WO2017166275A1 - 用于无人飞行器的机架连接组件及无人飞行器 - Google Patents

用于无人飞行器的机架连接组件及无人飞行器 Download PDF

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Publication number
WO2017166275A1
WO2017166275A1 PCT/CN2016/078287 CN2016078287W WO2017166275A1 WO 2017166275 A1 WO2017166275 A1 WO 2017166275A1 CN 2016078287 W CN2016078287 W CN 2016078287W WO 2017166275 A1 WO2017166275 A1 WO 2017166275A1
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WO
WIPO (PCT)
Prior art keywords
tube
auxiliary member
support tube
open end
support
Prior art date
Application number
PCT/CN2016/078287
Other languages
English (en)
French (fr)
Inventor
梁贵彬
孙亮
肖文龙
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.)
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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 CN201680002506.3A priority Critical patent/CN107074340B/zh
Priority to PCT/CN2016/078287 priority patent/WO2017166275A1/zh
Publication of WO2017166275A1 publication Critical patent/WO2017166275A1/zh

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Classifications

    • 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
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L25/00—Constructive types of pipe joints not provided for in groups F16L13/00 - F16L23/00 ; Details of pipe joints not otherwise provided for, e.g. electrically conducting or insulating means
    • 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 present invention relates to the field of unmanned aerial vehicles, and more particularly to a rack connection assembly for an unmanned aerial vehicle and an unmanned aerial vehicle.
  • Unmanned aerial vehicles mainly include: center frame, rack connection components and mounts.
  • the rack connection assembly generally comprises: a support tube and a fastener, wherein the fastener is used to fix the support tube and the connection portion provided on the center frame together.
  • the bottom of the center frame is used to mount the load.
  • connection portion of the existing center frame is generally provided in a hollow shape so that the support tube can be sleeved in the receiving cavity formed by the connecting portion.
  • the fasteners generally use long screws, and a set of symmetrical screw through holes are formed in the connecting portion and the supporting tube. When fixing, the long screw is passed through the above symmetrical screw through hole and then fixed by a nut, thereby achieving the purpose of fixing the connecting portion and the supporting tube together.
  • the existing connection causes the wall of the support tube to be squeezed when the long screw is tightened by the nut, resulting in a gap between the tube wall and the two ends of the screw, thereby making the UAV in flight.
  • the tripod or arm is closed and unfolded, there is jitter, which affects its normal flight.
  • the present invention provides the following technical solutions:
  • a rack connection assembly for an unmanned aerial vehicle comprising: a support tube, an auxiliary member, and a fastener;
  • the support tube is configured to connect a center frame of the UAV, and the center frame is provided a connecting portion that is sleeved with the open end of the support tube;
  • the auxiliary member is disposed inside or outside the open end of the support tube to clamp the tube wall of the open end of the support tube to the auxiliary
  • the fastener is used for fixedly connecting the auxiliary member, the open end of the support tube, and the connecting portion of the center frame; wherein The fastener passes through the wall of the open end of the support tube, and both ends of the fastener abut against the connecting portions of the auxiliary member and the center frame, respectively.
  • an unmanned aerial vehicle including: a center frame and a rack connection assembly;
  • the rack connection assembly includes: a support tube, an auxiliary member, and a fastener;
  • the support tube is configured to connect the center frame,
  • the center frame is provided with a connecting portion for interlacing with the open end of the support tube;
  • the auxiliary member is disposed inside or outside the open end of the support tube to clamp the wall of the open end of the support tube Holding between the auxiliary member and the connecting portion of the center frame;
  • the fastener is used for fixedly connecting the auxiliary member, the open end of the support tube, and the connecting portion of the center frame; Wherein the fastener passes through the wall of the open end of the support tube, and both ends of the fastener abut against the connecting portion of the auxiliary member and the center frame.
  • the rack connection assembly for an unmanned aerial vehicle and the unmanned aerial vehicle provided by the invention are provided with an auxiliary member on the inner side or the outer side of the tube wall at the open end of the support tube, thereby clamping the wall of the open end of the support tube to the auxiliary member and the connection.
  • the auxiliary member and the connecting portion the two ends of the fastener will respectively abut the auxiliary member and the connecting portion, that is, the wall of the open end of the supporting tube is point-contacted. The force is changed to the surface contact type force.
  • the fastening force of the pipe wall can be dispersed, and the problem of deformation of the pipe wall caused by the point contact is avoided, so that the gap between the pipe wall and the connecting portion of the open end of the support pipe is not easy to occur, and the problem is solved.
  • the flight stability of the unmanned aerial vehicle is improved when the human aircraft flies during the flight or when the tripod or the arm is retracted and unfolded due to the unstable connection.
  • FIG. 1 is a front elevational view of the rack connection assembly of the embodiment 1-3 according to the present invention when the connection portion is in a connected state;
  • Figure 2 is a cross-sectional view taken along line A-A of Figure 1;
  • FIG. 3 is a schematic structural view of the frame connecting assembly of the embodiment 4-9 according to the present invention when the connecting portion is in a connected state;
  • Figure 4 is an exploded view of Figure 3;
  • Figure 5 is a front elevational view of Figure 3;
  • Figure 6 is a cross-sectional view taken along line B-B of Figure 5 (wherein the fastener is a screw);
  • Figure 7 is a cross-sectional view taken along line B-B of Figure 5 (wherein the fastener is a rivet);
  • FIG. 8 is a schematic structural view of an unmanned aerial vehicle provided by the present invention.
  • Unmanned aerial vehicle 10. Rack connection assembly;
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • FIG. 1 is a front view of the frame connecting assembly and the connecting portion provided in the present embodiment
  • FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1
  • FIG. 8 is a schematic structural view of the unmanned aerial vehicle.
  • the rack connection assembly in this embodiment includes a support tube 110, an auxiliary member 130, and a fastener 140.
  • the open end of the support tube 110 is used to nest with the connecting portion 120 provided on the center frame 20 of the UAV 1 .
  • the support tube 110 can be coupled to the rotor power unit 30 or the tripod power unit.
  • the rotor power unit 30 can be carried on the support tube 110 or on the connecting member connected to the support tube 110; when the support tube 110 is a tripod or a component thereof,
  • the tripod power unit is capable of driving the support tube 110 or a connector connected to the support tube 110 to rotate such that the stand extends or contracts under the force of the stand power unit.
  • the auxiliary member 130 is disposed inside or outside the open end of the support tube 110 such that the tube wall 1102 of the open end of the support tube 110 is sandwiched between the auxiliary member 130 and the connecting portion 120 of the center frame 20.
  • the fastener 140 securely connects the support tube 110, the connecting portion 120 and the auxiliary member 130 through the tube wall 1102 at the open end, and both ends of the fastener 140 abut against the auxiliary member 130 and the connecting portion 120, respectively.
  • the rack connection assembly 10 of the present application will be described below by taking the rack connection assembly 10 carrying the rotor power unit 30 as an example, and those skilled in the art can carry the rotor power according to the following.
  • the rack connection assembly 10 of the device 30 extends to the load-bearing power unit or other structure in the unmanned aerial vehicle 1, and such expansion or deformation is still within the scope of the present application.
  • the support tube 110 should be interpreted broadly, which may be a completely hollow tube, i.e., only one cavity 1101 is formed in the tube wall 1102. At the same time, it may be a tube in which the plurality of cavities 1101 are partitioned in the tube wall 1102. It may even be a tube having a majority of solids having only a small portion of the hollow to be nested with the central frame 20 connection portion 120. Those skilled in the art will appreciate that any structural modifications to the tubular intermediate cavity 1101 are intended to be included within the scope of the present application.
  • the material of the support tube 110 may be any material, such as a metal material such as steel, aluminum or alloy, and of course, a non-metal material having a certain strength.
  • the support tube 110 can be made of a carbon fiber material to provide the UAV 1 with better joint strength and lighter weight.
  • the shape of the support tube 110 may be any shape, for example, the cross section of the support tube 110 may be a circle, a square, other closed curves or a closed straight line.
  • the circular, square, etc. referred to herein is an overall cross-sectional shape including the cavity 1101 in the tube wall 1102 of the support tube 110. If the cavity 1101 is removed, only from the cross section of the tube wall 1102, Then, the cross section of the support tube 110 is a ring, a square ring or the like.
  • the support tube 110 has an elliptical cross section and an elliptical ring after the cavity 1101 is removed.
  • the wind resistance of the frame connecting assembly 10 can be reduced, and the flying efficiency of the UAV 1 can be improved.
  • a better structural strength can be obtained by making the cross-section of the tube wall 1102 of the support tube 110 into an elliptical ring.
  • the connecting portion 120 provided on the center frame 20 may be a connecting portion 120 fixedly connected to the center frame 20 or a connecting portion 120 rotatably connected to the center frame 20.
  • the fixed connection manner may be, for example, various fixed connection manners such as welding, riveting, keying, or bolting.
  • the rotatably connected manner can be, for example, hinged, pivoted, or the like, and various existing rotatably connected means.
  • the material, shape and structure of the connecting portion 120 are not specifically limited in the embodiment, and a person skilled in the art can select a suitable workpiece as the connecting portion 120 according to the type, design weight and connection strength of the unmanned aerial vehicle 1.
  • a tube having a cavity 1101 can be selected, or a solid body can be selected as the connecting portion 120.
  • the fastener 140 can be selected from screws or rivets. Of course, other fasteners having a fastening function suitable for the prior art may be selected as the fastener 140 of the present embodiment.
  • the auxiliary member 130, the support tube 110 and the connecting portion 120 are fixedly coupled together through one end of the fastener 140 through the tube wall 1102 at the open end, and by this connection, the two ends of the fastener 140 are respectively associated with the auxiliary member
  • the 130 and the connecting portion 120 abut, so that the force is not directly applied to the tube wall 1102 of the open end of the support tube 110, but is transmitted through the auxiliary member 130 and the connecting portion 120.
  • the force transmission of the surface contact can reduce the tube wall 1102. The deformation improves the flight stability of the UAV 1.
  • the auxiliary member 130 is disposed on the inner side or the outer side of the tube wall 1102 at the open end of the support tube 110, thereby clamping the tube wall 1102 at the open end of the support tube 110 at Between the auxiliary member 130 and the connecting portion 120.
  • the two ends of the fastener 140 abut against the auxiliary member 130 and the connecting portion 120, that is, the support tube 110 is open.
  • the end wall 1102 is changed from a point contact type force to a surface contact type force.
  • the fastening force received by the pipe wall 1102 can be dispersed, and the problem of deformation of the pipe wall 1102 caused by the point contact is avoided, so that the pipe wall 1102 and the connecting portion 120 at the open end of the support pipe 110 are not easily generated.
  • the gap solves the jitter phenomenon caused by the unsteady connection when the UAV 1 is in flight or when the tripod or the arm is retracted and unfolded, and the flight stability of the UAV 1 is improved.
  • the auxiliary member 130 disposed in the open end cavity 1101 of the support tube 110 or the connecting portion 120 sleeved in the open end cavity 1101 of the support tube 110 can further provide a supporting force for the open end of the support tube 110 to further ensure the support.
  • the tube wall 1102 at the open end of the tube 110 is not deformed.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the present embodiment is based on the technical solution provided in Embodiment 1, and the fastener 140 that fixes the connecting portion 120, the tube wall 1102 of the open end of the support tube 110, and the auxiliary member 130 is disposed.
  • a plurality of the fasteners 140 are uniformly distributed on the tube wall 1102 at the open end to improve the connection strength of the support tube 110 and the connecting portion 120 and the auxiliary member 130, thereby further improving the unmanned aerial vehicle 1 in flight. stability.
  • the plurality of uniformly distributed fasteners 140 may be located on the same side of the axis of the support tube 110 or on both sides of the axis of the support tube 110.
  • the plurality of fasteners 140 are symmetrically disposed on both sides of the axis of the support tube 110 to make the wall of the tube wall 1102 at the open end of the support tube 110 and the connecting portion 120 and the auxiliary member 130 more uniform, and at the same time enable the frame The ability of the connecting assembly 10 to resist axial shear forces is better.
  • both sides of the axis of the support tube 110 refer to an arbitrary section through the axis of the support tube 110, and the two portions divided by the section are the two sides of the axis of the support tube 110.
  • a total of four fastening screws are provided, and the four fastening screws are symmetrically disposed at the upper and lower portions of the axis of the support tube 110.
  • two screws are arranged on the upper part and two screws are arranged on the lower part. Both ends of each screw abut against the auxiliary member 130 and the connecting portion 120, respectively, so that the tube wall 1102 at the open end is sandwiched between the auxiliary member 130 and the connecting portion 120.
  • both sides of the axis The cross-axis is made to be a cut surface in the left-right direction, so that the upper and lower portions of the cut surface are respectively on both sides of the axis of the support tube 110.
