WO2021013188A1 - 螺旋桨保护罩及飞行器 - Google Patents

螺旋桨保护罩及飞行器 Download PDF

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Publication number
WO2021013188A1
WO2021013188A1 PCT/CN2020/103560 CN2020103560W WO2021013188A1 WO 2021013188 A1 WO2021013188 A1 WO 2021013188A1 CN 2020103560 W CN2020103560 W CN 2020103560W WO 2021013188 A1 WO2021013188 A1 WO 2021013188A1
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WO
WIPO (PCT)
Prior art keywords
protective cover
arm
propeller
locking
mounting
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Application number
PCT/CN2020/103560
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English (en)
French (fr)
Inventor
张桂林
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深圳市道通智能航空技术有限公司
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Publication of WO2021013188A1 publication Critical patent/WO2021013188A1/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
    • B64U30/299—Rotor guards
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2/00—Friction-grip releasable fastenings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters

Definitions

  • This application relates to the technical field of aircraft, and in particular to a propeller protective cover for an aircraft and an aircraft having the propeller protective cover.
  • Unmanned aircraft is abbreviated as "Unmanned Aerial Vehicle” (UAV), which is an unmanned aerial vehicle operated by radio remote control equipment and its own program control device. It can also be completely or intermittently autonomously operated by a computer.
  • UAV Unmanned Aerial Vehicle
  • drone technology Since no specific staff is required to drive, the drone can take on some dangerous or repetitive tasks.
  • drone technology has matured for civilian use and is widely used in aerial photography, agriculture, plant protection, micro selfies, express transportation, disaster relief, observation of wild animals, monitoring of infectious diseases, surveying and mapping, news reports, power inspections, disaster relief, Film and television shooting and many other technical fields.
  • the drone may temporarily lose control during flight, causing the propeller to collide with other objects, causing damage to the propeller.
  • the manufacturer of the drone generally adds a protective cover around the propeller; in this way, the main body of the collision becomes a protective cover, and the protective cover can withstand a certain impact force, thereby effectively protecting the propeller. .
  • the present application provides a propeller protective cover and an aircraft with the propeller protective cover to solve the current technical problems of complicated structure and inconvenient disassembly and assembly of the propeller protective cover.
  • a propeller protective cover including:
  • the mounting seat is provided with a mounting slot for accommodating the end of the arm of the aircraft;
  • a protection frame connected to the mounting base, for protecting the propeller of the aircraft
  • a locking member is rotatably mounted on the mounting seat relative to the mounting seat, and the locking member includes a connecting portion rotatably mounted on the mounting seat and an end provided on the connecting portion ⁇ locking part;
  • the connecting portion can drive the locking portion to rotate to abut on the arm provided in the mounting base, so as to lock the arm in the mounting base.
  • the propeller protective cover further includes a holding member installed on the locking portion, and the holding member is configured to be configured when the locking portion abuts the arm Located between the arm and the locking part.
  • the locking portion is provided with a groove
  • the holding member is provided with a protrusion that is engaged with the groove, and the holding member passes through the protrusion and The groove is fitted on the locking portion.
  • the holding member is bonded to the locking portion.
  • the material of the holding member is a soft elastic material.
  • the material of the holding member includes silica gel or rubber.
  • the shape of the locking portion is adapted to the shape of the side surface of the arm, and the locking portion is used for abutting against the side surface.
  • the locking portion has a fan ring shape or an arc shape.
  • the width of the locking portion is greater than the width of the connecting portion.
  • the mounting seat includes a bottom wall and a side wall bent and extended from the bottom wall, the mounting groove is formed by the bottom wall and the side wall, and the side wall faces A hinge seat extends away from the installation slot, and the locking member is hinged to the hinge seat.
  • the side wall is U-shaped.
  • the hinge seat includes a first hinge seat extending from an upper part of one end of the side wall in a direction away from the mounting groove, and a first hinge seat extending away from the lower part of one end of the side wall.
  • first hinge seat and the second hinge seat are spaced apart, and the connecting portion is hinged between the first hinge seat and the second hinge seat.
  • the first hinge seat is provided with a first hinge hole
  • the second hinge seat is provided with a second hinge hole
  • the connecting portion is provided with a mounting hole
  • the connecting portion passes through a A rotating shaft placed in the mounting hole is hinged between the first hinge seat and the second hinge seat, and both ends of the rotating shaft are respectively matched with the first hinge hole and the second hinge hole .
