WO2018107434A1 - Couvercle de protection d'hélice et véhicule aérien sans pilote - Google Patents

Couvercle de protection d'hélice et véhicule aérien sans pilote Download PDF

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Publication number
WO2018107434A1
WO2018107434A1 PCT/CN2016/110100 CN2016110100W WO2018107434A1 WO 2018107434 A1 WO2018107434 A1 WO 2018107434A1 CN 2016110100 W CN2016110100 W CN 2016110100W WO 2018107434 A1 WO2018107434 A1 WO 2018107434A1
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WO
WIPO (PCT)
Prior art keywords
propeller
protection cover
mesh
annular body
cover according
Prior art date
Application number
PCT/CN2016/110100
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English (en)
Chinese (zh)
Inventor
黄宏升
陶冶
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201680003585.XA priority Critical patent/CN107108025A/zh
Priority to PCT/CN2016/110100 priority patent/WO2018107434A1/fr
Publication of WO2018107434A1 publication Critical patent/WO2018107434A1/fr

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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
    • B64U30/26—Ducted or shrouded rotors
    • 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
    • B64U10/16—Flying platforms with five or more distinct rotor axes, e.g. octocopters

Definitions

  • the embodiments of the present application relate to the field of aircrafts, and in particular, to a propeller protection cover and a drone.
  • Unmanned Aerial Vehicle is a non-manned aircraft based on radio remote control or controlled by its own program. Due to its low cost, high efficiency, high flexibility, high adaptability and safety and stability, Has received extensive attention and research fever.
  • the drone can be divided into fixed type, rotor, wing, flapping wing, etc.
  • the rotor drone has a compact structure, small volume, low noise, small heat radiation and super maneuvering.
  • the advantages that ordinary drones can't match have developed rapidly in recent years, and have gradually developed from the application in the military field to the wide application in the civilian field, such as the civilian industry in the movie industry, agriculture, and industry.
  • the frequency of drones is getting higher and higher, and the crowds controlling drones are no longer limited to professional players, but the market management in related fields is not perfect, public safety The awareness is also weak. In this case, the safety of drones is particularly important.
  • the propeller speed is high and the tip speed is fast. If the propeller is exposed to the object during the flight, the rotor tip is highly destructive, which will cause the rotor drone to be at high altitude. Falling or high-speed impacts cause greater damage to the aircraft itself and personal safety.
  • the existing rotary wing drones generally have corresponding protection devices to protect the propellers, such as the use of paddles to surround the propellers, but relatively speaking, on the one hand, if the paddles are not sufficiently enclosed, However, when the rotorcraft may hit the human body, it still cannot protect the personal safety. On the other hand, if the design of the paddle is relatively strong and closed, the material of the paddle may be used in a large amount and the weight is large, so that the rotor is unmanned. The load of the machine is also large, which results in the shortening of the life of the rotor drone.
  • the paddles are basically designed in the form of a protective frame, but the protection frame can only protect the propeller. It will not be damaged when it is hit, and it is difficult to protect the human body, thus reducing the adaptability and popularity of the paddle.
  • the embodiment of the invention provides a propeller protection cover, which can enhance the tightness of the propeller while reducing the load of the unmanned aerial vehicle, thereby preventing the propeller from being injured by the failure or operation error of the UAV, and capable of The protection propeller is not damaged in the event of a collision.
  • the first aspect of the present invention provides a propeller protection cover, the protective cover including an annular body and a mounting support;
  • the upper end surface of the annular body is provided with a top mesh, and the mounting support is connected to the lower end surface of the annular body;
  • the mounting bracket is used to support a propeller mounted on the arm, and the annular body, the top mesh, and the mounting bracket together define a space for receiving the propeller.
  • a second aspect of the present invention provides a drone that includes a body, an arm coupled to the body, and a propeller coupled to the arm;
  • the position of the propeller having the propeller is provided with the propeller protection cover according to the first aspect of the invention, and the propeller is accommodated in the propeller protection cover.
  • a propeller protection cover may include an annular body and a mounting support.
  • the upper and lower end faces of the annular body may be respectively provided with a top mesh and a mounting support.
  • the mounting support may be For supporting the propeller mounted on the arm, so that the propeller can be accommodated in the space enclosed by the annular body, the top mesh and the mounting support, then through the above-mentioned connecting structure, the propeller can be A certain degree of isolation from the outside world, the protective design of the top layer further enhances the sealing of the protective cover, improves the tightness of the propeller, and enables the drone to effectively protect the human body when it is in contact with the human body.
