本文選題：無人機　切入點：電傳飛控　出處：《電子科技大學》2015年碩士論文

【摘要】：隨著近年來在局部戰(zhàn)爭和反恐戰(zhàn)爭中的頻繁亮相,中低空無人機以其長航時、低油耗在“察-打一體”任務中發(fā)揮著關(guān)鍵作用。隨著無人機自主化、智能化的發(fā)展趨勢,數(shù)字化的電傳飛行控制系統(tǒng)已成為大中型無人機的標準應用。另一方面,自上世紀80年代多電/全電飛機概念提出以來,多電/全電飛機系統(tǒng)在戰(zhàn)場生存力、系統(tǒng)經(jīng)濟性、維護性和可靠性方面的優(yōu)點逐漸得到研究證實。作為多電/全電飛機系統(tǒng)核心技術(shù)之一,功率電傳飛控舵面作動系統(tǒng)也得到了新的發(fā)展;其中主要研究方向是電靜液作動器(Electro-hydrostatic Actuator,EHA)和機電作動器(Electro-Mechanical Actuators,EMA),二者因構(gòu)成不同相對彼此各有優(yōu)缺點。近年來,EMA因其在全電飛機中的潛在優(yōu)勢而受到了更多關(guān)注,隨著安全性和可靠性的不斷提高,機電作動器逐步開始了在主飛控作動系統(tǒng)上的應用。本文介紹一種適用于中小無人機的飛控機電作動系統(tǒng)的設計。文章首先從飛行器和飛行控制系統(tǒng)的發(fā)展和應用開始,對當前航空領(lǐng)域重點研究的電傳飛控系統(tǒng)、功率電傳作動系統(tǒng)的發(fā)展和技術(shù)特點進行詳細介紹,并對各種構(gòu)型下的飛控作動技術(shù)進行了舉例說明�；诒尘敖榻B和對比分析,某無人機飛控系統(tǒng)總體方案得以確定。飛控作動系統(tǒng)架構(gòu)則在滿足大系統(tǒng)要求的前提下根據(jù)飛機舵面配置進行優(yōu)化。為滿足某無人機平臺功率及安裝空間有限的需求,EMA被選定為飛控作動系統(tǒng)執(zhí)行機構(gòu)。EMA設計實現(xiàn)包括機電作動器硬件設計計算和安全可靠性分析。硬件設計采用自頂向下方法,通過EMA架構(gòu)分析、關(guān)鍵子組件選型和計算校核使作動器功能性能滿足技術(shù)要求。安全性和可靠性分析工作使設計過程和目標進一步清晰明確,并確保飛控舵面子系統(tǒng)滿足現(xiàn)代飛機設計要求。通過以副翼作動器為樣本的控制回路設計仿真、實物樣機測試和數(shù)據(jù)分析等工作,使得設計驗證過程完整有效。本項目中,以EMA為執(zhí)行機構(gòu)的分布式飛控機電作動系統(tǒng),具備了數(shù)字化、模塊化特性,有效提升了系統(tǒng)的可靠性、維護性和拓展性,有利于在不同平臺的移植和應用。
[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.
【學位授予單位】：電子科技大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V279

【相似文獻】

相關(guān)期刊論文 前10條

1 沙南生,李軍;功率電傳機載一體化電作動系統(tǒng)的研究[J];北京航空航天大學學報;2004年09期

2 李軍,付永領(lǐng),王占林;機載電靜液作動系統(tǒng)的發(fā)展現(xiàn)狀與關(guān)鍵技術(shù)研究[J];航空制造技術(shù);2005年11期

3 孫衛(wèi)華,裘麗華,祁曉野,王占林;電機-泵復合控制作動系統(tǒng)的建模與分析[J];系統(tǒng)仿真學報;2005年02期

4 李軍,付永領(lǐng);多學科多目標評價及其在電靜液作動系統(tǒng)中的應用[J];計算機集成制造系統(tǒng);2005年03期

5 齊蓉,陳明;多電飛機容錯作動系統(tǒng)拓撲結(jié)構(gòu)分析[J];航空計算技術(shù);2005年01期

6 郭宏;邢偉;;機電作動系統(tǒng)發(fā)展[J];航空學報;2007年03期

7 付永領(lǐng);張衛(wèi)衛(wèi);紀友哲;;電機泵閥協(xié)調(diào)控制作動系統(tǒng)的建模及仿真[J];機床與液壓;2010年11期

8 付永領(lǐng);齊海濤;王利劍;劉和松;;混合作動系統(tǒng)的工作模式研究[J];航空學報;2010年06期

9 田涌;;飛控作動系統(tǒng)通用測試環(huán)境設計[J];測控技術(shù);2010年06期

10 王e，

本文編號：1660871