  • an end of the side wall away from the hinge seat is provided with a limiting portion extending toward the inside of the mounting groove, and the limiting portion is used for abutting against the arm, Thus, the arm is clamped between the limiting portion and the bottom wall.
  • the bottom wall is also provided with a through hole for accommodating the landing gear.
  • the protection frame includes a circumferential frame and a radial frame, and two ends of the radial frame are respectively connected with the circumferential frame and the mounting seat.
  • An aircraft includes a fuselage, an arm connected to the fuselage, and a power assembly provided on the arm.
  • the aircraft also includes the above-mentioned propeller protection cover, the propeller protection cover being installed on the aircraft arm .
  • the propeller protective cover provided by one of the embodiments of the present application is hinged with a locking member on the mounting seat, and the locking member can be rotated to be tightly fixed with the arm installed in the mounting slot. If you need to disassemble the propeller protective cover, you only need to turn the locking piece in the opposite direction to separate the locking piece from the arm.
  • the overall structure of the propeller protective cover is simple, the manufacturing cost is low, and it also has the advantages of convenient disassembly and assembly.
  • Figure 1 is a three-dimensional schematic diagram of an aircraft provided by one of the embodiments of the application;
  • Fig. 2 is a perspective schematic view of a propeller protective cover in one direction in Fig. 1;
  • FIG 3 is an exploded schematic diagram of a propeller protective cover in Figure 1;
  • Fig. 4 is an enlarged schematic diagram of A in Fig. 3;
  • Figure 5 is an exploded schematic diagram of the combined propeller protective cover
  • Fig. 6 is a perspective schematic view of a combined propeller protective cover installed on one side of the aircraft in Fig. 1.
  • the "installation” includes welding, screwing, clamping, bonding, etc. to fix or restrict a certain element or device to a specific position or place, and the element or device can be held in a specific position or place. It can also move within a limited range without moving.
  • the element or device can be disassembled or cannot be disassembled after being fixed or restricted to a specific position or place, which is not limited in the embodiment of the present application.
  • FIG. 1 shows a three-dimensional schematic diagram of an aircraft provided by one of the embodiments of the present application.
  • the aircraft includes a fuselage 100, a plurality of arms 200 extending outward from the edges of the fuselage 100, and The power assembly 300 at the end of 200 away from the fuselage 100 and the propeller protection cover 400 provided on the periphery of the power assembly 300.
  • the fuselage 100 is the core component of the aircraft, and a communication module for interacting with a base station or a user and a control module for controlling the power assembly 300 are provided inside it.
  • the body 100 may also be fixedly connected with a camera assembly (not shown in the figure) for taking pictures or a box for installing objects (not shown in the figure), etc. according to application requirements.
  • the arm 200 extends from the side of the fuselage 100; preferably, the number of the arm 200 is four, and they are symmetrically distributed about the fuselage 100.
  • the end of the arm 200 away from the fuselage 100 is provided with a downwardly extending landing gear for stable parking when the aircraft is not in flight.
  • the power assembly 300 includes a propeller and a driving device that drives the propeller to rotate.
  • the driving device drives the propeller to rotate to provide power for the aircraft to fly.
  • the propeller protective cover 400 includes a mounting seat 410 and A protection frame 420 connected to the mounting base 410.
  • the mounting base 410 is provided with a mounting groove 411 for accommodating the arm 200
  • the protection frame 420 includes a radial bracket 421 fixedly connected to the side wall of the mounting base 410 and a circumferential bracket 422 connected to the above-mentioned radial bracket 421.
  • the bottom wall of the mounting seat 410 has a flat structure; the side wall of the mounting seat 410 is U-shaped as a whole, and extends from the edge of the bottom wall.
  • the bottom wall and the side wall jointly surround the mounting groove 411.
  • a locking member 430 is rotatably connected to one end of the side wall of the mounting base 410, and the locking member 430 can rotate in the first plane to realize the locked state and the unlocked state of the arm 200.
  • the above-mentioned first plane is a plane parallel to the bottom wall of the mounting seat and passing through the locking member 430.
  • one end of the side wall of the mounting seat 410 is provided with a hinge seat 412 extending in a direction away from the mounting groove 411; the hinge seat 412 includes an upper portion of one end of the side wall and a direction perpendicular to the side wall and away from the mounting groove.
  • a first hinge seat extending from one end of the side wall 411, and a second hinge seat extending from the lower part of one end of the side wall to an end away from the mounting groove 411 in a direction perpendicular to the side wall, the first hinge seat and the second hinge seat Parallel interval setting.