  • the protection propeller is not damaged in the event of a collision.
  • the structural characteristics of the top mesh can have a certain degree of weight reduction on the protective cover, thereby reducing the load on the drone.
  • Figure 1 is a schematic view of an eight-rotor aircraft
  • FIG. 2 is a schematic view showing the components of a propeller protection cover according to an embodiment of the present invention
  • FIG. 3 is a first schematic structural view of a top mesh of a propeller protection cover according to an embodiment of the present invention
  • Figure 4 is a schematic view showing the direction of the first stretcher of the top layer net in the embodiment shown in Figure 3;
  • FIG. 5 is a second schematic structural view of a top mesh of a propeller protection cover according to an embodiment of the present invention.
  • Figure 6 is a schematic view showing the course of the first stretcher of the top layer net in the embodiment shown in Figure 5;
  • FIG. 7 is a third schematic structural view of a top mesh of a propeller protection cover according to an embodiment of the present invention.
  • Figure 8 is a schematic view showing the direction of the first stretcher of the top layer net in the embodiment shown in Figure 7;
  • FIG. 9 is a fourth schematic structural view of a top mesh of a propeller protection cover according to an embodiment of the present invention.
  • Figure 10 is a schematic view showing the force of the top mesh of the propeller protection cover in the embodiment of the present invention.
  • FIG. 11 is a schematic structural view of an annular body of a propeller protection cover according to an embodiment of the present invention.
  • FIG. 12 is a front elevational view showing a propeller protection cover according to an embodiment of the present invention.
  • FIG. 13 is a first schematic structural view of a first mounting portion of an annular body of a propeller protection cover according to an embodiment of the present invention
  • FIG. 14 is a second schematic structural view of a first mounting portion of an annular body of a propeller protection cover according to an embodiment of the present invention.
  • Figure 15 is a schematic view showing the assembly of a propeller protection cover according to an embodiment of the present invention.
  • FIG. 16 is a first schematic structural view of a bottom mesh of a propeller protection cover according to an embodiment of the present invention.
  • 17 is a second schematic structural view of a bottom mesh of a propeller protection cover according to an embodiment of the present invention.
  • the embodiment of the invention provides a propeller protection cover, which can enhance the tightness of the propeller while reducing the load of the unmanned aerial vehicle, thereby preventing the propeller from being injured by the failure or operation error of the UAV, and capable of The protection propeller is not damaged in the event of a collision.
  • the drone may be an unmanned aerial vehicle, such as a rotorcraft, a fixed-wing aircraft, or an aircraft in which a fixed wing and a rotor are mixed.
  • the rotorcraft may include, but is not limited to, a single rotor, a double rotor, a three-rotor, a quadrotor, a six-rotor, and the like.
  • the eight-rotor aircraft 1 is taken as an example. As shown in FIG. 1, the eight-rotor aircraft 1 It has eight arm structures, and each arm structure is provided with a propeller.
  • the propellers on each arm will operate at high speed to drive the drone's body to complete the mission.
  • the eight-rotor aircraft 1 fails, it is possible to fall from a high altitude, and during the fall, due to the influence of the gravitational acceleration and the tip of the propeller exposed, the eight-rotor aircraft 1 will cause greater destructive force, then When the eight-rotor aircraft 1 is in contact with the human body, it may threaten the safety of the human body. If it collides with a heavy object, the propeller may be damaged.
  • a protection frame or a paddle can be provided at the propeller of the eight-rotor aircraft 1.
  • the sealing of the protection frame is not enough, it is difficult to protect the human body, and the safety performance needs to be strengthened.
  • the heavy paddle blade increases the load of the drone, which is not conducive to the improvement of endurance. .
  • a protective cover may be disposed at the propeller of the octagonal aircraft 1 , and the protective cover may use a ring body to initially shield the propeller from the outside, and the top and bottom mesh of the upper and lower end faces of the annular body and
  • the mounting bracket can further close the propeller to enhance the tightness of the propeller, but at the same time, due to the mesh structure of the top mesh, it is beneficial to reduce the weight of the protective cover, thereby While increasing the protection of the protective cover to the human body and the propeller, the load of the eight-rotor aircraft 1 can be alleviated.