  • the rack connecting component 10 of the embodiment can strengthen the connection strength of the rack connecting component 10 and the connecting portion 120 by providing a plurality of fasteners 140 uniformly distributed on the open end pipe wall 1102 of the supporting pipe 110, so that no one is connected.
  • the aircraft 1 is less prone to jitter during flight, improving its flight stability.
  • the force of the frame connecting assembly 10 can be more balanced, the ability to resist axial shearing force can be enhanced, and the service life of the unmanned aerial vehicle 1 can be improved.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the present embodiment is based on the technical solutions provided in Embodiment 1 and Embodiment 2, and the connecting portion 120 is sleeved in the cavity 1101 of the open end of the support tube 110, and in the support tube 110.
  • An auxiliary member 130 is disposed outside the open end wall 1102.
  • the connecting portion 120 may be any structural component that can be sleeved in the open end cavity 1101 of the support tube 110 and substantially conform to the shape of the cavity 1101.
  • a hollow or solid cylinder or other hollow or solid object of any cross-sectional shape that can be substantially in contact with the inner surface of the tube wall 1102.
  • the connecting portion 120 includes a cylinder and an elliptical cylinder.
  • the right end of the elliptical cylinder is sleeved in the cavity 1101 of the open end of the support tube 110 whose cross section is an elliptical ring; the right end of the cylinder is fixedly connected with the left end of the elliptical cylinder, and the left end of the cylinder and the center frame 20 Fixed connection or rotatable connection. More preferably, the cylinder and the elliptical cylinder are integrally formed into a single piece, thereby increasing the structural strength of the joint 120 to improve the flight performance of the UAV 1.
  • the outer wall of the elliptical cylinder is perfectly matched to the shape and size of the tube wall 1102 at the open end of the support tube 110, so that the elliptical cylinder can provide a good supporting force for the tube wall 1102 of the open end of the support tube 110, and is thus fastened.
  • the supporting force of the elliptical cylinder can better prevent the deformation of the pipe wall 1102, thereby improving the stability of the UAV 1.
  • the auxiliary member 130 may be a gasket or a cylindrical bushing.
  • the auxiliary member 130 may be an elastic spacer or a cylindrical elastic bushing, so that the elastic spacer or the elastic can be passed through The elastic deformation force of the bushing further reduces the deformation of the pipe wall 1102 to reduce the gap between the pipe wall 1102 and the connecting portion 120.
  • the size, shape and specific structure of the gasket are not specifically limited, and the skilled person can select any suitable gasket in the prior art or make a mat matching the specific type of the UAV 1 . sheet.
  • a solid connecting portion 120 is disposed.
  • One end of the connecting portion 120 is connected to the center frame 20, and one end is sleeved in the cavity 1101 of the open end of the supporting tube 110.
  • a cylindrical elastic outer bushing is provided outside the tube wall 1102 at the open end of the support tube 110.
  • a coaxial screw hole is formed in the elastic outer bushing, the pipe wall 1102 at the open end, and the connecting portion 120 that is sleeved in the open end cavity 1101.
  • the elastic outer bushing, the tube wall 1102 and the connecting portion 120 are then secured together using screws or rivets through the screw holes. Since four fasteners 140 (screws or rivets) uniformly distributed on both sides of the axis are used in FIG. 2, through holes can be directly formed in the elastic outer bushing, the pipe wall 1102 and the connecting portion 120, Reduce processing and steps to save processing time and costs.
  • a boss 1201 may be formed on the connecting portion 120 such that the tube wall 1102 at the open end of the support tube 110 abuts against the end surface of the boss 1201 to restrict the axial movement of the support tube 110.
  • the connecting portion 120 includes an integrally formed cylinder and an elliptical cylinder
  • the tube wall 1102 at the open end of the support tube 110 can be directly abutted against the right end of the cylinder, thereby avoiding the axis of the supporting tube 110. Move to improve the flight stability of the UAV 1.
  • the rack connection assembly 10 of the present embodiment can simplify the rack connection assembly 10 by arranging the connection portion 120 in the cavity 1101 of the open end of the support tube 110 and providing the auxiliary member 130 outside the tube wall 1102 at the open end of the support tube 110.
  • the structure, and when the connecting portion 120 is a solid integrated structure, can provide the UAV 1 with better structural strength, thereby making the UAV 1 have better flight stability.
  • the connecting portion 120 in the cavity 1101 at the open end of the support tube 110 can provide a supporting force to the open end wall 1102 to further reduce the deformation of the tube wall 1102 at the time of fixing, thereby improving the stability of the UAV 1 during flight.
  • the use of the elastic gasket or the elastic outer bushing can further reduce the deformation of the pipe wall 1102 at the open end of the support pipe 110, further improving the flight stability of the UAV 1.
  • the support tube 110, the auxiliary member 130, and the connecting portion are fixed by screws
  • the 120 can also realize the quick disassembly and assembly of the rack connection assembly 10, improve the environmental adaptability of the UAV 1 and the space occupied during storage, and also provide the possibility of replacing the different rotor power units 30, thereby making the multi-rotor free.
  • the human aircraft 1 can have different power rotor power units 30 to provide overall flight performance.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • FIG. 3 is a schematic structural view of the rack connecting component and the connecting portion in the connected state;
  • FIG. 4 is an exploded view of FIG. 3;
  • FIG. 5 is a front view of FIG. 3;
  • FIG. 7 is a cross-sectional view of the BB direction of FIG. 5 (wherein the fastener is a rivet).
  • a receiving cavity 1203 is formed in the connecting portion 120, and the supporting tube 110 is sleeved in the receiving space.
  • the right end of the auxiliary member 130 extends into the cavity 1101 of the open end of the support tube 110, thereby clamping the tube wall 1102 of the open end of the support tube 110 between the side wall 1202 where the connection portion 120 accommodates the cavity 1203 and the auxiliary member 130.
  • the connecting portion 120 may be any structure with a receiving cavity 1203 and being connectable with the center frame 20 and the receiving cavity 1203 can be sleeved with the open end of the supporting tube 110, for example, may be semi-closed.
  • the pipe of course, the ends of this semi-closed pipe can have different pipe diameters.
  • one end of the large diameter is a closed end for connecting with the center frame 20, thereby increasing the contact area between the connecting portion 120 and the center frame 20 to improve the connection strength between the two.
  • One end of the small diameter pipe is a socket end, and the open end of the support pipe 110 is sleeved in the receiving cavity 1203 of the socket end, so that the pipe wall 1102 of the open end of the support pipe 110 can be clamped on the side wall 1202 of the receiving cavity 1203 and Between the auxiliary members 130.
  • the frame connecting assembly 10 of the present embodiment forms a receiving cavity 1203 on the connecting portion 120, and sleeves the open end of the supporting tube 110 in the receiving cavity 1203 while also supporting the cavity at the open end of the tube 110.
  • the auxiliary member 130 is disposed in 1101 such that when the fastener 140 fixes the connecting portion 120 and the support tube 110, the tube wall 1102 of the open end of the support tube 110 can be clamped between the side wall 1202 of the receiving cavity 1203 and the auxiliary member 130. , thereby reducing the deformation of the support tube 110 and improving the unmanned flight The stability of the device 1 in the air.
  • the tube wall 1102 of the open end of the support tube 110 is not in point contact with the end of the fastener 140, but is in contact with both end faces of the fastener 140 through the auxiliary member 130 and the side wall 1202, thereby further reducing the wall 1102 at the time of fixing.
  • the deformation improves the flight stability of the UAV 1.
  • a protrusion may be formed on the auxiliary member 130, and the tube wall 1102 of the open end of the support tube 110 may be abutted against the end surface of the protrusion.
  • the shape and size of the protrusion are not specifically limited.
  • the protrusion may have an end surface extending obliquely from the upper surface of the auxiliary member 130 toward the open end of the support tube 110, so that the tube wall 1102 can be inserted.
  • the raised end face is interposed between the upper surface of the auxiliary member 130 to thereby clamp the support tube 110.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the present embodiment is based on the technical solution provided in Embodiment 4, and the auxiliary member 130 and the connecting portion 120 are formed into an integrally formed structure, thereby strengthening the connection strength between the auxiliary member 130 and the connecting portion 120. Further, the ability of the support tube 110 and the connecting portion 120 to resist axial shear force after the connection is increased, thereby making the UAV 1 more stable in the air.
  • the auxiliary member 130 may be any structure that can extend into the cavity 1101 of the open end of the support tube 110 at one end and provide support for the tube wall 1102 at the open end, and may be, for example, a solid or hollow cylindrical block. Elliptical column blocks, or other block structures or plate-like structures with curved surfaces.
  • the rack connection assembly 10 of the present embodiment improves the connection strength of the support tube 110 and the connecting portion 120 and the auxiliary member 130 by making the auxiliary member 130 and the connecting portion 120 into an integrally formed structure, so that the unmanned aerial vehicle 1 is more stable in flight. .
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the embodiment is based on the technical solution provided in Embodiment 4, the auxiliary member 130 and the connecting portion 120 are disposed as a split structure, and one end of the auxiliary member 130 is disposed at the open end of the support tube 110. In the cavity 1101, the other end of the auxiliary member 130 is disposed in the receiving cavity 1203 of the connecting portion 120.
  • the auxiliary member 130 may be any single structural part or multiple parts.
  • the combined structure is only required to satisfy the tube wall 1102 which can support the open end of the support tube 110 from the inside, and one end is located in the cavity 1101 of the open end, and the other end is located in the receiving cavity 1203 of the connecting portion 120.
  • the auxiliary member 130 may be a combined structure of a cylindrical block, an elliptical block, or two support plates having curved surfaces.
  • the diameter of the support tube 110 can be controlled very conveniently and the shape structure of the auxiliary member 130 can be adjusted to make the support tube 110,
  • the auxiliary member 130 and the connecting portion 120 receive the side wall 1202 of the cavity 1203 with a better fit to reduce the gap between the three fixed by the fastener 140, thereby improving the stability of the UAV 1 during flight.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the embodiment is based on Embodiment 4, Embodiment 5 and Embodiment 6, and the rib 1306 is formed on the auxiliary member 130 and formed on the tube wall 1102 at the open end of the support tube 110.
  • the card slot 1103 is engaged with the rib 1306 so that the rib 1306 can be snapped into the card slot 1103 during assembly, enabling rapid positioning of the assembly and preventing axial movement of the support tube 110.
  • the shape and size of the ribs 1306 can be set according to actual needs, and is not specifically limited herein.
  • the rack connection assembly 10 of the present embodiment realizes quick positioning and installation of the arm connecting assembly by preventing the ribs 1306 and the card slot 1103 on the tube wall 1102 at the open end of the auxiliary member 130 and the support tube 110.
  • the axial movement of the tube 110 ensures the flight stability of the unmanned aerial vehicle 1.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the present embodiment is formed on the side wall 1202 and the auxiliary member 130 of the connecting portion 120 receiving the cavity 1203 on the basis of the fourth embodiment, the fifth embodiment, the sixth embodiment and the seventh embodiment.
  • Interlocking structure that cooperates with each other.
  • a protrusion or a rib 1306 formed on the side wall 1202 and formed on the auxiliary member 130 to cooperate with the groove 1204 may be formed to constitute the above-mentioned snap-fit structure. It is of course also possible to form a projection formed on the side wall 1202 and form a groove 1204 on the auxiliary member 130 that cooperates with the projection.
  • the shape of the protrusion or the rib 1306 can be set according to actual needs, and is not specifically limited herein.
  • a rib 1306 is formed on the auxiliary member 130, and a positioning groove 1205 matching the rib 1306 is formed on the side wall 1202, so that the rib 1306 can be engaged in the positioning groove 1205, thereby preventing auxiliary The axial movement of the piece 130.
  • a positioning groove 1205 is formed on the side wall 1202 to cooperate with the rib 1306, and the rib 1306 is formed on the tube wall 1102.
  • the rib 1306 can be simultaneously clamped in the positioning slot 1205 and the card slot 1103, thereby achieving positioning of the gantry connection assembly 10 and preventing its axial movement.
  • the tube wall 1102 at the open end of the support tube 110 can be abutted on the above-mentioned snap-fit structure, so that the protrusion described in the above embodiment 4 can be omitted.
  • the tube wall 1102 of the support tube 110 is provided with the card slot 1103 that cooperates with the rib 1306, the support tube 110 and the rib 1306 can be clamped in the axial direction. Therefore, the above embodiment 4 can be omitted. Said protrusion.
  • the frame connecting assembly 10 of the embodiment improves the locking of the auxiliary member 130 and the connecting portion 120 by providing a mating engaging structure on the side wall 1202 of the receiving cavity 1203 and the auxiliary member 130.
  • the connection strength of the rack connection assembly 10 and the connecting portion 120 improves the flight stability of the UAV 1.
  • This embodiment provides a rack connection assembly for an unmanned aerial vehicle.
  • the embodiment is based on Embodiment 3, Embodiment 4, Embodiment 5, Embodiment 6, Embodiment 7, and Embodiment 8, and the auxiliary member 130 is specifically configured to include a support block.