  • the first hinge seat is provided with a first hinge hole extending along the normal direction of the first plane, and the second hinge seat is provided with a second hinge hole coaxial with the first hinge hole; both ends of the rotating shaft 440 are respectively at least partially provided In the first hinge hole and the second hinge hole, and fixedly connected with the mounting seat 410.
  • the locking member 430 is hinged between the first hinge seat and the second hinge seat, and is provided with a mounting hole corresponding to the above-mentioned hinge hole, and is sleeved on the rotating shaft 440 through the above-mentioned mounting hole.
  • the shaft 440 is a pin.
  • the cylindrical surface of at least one end of the pin is provided with knurled teeth arrayed in the circumferential direction, and the pin is tightly fitted and fixed with the hinge seat 412 through the knurled teeth.
  • the locking member 430 includes a locking portion 431 that is tightly secured to the arm 200 and a connecting portion 432 connected to the locking portion 431.
  • the connecting portion 432 is sleeved on the rotating shaft 440 and is hinged to the mounting seat 410.
  • the end of the locking portion 431 away from the connecting portion 432 is used to hold and fix the arm 200.
  • the entire locking portion 431 is fan-shaped to ensure the locking part The process of 430 resisting the arm 200 smoothly transitions.
  • the locking portion 431 may also be arc-shaped, which is not limited here one by one. It is only necessary to ensure that the shape of the locking portion 431 matches the shape of the arm 200.
  • the width of the locking portion 431 is greater than the width of the connecting portion 432.
  • the tangent line of the locking portion 431 is perpendicular to the extending direction of the connecting portion 432.
  • the locking portion 431 of the locking member 430 is provided with a holding member 433 at the end of the locking portion 431 away from the connecting portion 432.
  • a groove 434 is provided at one end of the locking portion 431 away from the connecting portion 432, and an end of the holding member 433 close to the locking portion 431 is provided with a protrusion 435 corresponding to the groove 434.
  • the holding member 433 passes through the protrusion 435 and The groove 434 is fitted on the locking portion 431 in cooperation.
  • the material of the holding member 433 can be selected from soft elastic materials such as rubber, silicone, etc., of course, it can also be a mixed material including rubber, silicone, and other materials.
  • the holding member 433 is made of silicone, which is fixed in the above-mentioned groove by bonding; it not only has the effect of preventing slippage and increasing the friction between the locking member 430 and the arm 200, but also can reduce the lock The degree of deformation of the tight piece 430 when it is tightly held with the arm 200.
  • the mounting seat 410 is provided with a through-locking groove 413 on the side wall where the hinge seat 412 is provided, which allows the locking member 430 to enter and exit the mounting groove 411 when rotating.
  • the locking groove 413 has a rectangular shape.
  • the mounting seat 410 is provided on a side wall away from the hinge seat 412 with a limiting portion 414 extending toward the inside of the mounting groove 411, which can resist the top of the arm 200 to restrict the arm from moving in a direction perpendicular to the first plane, thereby Clamp the arm between the limit part and the bottom wall.
  • the bottom wall of the mounting seat 410 is also provided with a through hole for the aircraft landing gear to pass through; the arc section of the side wall of the mounting seat 410 is provided with a protrusion arranged on the surface of the end of the arm 200 away from the fuselage 100 Matching positioning holes.
  • the locking member 430 can rotate to at least partially enter and exit the mounting groove 411; when the mounting groove 411 contains the organic arm 200, the locking member 430 can rotate to at least Part of it enters the mounting groove 411, and resists the arm 200 and pushes the arm 200 to engage with the limit part 414; a certain holding force is also formed between the locking member 430 and the arm 200, so that the arm 200 It is fixed under the action of the installation groove 411, the limiting portion 414 and the locking member 430.
  • the protective frame 420 includes a circumferential bracket 422 and a plurality of radial brackets 421, and the circumferential bracket 422 falls on the periphery of the propeller as a whole.
  • the two ends of the radial bracket 421 are respectively connected to the mounting seat 410 and the circumferential bracket 422, and the number is more than two. In this embodiment, the number of the radial brackets is two.
  • the two outermost radial brackets The circumferential support 422 between 421 is arc-shaped.
  • Figure 5 shows a combined propeller protective cover, which includes two cover bodies, each of which is a single structure of the above-mentioned propeller protective cover, and the two cover bodies are detachably connected Fixed connection.
