一种适用于中小无人机的飞控舵面机电作动系统设计

发布时间：2018-03-25 01:12

本文选题：无人机　切入点：电传飞控　出处：《电子科技大学》2015年硕士论文

【摘要】：随着近年来在局部战争和反恐战争中的频繁亮相,中低空无人机以其长航时、低油耗在“察-打一体”任务中发挥着关键作用。随着无人机自主化、智能化的发展趋势,数字化的电传飞行控制系统已成为大中型无人机的标准应用。另一方面,自上世纪80年代多电/全电飞机概念提出以来,多电/全电飞机系统在战场生存力、系统经济性、维护性和可靠性方面的优点逐渐得到研究证实。作为多电/全电飞机系统核心技术之一,功率电传飞控舵面作动系统也得到了新的发展;其中主要研究方向是电静液作动器(Electro-hydrostatic Actuator,EHA)和机电作动器(Electro-Mechanical Actuators,EMA),二者因构成不同相对彼此各有优缺点。近年来,EMA因其在全电飞机中的潜在优势而受到了更多关注,随着安全性和可靠性的不断提高,机电作动器逐步开始了在主飞控作动系统上的应用。本文介绍一种适用于中小无人机的飞控机电作动系统的设计。文章首先从飞行器和飞行控制系统的发展和应用开始,对当前航空领域重点研究的电传飞控系统、功率电传作动系统的发展和技术特点进行详细介绍,并对各种构型下的飞控作动技术进行了举例说明。基于背景介绍和对比分析,某无人机飞控系统总体方案得以确定。飞控作动系统架构则在满足大系统要求的前提下根据飞机舵面配置进行优化。为满足某无人机平台功率及安装空间有限的需求,EMA被选定为飞控作动系统执行机构。EMA设计实现包括机电作动器硬件设计计算和安全可靠性分析。硬件设计采用自顶向下方法,通过EMA架构分析、关键子组件选型和计算校核使作动器功能性能满足技术要求。安全性和可靠性分析工作使设计过程和目标进一步清晰明确,并确保飞控舵面子系统满足现代飞机设计要求。通过以副翼作动器为样本的控制回路设计仿真、实物样机测试和数据分析等工作,使得设计验证过程完整有效。本项目中,以EMA为执行机构的分布式飞控机电作动系统,具备了数字化、模块化特性,有效提升了系统的可靠性、维护性和拓展性,有利于在不同平台的移植和应用。
[Abstract]:With the frequent appearances in local wars and anti-terrorism wars in recent years, low fuel consumption plays a key role in the mission of "observing and fighting as one" during the long voyage of medium-low altitude UAVs. With the development trend of unmanned aerial vehicles (UAVs) becoming autonomous and intelligent, Digital telex flight control system has become the standard application of large and medium-sized UAVs. On the other hand, since the concept of multi-electric / all-electric aircraft was put forward in the 1980s, the system of multi-electric / all-electric aircraft has been viable and economical in the battlefield. The advantages of maintainability and reliability have been proved gradually. As one of the core technologies of multi-electric / all-electric aircraft system, the power fly-by-fly-control rudder surface actuating system has also been developed. The main research directions are Electro-hydrostatic Actuator (EHAA) and Electro-Mechanical Actuators (EMAA), both of which have their own advantages and disadvantages due to their different compositions. In recent years, EMA has attracted more and more attention for its potential advantages in all-electric aircraft. With the improvement of safety and reliability, The application of electromechanical actuators to the main flight control actuation system has gradually begun. This paper introduces the design of a kind of flight control electromechanical actuation system suitable for small and medium UAVs. Firstly, the development and application of the aircraft and flight control system are introduced in this paper. This paper introduces in detail the development and technical characteristics of the fly-by-wire flight control system and the power teletype actuation system, which are mainly studied in the aviation field at present, and gives an example to illustrate the flying control actuation technology under various configurations, based on the background introduction and comparative analysis, The overall scheme of a certain UAV flight control system can be determined. The structure of the flight control actuation system is optimized according to the aircraft rudder surface configuration on the premise of meeting the requirements of large scale systems. In order to satisfy the limited power and installation space of a certain UAV platform. EMA is selected as the actuators of flight control actuators. EMA design and implementation include hardware design calculation and safety reliability analysis of electromechanical actuators. The hardware design adopts top-down method. Through the analysis of EMA architecture, the selection of key sub-components and the calculation and checking of the actuator function can meet the technical requirements, and the safety and reliability analysis work makes the design process and objectives more clear and clear. And ensure that the face system of flight rudder meets the requirements of modern aircraft design. Through the design simulation of control loop based on aileron actuator, testing of physical prototype and data analysis, the design verification process is complete and effective. The distributed flight control electromechanical actuation system with EMA as the actuator has the characteristics of digitization and modularization, which effectively improves the reliability, maintainability and expansibility of the system, and is beneficial to the transplantation and application of different platforms.
【学位授予单位】：电子科技大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V279

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