容错计算机系统设计的关键技术，然后提出了二模相似余度容错飞控计算机系统设计方案，详细设计了以motorola公司生产的先进powerpc740微处理器为核心处理器、以高性能的国际标准化通用vme总线为内总线的交叉通道通信容错计算机系统。 |
| 10. | Most countries in the world attach importance to the use of long - time uav ( unmanned aerial vehicle ) in the military . the kernel question of long - time uav is how to improve the reliability of flight control computer . the research of how to improve the reliability of flight control computer has became more and more important today
长航时无人机的重要性尤其在军事上已经得到国内外的高度重视，其核心飞行控制计算机(以下简称“飞控计算机” )的可靠性问题变的日益突出，对其容错研究成为当今的热点。 |