  • the circumferential protection frame of each cover extends to the circumferential protection frame of the other cover to form a connecting end 423, and the two connecting ends 423 are connected and fixed by a buckle.
  • the two cover bodies may be integrally formed.
  • FIG. 6 shows a three-dimensional schematic diagram of the above-mentioned combined propeller protective cover mounted on the arm 200 of the aircraft.
  • the end of the arm 200 away from the fuselage 100 is installed in the mounting slot 411, and the locking member 430 is rotated in the direction of the arrow shown in the figure, and the locking portion 431 is connected to the arm 200
  • the side surfaces resist and hold tightly, and the arm 200 is fixed in the installation groove under the joint action of the side wall of the mounting seat 410 and the locking portion 431.
  • the overall shape of the mounting slot is not limited to the U shape in the above embodiment, and it can be adapted to match the actual shape of the aircraft arm.
  • the above-mentioned locking member can also be provided on the remaining side walls of the mounting seat.
  • the two propeller guards 400 on the same side of the aircraft are fixed into a combined propeller guard by snap connection, and the locking member 430 is rotated so that the entire locking member does not enter the installation groove 411 as a whole.
  • An end of the connecting portion 432 away from the locking portion 431 forms a hand-held wrench. If the propeller protection cover 400 needs to be removed, it is only necessary to rotate the wrench in the opposite direction to separate the locking portion 431 from the arm 200 to achieve an unlocked state.
  • the propeller protective cover provided by the above embodiment only includes parts such as the mounting seat, the protective frame, the locking member, and the rotating shaft, and the installation process can be completed by rotating the locking member and the arm.
  • the overall structure is simple and the manufacturing cost is low; at the same time, it also has the advantages of convenient disassembly and assembly.

