CN112061387A - Rotor wing mounting structure based on unmanned aerial vehicle wing - Google Patents
Rotor wing mounting structure based on unmanned aerial vehicle wingDownload PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- 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
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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Abstract
Translated fromChinese
Description
Translated fromChinese技术领域technical field
本发明属于无人机领域，涉及一种旋翼安装结构，特别是涉及一种基于无人机机翼的旋翼安装结构。The invention belongs to the field of unmanned aerial vehicles, and relates to a rotor installation structure, in particular to a rotor installation structure based on an unmanned aerial vehicle wing.
背景技术Background technique
固定翼无人机具有飞行速度快、续航时间长、载重能力强等优点，在军用和民用领域获得广泛应用。但常规固定翼无人机对起飞及降落场地要求高，从而限制了其进一步推广运用。具有垂直起降功能的旋翼无人机对地面起降场地依赖小，可灵活起降、空中悬停，但飞行的高度、速度及航时等指标相对较差。Fixed-wing UAVs have the advantages of fast flight speed, long endurance and strong load capacity, and are widely used in military and civilian fields. However, conventional fixed-wing UAVs have high requirements for take-off and landing sites, which limits their further promotion and application. The rotary-wing UAV with vertical take-off and landing function has little dependence on the ground take-off and landing site, and can take off and land flexibly and hover in the air, but the flight height, speed and flight time are relatively poor.
为结合两类无人机的优点，近年来多旋翼和固定翼结合的混合翼无人机获得了广泛关注，并诞生了很多机型。混合翼无人机通常将多旋翼分布安装在固定翼无人机机体结构上(多安装于机翼结构上)，通过旋翼实现垂直起降功能，升空后再转换为固定翼飞行模式。In order to combine the advantages of the two types of UAVs, in recent years, multi-rotor and fixed-wing hybrid-wing UAVs have attracted widespread attention, and many models have been born. The hybrid-wing UAV usually installs multi-rotors on the body structure of the fixed-wing UAV (mostly on the wing structure), realizes the vertical take-off and landing function through the rotor, and then converts to the fixed-wing flight mode after lift-off.
旋翼部件在固定翼机体结构上的安装形式主要有两类：一是借助机体结构布局，如将原无人机尾撑杆延长，并在尾撑杆两端布置旋翼。这种安装形式使机体结构布局与旋翼布局相耦合，设计约束较大；二是根据旋翼布局结果新增安装结构，如新增机翼载荷挂点。这种安装形式对原机体结构改动较大，且旋翼安装结构与原机体结构之间的气动干扰阻力较大。There are two main types of installation of rotor components on the fixed-wing body structure: one is to use the body structure layout, such as extending the original UAV tail strut, and arranging rotors at both ends of the tail strut. This installation form couples the airframe structure layout with the rotor layout, and the design constraints are relatively large; the second is to add a new installation structure according to the results of the rotor layout, such as adding a wing load hanging point. This installation form greatly changes the original airframe structure, and the aerodynamic interference resistance between the rotor installation structure and the original airframe structure is relatively large.
发明内容SUMMARY OF THE INVENTION
本发明解决的技术问题是：降低混合翼无人机的旋翼布局设计难度，将固定翼无人机设计和旋翼设计相解耦，后期通过安装结构组合而生成混合翼无人机。本发明提供一种基于无人机机翼的旋翼安装结构。本发明结构具有模块化程度高、结构简单、气动阻力小、安装位置灵活、适用于固定翼无人机改造等优点。The technical problem solved by the invention is: reducing the difficulty of designing the rotor layout of the hybrid-wing UAV, decoupling the fixed-wing UAV design and the rotor design, and generating the hybrid-wing UAV by combining the installation structures in the later stage. The invention provides a rotor mounting structure based on the wing of an unmanned aerial vehicle. The structure of the invention has the advantages of high modularity, simple structure, small aerodynamic resistance, flexible installation position, and suitability for the transformation of fixed-wing unmanned aerial vehicles.