  • the support block is disposed within the cavity 1101 of the open end of the support tube 110, and the support block, together with the side wall 1202 of the connection portion 120 receiving the cavity 1203, sandwiches the tube wall 1102 at the open end therebetween.
  • the head of the fastener 140 is secured to the support block through the side wall 1202 and the tube wall 1102, i.e., the ends of the fastener 140 are in contact with the side wall 1202 and the support block, respectively.
  • the support block of the present embodiment should be explained in a broad sense, for example, a sheet-like structure having a curved surface or a solid or hollow block-shaped structure, which can be specifically set by the person skilled in the art according to the parameters of the unmanned aerial vehicle 1.
  • the parameters of the unmanned aerial vehicle 1 described above may be, for example, the weight of the unmanned aerial vehicle 1, the strength of the rack connecting assembly 10, and the flying speed and lifting force, flexibility, and the like.
  • the rack connection assembly 10 of the present embodiment can reduce the structure of the assembly by specifically arranging the auxiliary member 130 as a support block, thereby reducing the weight of the UAV 1 to improve the life time and flight speed of the UAV 1 and climbing. Performance and other performance.
  • the support block may be configured to include a first support block 1301 and a second support block 1302.
  • the two support blocks are symmetrically disposed on both sides of the axis of the cavity 1101 at the open end of the support tube 110, thereby clamping the tube walls 1102 on both sides of the axis of the cavity 1101 to the side walls of the first support block 1301 and the receiving cavity 1203, respectively.
  • the right side wall 1102 is sandwiched between the right side wall 1202 and the first support block 1301, and the left side wall 1102 is clamped to the left side wall 1202.
  • the fastener 140 is disposed to include a first fastener 140 and a second fastener 140.
  • the head of the first fastener 140 is secured to the first support block 1301 through the right side wall 1202 and the right side wall 1102 to effect clamping of the right side wall 1102.
  • the head of the second fastener 140 is secured to the second support block 1302 through the left side wall 1202 and the left side tube wall 1102 to effect clamping of the left side wall 1102.
  • the fastener 140 can further include a third fastener 140 and a fourth fastener 140.
  • the third fastener 140 is spaced apart from the first fastener 140
  • the fourth fastener 140 is symmetric with the third fastener 140 such that the first fastener 140 and the second fastener 140 are The axis is parallel to the axes of the third fastener 140 and the fourth fastener 140.
  • the first support block 1301 and the second support block 1302 may be any shape of a structure capable of supporting the tube wall 1102 of the open end of the support tube 110, for example, may have a shape with the inner surface of the tube wall 1102.
  • the first branch can preferably be The shape of the support block 1301 and the second support block 1302 are set to be the same to reduce the processing difficulty of the parts and improve the processing efficiency.
  • one or more of the first fastener 140, the second fastener 140, the third fastener 140, and the fourth fastener 140 may use screws or rivets. For example, four screws may be used as shown in FIG.
  • a connecting plate may be disposed at both ends of the first support block 1301 and the second support block 1302 to connect the first support block 1301 and the second support block 1302 together.
  • the connecting plate comprises: a first connecting plate 1303 and a second connecting plate 1304. The first connecting plate 1303 and the second connecting plate 1304 are disposed at a distance.
  • the pressing force of the first supporting block 1301 and the second supporting block 1302 can be further dispersed by providing the first connecting plate 1303 and the second connecting plate 1304, thereby further reducing the pipe wall 1102 and the first supporting block 1301 and the second supporting block 1302.
  • the gap between them improves the flight stability of the UAV 1.
  • the bending directions of the first connecting plate 1303 and the second connecting plate 1304 are opposite, so that the direction of the pressing force received by the first supporting block 1301 and the second supporting block 1302 can be better adapted, so that the two are subjected to
  • the pressing force can be better dispersed to reduce the gap between the pipe wall 1102 and the first support block 1301 and the second support block 1302, thereby improving the flight stability of the UAV 1.
  • a reinforcing rib 1305 may be further disposed on the first supporting block 1301 to improve the supporting ability of the first supporting block 1301 to the pipe wall 1102.
  • the reinforcing ribs 1305 are disposed on the inner side surface of the first support block 1301, that is, the first support block 1301 and a side surface away from the inner surface of the tube wall 1102, that is, the right side surface shown in FIG.
  • the head of the first fastener 140 is fixed to the reinforcing rib 1305 through the connecting portion 120 accommodating the side wall 1202 of the cavity 1203 and the pipe wall 1102 and the first supporting block 1301. .
  • the reinforcing ribs 1305 may also be disposed on the inner side surface of the second supporting block 1302.
  • the inner side surface of the first support block 1301 and the inner side surface of the second support block 1302 may be provided with reinforcement.
  • the rib 1305 is provided with two first connecting plates 1303 and a second connecting plate 1304 respectively connected to the reinforcing ribs 1305, thereby forming an annular structure connected to the inner side surfaces of the first supporting block 1301 and the second supporting block 1302.
  • first support block 1301, the second support block 1302, the first connecting plate 1303, the second connecting plate 1304, and the reinforcing rib 1305 may be integrally manufactured to form an integral structure to strengthen the structure of the auxiliary member 130. strength.
  • This embodiment provides an unmanned aerial vehicle.
  • the unmanned aerial vehicle 1 provided in this embodiment includes a center frame 20, a frame connecting assembly 10, and a rotor power unit 30.
  • the center frame 20 is provided with a positioning module at the top of the center frame 20, and a processing module is disposed inside the center frame 20, and the mounting object is mounted under the center frame 20.
  • the center frame 20 carries the rotor power unit 30 through the frame connection assembly 10.
  • the rotor power unit 30 is carried by the gantry connection assembly 10 such that the unmanned aerial vehicle 1 can be provided with lift and steering force by the rotation of the rotor in the rotor power unit 30 while the UAV 1 is flying.
  • the adjustment of various flight attitudes such as flying, hovering, and steering of the unmanned aerial vehicle 1 is realized.
  • the electronic governor in the rotor power unit 30 controls the output of the motor through the processing chip of the center frame 20 to control the rotational speed of the rotor to control the flight speed of the unmanned aerial vehicle 1 to control the flight rhythm of the unmanned aerial vehicle 1.
  • the rack attachment assembly 10 is used to connect the stand to the center frame such that when the UAV 1 is docked, the rack link assembly 10 can be driven relative to the center frame 20 by the stand power unit. Thereby, the UAV 1 is smoothly docked on the ground or other fixed objects.
  • the rack connecting assembly 10 can be driven by the tripod power unit to contract relative to the center frame 20, thereby avoiding the rack connecting assembly 10, the tripod power unit and the objects in the air during the flight. Collisions occur, such as scratching the building or branches to damage the UAV 1, thereby increasing the life of the UAV 1.
  • the hanging object under the center frame 20 can be prevented from being blocked, and when the hanging object needs to be unfolded from the center frame 20, the frame can be prevented from being connected to the frame.
  • the assembly 10 interferes to avoid damage to the mount.
  • the mount of the center frame 20 is a pan/tilt head and a camera mounted on the pan/tilt head Time:
  • the frame connecting assembly 10 is driven to contract by the tripod power unit during take-off or before the pan/tilt is unfolded, and then the pan/tilt is unfolded and retracted after the entire shooting process is completed. Finally, before the UAV 1 is landed, the frame connecting assembly 10 is re-driven by the stand power unit to achieve stable docking on the ground or on the fixed object.
  • the rack connecting component 10 and the tripod power device do not interfere with the whole process of unfolding, photographing and retracting the gimbal, and do not block the shooting of the photographing device mounted on the gimbal, thereby Improve the working efficiency and service life of the entire UAV 1 .
  • the rack connection assembly 10 carrying the rotor power unit 30 will be described below as an example, and those skilled in the art can set the stand of the UAV 1 according to the example of the rack connection assembly 10 described below.
  • the rack attachment assembly 10 of the carrier power unit provided in accordance with the concept of the rack connection assembly 10 of the following rotor power unit 30 is still not divorced. The scope of protection of the invention.
  • FIG. 8 only shows the unmanned aerial vehicle 1 having the six-rotor, it will be understood by those skilled in the art that the present application can be applied to the unmanned aerial vehicle 1 having any number of rotors, for example, a single-rotor unmanned aerial vehicle. 1. Double-rotor unmanned aerial vehicle 1, four-rotor unmanned aerial vehicle 1 and so on.
  • the rack connection assembly 10 of the present embodiment supports the tube 110, the auxiliary member 130, and the fastener 140.
  • the open end of the support tube 110 is used in the middle of the UAV 1
  • the connecting portions 120 provided on the core frame 20 are sleeved together.
  • the support tube 110 can be coupled to the rotor power unit 30 or the tripod power unit.
  • the rotor power unit 30 can be carried on the support tube 110 or on a connector that is coupled to the support tube 110.
  • the auxiliary member 130 is disposed inside or outside the open end of the support tube 110 such that the tube wall 1102 of the open end of the support tube 110 is sandwiched between the auxiliary member 130 and the connecting portion 120 of the center frame 20.
  • the fastener 140 securely connects the support tube 110, the connecting portion 120 and the auxiliary member 130 through the tube wall 1102 at the open end, and both ends of the fastener 140 abut against the auxiliary member 130 and the connecting portion 120, respectively.
  • the tripod power device can drive the support tube 110 or the connecting member connected to the support tube 110 to rotate, so that the tripod functions as a tripod power device. Stretch or contract under force
  • the support tube 110 should be interpreted broadly, which may be a completely hollow tube, i.e., only one cavity 1101 is formed in the tube wall 1102. At the same time, it may be a tube in which the plurality of cavities 1101 are partitioned in the tube wall 1102. It may even be a tube having a majority of solids having only a small portion of the hollow to be nested with the central frame 20 connection portion 120. Those skilled in the art will appreciate that any structural modifications to the tubular intermediate cavity 1101 are intended to be included within the scope of the present application.
  • the material of the support tube 110 may be any material, such as a metal material such as steel, aluminum or alloy, and of course, a non-metal material having a certain strength.
  • the support tube 110 can be made of a carbon fiber material to provide the UAV 1 with better joint strength and lighter weight.
  • the shape of the support tube 110 may be any shape, for example, the cross section of the support tube 110 may be a circle, a square, other closed curves or a closed straight line.
  • the circular, square, etc. referred to herein is an overall cross-sectional shape including the cavity 1101 in the tube wall 1102 of the support tube 110. If the cavity 1101 is removed, only from the cross section of the tube wall 1102, Then, the cross section of the support tube 110 is a ring, a square ring or the like.
  • the support tube 110 has an elliptical cross section and an elliptical ring after the cavity 1101 is removed.
  • the wind resistance of the frame connecting assembly 10 can be reduced, and the flying efficiency of the UAV 1 can be improved.
  • a better structural strength can be obtained by making the cross-section of the tube wall 1102 of the support tube 110 into an elliptical ring.
  • the connecting portion 120 disposed on the center frame 20 may be fixed to the center frame 20
  • the fixed connection portion 120 is either a connection portion 120 rotatably coupled to the center frame 20.
  • the fixed connection manner may be, for example, various fixed connection manners such as welding, riveting, keying, or bolting.
  • the rotatably connected manner can be, for example, hinged, pivoted, or the like, and various existing rotatably connected means.
  • the material, shape and structure of the connecting portion 120 are not specifically limited in the embodiment, and a person skilled in the art can select a suitable workpiece as the connecting portion 120 according to the type, design weight and connection strength of the unmanned aerial vehicle 1.
  • a tube having a cavity 1101 can be selected, or a solid body can be selected as the connecting portion 120.
  • the fastener 140 can be selected from screws or rivets. Of course, other fasteners having a fastening function suitable for the prior art may be selected as the fastener 140 of the present embodiment.
  • the auxiliary member 130, the support tube 110 and the connecting portion 120 are fixedly coupled together through one end of the fastener 140 through the tube wall 1102 at the open end, and by this connection, the two ends of the fastener 140 are respectively associated with the auxiliary member
  • the 130 and the connecting portion 120 abut, so that the force is not directly applied to the tube wall 1102 of the open end of the support tube 110, but is transmitted through the auxiliary member 130 and the connecting portion 120.
  • the force transmission of the surface contact can reduce the tube wall 1102. The deformation improves the flight stability of the UAV 1.
  • the auxiliary member 130 is disposed on the inner side or the outer side of the tube wall 1102 at the open end of the support tube 110, thereby clamping the tube wall 1102 at the open end of the support tube 110 between the auxiliary member 130 and the connecting portion 120. between.
  • the fastener 140 when the open end of the support tube 110, the auxiliary member 130 and the connecting portion 120 are fixed by using the fastener 140, the two ends of the fastener 140 abut against the auxiliary member 130 and the connecting portion 120, that is, the support tube 110 is open.