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  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
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Abstract

本申请涉及飞行器技术领域，公开了一种螺旋桨保护罩及飞行器。该螺旋桨保护罩包括：安装座，所述安装座设有用于容置飞行器的机臂末端的安装槽；保护架，与所述安装座连接，用于保护所述飞行器的螺旋桨；以及锁紧件，所述锁紧件可相对于所述安装座转动地安装于所述安装座，所述锁紧件包括转动安装于所述安装座的连接部和设于所述连接部一端的锁止部；所述连接部可带动所述锁止部转动至与设于所述安装座内的所述机臂抵接，以将所述机臂锁紧在所述安装座内。该螺旋桨保护罩在安装座上铰接有锁紧件，并且能够通过转动该锁紧件，使其与安装于安装槽内机臂抱紧固定。该螺旋桨保护罩的整体结构简单，制造成本较低。

Description

螺旋桨保护罩及飞行器
本申请要求于2019年7月22日提交中国专利局、申请号为201921159541.3、申请名称为“螺旋桨保护罩及飞行器”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请涉及飞行器技术领域，尤其涉及一种用于飞行器的螺旋桨保护罩和具有该螺旋桨保护罩的飞行器。
背景技术
无人驾驶飞机简称“无人机”(UAV)，是利用无线电遥控设备和自备的程序控制装置操纵的非载人飞行器，其还可以由计算机完全地或间歇地自主操作。
由于不需要特定的工作人员驾驶，所以无人机能够承担一些危险或者重复性的工作。目前，无人机技术已经成熟的民用化，并广泛运用于航拍、农业、植保、微型自拍、快递运输、灾难救援、观察野生动物、监控传染病、测绘、新闻报道、电力巡检、救灾、影视拍摄等等诸多技术领域。
由于用户的操控失误或者受到外部干扰，无人机在飞行时可能会短暂失控以致螺旋桨与其他物体发生碰撞，使螺旋桨损坏。为避免这一情况，无人机的制造商一般会在螺旋桨的外围加设保护罩；如此，碰撞的主体则变成了保护罩，且保护罩能够承受一定的撞击力，从而有效保护了螺旋桨。
但是，目前用于无人机领域内的螺旋桨保护罩大多结构复杂，导致成本较高，并且在拆装时十分繁琐。
发明内容
本申请提供一种螺旋桨保护罩及具有该螺旋桨保护罩的飞行器以解决目前的螺旋桨保护罩结构复杂、拆装不便的技术问题。
本申请解决其技术问题采用以下技术方案：
一种螺旋桨保护罩，包括：
安装座，所述安装座设有用于容置飞行器的机臂末端的安装槽；
保护架，与所述安装座连接，用于保护所述飞行器的螺旋桨；以及
锁紧件，所述锁紧件可相对于所述安装座转动地安装于所述安装座，所述锁紧件包括转动安装于所述安装座的连接部和设于所述连接部的一端的锁止部；
所述连接部可带动所述锁止部转动至与设于所述安装座内的所述机臂抵 接，以将所述机臂锁紧在所述安装座内。
作为上述技术方案的进一步改进方案，所述螺旋桨保护罩还包括安装于所述锁止部的抱紧件，所述抱紧件被设置为当所述锁止部与所述机臂抵接时位于所述机臂与所述锁止部之间。
作为上述技术方案的进一步改进方案，所述锁止部设有凹槽，所述抱紧件设有与所述凹槽卡接的凸起部，所述抱紧件通过所述凸起部和所述凹槽的配合安装于所述锁止部上。
作为上述技术方案的进一步改进方案，所述抱紧件与所述锁止部粘接。
作为上述技术方案的进一步改进方案，所述抱紧件的材料为软质弹性材料。
作为上述技术方案的进一步改进方案，所述抱紧件的材料包括硅胶或者橡胶。
作为上述技术方案的进一步改进方案，所述锁止部的形状与所述机臂的侧面形状相适配，所述锁止部用于与所述侧面抵接。
作为上述技术方案的进一步改进方案，所述锁止部呈扇环状或圆弧状。
作为上述技术方案的进一步改进方案，所述锁止部的宽度大于所述连接部的宽度。
作为上述技术方案的进一步改进方案，所述安装座包括底壁和自所述底壁弯折延伸的侧壁，所述安装槽由所述底壁和所述侧壁形成，所述侧壁向远离所述安装槽的方向延伸有铰接座，所述锁紧件铰接于所述铰接座。
作为上述技术方案的进一步改进方案，所述侧壁呈U形。
作为上述技术方案的进一步改进方案，所述铰接座包括自所述侧壁的一端的上部向远离所述安装槽的方向延伸的第一铰接座和自所述侧壁的一端的下部向远离所述安装槽的方向延伸的第二铰接座，所述第一铰接座与所述第二铰接座间隔设置，所述连接部铰接于所述第一铰接座和所述第二铰接座之间。