  • an embodiment of the propeller protection cover in the embodiment of the present invention includes:
  • the protective cover may include an annular body 10 and a mounting support 30;
  • the upper end surface of the annular body 10 may be provided with a top mesh 20, and the mounting support 30 may be connected to the lower end surface of the annular body 10;
  • the mounting bracket 30 can be used to support a propeller 40 mounted to the arm, and the annular body 10, the top mesh 20, and the mounting bracket 30 can collectively define a space for receiving the propeller 40 therein.
  • the annular body 10 serves as a carrier for the propeller cover, and can form a relatively tight space with the top and bottom mesh 20 of the upper and lower end faces and the mounting support 30, and 30 can be used to support the propeller 40 on the arm, then as shown in Fig. 2, the propeller 40 can be located in the confined space formed by the annular body 10, the top mesh 20 and the mounting support 30, so that the propeller 40 can be obtained from the outside world.
  • the degree of isolation enhances the tight enclosure of the propeller 40 in an all-round way, so that during the operation of the propeller 40, when a possible collision occurs, the propeller 40 and the human body can be protected, or an abnormal shot can occur.
  • the propeller 40 does not fly out of the propeller cover, and the probability of interference of the undesired factors such as branches and leaves on the propeller 40 can be reduced.
  • the grid design structure of the top mesh 20 not only plays a role of confinement, but also helps to reduce the overall weight of the propeller cover, thereby reducing the load of the drone, and thereby improving the endurance of the drone.
  • FIG. 3 to FIG. 9 another embodiment of the propeller protection cover in the embodiment of the present invention further includes:
  • the top mesh 20 may be a mesh structure formed by the first stretcher threading the annular body 10 according to a predetermined routing method.
  • the first stretcher wire with a lighter and softer shape may be used to perform the dressing on the ring main body 10 according to a preset routing method.
  • the radial rigidity of the annular body 10 can be strengthened by the tension of the first stretcher in the wearing direction, so that the uniformity of the force of the annular body 10 during use can also be improved, and the annular body 10 is advantageously at a high altitude. Maintain the original condition under the influence of airflow or external force.
  • annular body 10 and its corresponding upper and lower end faces in this embodiment may be a circle.
  • the shape may also be a square shape, and may also be other shapes that can be utilized, and is not limited herein.
  • the propeller protection cover in this embodiment may be a propeller equipped with a propeller protection cover, or two or more propellers equipped with a propeller protection cover, which may be according to the drone.
  • the number of rotors and the actual needs of the design, specifically here is not limited.
  • the number of the first stretchers may be one, so that in the process of preparing the top mesh 10, You can follow the principle of a stretcher thread passing through the entire net.
  • the routing method in order to avoid excessive chaotic routing, the chaos of the routing is caused.
  • the routing method is used to thread the first stretcher:
  • the first stretcher can be bent back and forth on the annular body 10 to form a plurality of meshes, and the mesh can include a rectangular mesh.
  • the first stretcher may have a starting point of the point A in the circumference, and may pass through the circumference at the starting point of the threading.
  • the point B of the symmetry point is then bent through the point C on the circumference, and then parallel through the point D on the circumference from the point C, thereby performing parallel folding back and forth according to the arrow direction in the figure to complete the top layer net 20 Threading design.
  • the first stretcher can form four strikes, and can strengthen the corresponding vertical direction stiffness of the annular body on the four strikes, and the edge region surrounded by the circumference and the first stretcher, first
  • the mesh formed by the stretch lines may be a rectangular mesh.
  • the first stretcher can be formed on the annular body 10 at a predetermined angle to form a plurality of meshes, and the mesh can include a grid of parallelograms and non-parallel polygons.
  • the first stretcher may take the A1 point in the circumference as the starting point of the threading, and may pass through the circumference at the starting point of the threading.
  • Symmetric point B1 point then pass through the C1 point in the circumference from the point B1 at a predetermined angle, and then pass through the point D1 on the circumference from the point C1, thereby performing the predetermined angle according to the arrow direction in the figure to complete the top layer.