  • the end wall 1102 is changed from a point contact type force to a surface contact type force.
  • the fastening force received by the pipe wall 1102 can be dispersed, and the problem of deformation of the pipe wall 1102 caused by the point contact is avoided, so that the pipe wall 1102 and the connecting portion 120 at the open end of the support pipe 110 are not easily generated.
  • the gap solves the jitter phenomenon caused by the unsteady connection when the UAV 1 is in flight or when the tripod or the arm is retracted and unfolded, and the flight stability of the UAV 1 is improved.
  • the auxiliary member 130 disposed in the open end cavity 1101 of the support tube 110 or the connecting portion 120 sleeved in the open end cavity 1101 of the support tube 110 can further provide a supporting force for the open end of the support tube 110 to further ensure the support.
  • the tube wall 1102 at the open end of the tube 110 is not deformed.
  • This embodiment provides an unmanned aerial vehicle.
  • the fastener 140 fixedly connecting the connecting portion 120, the tube wall 1102 of the open end of the support tube 110, and the auxiliary member 130 is set as A plurality of fasteners 140 are evenly distributed on the tube wall 1102 at the open end to improve the connection strength of the support tube 110 and the connecting portion 120 and the auxiliary member 130, thereby further improving the stability of the UAV 1 during flight. Sex.
  • the plurality of uniformly distributed fasteners 140 may be located on the same side of the axis of the support tube 110 or on both sides of the axis of the support tube 110.
  • the plurality of fasteners 140 are symmetrically disposed on both sides of the axis of the support tube 110 to make the wall of the tube wall 1102 at the open end of the support tube 110 and the connecting portion 120 and the auxiliary member 130 more uniform, and at the same time enable the frame The ability of the connecting assembly 10 to resist axial shear forces is better.
  • both sides of the axis of the support tube 110 refer to an arbitrary section through the axis of the support tube 110, and the two portions divided by the section are the two sides of the axis of the support tube 110.
  • a total of four fastening screws are provided, and the four fastening screws are symmetrically disposed at the upper and lower portions of the axis of the support tube 110.
  • two screws are arranged on the upper part and two screws are arranged on the lower part. Both ends of each screw abut against the auxiliary member 130 and the connecting portion 120, respectively, so that the tube wall 1102 at the open end is sandwiched between the auxiliary member 130 and the connecting portion 120.
  • both sides of the axis form a left-right direction of the cross-section, so that the upper and lower portions of the section are respectively on both sides of the axis of the support tube 110.
  • the UAV 1 of the present embodiment can strengthen the connection strength of the rack connection assembly 10 and the connecting portion 120 by providing a plurality of fasteners 140 uniformly distributed on the open end pipe wall 1102 of the support pipe 110, so that the UAV can be used. 1 It is not easy to shake during flight and improve its flight stability. Moreover, by symmetrically arranging the plurality of fasteners 140, the force of the frame connecting assembly 10 can be more balanced, the ability to resist axial shearing force can be enhanced, and the service life of the unmanned aerial vehicle 1 can be improved.
  • This embodiment provides an unmanned aerial vehicle.
  • the present embodiment is based on the technical solutions provided in Embodiment 10 and Embodiment 11, and the connecting portion 120 is sleeved in the cavity 1101 of the open end of the support tube 110, and is supported.
  • An auxiliary member 130 is disposed outside the tube wall 1102 at the open end of the tube 110.
  • the connecting portion 120 may be any structural component that can be sleeved in the open end cavity 1101 of the support tube 110 and substantially conform to the shape of the cavity 1101.
  • a hollow or solid cylinder or other hollow or solid object of any cross-sectional shape that can be substantially in contact with the inner surface of the tube wall 1102.
  • the connecting portion 120 includes a cylinder and an elliptical cylinder.
  • the right end of the elliptical cylinder is sleeved in the cavity 1101 of the open end of the support tube 110 whose cross section is an elliptical ring; the right end of the cylinder is fixedly connected with the left end of the elliptical cylinder, and the left end of the cylinder and the center frame 20 Fixed connection or rotatable connection. More preferably, the cylinder and the elliptical cylinder are integrally formed into a single piece, thereby increasing the structural strength of the joint 120 to improve the flight performance of the UAV 1.
  • the outer wall of the elliptical cylinder is perfectly matched to the shape and size of the tube wall 1102 at the open end of the support tube 110, so that the elliptical cylinder can provide a good supporting force for the tube wall 1102 of the open end of the support tube 110, and is thus fastened.
  • the supporting force of the elliptical cylinder can better prevent the deformation of the pipe wall 1102, thereby improving the stability of the UAV 1.
  • the auxiliary member 130 may be a gasket or a cylindrical bushing.
  • the auxiliary member 130 may be an elastic gasket or a cylindrical elastic bushing, so that the elastic deformation force of the elastic gasket or the elastic bushing can further reduce the deformation of the pipe wall 1102 to reduce the pipe wall 1102 and the connection.
  • the gap between the portions 120 may be a gasket or a cylindrical bushing.
  • the auxiliary member 130 may be an elastic gasket or a cylindrical elastic bushing, so that the elastic deformation force of the elastic gasket or the elastic bushing can further reduce the deformation of the pipe wall 1102 to reduce the pipe wall 1102 and the connection.
  • the gap between the portions 120 the size, shape and specific structure of the gasket are not specifically limited, and the skilled person can select any suitable gasket in the prior art or make a mat matching the specific type of the UAV 1 . sheet.
  • a solid connecting portion 120 is disposed.
  • One end of the connecting portion 120 is connected to the center frame 20, and one end is sleeved in the cavity 1101 of the open end of the supporting tube 110.
  • a cylindrical elastic outer bushing is provided outside the tube wall 1102 at the open end of the support tube 110.
  • a coaxial screw hole is formed in the elastic outer bushing, the pipe wall 1102 at the open end, and the connecting portion 120 that is sleeved in the open end cavity 1101.
  • the elastic outer bushing, the tube wall 1102 and the connecting portion 120 are then secured together using screws or rivets through the screw holes. Since four symmetrical fasteners 140 (screw or rive) are provided in Figure 2 that are evenly distributed on both sides of the axis Nail), so that through holes can be formed directly on the elastic outer bushing, the pipe wall 1102 and the connecting portion 120 to reduce the processing flow and steps to save processing time and cost.
  • a boss 1201 may be formed on the connecting portion 120 such that the tube wall 1102 at the open end of the support tube 110 abuts against the end surface of the boss 1201 to restrict the axial movement of the support tube 110.
  • the connecting portion 120 includes an integrally formed cylinder and an elliptical cylinder
  • the tube wall 1102 at the open end of the support tube 110 can be directly abutted against the right end of the cylinder, thereby avoiding the axis of the supporting tube 110. Move to improve the flight stability of the UAV 1.
  • the UAV 1 of the present embodiment is disposed in the cavity 1101 of the open end of the support tube 110 of the rack connection assembly 10, and the auxiliary member 130 is disposed outside the tube wall 1102 at the open end of the support tube 110.
  • the structure of the rack connection assembly 10 is simplified, and the unmanned aerial vehicle 1 can be provided with superior structural strength when the joint portion 120 is a solid unitary structure, thereby providing the unmanned aerial vehicle 1 with better flight stability.
  • the connecting portion 120 in the cavity 1101 at the open end of the support tube 110 can provide a supporting force to the open end wall 1102 to further reduce the deformation of the tube wall 1102 at the time of fixing, thereby improving the stability of the UAV 1 during flight.
  • the use of the elastic gasket or the elastic outer bushing can further reduce the deformation of the pipe wall 1102 at the open end of the support pipe 110, further improving the flight stability of the UAV 1.
  • the fixing of the support tube 110, the auxiliary member 130 and the connecting portion 120 by screws can also realize the quick disassembly and assembly of the rack connecting assembly 10, improve the environmental adaptability of the unmanned aerial vehicle 1 and the space occupied during storage, and also for different rotors.
  • the replacement of the power unit 30 provides the possibility that the multi-rotor UAV 1 can have different power rotor power units 30 to provide overall flight performance.
  • This embodiment provides an unmanned aerial vehicle.
  • the present embodiment is based on the technical solutions provided in Embodiment 10 and Embodiment 11, in which the receiving portion 120 is formed with a receiving cavity 1203, and the supporting tube 110 is sleeved in the receiving cavity.
  • the right end of the auxiliary member 130 extends into the cavity 1101 of the open end of the support tube 110, thereby clamping the tube wall 1102 of the open end of the support tube 110 between the side wall 1202 where the connection portion 120 accommodates the cavity 1203 and the auxiliary member 130.
  • the connecting portion 120 can be provided with the receiving cavity 1203 and can be combined with The core frame 20 is connected and the receiving cavity 1203 can be sleeved with any structure of the open end of the support tube 110, for example, it can be a semi-closed pipe.
  • the two ends of the semi-closed pipe can have different pipe diameters.
  • one end of the large diameter is a closed end for connecting with the center frame 20, thereby increasing the contact area between the connecting portion 120 and the center frame 20 to improve the connection strength between the two.
  • One end of the small diameter pipe is a socket end, and the open end of the support pipe 110 is sleeved in the receiving cavity 1203 of the socket end, so that the pipe wall 1102 of the open end of the support pipe 110 can be clamped on the side wall 1202 of the receiving cavity 1203 and Between the auxiliary members 130.
  • the UAV 1 of the present embodiment forms a receiving cavity 1203 on the connecting portion 120 of the rack connecting assembly 10, and sleeves the open end of the supporting tube 110 in the receiving cavity 1203 while still supporting the tube
  • An auxiliary member 130 is disposed in the cavity 1101 at the open end of the 110, so that when the fastener 140 fixes the connecting portion 120 and the support tube 110, the tube wall 1102 of the open end of the support tube 110 can be clamped to the side wall 1202 of the receiving cavity 1203 and Between the auxiliary members 130, thereby reducing the deformation of the support tube 110, and improving the stability of the UAV 1 in the air.
  • the tube wall 1102 of the open end of the support tube 110 is not in point contact with the end of the fastener 140, but is in contact with both end faces of the fastener 140 through the auxiliary member 130 and the side wall 1202, thereby further reducing the wall 1102 at the time of fixing.
  • the deformation improves the flight stability of the UAV 1.
  • a protrusion may be formed on the auxiliary member 130, and the tube wall 1102 of the open end of the support tube 110 may be abutted against the end surface of the protrusion.
  • the shape and size of the protrusion are not specifically limited.
  • the protrusion may have an end surface extending obliquely from the upper surface of the auxiliary member 130 toward the open end of the support tube 110, so that the tube wall 1102 can be inserted.
  • the raised end face is interposed between the upper surface of the auxiliary member 130 to thereby clamp the support tube 110.
  • This embodiment provides an unmanned aerial vehicle.
  • the present embodiment is based on the technical solution provided in Embodiment 13, and the auxiliary member 130 and the connecting portion 120 are formed into an integrally formed structure, thereby strengthening the connection strength between the auxiliary member 130 and the connecting portion 120. Further, the ability of the support tube 110 and the connecting portion 120 to resist axial shear force after the connection is increased, thereby making the UAV 1 more stable in the air.
  • the auxiliary component 130 may have one end capable of extending into the support tube 110. Any structure within the cavity 1101 at the mouth end that provides support for the tube wall 1102 at the open end, such as a solid or hollow cylindrical block, an elliptical column block, or other block or plate-like structure having a curved surface.
  • the UAV 1 of the present embodiment improves the connection strength of the support tube 110 and the connecting portion 120 and the auxiliary member 130 by making the auxiliary member 130 and the connecting portion 120 in the rack connecting assembly 10 into an integrally formed structure, so that no The human aircraft 1 flight is more stable.
  • This embodiment provides an unmanned aerial vehicle.
  • this embodiment is based on the technical solution provided in Embodiment 13, and the auxiliary member 130 and the connecting portion 120 are disposed as a split structure, and one end of the auxiliary member 130 is disposed at the open end of the support tube 110. In the cavity 1101, the other end of the auxiliary member 130 is disposed in the receiving cavity 1203 of the connecting portion 120.
  • the auxiliary member 130 may be a part of any single structure or a combined structure in which a plurality of parts are combined, and only needs to satisfy the tube wall 1102 which can support the open end of the support tube 110 from the inside and one end is located at the open end.
  • the inside of the cavity 1101 and the other end may be located in the receiving cavity 1203 of the connecting portion 120.
  • the auxiliary member 130 may be a combined structure of a cylindrical block, an elliptical block, or two support plates having curved surfaces.
  • the unmanned aerial vehicle 1 of the present embodiment can control the diameter of the support tube 110 and adjust the shape and structure of the auxiliary member 130 by setting the auxiliary member 130 and the connecting portion 120 in the rack connecting assembly 10 as a separate structure.
  • the side wall 1202 of the cavity 1203 is supported by the support tube 110, the auxiliary member 130 and the connecting portion 120 to have a better fit to reduce the gap between the three fasteners 140, thereby improving the UAV 1 Stability during flight.