作为上述技术方案的进一步改进方案，所述第一铰接座设有第一铰接孔，所述第二铰接座设有第二铰接孔，所述连接部设有安装孔，所述连接部通过一置于所述安装孔内的转轴铰接于所述第一铰接座和所述第二铰接座之间，且所述转轴的两端分别与所述第一铰接孔和所述第二铰接孔配合。
作为上述技术方案的进一步改进方案，所述侧壁远离所述铰接座的一端设有向所述安装槽的内部延伸的限位部，所述限位部用于与所述机臂抵接，从而将所述机臂卡接于所述限位部和所述底壁之间。
作为上述技术方案的进一步改进方案，所述底壁还设有用于收容起落架的通孔。
作为上述技术方案的进一步改进方案，所述保护架包括周向支架和径向支架，所述径向支架的两端分别与所述周向支架和所述安装座连接。
本申请解决其技术问题还采用以下技术方案：
一种飞行器，包括机身、与所述机身相连的机臂和设于所述机臂的动力组件，所述飞行器还包括上述的螺旋桨保护罩，所述螺旋桨保护罩安装于所述机臂。
本申请的有益效果是：
本申请其中一实施例提供的螺旋桨保护罩在安装座上铰接有锁紧件，并且能够通过转动该锁紧件，使其与安装于安装槽内机臂抱紧固定。如需拆卸该螺旋桨保护罩，即仅需反向转动锁紧件，使锁止件与机臂分离。
该螺旋桨保护罩的整体结构简单，制造成本较低，同时还具有拆装方便的优点。
附图说明
一个或多个实施例通过与之对应的附图进行示例性说明，这些示例性说明并不构成对实施例的限定，附图中具有相同参考数字标号的元件表示为类似的元件，除非有特别申明，附图中的图不构成比例限制。
图1为本申请其中一实施例提供的飞行器的立体示意图；
图2为图1中一个螺旋桨保护罩的一个方向的立体示意图；
图3为图1中一个螺旋桨保护罩的分解示意图；
图4为图3中A处的放大示意图；
图5为组合式螺旋桨保护罩的分解示意图；
图6为图1中飞行器的一侧安装有组合式螺旋桨保护罩的立体示意图。
具体实施方式
为了便于理解本申请，下面结合附图和具体实施例，对本申请进行更详细的说明。需要说明的是，当元件被表述“固定于”另一个元件，它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件，它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”、“内”、“外”以及类似的表述只是为了说明的目的。
除非另有定义，本说明书所使用的所有的技术和科学术语与属于本申请的技术领域的技术人员通常理解的含义相同。在本申请的说明书中所使用的术语只是为了描述具体的实施例的目的，不是用于限制本申请。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
此外，下面所描述的本申请不同实施例中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
在本说明书中，所述“安装”包括焊接、螺接、卡接、粘合等方式将某一元件或装置固定或限制于特定位置或地方，所述元件或装置可在特定位置或地方保持不动也可在限定范围内活动，所述元件或装置固定或限制于特定位置或地方后可进行拆卸也可不能进行拆卸，在本申请实施例中不作限制。
请参照图1，其示出了本申请其中一实施例提供的飞行器的立体示意图，该飞行器包括机身100、从机身100的边缘向外伸出的若干根机臂200、设于机臂200远离机身100的一端的动力组件300及设于动力组件300外围的螺旋桨保护罩400。
机身100为该飞行器的核心部件，其内部设有用于与基站或者用户交互的通信模块和用于控制动力组件300的控制模块。机身100还可以根据应用需要，固接有用于拍照的摄像组件(图中未示出)或者用于装设物件的箱体(图中未示出)等。
机臂200从机身100的侧部伸出；优选的，机臂的数量为四根，且关于机身100左右对称分布。机臂200远离机身100的一端设有向下延伸起落架，用于飞行器处于非飞行状态时的稳定停放。
动力组件300包括螺旋桨及驱动螺旋桨转动的驱动装置，驱动装置驱动螺旋桨旋转以为飞行器提供飞行的动力。
参照图2至图4，其示出了本申请提供的螺旋桨保护罩400的一个实施例的立体示意图、分解示意图及局部放大示意图；请同时结合图1，该螺旋桨保护罩400包括安装座410和与该安装座410连接的保护架420。安装座410设有用于容置机臂200的安装槽411，保护架420包括与安装座410的侧壁固接的径向支架421和与上述径向支架421连接的周向支架422。
优选的，安装座410的底壁为扁平状结构；安装座410的侧壁整体呈U形形状，自底壁的边缘弯折延伸，上述底壁与侧壁共同围绕成上述安装槽411。 安装座410的侧壁的一端转动连接有锁紧件430，锁紧件430能够于第一平面内转动以实现机臂200的锁止状态与解锁状态。上述第一平面为与安装座的底壁平行，且穿过锁紧件430的平面。