  • the first stretcher can form five strikes, and can strengthen the corresponding vertical direction stiffness of the annular body on the five strikes, and the edge region surrounded by the circumference and the first stretcher, first
  • the mesh formed by the stretch lines may include a grid of parallelograms and non-parallel polygons, such as a pentagon. It can be understood that if the predetermined angles are different, the mesh structure formed by the top mesh 10 will be inconsistent. For example, as shown in FIG. 7, the same is also performed at a predetermined angle according to the arrow traces in the figure, that is, according to A2. B2, C2, D2 This advancing arrow direction can form an enhancement of the corresponding vertical direction stiffness of the annular body in six directions as shown in Fig. 8, and the mesh structures shown in Figs. 5 and 7, respectively, are inconsistent.
  • the structural design of the top layer network 20 can be selected according to actual needs, and the tightness of the top layer network 20 can also be adjusted by adjusting the grid size. It can be designed according to the size of the annular body 10 and the propeller 40.
  • the corresponding first stretcher is eight strikes, and may also be seven strikes, nine strikes or more, as long as it can form a top layer that has a confining effect and does not affect the use effect.
  • the network 20 can be, and is not limited herein.
  • the top mesh 20 in this embodiment is a mesh structure formed by the intermediate mesh 201 and the surrounding mesh 202, wherein the intermediate mesh 201 located in the central region of the top mesh 20 can serve as an intermediate vacancy structure, and
  • the intermediate vacancy structure is used to mount the propeller 40, the intermediate grid 201 may be sized larger than the surrounding grid 202, and the surrounding grid 202 may be used to increase the tightness of the top grid 20.
  • the intermediate vacancy structure may not be added, that is, the intermediate mesh 201 and the surrounding mesh 202 are not differentiated in size, and the top mesh is
  • the installation of the propeller 40 can be achieved by any of the meshes of 20, but the larger mesh size is not conducive to the design of the tightness, and the tightness can be improved while a part of the space can be reserved in the top mesh 20 for installation.
  • the propeller 40 that is, the intermediate grid 201 as an intermediate vacancy structure, the remainder of the top mesh 20, i.e., the surrounding grid 202, can control the grid size according to the actual tightness requirements.
  • the intermediate vacancy structure may be a geometric mesh, and may be designed according to the first stretcher when it is placed on the annular body 10, for example, as shown in FIG. 4, FIG. 6, and FIG. 8, the intermediate vacancy structure.
  • the corresponding quadrilateral, regular pentagon and regular hexagon may correspond to the number of strikes of the first stretcher.
  • the shape of the intermediate vacancy structure in this embodiment may be a non-normal polygon in addition to the regular polygon described above, and is not limited herein.
  • an octagonal grid may be used as the intermediate vacancy structure.
  • the influence of the deformation stiffness is mainly considered, and the deformation stiffness can be determined by the top mesh 20 In the mesh reinforcement, for example, as shown in Fig.
  • the line of tension perpendicular to the direction of the force action line pulls the annular body 10 and can act perpendicular to the force
  • the linear direction of the wire has a good lateral stiffness, that is, the direction indicated by the arrow in the top mesh 20 to form a certain tension, so that the annular body 10 can remain as it is under the action of the external force F, without Deformation occurred.
  • the material of the first stretch line in this embodiment may be composite nylon fiber or carbon fiber or glass fiber. It should be noted that, in addition to the three materials described in the first stretcher, other high-strength, high-resistance, soft stretcher wires can be used in practical applications, which is not limited herein.
  • an intermediate vacancy structure having a geometric mesh shape may be provided in the top mesh 20 according to actual confinement requirements and the need to install the propeller 40, and the intermediate vacancy structure may be
  • the first stretcher is threaded through the annular body 10 according to a preset wire-traveling method, which has a large variability and can adapt to various needs of the propeller cover.
  • a light and soft wire material can be selected to achieve further weight reduction design of the propeller cover.
  • another embodiment of the propeller protection cover in this embodiment may include:
  • the annular surface of the annular body 10 may be provided with a negative through hole 101.
  • the annular body 10 can be hollowed out, that is, the negative through hole 101 is disposed on the annular surface, and the negative through hole 101 can not only provide a direction for the high-speed airflow during the use of the propeller protection cover, It can alleviate the vibration caused by the high-speed airflow to the propeller cover and improve the stability of the drone. It can further reduce the load of the drone due to the addition of the propeller cover.
  • the shape of the negative-passing through hole 101 may include one or more of a square shape, a circular shape, and an elliptical shape.