  • This embodiment provides an unmanned aerial vehicle.
  • a rib 1306 is formed on the auxiliary member 130, and is formed on the tube wall 1102 at the open end of the support tube 110.
  • the rib 1306 cooperates with the card slot 1103 so that the rib 1306 can be snapped into the card slot 1103 during assembly, enabling rapid positioning of the assembly and preventing axial movement of the support tube 110.
  • the shape and size of the ribs 1306 can be set according to actual needs, and is not specifically limited herein.
  • the UAV 1 of the present embodiment realizes the arm connecting assembly by providing the engaging ribs 1306 and the card slots 1103 on the auxiliary member 130 in the rack connecting assembly 10 and the tube wall 1102 at the open end of the supporting tube 110.
  • the rapid positioning of the mounting and the prevention of the axial movement of the support tube 110 ensure the flight stability of the unmanned aerial vehicle 1.
  • This embodiment provides an unmanned aerial vehicle.
  • the present embodiment is formed on the side wall 1202 and the auxiliary member 130 of the connecting portion 120 accommodating the cavity 1203 on the basis of the embodiment 13, the embodiment 14, the embodiment 15, and the embodiment 16.
  • Interlocking structure that cooperates with each other.
  • a protrusion or a rib 1306 formed on the side wall 1202 and formed on the auxiliary member 130 to cooperate with the groove 1204 may be formed to constitute the above-mentioned snap-fit structure. It is of course also possible to form a projection formed on the side wall 1202 and form a groove 1204 on the auxiliary member 130 that cooperates with the projection.
  • the shape of the protrusion or the rib 1306 can be set according to actual needs, and is not specifically limited herein.
  • a rib 1306 is formed on the auxiliary member 130, and a positioning groove 1205 matching the rib 1306 is formed on the side wall 1202, so that the rib 1306 can be engaged in the positioning groove 1205, thereby preventing auxiliary The axial movement of the piece 130.
  • a positioning groove 1205 is formed on the side wall 1202 to cooperate with the rib 1306, and the rib 1306 is formed on the tube wall 1102.
  • the rib 1306 can be simultaneously clamped in the positioning slot 1205 and the card slot 1103, thereby achieving positioning of the gantry connection assembly 10 and preventing its axial movement.
  • the tube wall 1102 at the open end of the support tube 110 can be abutted on the above-mentioned snap-fit structure, so that the convexity described in the above embodiment 13 can be omitted.
  • the tube wall 1102 of the support tube 110 is provided with the card slot 1103 that cooperates with the above-mentioned rib 1306, the support tube 110 and the rib 1306 can be clamped in the axial direction. Therefore, the above embodiment 13 can be omitted. Said protrusion.
  • the UAV 1 of the present embodiment achieves the clamping of the auxiliary member 130 and the connecting portion 120 by providing a mating engaging structure on the side wall 1202 of the cavity 1203 and the auxiliary member 130 in the rack connecting assembly 10. Thereby, the connection strength of the rack connection assembly 10 and the connecting portion 120 is improved, and the flight stability of the UAV 1 is improved.
  • This embodiment provides an unmanned aerial vehicle.
  • the embodiment is based on Embodiment 3, Embodiment 13, Embodiment 14, Embodiment 15, Embodiment 6, and Embodiment 17, and the auxiliary member 130 is specifically configured to include a support block.
  • the support block is disposed within the cavity 1101 of the open end of the support tube 110, and the support block, together with the side wall 1202 of the connection portion 120 receiving the cavity 1203, sandwiches the tube wall 1102 at the open end therebetween.
  • the head of the fastener 140 is secured to the support block through the side wall 1202 and the tube wall 1102, i.e., the ends of the fastener 140 are in contact with the side wall 1202 and the support block, respectively.
  • the support block of the present embodiment should be explained in a broad sense, for example, a sheet-like structure having a curved surface or a solid or hollow block-shaped structure, which can be specifically set by the person skilled in the art according to the parameters of the unmanned aerial vehicle 1.
  • the parameters of the unmanned aerial vehicle 1 described above may be, for example, the weight of the unmanned aerial vehicle 1, the strength of the rack connecting assembly 10, and the flying speed and lifting force, flexibility, and the like.
  • the UAV 1 of the present embodiment can reduce the number of components of the UAV 1 by specifically arranging the auxiliary components 130 in the Rack Attachment Assembly 10 as support blocks, thereby reducing the weight of the UAV 1 to improve the life of the UAV 1 .
  • Performance such as time and flight speed as well as climbing ability.
  • the support block may be configured to include a first support block 1301 and a second support block 1302.
  • the two support blocks are symmetrically disposed on both sides of the axis of the cavity 1101 at the open end of the support tube 110, thereby clamping the tube walls 1102 on both sides of the axis of the cavity 1101 to the side walls of the first support block 1301 and the receiving cavity 1203, respectively.
  • the right side wall 1102 is sandwiched between the right side wall 1202 and the first support block 1301, and the left side wall 1102 is clamped to the left side wall 1202.
  • the fastener 140 is disposed to include a first fastener 140 and a second fastener 140.
  • the head of the first fastener 140 is secured to the first support block 1301 through the right side wall 1202 and the right side wall 1102 to effect clamping of the right side wall 1102.
  • the head of the second fastener 140 is secured to the second support block 1302 through the left side wall 1202 and the left side tube wall 1102 to effect clamping of the left side wall 1102.
  • the fastener 140 may further include: a third fastener 140 and a fourth fastener 140 .
  • the third fastener 140 is spaced apart from the first fastener 140
  • the fourth fastener 140 is symmetric with the third fastener 140 such that the first fastener 140 and the second fastener 140 are The axis is parallel to the axes of the third fastener 140 and the fourth fastener 140.
  • the first support block 1301 and the second support block 1302 may be any shape of a structure capable of supporting the tube wall 1102 of the open end of the support tube 110, for example, may have a shape with the inner surface of the tube wall 1102.
  • the plate-like structure of the matching surface may be preferably set to be the same to reduce the processing difficulty of the parts and improve the processing efficiency.
