WO2016000485A1 - 无人直升机的工字梁式机身结构 - Google Patents

无人直升机的工字梁式机身结构 Download PDF

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Publication number
WO2016000485A1
WO2016000485A1 PCT/CN2015/077906 CN2015077906W WO2016000485A1 WO 2016000485 A1 WO2016000485 A1 WO 2016000485A1 CN 2015077906 W CN2015077906 W CN 2015077906W WO 2016000485 A1 WO2016000485 A1 WO 2016000485A1
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WIPO (PCT)
Prior art keywords
beams
fuselage structure
unmanned helicopter
side frames
fuselage
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PCT/CN2015/077906
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English (en)
French (fr)
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赵泓波
赵曙光
马啟兴
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青岛宏百川金属精密制品有限公司
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Publication of WO2016000485A1 publication Critical patent/WO2016000485A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/17—Helicopters
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the utility model relates to the technical field of unmanned helicopters, in particular to an I-beam type fuselage structure of an unmanned helicopter.
  • the fuselage structure of the unmanned helicopter in the prior art is mainly improved by the fuselage structure of the aircraft model, and follows the design method of the side plate force.
  • the space structure of the airframe is narrow, the strength is low, and the airborne can not be given. Good protection of the equipment.
  • the utility model aims at the current unmanned helicopter fuselage structure, has complicated design, many parts, high cost, insufficient strength, complicated assembly, inconvenient maintenance of unmanned helicopters, etc., and designs an unmanned helicopter I-beam type machine. Body structure.
  • the I-beam body structure of the unmanned helicopter of the utility model comprises two side frames and a rotor frame mounted between the side frames, and the side frame is an I-beam.
  • the I-beam comprises two beams arranged in parallel, and two connecting beams are fixed between the beams, and the connecting beams are inclined, so that a trapezoidal structure is formed between the two connecting beams, and the connecting beams are also fixed Reinforced beams, beams and connecting beams are all H-type aerospace aluminum or steel.
  • a plurality of engine mounts are also mounted between the side frames.
  • the beam is mounted in parallel with the extension beam, and the engine mount is fixed to the extension beam.
  • the reinforcing beam is parallel to the beam, and the reinforcing beam is provided with a plurality of hollow grooves.
  • the frame plates are installed between the reinforcing beams of the two side frames, and the plugs disposed on both sides of the frame plate are inserted into the corresponding hollow slots.
  • the utility model has the beneficial effects that the fuselage structure has the I-beam as the main body of the structure, and the inside has a trapezoidal structure, and is added by Strong beam reinforcement, high strength, simple structure, few components, is conducive to rapid disassembly and maintenance, each beam structure uses H-beam, which further increases the lateral stiffness and bending resistance of the fuselage structure, and also reduces the fuselage structure
  • the size and weight of the drone reduce the weight of the drone and increase the idle time and work efficiency of the drone.
  • the components of the UAV can be installed on the extension beam installed in parallel, which improves the flexibility of the fuselage structure assembly.
  • the added extension beam increases the strength of the I-beam beam. .
  • Reinforced hollowing grooves on the beam not only facilitate the installation of the fascia but also further reduce the weight of the fuselage structure.
  • Figure 1 is a structural view of the I-beam type fuselage structure
  • Figure 2 is a structural view of an I-beam.
  • the I-beam structure of the unmanned helicopter of the present invention as shown in FIG. 1 , comprises two side frames 1 and a rotor frame 2 installed between the side frames 1 , and the rotor of the drone is mounted on the rotor frame On the upper side, the side frame 1 is an I-beam.
  • the I-beam includes two beams 3 arranged in parallel, and two connecting beams 4 are fixed between the beams 3, and the connecting beams 4 are inclined, so that the two connecting beams 4 and the two beams 3 are composed.
  • a structure having a trapezoidal shape inside, and a reinforcing beam 5 is also fixed between the connecting beams 4.
  • Both the beam 3 and the connecting beam 4 are H-shaped steel, and a plurality of engine mounts 6 are mounted between the side frames 1, and the engine of the drone is mounted on the engine mount 6.
  • the extension beam 7 can be installed in parallel on the beam 3, so that the engine mount 6 or other equipment in the drone is fixed on the extension beam 7.
  • the extension beam 7 can be mounted on any of the beams 3 of each of the I-beams, or the extension beams 7 can be added to both of the beams 3.
  • the reinforcing beam 5 is parallel to the beam 3, so that two trapezoidal structures are formed between the two connecting beams 4, further increasing the strength of the I-beam and the overall structure of the fuselage.
  • a plurality of hollow grooves 8 are disposed on the reinforcing beam 5, and a frame plate 9 is installed between the reinforcing beams 5 of the two side frames 1.
  • the plugs provided on both sides of the frame plate 9 are inserted into the corresponding hollow grooves 8.
  • the shelf 9 can be used to support a main gear mounted on the rotor main shaft or to mount other components within the drone.
  • the fuselage structure When assembling the unmanned helicopter, the fuselage structure only needs to install brackets between the side frames 1 and install other components in the drone on these brackets.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Automatic Assembly (AREA)
  • Working Measures On Existing Buildindgs (AREA)