  • the negative-reduction through-hole 101 can be designed as a square shape, and the negative-reduction through-hole 101 shown in FIG. 10 is only described by taking an elliptical shape as an example. Further, it is also possible to reduce the gap between the negative-passing holes 101 as much as possible to increase the proportion of the negative-passing holes 101 on the annular surface of the annular body 10, and further reduce the load caused by the annular body 10.
  • the shape of the subtraction through hole 101 in this embodiment may be other shapes, such as a triangle, a pentagon or other polygons, in particular, here. Not limited. Further, in order to reduce the stress generated on the annular body 10 at the sharp corner of the negative-reduction through-hole 101 when the annular body 10 is stressed, it is preferable that the negative-reduction through-hole 101 has the above-described shape having a chamfered shape.
  • the annular surface of the annular body 10 may further be provided with a plurality of first mounting portions 102, which may be used to mount the top mesh 20, that is, the first stretcher may be in the first mounting portion. 102 is worn to form the top mesh 20, specifically the preset routing method as shown in FIGS. 3, 5, 7, and 9.
  • the first mounting portion 102 may be a hole-shaped structure, such as a circular hole, or a through-groove structure formed by recessing from the upper end surface of the annular body 10, such as an L-shaped hook groove. If it is a circular hole, as shown in FIG. 13, the first stretcher can be pierced by passing through two adjacent circular holes. If it is an L-shaped hook groove, as shown in FIG.
  • the annular body 10 is as shown in FIG.
  • the first mounting portion 102 on the torus surface can be designed based on two L-shaped hook grooves, that is, a positive L-shaped hook groove and an inverted L-shaped hook groove.
  • the first stretch line can pass through the two opposite arrangements.
  • the L-shaped hook groove is worn.
  • the first mounting portion 102 in this embodiment may be an L-shaped hook groove.
  • the first mounting portion 102 in the embodiment may adopt other structures in the actual application, as long as the first stretching wire can be formed through the first mounting portion 102 to form a tighter structure.
  • the top layer network 20 can be used, and is not limited herein.
  • the material of the annular body 10 may be a carbon fiber material, so that the weight of the propeller protection cover can be reduced from the weight source of the annular body 10 on the basis of the negative through hole 101. It should be noted that, in addition to the carbon fiber material, the material of the annular body 10 in this embodiment may be other materials in practical applications, as long as it has high performances such as specific modulus and specific strength, etc. Make a limit.
  • the propeller protection cover in the embodiment can greatly reduce the weight of the propeller protection cover by selecting the high-quality material of the annular main body 10 and designing the negative-reduction through-hole 101 on the annular surface of the annular main body 10, so as to greatly reduce the weight of the propeller protection cover.
  • the improvement of man-machine endurance can be provided with the first mounting portion 102 in cooperation with the top mesh 20, so that the connection between the top mesh 20 and the annular body 10 can be made closer, and the overall tightness of the propeller cover is enhanced.
  • another embodiment of the propeller protection cover in this embodiment may include:
  • the mounting bracket 30 can include a cavity structure 301 and two or more support rods 302 that can extend outwardly from the cavity structure 301.
  • the mounting bracket 30 may be provided with a cavity structure 301, wherein the propeller 40 may be coupled to the motor 50 that drives its movement, and the motor 50 may be received in the cavity structure 301, then when the propeller guard should be When the propeller 40 is spatially isolated from the center region, since the cavity structure 301 of the mounting bracket 30 accommodates the motor 50 connected to the propeller 40, the axial position of the cavity structure 301 is the center position of the propeller guard, and thus the practical application
  • the mounting bracket 30 may be provided with two or more support rods 302 to support the annular body 10, preferably,
  • the support rod 302 and the cavity structure 301 may be of a unitary structure to enhance the supporting action of the support rod 302.
  • the number of rods 302 can be five, so that the weight of the annular body 10 and the top mesh 20 can be dispersed in five directions.
  • the annular surface of the annular body 10 may be provided with a connecting groove 103.
  • the number of the connecting grooves 103 may be supported by the mounting bracket 30.
  • the number of the rods 302 is the same, and the end of the support rod 302 can be inserted into the connecting groove 103 to enable preliminary positioning of the support rod 302.
  • the present embodiment can be utilized at the insertion of the support rod 302 and the connecting groove 103 in view of production cost and process difficulty.
  • Such as waterproof glue for gluing the type of waterproof rubber is not limited, but should be highly waterproof and highly adhesive to prevent adverse effects of rain or other conditions, and at the same time ensure stable installation of the mounting support 30 and the annular body 10. Sex.