本发明的技术方案是：一种基于无人机机翼的旋翼安装结构，包括机架组件、撑杆组件和旋翼动力单元，所述机架组件位于机翼上，撑杆组件一端与机架组件连接，另一端与旋翼动力单元连接；The technical scheme of the present invention is: a rotor installation structure based on the wing of an unmanned aerial vehicle, comprising a frame assembly, a strut assembly and a rotor power unit, the frame assembly is located on the wing, and one end of the strut assembly is connected to the frame The components are connected, and the other end is connected with the rotor power unit;
机架组件包括上梁、下梁、前接头和后接头，上梁和下梁包裹机翼翼型且上梁、下梁与机翼表面为曲面贴合；上梁和下梁两段通过前接头和后接头固连；The frame assembly includes an upper beam, a lower beam, a front joint and a rear joint. The upper beam and the lower beam wrap the wing airfoil, and the upper beam, the lower beam and the surface of the wing are curved; the upper beam and the lower beam pass through the front joint. Fixed connection with the rear connector;
撑杆组件：包括撑杆和安装座，撑杆为空心杆状结构，撑杆一端与前接头或后接头固连，另一端与安装座固连；Support rod assembly: including a support rod and a mounting seat, the support rod is a hollow rod-like structure, one end of the support rod is fixedly connected with the front joint or the rear joint, and the other end is fixedly connected with the mounting seat;
安装座用于安装旋翼动力单元；The mounting seat is used to install the rotor power unit;
旋翼动力单元提供旋翼动力输出，包括发动机和螺旋桨；发动机固定在安装座上，发动机可带动螺旋桨旋转。The rotor power unit provides the power output of the rotor, including the engine and the propeller; the engine is fixed on the mounting seat, and the engine can drive the propeller to rotate.
本发明进一步的技术方案是：所述安装座为一体成型件，分为圆盘状和柱状体两部分，柱状体周线与圆盘状轴线相互垂直，两者内部为空腔且相互贯通；圆盘状结构用于安装发动机，柱状体与撑杆固连。A further technical solution of the present invention is: the mounting seat is an integral molded part, which is divided into two parts: a disc-shaped body and a column-shaped body; The disc-shaped structure is used to install the engine, and the cylindrical body is fixedly connected with the strut.
本发明进一步的技术方案是：所述发动机选用电动机或燃油发动机。A further technical solution of the present invention is that: the engine is an electric motor or a fuel engine.
本发明进一步的技术方案是：所述螺旋桨可以选用两叶桨或多叶桨，螺旋桨方向可以是正桨或反桨。A further technical solution of the present invention is that: the propeller can be a two-blade propeller or a multi-blade propeller, and the direction of the propeller can be a forward propeller or a reverse propeller.
本发明进一步的技术方案是：所述上梁和下梁外表面连续光顺，沿航向流线型设计。A further technical solution of the present invention is that the outer surfaces of the upper beam and the lower beam are continuously smooth and streamlined along the course.
发明效果Invention effect
本发明的技术效果在于：采用本发明旋翼安装结构的有益效果是：The technical effect of the present invention is: the beneficial effect of adopting the rotor mounting structure of the present invention is:
1、模块化程度高：混合翼无人机一般包括多个旋翼动力单元，本发明中用于安装旋翼动力单元的撑杆组件采用模块化设计，撑杆组件具有互换性，便于维修更换，可有效降低生产和管理成本。1. High degree of modularity: The hybrid-wing UAV generally includes a plurality of rotor power units. The strut assembly used to install the rotor power unit in the present invention adopts a modular design, and the strut assembly is interchangeable, which is convenient for maintenance and replacement. It can effectively reduce production and management costs.
2、结构简单：本发明结构部件功能明确，传力路线清晰，零部件数量少，均为常规结构，生产加工及装配成本低。2. The structure is simple: the structural components of the present invention have clear functions, clear force transmission routes, few parts and components, all of which are conventional structures, and have low production, processing and assembly costs.
3、气动阻力小：本发明机架组件上下包裹机翼，表面光顺，外形采用流线型设计，可将气动型阻和干扰阻力降至最低。3. Small aerodynamic resistance: the frame assembly of the present invention wraps the wings up and down, the surface is smooth, and the shape adopts a streamlined design, which can minimize aerodynamic resistance and interference resistance.