Abstract

一种无人直升机的工字梁式机身结构，包括两个侧架和安装在侧架之间的旋翼架，侧架为工字梁。机身结构以工字梁做为结构主体，内部呈梯形结构，并由加强梁加固，强度高，而且结构简单，组件少，有利于快速拆装维修，各个梁结构采用H型钢，又进一步增加了机身结构的侧向刚度和抗弯能力，还减小了机身结构的体积和重量，从而减轻了无人机的重量，提高了无人机的留空时间和工作效率。当工字梁的横梁长度不足时，可将无人机的部件安装在平行安装的加长梁上，提高了机身结构装配的灵活性，加装的加长梁又提高了工字梁横梁的强度。加强梁上的镂空槽不仅便于架板的安装，还进一步的减轻了机身结构的重量。

Description

无人直升机的工字梁式机身结构 技术领域
本实用新型涉及无人直升机技术领域，具体涉及一种无人直升机的工字梁式机身结构。
背景技术
现有技术中的无人直升机的机身结构主要是以航模的机身结构改进而成的，沿袭了侧板受力的设计方法，这种机身结构空间狭窄，强度低，不能给机载设备良好的保护。
在先专利《涡轮轴无人驾驶直升机桥梁式机身结构》(申请号：201110434831.6)提出了一种不一样的机身结构，虽然解决了上述问题，但依然存在较多不足，这种机身结构设计过于复杂，零件众多，制造难度大、成本高，装配麻烦，强度依然较为不足，当无人直升机内部需要维修时，这种结构设计也给拆装造成了极大难度，不利于无人直升机的维修。
实用新型内容
本实用新型针对目前的无人直升机机身结构，设计复杂，零件多，成本高，强度不足，装配麻烦，不便于无人直升机维修等问题，设计了一种无人直升机的工字梁式机身结构。
本实用新型的无人直升机的工字梁式机身结构，包括两个侧架和安装在侧架之间的旋翼架，侧架为工字梁。
所述的工字梁包括平行设置的两个横梁，横梁之间固接有两个连接梁，连接梁都倾斜设置，使两个连接梁之间形成梯形结构，连接梁之间还固接有加强梁，横梁和连接梁都为H型航空铝或钢材。
侧架之间还安装有多个发动机固定架。
优选的是，横梁上平行安装有加长梁，发动机固定架固定在加长梁上。
优选的是，加强梁与横梁平行，加强梁上设置有多个镂空槽。
优选的是，两个侧架的加强梁之间安装有架板，架板两侧设置的插头插在对应的镂空槽中。
本实用新型的有益效果是：机身结构以工字梁做为结构主体，内部呈梯形结构，并由加 强梁加固，强度高，而且结构简单，组件少，有利于快速拆装维修，各个梁结构采用H型钢，又进一步增加了机身结构的侧向刚度和抗弯能力，还减小了机身结构的体积和重量，从而减轻了无人机的重量，提高了无人机的留空时间和工作效率。当工字梁的横梁长度不足时，可将无人机的部件安装在平行安装的加长梁上，提高了机身结构装配的灵活性，加装的加长梁又提高了工字梁横梁的强度。加强梁上的镂空槽不仅便于架板的安装，还进一步的减轻了机身结构的重量。
附图说明
附图1为本工字梁式机身结构的结构图；
附图2为工字梁的结构图。
具体实施方式
本实用新型的无人直升机的工字梁式机身结构，如图1所示，包括两个侧架1和安装在侧架1之间的旋翼架2，无人机的旋翼装在旋翼架上，侧架1为工字梁。
如图2所示，工字梁包括平行设置的两个横梁3，横梁3之间固接有两个连接梁4，连接梁4都倾斜设置，使两个连接梁4和两个横梁3组成一个内部为梯形的结构，连接梁4之间还固接有加强梁5。
横梁3和连接梁4都为H型钢，侧架1之间还安装有多个发动机固定架6，无人机的发动机安装在发动机固定架6上。
根据结构的需要，横梁3上可平行安装加长梁7，让发动机固定架6或者无人机内的其他设备固定在加长梁7上。加长梁7可装在每一个工字梁的任意一个横梁3上，也可两个横梁3上都加装加长梁7。
加强梁5与横梁3平行，使两个连接梁4之间形成两个梯形结构，进一步增加工字梁以及机身结构整体的强度，
加强梁5上设置有多个镂空槽8，两个侧架1的加强梁5之间安装有架板9，架板9两侧设置的插头插在对应的镂空槽8中。架板9可用于支撑安装在旋翼主轴上的主齿轮，也可用于安装无人机内的其他部件。
这种机身结构在组装无人直升机时，只需要在侧架1之间安装支架，把无人机内的其他零部件装在这些支架上即可。