  • one or more of the first fastener 140, the second fastener 140, the third fastener 140, and the fourth fastener 140 may use screws or rivets.
  • four screws can be used as shown in Figures 3-7 to achieve quick disassembly of the rack attachment assembly 10.
  • a connecting plate may be disposed at both ends of the first support block 1301 and the second support block 1302 to connect the first support block 1301 and the second support block 1302 together.
  • the connecting plate comprises: a first connecting plate 1303 and a second connecting plate 1304. The first connecting plate 1303 and the second connecting plate 1304 are disposed at a distance.
  • the pressing force of the first supporting block 1301 and the second supporting block 1302 can be further dispersed by providing the first connecting plate 1303 and the second connecting plate 1304, thereby further reducing the pipe wall 1102 and the first supporting block 1301, the second branch
  • the gap between the blocks 1302 improves the flight stability of the UAV 1.
  • the bending directions of the first connecting plate 1303 and the second connecting plate 1304 are opposite, so that the direction of the pressing force received by the first supporting block 1301 and the second supporting block 1302 can be better adapted, so that the two are subjected to
  • the pressing force can be better dispersed to reduce the gap between the pipe wall 1102 and the first support block 1301 and the second support block 1302, thereby improving the flight stability of the UAV 1.
  • a reinforcing rib 1305 may be further disposed on the first supporting block 1301 to improve the supporting ability of the first supporting block 1301 to the pipe wall 1102.
  • the reinforcing ribs 1305 are disposed on the inner side surface of the first support block 1301, that is, the first support block 1301 and a side surface away from the inner surface of the tube wall 1102, that is, the right side surface shown in FIG.
  • the head of the first fastener 140 is fixed to the reinforcing rib 1305 through the connecting portion 120 accommodating the side wall 1202 of the cavity 1203 and the pipe wall 1102 and the first supporting block 1301. .
  • the reinforcing ribs 1305 may also be disposed on the inner side surface of the second supporting block 1302.
  • the reinforcing ribs 1305 may be disposed on both the inner side surface of the first supporting block 1301 and the inner side surface of the second supporting block 1302, and two of the reinforcing ribs 1305 are respectively connected.
  • the first connecting plate 1303 and the second connecting plate 1304 form an annular structure connected to the inner side surfaces of the first supporting block 1301 and the second supporting block 1302.
  • first support block 1301, the second support block 1302, the first connecting plate 1303, the second connecting plate 1304, and the reinforcing rib 1305 may be integrally manufactured to form an integral structure to strengthen the structure of the auxiliary member 130. strength.

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  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
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  • Supports For Pipes And Cables (AREA)
  • Manipulator (AREA)

Abstract

一种用于无人飞行器的机架连接组件，包括：支撑管(110)、辅助件(130)和紧固件(140)；支撑管(110)的开口端用于与无人飞行器中心架上设置的连接部相互套接；辅助件(130)设于支撑管(110)的开口端内侧或外侧，以将支撑管(110)的开口端的管壁夹持在辅助件(130)与中心架的连接部之间；紧固件(140)穿过支撑管(110)的开口端的管壁将辅助件(130)、支撑管(110)的开口端、以及中心架的连接部固定连接起来，且紧固件(140)的两端分别与辅助件(130)及中心架的连接部抵接。本发明提供的用于无人飞行器的机架连接组件及无人飞行器，通过将支撑管(110)开口端的管壁夹持在辅助件(130)和连接部之间，从而在用紧固件(140)对其进行固定时不会使管壁变形，进而使无人飞行器飞行或者起降时更加稳定。

Description

用于无人飞行器的机架连接组件及无人飞行器 技术领域
本发明涉及无人飞行器技术领域，尤其涉及一种用于无人飞行器的机架连接组件及无人飞行器。
背景技术
随着科技的发展，越来越多的消费者开始关注和使用无人飞行器。无人飞行器主要包括：中心架、机架连接组件和挂载物。其中，机架连接组件一般包含：支撑管和紧固件，其中紧固件用来将支撑管和中心架上设置的连接部固定在一起。中心架的下方则用来安装挂载物。
现有中心架的连接部一般设置成空心状，从而可以将支撑管套接在连接部所形成的容纳空腔内。紧固件一般采用长螺丝，在连接部和支撑管上则开设一组对称的螺丝通孔。在固定时，将长螺丝穿过上述对称的螺丝通孔后用螺母固定，从而实现将连接部和支撑管固定在一起的目的。
但是，现有的这种连接，在用螺母对长螺丝进行旋紧的时候会挤压支撑管的管壁，导致管壁与螺丝的两端之间出现间隙，从而使得无人飞行器在飞行过程中或者收起和展开脚架或机臂时出现抖动现象，影响其正常飞行。
发明内容
本发明的目的是提供一种用于无人飞行器的机架连接组件及无人飞行器，以解决现有技术中支撑管管壁和紧固件两端之间具有间隙造成飞行状态不稳的技术问题。
为了实现上述目的，本发明提供了以下技术方案：
第一方面，提供一种用于无人飞行器的机架连接组件，包括：支撑管、辅助件和紧固件；所述支撑管用于连接所述无人飞行器的中心架，所述中心架设有用于与所述支撑管的开口端相互套接的连接部；所述辅助件设于所述支撑管的开口端内侧或外侧，以将所述支撑管的开口端的管壁夹持在所述辅 助件与所述中心架的连接部之间；所述紧固件用于将所述辅助件、所述支撑管的开口端、以及所述中心架的连接部固定连接起来；其中，所述紧固件穿过所述支撑管的开口端的管壁，并且所述紧固件的两端分别与所述辅助件及所述中心架的连接部抵接。
第二方面，提供一种无人飞行器，包括：中心架及机架连接组件；所述机架连接组件包括：支撑管、辅助件和紧固件；所述支撑管用于连接所述中心架，所述中心架设有用于与所述支撑管的开口端相互套接的连接部；所述辅助件设于所述支撑管的开口端内侧或外侧，以将所述支撑管的开口端的管壁夹持在所述辅助件与所述中心架的连接部之间；所述紧固件用于将所述辅助件、所述支撑管的开口端、以及所述中心架的连接部固定连接起来；其中，所述紧固件穿过所述支撑管的开口端的管壁，并且所述紧固件的两端分别与所述辅助件及所述中心架的连接部抵接。
本发明提供的用于无人飞行器的机架连接组件及无人飞行器，通过在支撑管开口端的管壁的内侧或者外侧设置辅助件，从而将支撑管开口端的管壁夹持在辅助件和连接部之间。这样，在使用紧固件固定支撑管开口端、辅助件和连接部时，紧固件的两端将分别与辅助件和连接部抵接，也即，支撑管开口端的管壁由点接触式受力改变为面接触式受力。通过以上方式就可以将管壁受到的紧固力分散，避免了点接触所造成的管壁变形的问题，也就使得支撑管开口端的管壁和连接部之间不容易产生间隙，解决了无人飞行器在飞行过程中或者收起和展开脚架或机臂时由于连接不稳造成的抖动现象，提高了无人飞行器的飞行稳定性。
附图说明
图1为本发明提供的实施例1-3的机架连接组件与连接部处于连接状态时的正视图；
图2为图1中A-A向的剖视图；
图3为本发明提供的实施例4-9的机架连接组件与连接部处于连接状态时的结构示意图；
图4为图3的分解视图；
图5为图3的正视图；
图6为图5中B-B向的剖视图(其中，紧固件为螺丝)；
图7为图5中B-B向的剖视图(其中，紧固件为铆钉)；
图8为本发明所提供的无人飞行器的结构示意图。
图中：
1、无人飞行器；                     10、机架连接组件；
110、支撑管；                       1101、空腔；
1102、管壁；                        1103、卡槽；
120、连接部；                       1201、凸台；
1202、侧壁；                        1203、容纳空腔；
1204、凹槽；                        1205、定位槽；
130、辅助件；                       1301、第一支撑块；
1302、第二支撑块；                  1303、第一连接板；
1304、第二连接板；                  1305、加强筋；
1306、凸条；                        140、紧固件；
20、中心架；                        30、旋翼动力装置。
具体实施方式
下面结合附图，对本发明的一些实施方式作详细说明。
在本发明中，使用的技术术语：“上”、“下”、“左”“右”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。
在本说明书的描述中，在不相互矛盾的情况下，本领域的技术人员可以将本说明书中描述的不同实施例或示例以及不同实施例或示例的特征进行结合和组合。
实施例1
本实施例提供一种用于无人飞行器的机架连接组件
图1为本实施例提供的机架连接组件与连接部处于连接状态时的正视图；图2为图1中A-A向的剖视图；图8为无人飞行器的结构示意图。
如图1、图2和图8所示，本实施例中的机架连接组件包括：支撑管110、辅助件130和紧固件140。其中，支撑管110的开口端用于与无人飞行器1的中心架20上所设置的连接部120相互套接在一起。支撑管110可以与旋翼动力装置30或者脚架动力装置连接。例如，当支撑管110为机臂或其组成元件时，旋翼动力装置30可以承载在支撑管110上或与支撑管110相连的连接件上；当支撑管110为脚架或其组成元件时，脚架动力装置能够驱动支撑管110或与支撑管110相连的连接件转动，以使该脚架在脚架动力装置的作用力下伸展或收缩。同时，在支撑管110开口端的内侧或者外侧设置辅助件130，从而使得支撑管110的开口端的管壁1102夹持在该辅助件130和中心架20的连接部120之间。紧固件140穿过开口端的管壁1102将支撑管110、连接部120和辅助件130固定连接在一起，并且该紧固件140的两端分别与辅助件130和连接部120抵接。
在本申请中，为了描述更加简洁和方便，以下将以承载旋翼动力装置30的机架连接组件10为例来介绍本申请的机架连接组件10，本领域技术人员可以根据下述承载旋翼动力装置30的机架连接组件10扩展到承载脚架动力装置或者承载无人飞行器1中的其他结构，这种扩展或变形依然在本申请的保护范围以内。
在本申请中，支撑管110应做广义解释，其可以是一根完全中空的管材，也即管壁1102内仅形成有一个空腔1101。同时，也可以是管壁1102内被隔成有多个空腔1101的管材。甚至还可以是具有大部分实心仅具有少部分空心以与中心架20连接部120套接的管材。本领域技术人员应该理解，对于管材中间空腔1101的任意结构变形均应包括在本申请的保护范围之内。
在本本实施例中，支撑管110的材质可以是任意材质，比如可以是钢材、铝材或者合金等金属材料，当然，也可以是具有一定强度的非金属材料。优 选地，支撑管110可以使用碳纤维材料制作，从而使无人飞行器1具有更好的连接强度和更轻的重量。
同时，在本实施例中，支撑管110的形状可以是任意形状，比如，该支撑管110的横截面可以是圆形、方形、其他闭合曲线或者闭合直线。当然，此处说的圆形、方形等是包括了支撑管110管壁1102内的空腔1101在内的整体横截面形状，如果去除空腔1101，仅从管壁1102的横截面而言，那么该支撑管110的横截面为圆环、方环等。优选地，该支撑管110的横截面为椭圆，去除空腔1101后为椭圆环。将支撑管110的管壁1102横截面做成椭圆环，可以减少机架连接组件10的风阻，提高无人飞行器1的飞行效率。并且，将支撑管110的管壁1102横截面做成椭圆环还可以取得更好的结构强度。
