小型长航时无人机结构初步设计及强度分析

PRELIMINARY DESIGN AND STRENGTH ANALYSIS OF SMALL LONG-ENDURANCE UAV STRUCTURE

赵中锋

11749147

硕士

机械工程

韩松

2019-05-30

2019-06-28

哈尔滨工业大学

深圳

作为一种新型的无人飞行器，小型长航时无人机具有续航时间长、操作方便、起降灵活、载荷配置多样、携带和运输方便等诸多优点，成为国内外无人机领域研究的热点。本文开展了小型长航时无人机结构初步设计及其强度与刚度的分析研究，主要内容如下：（1）在小型长航时无人机结构初步设计方面。本文先后开展了无人机结构材料的选择，结构布局形式的确定，结构的传力分析，机身、机翼、尾撑和尾翼的初步设计及主要结构分离面的连接设计；针对小型长航时无人机载荷配置多样化、机体结构通用性高的特点，本文提出了一种可重构的机体结构模块化设计方法；针对小型长航时无人机对快速拆装和便捷使用的要求，本文提出了无工具拆装的结构分离面连接设计方法，同时也实现了结构和电气一体化的共形连接；本文所设计的小型长航时无人机结构具有结构重量轻、模块化程度高、操作使用便捷等特点。（2）在无人机结构有限元分析方面。本文先后开展了复合材料有限元法的理论研究，机翼、尾撑和尾翼结构的有限元分析和结构优化，整机结构强度与刚度的校核；针对小型长航时无人机结构轻量化的设计要求，本文重点开展了机翼蒙皮和翼梁的铺层设计与结构尺寸优化，尾撑杆的铺层设计和截面尺寸优化；优化后：整机结构重量约12.87kg（占起飞重量的比值为21.45%），结构的最大应力为1686.9MPa，机翼最大变形和半翼展的比值约4.94%，尾撑杆的最大转角为1.47°。（3）在起落架设计方面。针对小型长航时无人机野外滑降的使用特点，进行了不同起落架方案的对比择优，设计了一款满足滑降回收的滑橇式起落架，并进行了滑橇起落架的结构设计和有限元分析，在此基础上通过铺层设计、结构尺寸优化、材料优化，实现了滑橇起落架结构的轻量化设计。起落架的弓形梁结构优化后，其铺层组为[45°/-45°/0°/45°/-45°/0°/45°/-45°/0°/45°/90°/0°/°]s，截面宽度为40mm、截面厚度为5mm；起落架的结构材料优化后，其结构重量为1.187kg，最大应力为281.8MPa，高度方向的最大变形为20.2 mm，Tsai-Wu失效因子为0.7841。

As a new type of UAV, the small long-endurance UAV has many advantages such as long endurance, convenient operation, flexible take-off and landing, various load configurations, convenient carrying and transportation, etc. It has become a hot research topic in the field of UAV at domestic and overseas. In this paper, the preliminary design of the small long-endurance UAV structure and its strength and stiffness analysis are carried out. The main contents are as follows: (1) In the preliminary design of the small long-endurance UAV structure. This paper has carried out the selection of UAV structural materials, the determination of structural layout, the structural force analysis, the preliminary design of the fuselage, wing, tail support and tail and the connection design of the main structural separation surface; In view of the diversified load configuration of the UAV and the high versatility of the structure of the UAV, this paper proposes a reconfiguration modular design method for the structure of the UAV; Aiming at the requirements of quick disassembling and portable use of small long-endurance UAV, this paper proposes a design method for structural separation surface connection without tools disassembly and assembly, and also realizes the structural and electrical integration of common connection; The small long-endurance UAV structure designed in this paper has the characteristics of light weight, high modularity and convenient operation and use. (2) In terms of finite element analysis of the UAV structure. In this paper, the theoretical research of composite material finite element method has been carried out, the finite element analysis and structural optimization of wing, tail support and tail structure, the structural strength and stiffness of the whole UAV are checked; The design requirements of this paper focus on the layer design and structural dimension optimization of the wing skin and spar, the layer design and section size optimization of the tail support; After optimization: the structure weight of the whole UAV is about 12.87kg (the ratio of take-off weight is 21.45%), the maximum stress of the structure is 1686.9MPa, the ratio of the maximum deformation to the half-span of the wing is about 4.94%, and the maximum angle of the tail support is 1.47 degree. (3) In terms of landing gear design. Aiming at the use characteristics of small long-endurance UAV in the field, the different landing gear schemes were compared and optimized. A slid landing gear that meets the downhill recovery is designed, and the structural design and finite element analysis of the skid landing gear are carried out. On this basis, the lightweight design of the skid landing gear structure is realized through the layer design, structural dimension optimization and material optimization. After optimization of the bow beam structure of the landing gear, the layup group is [45°/-45°/0°/45°/-45°/0°/45°/-45°/0°/45°/90°/0°/°]s , the section width is 40mm and the section thickness is 5mm; After the structural material of the landing gear is optimized, its structural weight is 1.187kg, the maximum stress is 281.8MPa, and the maximum deformation in the height direction is 20.2 mm, Tsai-Wu failure factor is 0.7841.

无人机 复合材料 结构设计 强度 有限元分析 起落架

UAV composite material structural design strength finite element analysis landing gear

中文

联合培养

南方科技大学

赵中锋. 小型长航时无人机结构初步设计及强度分析[D]. 深圳. 哈尔滨工业大学,2019.