Claims (4)

  1. 一种无人直升机的工字梁式机身结构，其特征在于，包括两个侧架(1)和安装在侧架(1)之间的旋翼架(2)，侧架(1)为工字梁；
    所述的工字梁包括平行设置的两个横梁(3)，横梁(3)之间固接有两个连接梁(4)，连接梁(4)都倾斜设置，使两个连接梁(4)之间形成梯形结构，连接梁(4)之间还固接有加强梁(5)，横梁(3)和连接梁(4)的横截面都为H型；
    侧架(1)之间还安装有多个发动机固定架(6)。
  2. 根据权利要求1所述的无人直升机的工字梁式机身结构，其特征在于，横梁(3)上平行安装有加长梁(7)，发动机固定架(6)固定在加长梁(7)上。
  3. 根据权利要求1所述的无人直升机的工字梁式机身结构，其特征在于，加强梁(5)与横梁(3)平行，加强梁(5)上设置有多个镂空槽(8)。
  4. 根据权利要求3所述的无人直升机的工字梁式机身结构，其特征在于，两个侧架(1)的加强梁(5)之间安装有架板(9)，架板(9)两侧设置的插头插在对应的镂空槽(8)中。
PCT/CN2015/077906 2014-07-03 2015-04-30 无人直升机的工字梁式机身结构 WO2016000485A1 (zh)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106477019A (zh) * 2016-11-08 2017-03-08 芜湖万户航空航天科技有限公司 直升机机身上板
CN106672194A (zh) * 2017-02-24 2017-05-17 沈阳卓翼航空科技有限公司 农用无人机骨架结构
CN109808876A (zh) * 2019-03-26 2019-05-28 河南谷翼自动化科技有限公司 一种共轴双翼飞行器

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104590583B (zh) * 2014-12-19 2016-06-29 四川精石航空科技开发有限公司 一种用于超轻型直升飞机主框架的工装
CN105156873B (zh) * 2015-09-09 2019-04-09 申科谱自动化科技（珠海）有限公司 一种型材
CN105752326B (zh) * 2016-04-07 2018-06-22 珠海紫燕无人飞行器有限公司 机架及无人直升机
CN109677584A (zh) * 2018-12-29 2019-04-26 一飞智控(天津)科技有限公司 双旋翼无人机机身
CN109850118A (zh) * 2019-04-03 2019-06-07 天津宏泽天成科技有限公司 一种无人直升机非承载式机身结构
CN111928092A (zh) * 2020-07-17 2020-11-13 中国航空工业集团公司沈阳飞机设计研究所 一种安装架及具有其的安装结构

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2896770A1 (fr) * 2006-01-27 2007-08-03 Eurocopter France Structure composite anti-crash a maintien lateral pour aeronef.
CN101384477A (zh) * 2005-08-03 2009-03-11 西科尔斯基飞机公司 复合热塑性基体机身结构及其制造方法
CN101443235A (zh) * 2005-02-24 2009-05-27 西科尔斯基飞机公司 用于直升飞行器的能量吸收机架
JP5260778B1 (ja) * 2012-10-08 2013-08-14 ヒロボー株式会社 無人ヘリコプタ
CN103523199A (zh) * 2013-09-29 2014-01-22 郭献民 一种新型管式结构电动无人直升机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101443235A (zh) * 2005-02-24 2009-05-27 西科尔斯基飞机公司 用于直升飞行器的能量吸收机架
CN101384477A (zh) * 2005-08-03 2009-03-11 西科尔斯基飞机公司 复合热塑性基体机身结构及其制造方法
FR2896770A1 (fr) * 2006-01-27 2007-08-03 Eurocopter France Structure composite anti-crash a maintien lateral pour aeronef.
JP5260778B1 (ja) * 2012-10-08 2013-08-14 ヒロボー株式会社 無人ヘリコプタ
CN103523199A (zh) * 2013-09-29 2014-01-22 郭献民 一种新型管式结构电动无人直升机

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106477019A (zh) * 2016-11-08 2017-03-08 芜湖万户航空航天科技有限公司 直升机机身上板
CN106672194A (zh) * 2017-02-24 2017-05-17 沈阳卓翼航空科技有限公司 农用无人机骨架结构
CN109808876A (zh) * 2019-03-26 2019-05-28 河南谷翼自动化科技有限公司 一种共轴双翼飞行器
CN109808876B (zh) * 2019-03-26 2023-09-19 河南谷翼自动化科技有限公司 一种共轴双翼飞行器

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