在本实施例中，中心架20上设置的连接部120，可以是与中心架20固定连接的连接部120或者是与中心架20可转动连接的连接部120。具体的，当中心架20和连接部120固定连接时，其固定连接方式例如可以是焊接、铆接、键连接或者螺栓连接等各种固定连接方式。当中心架20和连接部120可转动连接时，其可转动连接方式例如可以是铰接、枢接等各种现有的可转动连接方式。同时，连接部120的材料、形状和结构在本实施例中不作具体限定，本领域技术人员可以根据无人飞行器1的类型、设计重量以及连接强度等条件选择合适的工件作为连接部120。举例来说，可以选择具有空腔1101的管材，或者选择实心的主体作为连接部120。
在本实施例中，紧固件140可以选择螺丝或者铆钉。当然，也可以选择其他现有技术中合适的具有紧固功能的零件作为本实施例的紧固件140。将紧固件140的一端穿过开口端的管壁1102将辅助件130、支撑管110和连接部120固定连接在一起，并且，通过这种连接方式，紧固件140的两端分别与辅助件130和连接部120抵接，从而不会直接对支撑管110开口端的管壁1102施加作用力，而是通过辅助件130和连接部120进行传递，这种面接触的力传递可以减少管壁1102的变形，提高无人飞行器1的飞行稳定性。
本实施例的机架连接组件10，通过在支撑管110开口端的管壁1102的内侧或者外侧设置辅助件130，从而将支撑管110开口端的管壁1102夹持在 辅助件130和连接部120之间。这样，在使用紧固件140固定支撑管110开口端、辅助件130和连接部120时，紧固件140的两端分别与辅助件130和连接部120抵接，也即，支撑管110开口端的管壁1102由点接触式受力改变为面接触式受力。通过以上方式就可以将管壁1102受到的紧固力分散，避免了点接触所造成的管壁1102变形的问题，也就使得支撑管110开口端的管壁1102和连接部120之间不容易产生间隙，解决了无人飞行器1在飞行过程中或者收起和展开脚架或机臂时由于连接不稳造成的抖动现象，提高了无人飞行器1的飞行稳定性。并且，设置在支撑管110开口端空腔1101内的辅助件130或者套接在支撑管110开口端空腔1101内的连接部120还能为支撑管110的开口端提供支撑力，进一步保证支撑管110开口端的管壁1102不变形。
实施例2
本实施例提供一种用于无人飞行器的机架连接组件。
继续参考图1和图2，本实施例是在实施例1提供的技术方案的基础上，将固定连接上述连接部120、支撑管110开口端的管壁1102和辅助件130的紧固件140设置为多个，并将这多个紧固件140在开口端的管壁1102上均匀分布，以提高支撑管110和连接部120、辅助件130的连接强度，进一步提高无人飞行器1在飞行中的稳定性。
具体的，在本实施例中，多个均匀分布的紧固件140可以位于支撑管110轴线的同一侧，也可以位于支撑管110轴线的两侧。优选地，这多个紧固件140对称设置在支撑管110的轴线两侧从而使支撑管110开口端的管壁1102以及连接部120、辅助件130的受力更加均匀，同时还能使得机架连接组件10对抗轴向剪切力的能力更好。在本申请中，支撑管110的轴线两侧是指经过支撑管110的轴线作一个任意切面，被该切面分成的两部分即为支撑管110的轴线两侧。比如，参考附图2所示，在该机架连接组件10中，共设置有四个紧固螺丝，在四个紧固螺丝对称设置在支撑管110轴线的上部和下部。其中，上部设置两个螺丝，下部设置两个螺丝。每个螺丝的两端均分别与辅助件130和连接部120抵接，从而将开口端的管壁1102夹持在辅助件130和连接部120之间。在图2中，轴线两侧即 使过轴线做一个左右方向的切面，从而该切面的上下两部分分别为支撑管110的轴线两侧。
本实施例的机架连接组件10，通过设置多个均匀分布在支撑管110开口端管壁1102上的紧固件140，可以加强机架连接组件10与连接部120的连接强度，使得无人飞行器1在飞行中不易出现抖动，提高其飞行稳定性。并且，通过将多个紧固件140对称设置，还可以使机架连接组件10的受力更加均衡，增强其抗轴向剪切力的能力，提高无人飞行器1的使用寿命。
实施例3
本实施例提供一种用于无人飞行器的机架连接组件。
继续参考图1和图2，本实施例是在实施例1和实施例2提供的技术方案的基础上，将连接部120套设在支撑管110开口端的空腔1101中，并在支撑管110开口端的管壁1102外侧设置辅助件130。
在本实施例中，连接部120可以为能够套设在支撑管110开口端空腔1101内并且与空腔1101形状基本一致的任意结构零件。比如，空心或者实心的圆柱体或者其他能够与管壁1102的内表面大致可接触的具有任意横截面形状的空心或者实心物体。优选地，如图2所示，连接部120包括一个圆柱体和一个椭圆柱体。其中，椭圆柱体的右端套接在管壁1102横截面为椭圆环的支撑管110的开口端的空腔1101内；圆柱体右端与椭圆柱体的左端固定连接，圆柱体的左端与中心架20固定连接或者可转动连接。更优选地，圆柱体和椭圆柱体通过一体成形方式加工成一体件，从而增加连接部120的结构强度，以提升无人飞行器1的飞行性能。再优选地，椭圆柱体的外壁与支撑管110开口端的管壁1102形状和大小完全匹配，从而使椭圆柱体能够为支撑管110开口端的管壁1102提供良好的支撑力，进而在用紧固件140进行固定时，椭圆柱体的支撑力能够更好的防止管壁1102变形，从而提高无人飞行器1的稳定性。
在本实施例中，辅助件130可以是垫片或者筒状的衬套。优选地，辅助件130可以是弹性垫片或者筒状的弹性衬套，从而可以通过弹性垫片或者弹 性衬套的弹性变形力以进一步减小管壁1102的变形，以减少管壁1102与连接部120之间的间隙。当然，在本实施例中对于垫片的大小、形状和具体的结构不作具体的限定，技术人员可以选用现有技术中任意合适的垫片或者制作与具体的无人飞行器1类型相匹配的垫片。同时，筒状衬套的大小和具体细部结构也不作具体限定，技术人员也可从现有技术中选择合适的衬套或者制作与具体无人飞行器1类型相匹配的衬套结构。优选地，如图2所示，设置一实心的连接部120，该连接部120一端与中心架20连接，一端则套接在支撑管110开口端的空腔1101内。同时，在支撑管110开口端的管壁1102外侧设置筒状的弹性外衬套。并且在弹性外衬套、开口端的管壁1102以及套接在开口端空腔1101内的连接部120上开设同轴的螺丝孔。然后使用螺丝或者铆钉穿过螺丝孔将弹性外衬套、管壁1102和连接部120固定在一起。由于在图2中使用了四个均匀分布在轴线两侧且对称的紧固件140(螺丝或者铆钉)，所以可以直接在弹性外衬套、管壁1102和连接部120上开设通孔，以减少加工流程和步骤以节省加工时间和成本。
进一步，可以在连接部120上形成一凸台1201，以使支撑管110开口端的管壁1102抵顶在该凸台1201的端面上从而限制支撑管110的轴向移动。比如，如图2所示，当连接部120包括一体成形的圆柱体和椭圆柱体时，可以将支撑管110开口端的管壁1102直接抵顶在圆柱体的右端，从而避免支撑管110的轴向移动，提高无人飞行器1的飞行稳定性。
本实施例的机架连接组件10，通过将连接部120套设在支撑管110开口端的空腔1101内并在支撑管110开口端的管壁1102外侧设置辅助件130，可以简化机架连接组件10的结构，并且当连接部120为实心的一体结构时能够为无人飞行器1提供更优的结构强度，从而使无人飞行器1具有更好的飞行稳定性。而且，位于支撑管110开口端的空腔1101内的连接部120可以为开口端的管壁1102提供支撑力以进一步减少固定时管壁1102的变形，从而提高无人飞行器1飞行时的稳定性。同时，弹性垫片或者弹性外衬套的使用还能进一步减少支撑管110开口端的管壁1102的变形，进一步提高无人飞行器1的飞行稳定性。另外，通过螺丝固定支撑管110、辅助件130和连接部 120还可以实现机架连接组件10的快速拆装，提高无人飞行器1的环境适应性和保存时占用的空间大小，也为不同旋翼动力装置30的更换提供了可能，从而可以使多旋翼无人飞行器1可以具有不同动力的旋翼动力装置30，以提供整体的飞行性能。
实施例4
本实施例提供一种用于无人飞行器的机架连接组件。
图3为本实施例提供的机架连接组件与连接部连处于接状态时的结构示意图；图4为图3的分解视图；图5为图3的正视图；图6为图5中B-B向的剖视图(其中，紧固件为螺丝)；图7为图5中B-B向的剖视图(其中，紧固件为铆钉)。
如图3-7所示，本实施例是在实施例1和实施例2提供的技术方案的基础上，在连接部120形成有容纳空腔1203，并将支撑管110套接在该容纳空腔1203内。辅助件130的右端伸入到支撑管110开口端的空腔1101内，从而将支撑管110开口端的管壁1102夹持在连接部120容纳空腔1203位置的侧壁1202和辅助件130之间。
具体的，在本实施例中，连接部120可以是带有容纳空腔1203并能与中心架20连接且该容纳空腔1203内可以套接支撑管110开口端的任意结构，例如可以是半封闭的管材，当然这个半封闭的管材的两端可以具有不同的管径。优选地，大管径一端为封闭端，用于与中心架20连接，从而增大连接部120与中心架20之间的接触面积以提高二者的连接强度。小管径一端为套接端，支撑管110开口端的套接在该套接端的容纳空腔1203内，以使支撑管110开口端的管壁1102能夹持在容纳空腔1203的侧壁1202与辅助件130之间。
本实施例的机架连接组件10，通过在连接部120上形成容纳空腔1203，并将支撑管110的开口端套接在该容纳空腔1203内，同时还在支撑管110开口端的空腔1101内设置辅助件130，从而使得紧固件140固定连接部120和支撑管110时，可以将支撑管110开口端的管壁1102夹持在容纳空腔1203的侧壁1202和辅助件130之间，从而减少支撑管110的变形，提高无人飞行 器1在空中的稳定性。并且，支撑管110开口端的管壁1102并不是与紧固件140的端部点接触，而是通过辅助件130和侧壁1202与紧固件140的两端面接触，进一步减少固定时管壁1102的变形，提高无人飞行器1的飞行稳定性。
进一步，为了限制支撑管110在轴向上的移动，还可以在辅助件130上形成凸起，并肩支撑管110开口端的管壁1102抵顶在该凸起的端面上。在本实施例中，对于上述凸起的形状和大小不作具体的限定，例如该凸起可以具有从辅助件130上表面往支撑管110开口端方向倾斜延伸的端面，这样，管壁1102可以插入凸起端面与辅助件130上表面之间，从而卡紧该支撑管110。
实施例5
本实施例提供一种用于无人飞行器的机架连接组件。
继续参考图3-7，本实施例是在实施例4提供的技术方案的基础上，将辅助件130和连接部120制作成为一体成型结构，从而加强辅助件130和连接部120的连接强度，进而提高支撑管110和连接部120连接以后抗轴向剪切力的能力，从而使无人飞行器1在空中飞行更加稳定。
具体的，在本实施例中，辅助件130可以是一端能够伸入支撑管110开口端的空腔1101内并为开口端的管壁1102提供支撑的任意结构，例如可以是实心或者空心的圆柱块、椭圆柱块，或者其他具有弧形表面的块状结构或板状结构。
本实施例的机架连接组件10，通过将辅助件130和连接部120制作成为一体成型结构，提高了支撑管110和连接部120以及辅助件130的连接强度，使得无人飞行器1飞行更加稳定。
实施例6
本实施例提供一种用于无人飞行器的机架连接组件。
继续参考图3-7，本实施例是在实施例4提供的技术方案的基础上，将辅助件130和连接部120设置为分体结构，辅助件130的一端设置在支撑管110的开口端的空腔1101内，辅助件130的另一端设置在连接部120的容纳空腔1203内。
在本实施例中，辅助件130可以为任意单一结构的零件或者是多个零件 组合在一起的组合结构，其仅需满足可以从内部支撑上述支撑管110开口端的管壁1102并一端位于开口端的空腔1101内、另一端位于连接部120的容纳空腔1203内即可。例如，该辅助件130可以是圆柱块、椭圆块或者两个具有曲面的支撑板所组成的组合结构。
本实施例的机架连接组件10，通过将辅助件130和连接部120设置为分体结构，可以非常方便的控制支撑管110的管径并调整辅助件130的形状结构以使支撑管110、辅助件130和连接部120容纳空腔1203的侧壁1202具有更好的配合度以减少三者之间用紧固件140固定后的间隙，从而提高无人飞行器1在飞行时的稳定性。
实施例7
本实施例提供一种用于无人飞行器的机架连接组件。
请继续参阅图3-7，本实施例是在实施例4、实施例5和实施例6的基础上，再辅助件130上形成凸条1306，并在支撑管110开口端的管壁1102上形成与该凸条1306相配合的卡槽1103，从而在装配时可以将凸条1306卡入该卡槽1103中，实现装配的快速定位并防止支撑管110的轴向移动。
在本实施例中，凸条1306的形状大小，可以根据实际需要进行设置，在此不作具体的限定。
需要说明的是，当支撑管110的管壁1102上设置有与上述凸条1306相配合的卡槽1103时，支撑管110和凸条1306可以在轴向上卡紧，因而可以省略上述实施例4中所述的凸起。
本实施例的机架连接组件10，通过在辅助件130和支撑管110开口端的管壁1102上设置相互配合的凸条1306和卡槽1103，实现了机臂连接组件的快速定位安装和防止支撑管110的轴向移动，保证了无人飞行器1的飞行稳定性。
实施例8
本实施例提供一种用于无人飞行器的机架连接组件。
请参阅图3-7，本实施例是在实施例4、实施例5、实施例6和实施例7的基础上，在连接部120容纳空腔1203的侧壁1202和辅助件130上形成有 相互配合的卡接结构。例如，可以是在侧壁1202上形成凹槽1204并在辅助件130上形成的与该凹槽1204相配合的凸起或者凸条1306，从而组成上述卡接结构。当然也可以是在侧壁1202上形成的凸起并在辅助件130上形成与该凸起相配合的凹槽1204。
在本实施例中，凸起或者凸条1306的形状可以根据实际需要进行设置，在此不作具体的限定。
优选地，在辅助件130上形成凸条1306，并在侧壁1202上形成与该凸条1306相匹配的定位槽1205，从而使得凸条1306可以卡接在该定位槽1205中，从而防止辅助件130的轴向移动。
需要说明的是，当在辅助件130上形成凸条1306，并在侧壁1202上形成有与该凸条1306相配合的定位槽1205，以及在管壁1102上形成有与该凸条1306相配合的卡槽1103的情况下，凸条1306可以同时卡紧在定位槽1205和卡槽1103中，从而实现机架连接组件10的定位并防止其轴向移动。
另外，在本实施例中，当设置上述卡接结构时，支撑管110开口端的管壁1102可以抵顶在上述卡接结构上，从而可以省略上述实施例4所述的凸起。尤其是当支撑管110的管壁1102上设置有与上述凸条1306相配合的卡槽1103时，支撑管110和凸条1306可以在轴向上卡紧，因此，更可以省略上述实施例4所述的凸起。
本实施例的机架连接组件10，通过在容纳空腔1203的侧壁1202和辅助件130上设置相互配合的卡接结构，实现了辅助件130和连接部120的卡紧，从而提高了机架连接组件10与连接部120的连接强度，提高了无人飞行器1的飞行稳定性。
实施例9
本实施例提供一种用于无人飞行器的机架连接组件。
继续参考图3-7，本实施例是在实施例3、实施例4、实施例5、实施例6、实施例7和实施例8的基础上，具体将辅助件130设置为包括支撑块，该支撑块设置在支撑管110开口端的空腔1101内，并且该支撑块与连接部120容纳空腔1203的侧壁1202一起将开口端的管壁1102夹持在这二者之间。同时， 紧固件140的头部穿过侧壁1202和管壁1102固定在支撑块上，也即，紧固件140的两端分别与侧壁1202和支撑块接触。
具体的，本实施例的支撑块应做广义解释，例如可以是具有曲面的片状结构或者是实心或者空心的块状结构，本领域技术人员可以根据无人飞行器1的参数具体设置。上述无人飞行器1的参数例如可以是：无人飞行器1的重量、机架连接组件10的强度以及飞行速度和提升力、灵活度等。
本实施例的机架连接组件10，通过将辅助件130具体设置成支撑块可以减少组件的结构数量，从而降低无人飞行器1的重量，以提高无人飞行器1的续航时间和飞行速度以及爬升能力等性能。