  • the end of the support rod 302 extending outward from the cavity structure 301 may be designed as a claw-shaped structure.
  • a claw-shaped structure in addition to the above-described claw-shaped structure, in the practical application, other structures, such as a U-shaped structure, may be adopted, so that the annular body 10 can be locked in the U-shaped structure to be fixed.
  • the specific structure is not limited herein.
  • the number of the connecting slots 103 in this embodiment may also be different from the number of the supporting rods 302 on the mounting bracket 30.
  • the number of the supporting rods 302 is five
  • the number of the connecting slots 103 may be five.
  • connection manner of the annular body 10 and the mounting support 30 is not limited to the above described adhesive. In practical applications, other methods may be used, such as using in-mold molding, as long as the annular body 10 is
  • the mounting brackets 30 have a relatively stable connection, which is not limited herein.
  • the lower end of the cavity structure 301 in the mounting support 30 may be provided with a buckle 304, which can quickly mount the support 30
  • the grounding is fastened to the arm of the unmanned aerial vehicle corresponding to the propeller 40, and the mounting bracket 30 can also be quickly disassembled on the arm, which is beneficial to reduce the time cost.
  • the material of the mounting bracket 30 can be plastic material or nylon plus glass fiber or nylon plus carbon fiber, and the strength of the support rod 302 can be improved, and the weight reduction design of the propeller protection cover can be achieved.
  • the material of the mounting bracket 30 in this embodiment may be other materials, such as molding with a carbon fiber material to obtain the mounting bracket 30, which is not used here. limited.
  • the installation support 30 can enrich the installation manner of the propeller 40 by designing the cavity structure 301, and the support of the annular body 10 can be realized by designing the support rod 302.
  • the tightness and weight adjustment of the propeller cover can be further achieved.
  • the propeller 40 can be protected by the following installation methods: 1.
  • the motor 50 is mounted on the arm of the drone; 2.
  • the mounting bracket 30 in the propeller guard is fastened.
  • the propeller 40 passes through the intermediate vacancy structure of the top mesh 20 to the propeller guard
  • the installation is carried out in a confined space in which the propeller 40 is coupled to the motor 50 such that the propeller guard can isolate the propeller 40 from the outside.
  • the annular body 10, the top mesh 20 and the mounting support 30 can control the propeller by controlling the corresponding object, that is, the shape and density of the negative through hole 101, the mesh size, and the number of the support bars 302.
  • the weight of the cover and the degree of tightness are adjusted, and can be set according to actual needs.
  • the propeller protection cover may be further referred to, as shown in FIG. 2, FIG. 11, FIG. 16, and FIG.
  • the propeller cover may further include a bottom mesh 60, and the bottom mesh 60 may be disposed on the lower end surface of the annular body 10 and connected to the mounting support 30.
  • the bottom mesh 60 may be disposed on the lower end surface to further enhance the tightness of the propeller protection cover, and the mounting support 30 may be effectively matched to reduce the support rod 302.
  • the tension of the top mesh 20 against the annular body 10 can be balanced by the underlying web 60.
  • the annular surface of the annular body 10 may be provided with a plurality of second mounting portions 104, and the cavity structure 301 in the mounting support 30 may be provided with a plurality of third mounting portions 303. Then, the second stretcher is disposed between the second mounting portion 104 and the third mounting portion 303, and the bottom mesh 60 centered on the cavity structure 301 can be formed to achieve the purpose of more restraining the propeller 40.
  • connecting groove 103 and the second mounting portion 104 of the annular body 10 in this embodiment may have the same structure. In practical applications, the connecting groove 103 may be respectively performed on the ring surface of the annular body 10.
  • the design of the second mounting portion 104 is not limited herein.
  • the underlying mesh 60 may not adopt a mesh structure such as the top mesh 20, and the mesh in the underlying mesh 60 may be designed to be sparse than the mesh in the top mesh 20, and
  • the radiant mesh can be used in conjunction with the shape of the support rod 302, and the specific routing path of the second stretcher can be as shown in FIG.
  • the number of the second stretch wires may also be one, thereby preparing the underlying mesh 60. You can follow the principle of a stretcher thread passing through the entire net.
  • the second mounting portion 104 in this embodiment may be a circular hole, a T-shaped hook groove or an L-shaped hook groove, and the third mounting portion 303 may also be a circular hole, and in order to facilitate the insertion of the second stretching wire and The processing time is saved.