具体的，安装座410的侧壁的一端设有沿远离安装槽411的方向延伸的铰接座412；该铰接座412包括自上述侧壁的一端的上部沿垂直该侧壁的方向向远离安装槽411的一端延伸的第一铰接座，以及自上述侧壁的一端的下部沿垂直该侧壁的方向向远离安装槽411的一端延伸的第二铰接座，该第一铰接座与第二铰接座平行间隔设置。
第一铰接座设有沿上述第一平面的法向延伸的第一铰接孔，第二铰接座设有与上述第一铰接孔同轴的第二铰接孔；转轴440的两端分别至少部分设于该第一铰接孔与第二铰接孔内，并与安装座410固定连接。锁紧件430铰接于第一铰接座与第二铰接座之间，并设有与上述铰接孔对应的安装孔，其通过上述安装孔套设于转轴440上。
优选的，转轴440为销钉，进一步的，该销钉的至少一个端部的圆柱面上设置有沿周向阵列的滚花齿，该销钉通过上述滚花齿与铰接座412紧配合固定。
锁紧件430包括与机臂200抱紧固定的锁止部431及与锁止部431连接的连接部432。连接部432套设于转轴440上与安装座410铰接，锁止部431远离连接部432的一端用于与机臂200抱紧固定，锁止部431整体呈扇环状，以保证锁紧件430与机臂200抵持的过程平滑过渡。此外，锁止部431也可是圆弧状，在此不一一限定，仅需保证锁止部431的形状与机臂200形状相适配即可。
进一步的，为使锁紧件430与机臂200抱紧固定时受力均匀，锁止部431的宽度大于连接部432的宽度。优选的，于与连接部432的连接处，锁止部431的切线与连接部432的延伸方向垂直。
更进一步的，为防止锁止部431与机臂200在抱紧后发生打滑，锁紧件430的锁止部431远离连接部432的端部设有抱紧件433。锁止部431远离连接部432的一端设有凹槽434，抱紧件433靠近锁止部431的一端设有与凹槽434对应的凸起部435，抱紧件433通过凸起部435和凹槽434的配合安装于所述锁止部431上。抱紧件433的材料可以选取橡胶、硅胶等软质弹性材料，当然也可以是包括橡胶、硅胶及其他材料的混合材料。在本实施例中，抱紧件433为硅胶，通过粘接固定在上述凹槽内；其不仅能起到防滑、增大锁紧件430与机臂200摩擦力的功效，还能够减小锁紧件430与机臂200抱紧时的变形程度。
安装座410于设有铰接座412的侧壁部位上设有贯通的锁止槽413，其可容许锁紧件430在转动时进出上述安装槽411。优选的，该锁止槽413为矩形形状。
安装座410于远离铰接座412的侧壁上设有向安装槽411内部延伸的限 位部414，其能够与机臂200的顶部抵持以限制机臂沿垂直第一平面的方向移动，从而将机臂卡接于限位部和底壁之间。
此外，安装座410的底壁上还设有供飞行器起落架穿过的通孔；安装座410侧壁的弧形段上，设有与机臂200远离机身100的一端的表面设置的突起相互配合的定位孔。
当安装槽411内未容置有机臂200时，锁紧件430能够转动至至少部分进出所述安装槽411；当所述安装槽411内容置有机臂200时，锁紧件430能够转动至至少部分进入安装槽411，与机臂200抵持并将机臂200推至与限位部414卡合；锁紧件430与机臂200之间亦形成一定的抱紧力，从而使机臂200在安装槽411、限位部414及锁紧件430的作用下保持固定。
结合图1至图4，保护架420包括周向支架422及若干根径向支架421，周向支架422整体落在螺旋桨的外围。径向支架421的两端分别于安装座410及周向支架422连接，其数量为两根以上，本实施例中径向支架的数量为两根，优选的，最外侧的两根径向支架421之间的周向支架422为圆弧状。
图5示出了一种组合式螺旋桨保护罩，其包括两个罩体，每个罩体均为上文中的螺旋桨保护罩的单体结构，该两个罩体之间通过可拆卸连接的方式固接。优选的，相互连接的两罩体之间，每一个罩体的周向保护架均向另一个罩体的周向保护架延伸形成连接端423，两连接端423通过卡扣连接固定。应当理解，在本申请的其他实施例中，两所述罩体之间可以一体成型。
请参照图6，其示出了上述组合式螺旋桨保护罩安装于飞行器的机臂200上的立体示意图。结合其余附图，如图所示，机臂200远离机身100的一端装设于安装槽411内，依照图示箭头的方向转动锁紧件430，锁止部431则会与机臂200的侧面抵持并抱紧，在安装座410的侧壁及锁止部431的共同作用下，机臂200被固定于安装槽内。
应当理解，安装槽的整体形状并不局限于上述实施例中的U形，其可以根据飞行器的机臂的实际形状做出适应性的匹配。此外，还可以在安装座的其余侧壁上亦设置上述的锁紧件。
以四旋翼飞行器为例，以下结合各附图对螺旋桨保护罩的安装过程进行简要说明：
首先将位于飞行器同一侧的两螺旋桨保护罩400通过卡扣连接固定成组合式螺旋桨保护罩，转动锁紧件430，使锁紧件整体未进入安装槽411内部。
然后，将起落架穿过安装座410底壁的通孔，直至机臂200对应地安装于安装槽411，且机臂200远离主体10一端的突起刚好落在安装座410弧形侧壁上的定位孔内。