4、安装位置灵活：本发明旋翼安装结构无机翼安装挂点需求，机翼进行区域性增强设计后，本发明旋翼安装结构安装位置灵活，便于后期换装多种规格发动机及旋翼。4. Flexible installation position: The rotor installation structure of the present invention has no requirement for wing installation hang points. After the wings are regionally enhanced, the installation position of the rotor installation structure of the present invention is flexible, which is convenient for later replacement of various specifications of engines and rotors.
5、适用于固定翼无人机改造：根据机翼强度计算结果和旋翼载荷需求，确定机翼上旋翼的可安装区域后，采用本发明旋翼安装结构能够不改变机翼结构而实现旋翼安装。5. Applicable to the transformation of fixed-wing UAV: according to the calculation result of the wing strength and the load requirement of the rotor, after determining the installable area of the rotor on the wing, the rotor installation structure of the present invention can realize the rotor installation without changing the wing structure.
附图说明Description of drawings
图1是本发明实例的安装效果图；Fig. 1 is the installation effect diagram of the example of the present invention;
图2是本发明实例的组件分解示意图；Fig. 2 is the component exploded schematic diagram of the example of the present invention;
图3是本发明实例的主要零部件分解示意图。FIG. 3 is an exploded schematic view of the main components of the example of the present invention.
其中：1—机翼、2—旋翼安装结构、3—机架组件、4—撑杆组件、5—旋翼动力单元、6—上梁、7—后接头、8—下梁、9—前接头、10—快卸销、11—撑杆、12—安装座、13—发动机、14—螺旋桨。Among them: 1-wing, 2-rotor mounting structure, 3-frame assembly, 4-strut assembly, 5-rotor power unit, 6-upper beam, 7-rear joint, 8-lower beam, 9-front joint , 10—Quick release pin, 11—Strut, 12—Mounting seat, 13—Engine, 14—Propeller.
具体实施方式Detailed ways
参见图1—图3，下面将结合附图和具体实施方式对本发明实例作进一步的详细说明。Referring to FIG. 1 to FIG. 3 , the examples of the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.
本发明旋翼安装结构主要由机架组件、撑杆组件和旋翼动力单元组成：The rotor installation structure of the present invention is mainly composed of a frame assembly, a strut assembly and a rotor power unit:
1、机架组件：安装固定在机翼结构上，提供撑杆组件的安装接口。机架组件构成主要包括上梁、下梁、前接头和后接头。机架组件通过上梁、下梁包裹机翼翼型，上梁、下梁与机翼表面为曲面贴合，上梁、下梁外表面连续光顺，沿航向流线型设计。前接头、后接头分别位于机架组件的最前端和最后端，并与上梁、下梁固连。1. Rack assembly: It is installed and fixed on the wing structure and provides the installation interface of the strut assembly. The frame components mainly include upper beam, lower beam, front joint and rear joint. The frame assembly wraps the wing airfoil through the upper beam and the lower beam. The upper beam and the lower beam and the surface of the wing are curved. The outer surfaces of the upper beam and the lower beam are continuously smooth and streamlined along the course. The front joint and the rear joint are respectively located at the front end and the rear end of the frame assembly, and are fixedly connected with the upper beam and the lower beam.
2、撑杆组件：安装固定在机架组件上，提供旋翼动力单元的安装接口。撑杆组件构成主要包括撑杆和安装座。撑杆为空心杆状结构，长度参考旋翼尺寸确定。撑杆一端连接机架组件，一端连接安装座。安装座用于安装旋翼动力单元，机械接口根据旋翼动力单元安装需求协调设计。2. Support rod assembly: It is installed and fixed on the frame assembly to provide the installation interface of the rotor power unit. The strut assembly mainly includes struts and mounting seats. The strut is a hollow rod-like structure, and the length is determined with reference to the size of the rotor. One end of the strut is connected to the rack assembly, and the other end is connected to the mounting base. The mounting seat is used to install the rotor power unit, and the mechanical interface is coordinated and designed according to the installation requirements of the rotor power unit.