  • the second mounting portion 104 may be a T-shaped hook groove. It can be seen that the difference in shape of the first mounting portion 102 and the second mounting portion 104 can depend on the structural features of the top mesh 20 and the underlying web 60, respectively.
  • the number of radiations of the bottom mesh 60 is not limited to 18 as shown in FIG. 16. In practical applications, the size of the propeller cover and the required sealing requirements may be appropriately increased or decreased. As shown in FIG. 17, the number of radiations of the underlying network 60 may be 23, which is not limited herein.
  • the second mounting portion 104 and the third mounting portion 303 may have other structures in addition to the above-described configuration, as long as the second stretching wire can be passed through the second mounting portion.
  • the lower mounting portion 303 of the first mounting portion 303 and the third mounting portion 303 may be formed, and is not limited herein.
  • the influence of the displacement stiffness is mainly considered.
  • the displacement stiffness can be reinforced by the radial wire mesh in the underlying web 60.
  • each of the arrow radiation lines on the circumference of the underlying web 60 has a good displacement stiffness to form a certain tension and can
  • the tension generated by the top mesh 20 that balances the upper end face of the annular body 10 is more advantageous in that the annular body 10 can remain as it is.
  • the deformation stiffness of the top mesh 20 and the displacement stiffness of the bottom mesh 60 can maintain the relative space of the propeller 40 and the propeller cover under a certain degree of lateral impact, so that the propeller 40 is not caught by the propeller 40 and the propeller cover. damage.
  • the tension of the top mesh 20 and the underlying web 60 can be designed according to the rigidity and strength of the annular body 10. Generally, the higher the material specific strength of the annular body 10, the more fatigue resistance and creep resistance.
  • the top mesh 20 and the bottom mesh 60 can be designed with higher wire tension to better enhance the deformation stiffness and displacement stiffness.
  • the first stretcher for threading the top mesh 20 and the second stretcher for laying the underlying web 60 may be the same stretcher, but due to the top mesh 20 and the bottom mesh 60
  • the tension of the stretcher may vary from one design to another.
  • the first stretcher and the second stretcher may not be the same stretcher.
  • the material of the second stretcher may also be a composite nylon fiber or a carbon fiber wire or a glass fiber wire to further reduce the weight of the propeller cover, but at the same time, the bottom mesh may not be affected. 60 use effect. It should be noted that, in addition to the three materials described in the second stretcher, other high-strength soft stretch wires can be used in practical applications, which is not limited herein.
  • the negative through hole 101 of the annular body 10 may be provided in two or more sizes, and the rigidity and strength of the annular body 10 are weakened in order to avoid being too close to the first mounting portion 102 and the second mounting portion 104.
  • the differently sized negative through holes 101 may be designed to be staggered according to the positions of the first mounting portion 102 and/or the second mounting portion 104. For example, as shown in FIG.
  • the annular surface of the annular body 10 may be provided with one or two small-sized elliptical negative-reducing through-holes 101, and the two-dimensional elliptical negative-reducing through-holes 101 may be staggered, that is, A small elliptical negative through hole 101 may be provided at a position having the first mounting portion 102 and the second mounting portion 104, and the large elliptical negative reducing through hole 101 may be staggered according to the small elliptical negative reducing through hole 101. .
  • the negative-passing via 101 it is not limited to the staggered arrangement of the different sizes of the negative-passing vias 101. In practical applications, it may also be arranged up and down, or other arrangements that are advantageous for the separation of the high-speed airflow and the reduction of the negative. Design, specifically not limited here.
  • the underlying mesh 60 to the lower end surface of the annular body 10
  • the body is reinforced, and the mounting bracket 30 and the annular body 10 can be tightened, the connection between the mounting bracket 30 and the annular body 10 can be stabilized, and the tension of the top mesh 20 can be balanced to facilitate maintaining the original shape of the annular body 10.
  • the embodiment of the present invention further provides a drone, which can include a body, a arm connected to the body, and a propeller 40 connected to the arm, wherein the position of the propeller 40 on the arm can be set With the propeller guard mentioned in the above embodiment, the propeller 40 can be accommodated in the propeller guard.
  • the unmanned aerial vehicle in this embodiment may adopt various suitable structures that are currently known, wherein the arm of the propeller 40 is disposed on the arm of the drone, and the motor 50 may be disposed.