转动锁紧件430使锁止部431朝向机臂200运动，并推动机臂200转动至安装座410远离锁紧件430的侧壁处，此时限位部414与机臂200的顶部抵持固定；继续转动锁紧件430直至锁紧件430与机臂200之间抱紧固定实现锁止状态。此时，抱紧件位于锁止部与机臂的侧面之间，增大锁止部与机 臂侧面的摩擦力，锁止的效果极好。
同理，按照相同的方式安装另一侧的螺旋桨保护罩400。
连接部432远离锁止部431的一端形成可手持的扳手，如需拆卸螺旋桨保护罩400，即仅需反向转动该扳手使锁止部431与机臂200分离实现解锁状态。
综上，上述实施例提供的螺旋桨保护罩仅包括安装座、保护架、锁紧件和转轴等零件，可以通过转动锁紧件与机臂抱紧固定完成安装过程。整体结构简单，制造成本较低；同时还具有拆装方便的优点。
最后应说明的是：以上实施例仅用以说明本申请的技术方案，而非对其限制；在本申请的思路下，以上实施例或者不同实施例中的技术特征之间也可以进行组合，步骤可以以任意顺序实现，并存在如上所述的本申请的不同方面的许多其它变化，为了简明，它们没有在细节中提供；尽管参照前述实施例对本申请进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本申请各实施例技术方案的范围。

Claims (17)

  1. 一种螺旋桨保护罩，其特征在于，包括：
    安装座，所述安装座设有用于容置飞行器的机臂末端的安装槽；
    保护架，与所述安装座连接，用于保护所述飞行器的螺旋桨；以及
    锁紧件，所述锁紧件可相对于所述安装座转动地安装于所述安装座，所述锁紧件包括转动安装于所述安装座的连接部和设于所述连接部的一端的锁止部；
    所述连接部可带动所述锁止部转动至与设于所述安装座内的所述机臂抵接，以将所述机臂锁紧在所述安装座内。
  2. 根据权利要求1所述的螺旋桨保护罩，其特征在于，所述螺旋桨保护罩还包括安装于所述锁止部的抱紧件，所述抱紧件被设置为当所述锁止部与所述机臂抵接时位于所述机臂与所述锁止部之间。
  3. 根据权利要求2所述的螺旋桨保护罩，其特征在于，所述锁止部设有凹槽，所述抱紧件设有与所述凹槽卡接的凸起部，所述抱紧件通过所述凸起部和所述凹槽的配合安装于所述锁止部上。
  4. 根据权利要求2所述的螺旋桨保护罩，其特征在于，所述抱紧件与所述锁止部粘接。
  5. 根据权利要求2所述的螺旋桨保护罩，其特征在于，所述抱紧件的材料为软质弹性材料。
  6. 根据权利要求2所述的螺旋桨保护罩，其特征在于，所述抱紧件的材料包括硅胶或者橡胶。
  7. 根据权利要求1-6中任一项所述的螺旋桨保护罩，其特征在于，所述锁止部的形状与所述机臂的侧面形状相适配，所述锁止部用于与所述侧面抵接。
  8. 根据权利要求7所述的螺旋桨保护罩，其特征在于，所述锁止部呈扇环状或圆弧状。
  9. 根据权利要求1所述的螺旋桨保护罩，其特征在于，所述锁止部的宽度大于所述连接部的宽度。
  10. 根据权利要求1所述的螺旋桨保护罩，其特征在于，所述安装座包括底壁和自所述底壁弯折延伸的侧壁，所述安装槽由所述底壁和所述侧壁形成，所述侧壁向远离所述安装槽的方向延伸有铰接座，所述锁紧件铰接于所述铰接座。
  11. 根据权利要求10所述的螺旋桨保护罩，其特征在于，所述侧壁呈U形。
  12. 根据权利要求10所述的螺旋桨保护罩，其特征在于，所述铰接座包括自所述侧壁的一端的上部向远离所述安装槽的方向延伸的第一铰接座和自所述侧壁的一端的下部向远离所述安装槽的方向延伸的第二铰接座，所述第一铰接座与所述第二铰接座间隔设置，所述连接部铰接于所述第一铰接座和所述第二铰接座之间。
  13. 根据权利要求12所述的螺旋桨保护罩，其特征在于，所述第一铰接座设有第一铰接孔，所述第二铰接座设有第二铰接孔，所述连接部设有安装孔，所述连接部通过一置于所述安装孔内的转轴铰接于所述第一铰接座和所述第二铰接座之间，且所述转轴的两端分别与所述第一铰接孔和所述第二铰接孔配合。
  14. 根据权利要求10-13中任一项所述的螺旋桨保护罩，其特征在于，所述侧壁远离所述铰接座的一端设有向所述安装槽的内部延伸的限位部，所述限位部用于与所述机臂抵接，从而将所述机臂卡接于所述限位部和所述底壁之间。
  15. 根据权利要求10所述的螺旋桨保护罩，其特征在于，所述底壁还设有用于收容起落架的通孔。
  16. 根据权利要求1所述的螺旋桨保护罩，其特征在于，所述保护架包括周向支架和径向支架，所述径向支架的两端分别与所述周向支架和所述安装座连接。
  17. 一种飞行器，包括机身、与所述机身相连的机臂和设于所述机臂的动力组件，其特征在于，所述飞行器还包括如权利要求1至16中任一项所述的螺旋桨保护罩，所述螺旋桨保护罩安装于所述机臂。
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