3、旋翼动力单元：安装固定在撑杆组件上，提供旋翼动力输出。旋翼动力单元构成主要包括发动机和螺旋桨。根据总体设计，发动机可以选用电动机或燃油发动机等形式。螺旋桨结构可以选用两叶桨或多叶桨，螺旋桨方向可以是正桨或反桨。3. Rotor power unit: installed and fixed on the strut assembly to provide rotor power output. The rotor power unit mainly includes the engine and the propeller. According to the overall design, the engine can choose the form of electric motor or fuel engine. The propeller structure can choose two-blade propeller or multi-blade propeller, and the propeller direction can be forward propeller or reverse propeller.
机架组件与机翼之间、旋翼动力单元与撑杆组件之间均为设计分离面，使用中不拆卸，仅在系统出现故障需要检修时拆卸。撑杆组件与机架组件之间为使用分离面，可采用快装快卸设计，拆卸分离后可减小部件尺寸，便于无人机部件装箱或装车。Between the frame assembly and the wing, between the rotor power unit and the strut assembly are designed separation surfaces, which are not disassembled during use, but only when the system fails and needs to be repaired. There is a separation surface between the strut assembly and the rack assembly, which can be designed with quick assembly and quick disassembly. After disassembly and separation, the size of the parts can be reduced, which is convenient for the UAV parts to be packed into boxes or trucks.
图1为本发明实例安装效果图，旋翼安装结构2通过夹持的方式固定在机翼1的指定截面位置。安装效果简洁，不破坏机翼结构整体性。图2为本发明实例的组件分解示意图，旋翼安装结构2分为机架组件3、撑杆组件4和旋翼动力单元5。前撑杆组件和后撑杆组件采用模块化设计，具有互换性。使用维护时为便于部件装车或装箱，将撑杆组件4和旋翼动力单元5作为一个整体部件拆装。FIG. 1 is an installation effect diagram of an example of the present invention. The rotor installation structure 2 is fixed at the designated cross-sectional position of the wing 1 by clamping. The installation effect is simple and does not destroy the integrity of the wing structure. FIG. 2 is an exploded schematic view of the components of the example of the present invention. The rotor mounting structure 2 is divided into a
图3为主要零部件分解示意图，机架组件3组成包括上梁6、后接头7、下梁8和前接头9。上梁6和下梁8的航向外形采用流线型设计，最大化减小气动阻力。上梁6和下梁8上下包裹机翼1，与机翼1外表面融合过渡，最大化减小部件气动干扰阻力。上梁6和下梁8采用中空带翻边设计，保证结构强度的同时，最大化减小结构重量，并将旋翼载荷通过面接触的形式传递给机翼1。前接头9和后接头7装配在上梁6和下梁8内测，将旋翼载荷传递至上梁6和下梁8。撑杆组件4组成包括快卸销10、撑杆11和安装座12。撑杆11为薄壁柱状结构，可承受旋翼动力单元5传递的各种载荷。撑杆11一侧连接安装座12，另一侧与机架组件3对接，撑杆11通过快卸销10安装固定在机架组件3的前接头9或后接头7上。旋翼动力单元5构成包括发动机13和螺旋桨14，本实例中发动机13选用无刷电机，螺旋桨14选用双叶定距桨。FIG. 3 is an exploded schematic view of the main components. The
本发明的上述实施方式不能认为是对本发明权利要求所作的限制，如果本领域的技术人员通过本发明的启发不需要创造性的劳动做出相应的变化，都应该落入本发明权利要求的保护范围内。The above-mentioned embodiments of the present invention should not be considered as limitations on the claims of the present invention. If those skilled in the art do not need creative work to make corresponding changes through the inspiration of the present invention, they should fall within the protection scope of the claims of the present invention. Inside.
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| US20150136897A1 (en)* | 2012-06-01 | 2015-05-21 | Logo-Team Ug (Haftungsbeschrankt) | Aircraft, preferably unmanned |
| US20190152593A1 (en)* | 2015-11-04 | 2019-05-23 | Fuvex Sistemas, S.L. (95%) | Aerodyne with vertical-takeoff-and-landing ability |
| CN106741820A (en)* | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN206766345U (en)* | 2017-04-20 | 2017-12-19 | 西北工业大学明德学院 | A kind of four rotor wing unmanned aerial vehicles with crawl function |
| CN109178301A (en)* | 2018-09-04 | 2019-01-11 | 西北工业大学 | A kind of fixed-wing rotor mixing unmanned plane |
| CN109720564A (en)* | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
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