  • the connection mode of the arm is prior art, and details are not described herein again.
  • the propeller protection cover can avoid any contact between the propeller 40 and the human body, which is beneficial to ensure personal safety.
  • the propeller protection cover can withstand and pass the elasticity. The deformation absorbs a certain amount of energy, reduces the impact destructiveness, further improves the safety performance of the propeller 40, and is also beneficial for forming protection of the propeller 40.
  • the arm of the drone can also be provided with a buckle, which can be engaged with the buckle 304 in the mounting bracket 30, so that the mounting bracket 30 can be fastened to the machine where the propeller 40 is located.
  • a buckle which can be engaged with the buckle 304 in the mounting bracket 30, so that the mounting bracket 30 can be fastened to the machine where the propeller 40 is located.
  • the propeller 40 in this embodiment may include, but is not limited to, a folded quick release paddle.
  • each of the propellers 40 of the drone is enclosed in the propeller protection cover, and the tightness is strong, so that the propeller 40 is difficult to directly touch the human body and cause damage to the human body.
  • the hazard also makes the propeller 40 difficult to directly collide with other collision objects, causing damage, and the human body and the propeller 40 are protected, which is beneficial to the safety performance of the drone.
  • the propeller cover has a certain weight reduction design, which reduces the load of the drone and is beneficial to the endurance of the endurance.

Abstract

L'invention concerne un couvercle de protection d'hélice, comprenant un corps principal annulaire (10) et une base de support d'installation (30), une face d'extrémité supérieure du corps principal annulaire (10) étant pourvue d'un filet de couche supérieure (20) et la base de support d'installation (30) étant reliée à une face d'extrémité inférieure du corps principal annulaire (10) ; la base de support d'installation (30) est utilisée pour supporter une hélice (40) qui est installée sur un bras de moteur ; le corps principal annulaire (10), le filet de couche supérieure (20) et la base de support d'installation (30) forment ensemble un espace utilisé pour maintenir l'hélice (40) à l'intérieur. Le couvercle de protection d'hélice peut améliorer une propriété anti-fuite de l'hélice tout en réduisant la charge d'un véhicule aérien sans pilote, ce qui permet d'empêcher l'hélice de blesser les personnes en raison d'un mauvais fonctionnement du véhicule aérien sans pilote ou d'un défaut de fonctionnement, et de protéger l'hélice d'un endommagement lors d'un impact. L'invention concerne également un véhicule aérien sans pilote équipé du couvercle de protection d'hélice.
PCT/CN2016/110100 2016-12-15 2016-12-15 Couvercle de protection d'hélice et véhicule aérien sans pilote WO2018107434A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201680003585.XA CN107108025A (zh) 2016-12-15 2016-12-15 一种螺旋桨保护罩以及无人机
PCT/CN2016/110100 WO2018107434A1 (fr) 2016-12-15 2016-12-15 Couvercle de protection d'hélice et véhicule aérien sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/110100 WO2018107434A1 (fr) 2016-12-15 2016-12-15 Couvercle de protection d'hélice et véhicule aérien sans pilote

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WO2018107434A1 true WO2018107434A1 (fr) 2018-06-21

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CN114261514A (zh) * 2021-12-27 2022-04-01 广东电网有限责任公司广州供电局 一种无人机防坠机装置

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CN112638774A (zh) * 2020-03-24 2021-04-09 深圳市大疆创新科技有限公司 螺旋桨的保护罩和无人机
CN111874244A (zh) * 2020-07-28 2020-11-03 东南大学 一种新型无人机桨叶保护罩
CN113371196B (zh) * 2021-07-15 2022-10-04 吉林建筑大学 一种安全性高的遥感测绘无人机
CN114476064B (zh) * 2022-03-22 2023-09-29 山东翔林规划设计有限公司 一种用于林业勘探的无人机

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DE102014012801A1 (de) * 2014-08-28 2016-03-03 Frank Ketteler Schutzvorrichtung für einen Propeller
WO2016112124A2 (fr) * 2015-01-08 2016-07-14 Vantage Robotics, Llc Véhicule aérien sans pilote à protection d'hélice et capacité de survie aux impacts élevée
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CN114261514A (zh) * 2021-12-27 2022-04-01 广东电网有限责任公司广州供电局 一种无人机防坠机装置

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