进一步，可以将支撑块设置成包括：第一支撑块1301和第二支撑块1302。这两个支撑块对称设置在支撑管110开口端的空腔1101的轴线两侧，从而将空腔1101轴线两侧的管壁1102分别夹持在第一支撑块1301和容纳空腔1203的侧壁1202之间，以及夹持在第二支撑块1302和容纳空腔1203的侧壁1202之间。具体来说，就是如图3所示的那样，右侧的管壁1102夹持在右侧侧壁1202和第一支撑块1301之间，左侧的管壁1102夹持在左侧侧壁1202和第二支撑块1302之间。
同时，为了紧固上述第一支撑块1301和第二支撑块1302，将紧固件140设置成包括：第一紧固件140和第二紧固件140。第一紧固件140的头部穿过右侧的侧壁1202和右侧的管壁1102固定在第一支撑块1301上从而实现右侧的管壁1102的夹紧。第二紧固件140的头部穿过左侧的侧壁1202和左侧的管壁1102固定在第二支撑块1302上从而实现左侧的管壁1102的夹紧。
优选地，继续参考图3，紧固件140还可以包括：第三紧固件140和第四紧固件140。其中，第三紧固件140与第一紧固件140间隔一定距离，第四紧固件140与第三紧固件140对称，从而使得第一紧固件140和第二紧固件140的轴线与第三紧固件140和第四紧固件140的轴线平行。
在本实施例中，第一支撑块1301和第二支撑块1302可以为任意形状的能够为支撑管110开口端的管壁1102提供支撑的结构，例如，可以是，具有与管壁1102内表面形状匹配的曲面的板状结构。并且，可以优选地将第一支 撑块1301和第二支撑块1302的形状设置成相同的以降低零部件的加工难度，提高加工效率。同时，第一紧固件140、第二紧固件140、第三紧固件140、第四紧固件140中的一个或者多个可以使用螺丝或者铆钉。例如，可以是如图3-6所示的使用四个螺丝，从而实现机架连接组件10的可快速拆装的目的；或者，也可以是如图7所示的使用四个铆钉，从而进一步降低管壁1102与侧壁1202和支撑块之间的间隙，提高无人飞行器1的飞行稳定性。
再进一步，可以在第一支撑块1301和第二支撑块1302的两端设置连接板，以将第一支撑块1301和第二支撑块1302连接在一起。这样，在使用紧固件140固定管壁1102和第一支撑块1301、第二支撑块1302时，第一支撑块1301和第二支撑块1302所受到的压紧力可以部分分散到连接板上，从而防止管壁1102和支撑块之间出现间隙，提高无人飞行器1飞行时的稳定性。优选地，如图3-6所示，连接板包括：第一连接板1303和第二连接板1304。其中，第一连接板1303和第二连接板1304间隔一段距离设置。通过设置第一连接板1303和第二连接板1304可以进一步分散第一支撑块1301和第二支撑块1302的压紧力，从而进一步减少管壁1102与第一支撑块1301、第二支撑块1302之间的间隙，提高无人飞行器1的飞行稳定性。更优选地，第一连接板1303和第二连接板1304的弯曲方向相反，从而能更好的适应第一支撑块1301和第二支撑块1302所受到的压紧力的方向，使得二者受到的压紧力能更好的被分散以降低管壁1102与第一支撑块1301、第二支撑块1302之间的间隙，从而提高无人飞行器1的飞行稳定性。
更进一步，在第一支撑块1301上还可以设置加强筋1305，以提高第一支撑块1301对管壁1102的支撑能力。具体的，加强筋1305设置在第一支撑块1301的内侧表面，也即第一支撑块1301与远离管壁1102内表面的一侧表面，也即，图4中所示的右侧表面。在固定管壁1102和辅助件130时，第一紧固件140的头部穿过连接部120容纳空腔1203的侧壁1202、管壁1102和第一支撑块1301后固定在加强筋1305上。同理的，加强筋1305也可以设置在第二支撑块1302的内侧表面上。优选地，如图4、图6和图7所示，可以在第一支撑块1301的内侧表面以及第二支撑块1302的内侧表面均设置加强 筋1305，同时设置两个分别与加强筋1305连接的第一连接板1303和第二连接板1304，从而形成一个与第一支撑块1301和第二支撑块1302的内侧表面连接的环状结构。当然，在具体制作时，可以将上述第一支撑块1301、第二支撑块1302、第一连接板1303、第二连接板1304以及加强筋1305一体制造从而形成一体结构以加强辅助件130的结构强度。
实施例10
本实施例提供一种无人飞行器。
请参考图1-8，本实施例提供的无人飞行器1包括：中心架20、机架连接组件10、旋翼动力装置30。其中，中心架20的顶部设置有定位模块，中心架20内部设置有处理模块，中心架20的下方搭载挂载物。同时，中心架20通过机架连接组件10承载旋翼动力装置30。
在本实施例中，旋翼动力装置30通过机架连接组件10承载，这样，在无人飞行器1飞行时通过旋翼动力装置30中旋翼的转动可以为无人飞行器1提供升力以及转向力等，以实现无人飞行器1在空中飞行、悬停以及转向等各种飞行姿态的调整。并且通过中心架20的处理芯片控制旋翼动力装置30中的电子调速器控制电动机的输出以控制旋翼的转速从而控制无人飞行器1的飞行速度，以实现无人飞行器1飞行节奏的控制。
在其他实施例中，机架连接组件10用于连接脚架与中心架，这样，在无人飞行器1停靠的时候，可以通过脚架动力装置驱动机架连接组件10相对于中心架20展开，从而使无人飞行器1平稳的停靠在地面或者其他定着物上。而在无人飞行器1起飞或者飞行时，可以通过脚架动力装置驱动机架连接组件10相对于中心架20收缩，从而避免在飞行过程中机架连接组件10、脚架动力装置与空中的物体发生碰撞，比如与建筑物或者树枝刮擦损坏无人飞行器1，进而提高无人飞行器1的使用寿命。并且，将承载脚架动力装置的机架连接组件10收缩以后可以使中心架20下方的挂载物不被遮挡，而且当挂载物需要从中心架20展开时也能避免其与机架连接组件10发生干涉从而避免挂载物损坏。
举例来说，当中心架20的挂载物是云台以及云台上安装的拍摄装置 时：在起飞时或者云台展开前通过脚架动力装置驱动机架连接组件10收缩，然后云台展开并完成整个拍摄过程后收回。最后，在无人飞行器1降落前再通过脚架动力装置重新驱动机架连接组件10展开以实现稳定停靠在地面或者定着物上的目的。通过上述过程，机架连接组件10和脚架动力装置在云台展开、拍摄以及收回的整个过程中均不会与其发生干涉，也不会阻挡云台上所搭载的拍摄装置的拍摄，从而可以提高整个无人飞行器1的工作效率和使用寿命。
以上详细描述了无人飞行器1的旋翼动力装置30和脚架动力装置通过机架连接组件10承载的具体方案。但是，本领域技术人员应该理解的是，并不限于旋翼动力装置30通过机架连接组件10承载，或者，仅是脚架动力装置通过机架连接组件10承载。并且，对于多旋翼无人飞行器1而言，可以仅某些旋翼动力装置30通过下述的机架连接组件10承载，也可以全部的旋翼动力装置30均通过下述的机架连接组件10承载。比如，图8示出了一个六旋翼的无人飞行器1，在具体设置时，可以在将一个旋翼动力装置30或者两个及以上的旋翼动力装置30通过下述的机架连接组件10承载。因此，上述对于无人飞行器1的具体描述，应该理解为对本申请发明构思的一种描述，而不应该视为对本申请的具体限制。
为了描述更加简洁，以下将以承载旋翼动力装置30的机架连接组件10为例进行介绍，本领域技术人员可以根据下述机架连接组件10的示例设置无人飞行器1的脚架。但正如上述对无人飞行器1的具体描述中所指出的那样，根据下述承载旋翼动力装置30的机架连接组件10的构思设置的承载脚架动力装置的机架连接组件10依然未脱离本发明的保护范围。
另外，虽然图8仅示出了具有六旋翼的无人飞行器1，但本领域技术人员应该理解，本申请可以应用到具有任意旋翼个数的无人飞行器1上，例如，单旋翼无人飞行器1、双旋翼无人飞行器1、四旋翼无人飞行器1等。
请参阅图1和图2，本实施例中的机架连接组件10支撑管110、辅助件130和紧固件140。其中，支撑管110的开口端用于与无人飞行器1的中 心架20上所设置的连接部120相互套接在一起。支撑管110可以与旋翼动力装置30或者脚架动力装置连接。例如，当支撑管110为机臂或其组成元件时，旋翼动力装置30可以承载在支撑管110上或与支撑管110相连的连接件上。同时，在支撑管110开口端的内侧或者外侧设置辅助件130，从而使得支撑管110的开口端的管壁1102夹持在该辅助件130和中心架20的连接部120之间。紧固件140穿过开口端的管壁1102将支撑管110、连接部120和辅助件130固定连接在一起，并且该紧固件140的两端分别与辅助件130和连接部120抵接。可以理解的是，当支撑管110为脚架或其组成元件时，脚架动力装置能够驱动支撑管110或与支撑管110相连的连接件转动，以使该脚架在脚架动力装置的作用力下伸展或收缩
在本申请中，支撑管110应做广义解释，其可以是一根完全中空的管材，也即管壁1102内仅形成有一个空腔1101。同时，也可以是管壁1102内被隔成有多个空腔1101的管材。甚至还可以是具有大部分实心仅具有少部分空心以与中心架20连接部120套接的管材。本领域技术人员应该理解，对于管材中间空腔1101的任意结构变形均应包括在本申请的保护范围之内。
在本本实施例中，支撑管110的材质可以是任意材质，比如可以是钢材、铝材或者合金等金属材料，当然，也可以是具有一定强度的非金属材料。优选地，支撑管110可以使用碳纤维材料制作，从而使无人飞行器1具有更好的连接强度和更轻的重量。
同时，在本实施例中，支撑管110的形状可以是任意形状，比如，该支撑管110的横截面可以是圆形、方形、其他闭合曲线或者闭合直线。当然，此处说的圆形、方形等是包括了支撑管110管壁1102内的空腔1101在内的整体横截面形状，如果去除空腔1101，仅从管壁1102的横截面而言，那么该支撑管110的横截面为圆环、方环等。优选地，该支撑管110的横截面为椭圆，去除空腔1101后为椭圆环。将支撑管110的管壁1102横截面做成椭圆环，可以减少机架连接组件10的风阻，提高无人飞行器1的飞行效率。并且，将支撑管110的管壁1102横截面做成椭圆环还可以取得更好的结构强度。
在本实施例中，中心架20上设置的连接部120，可以是与中心架20固 定连接的连接部120或者是与中心架20可转动连接的连接部120。具体的，当中心架20和连接部120固定连接时，其固定连接方式例如可以是焊接、铆接、键连接或者螺栓连接等各种固定连接方式。当中心架20和连接部120可转动连接时，其可转动连接方式例如可以是铰接、枢接等各种现有的可转动连接方式。同时，连接部120的材料、形状和结构在本实施例中不作具体限定，本领域技术人员可以根据无人飞行器1的类型、设计重量以及连接强度等条件选择合适的工件作为连接部120。举例来说，可以选择具有空腔1101的管材，或者选择实心的主体作为连接部120。
在本实施例中，紧固件140可以选择螺丝或者铆钉。当然，也可以选择其他现有技术中合适的具有紧固功能的零件作为本实施例的紧固件140。将紧固件140的一端穿过开口端的管壁1102将辅助件130、支撑管110和连接部120固定连接在一起，并且，通过这种连接方式，紧固件140的两端分别与辅助件130和连接部120抵接，从而不会直接对支撑管110开口端的管壁1102施加作用力，而是通过辅助件130和连接部120进行传递，这种面接触的力传递可以减少管壁1102的变形，提高无人飞行器1的飞行稳定性。
本实施例的机架连接组件10，通过在支撑管110开口端的管壁1102的内侧或者外侧设置辅助件130，从而将支撑管110开口端的管壁1102夹持在辅助件130和连接部120之间。这样，在使用紧固件140固定支撑管110开口端、辅助件130和连接部120时，紧固件140的两端分别与辅助件130和连接部120抵接，也即，支撑管110开口端的管壁1102由点接触式受力改变为面接触式受力。通过以上方式就可以将管壁1102受到的紧固力分散，避免了点接触所造成的管壁1102变形的问题，也就使得支撑管110开口端的管壁1102和连接部120之间不容易产生间隙，解决了无人飞行器1在飞行过程中或者收起和展开脚架或机臂时由于连接不稳造成的抖动现象，提高了无人飞行器1的飞行稳定性。并且，设置在支撑管110开口端空腔1101内的辅助件130或者套接在支撑管110开口端空腔1101内的连接部120还能为支撑管110的开口端提供支撑力，进一步保证支撑管110开口端的管壁1102不变形。实施例11
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例10提供的技术方案的基础上，将固定连接上述连接部120、支撑管110开口端的管壁1102和辅助件130的紧固件140设置为多个，并将这多个紧固件140在开口端的管壁1102上均匀分布，以提高支撑管110和连接部120、辅助件130的连接强度，进一步提高无人飞行器1在飞行中的稳定性。
具体的，在本实施例中，多个均匀分布的紧固件140可以位于支撑管110轴线的同一侧，也可以位于支撑管110轴线的两侧。优选地，这多个紧固件140对称设置在支撑管110的轴线两侧从而使支撑管110开口端的管壁1102以及连接部120、辅助件130的受力更加均匀，同时还能使得机架连接组件10对抗轴向剪切力的能力更好。在本申请中，支撑管110的轴线两侧是指经过支撑管110的轴线作一个任意切面，被该切面分成的两部分即为支撑管110的轴线两侧。比如，参考附图2所示，在该机架连接组件10中，共设置有四个紧固螺丝，在四个紧固螺丝对称设置在支撑管110轴线的上部和下部。其中，上部设置两个螺丝，下部设置两个螺丝。每个螺丝的两端均分别与辅助件130和连接部120抵接，从而将开口端的管壁1102夹持在辅助件130和连接部120之间。在图2中，轴线两侧即使过轴线做一个左右方向的切面，从而该切面的上下两部分分别为支撑管110的轴线两侧。
本实施例的无人飞行器1，通过设置多个均匀分布在支撑管110开口端管壁1102上的紧固件140，可以加强机架连接组件10与连接部120的连接强度，使得无人飞行器1在飞行中不易出现抖动，提高其飞行稳定性。并且，通过将多个紧固件140对称设置，还可以使机架连接组件10的受力更加均衡，增强其抗轴向剪切力的能力，提高无人飞行器1的使用寿命。
实施例12
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例10和实施例11提供的技术方案的基础上，将连接部120套设在支撑管110开口端的空腔1101中，并在支撑 管110开口端的管壁1102外侧设置辅助件130。
在本实施例中，连接部120可以为能够套设在支撑管110开口端空腔1101内并且与空腔1101形状基本一致的任意结构零件。比如，空心或者实心的圆柱体或者其他能够与管壁1102的内表面大致可接触的具有任意横截面形状的空心或者实心物体。优选地，如图2所示，连接部120包括一个圆柱体和一个椭圆柱体。其中，椭圆柱体的右端套接在管壁1102横截面为椭圆环的支撑管110的开口端的空腔1101内；圆柱体右端与椭圆柱体的左端固定连接，圆柱体的左端与中心架20固定连接或者可转动连接。更优选地，圆柱体和椭圆柱体通过一体成形方式加工成一体件，从而增加连接部120的结构强度，以提升无人飞行器1的飞行性能。再优选地，椭圆柱体的外壁与支撑管110开口端的管壁1102形状和大小完全匹配，从而使椭圆柱体能够为支撑管110开口端的管壁1102提供良好的支撑力，进而在用紧固件140进行固定时，椭圆柱体的支撑力能够更好的防止管壁1102变形，从而提高无人飞行器1的稳定性。
在本实施例中，辅助件130可以是垫片或者筒状的衬套。优选地，辅助件130可以是弹性垫片或者筒状的弹性衬套，从而可以通过弹性垫片或者弹性衬套的弹性变形力以进一步减小管壁1102的变形，以减少管壁1102与连接部120之间的间隙。当然，在本实施例中对于垫片的大小、形状和具体的结构不作具体的限定，技术人员可以选用现有技术中任意合适的垫片或者制作与具体的无人飞行器1类型相匹配的垫片。同时，筒状衬套的大小和具体细部结构也不作具体限定，技术人员也可从现有技术中选择合适的衬套或者制作与具体无人飞行器1类型相匹配的衬套结构。优选地，如图2所示，设置一实心的连接部120，该连接部120一端与中心架20连接，一端则套接在支撑管110开口端的空腔1101内。同时，在支撑管110开口端的管壁1102外侧设置筒状的弹性外衬套。并且在弹性外衬套、开口端的管壁1102以及套接在开口端空腔1101内的连接部120上开设同轴的螺丝孔。然后使用螺丝或者铆钉穿过螺丝孔将弹性外衬套、管壁1102和连接部120固定在一起。由于在图2中使用了四个均匀分布在轴线两侧且对称的紧固件140(螺丝或者铆 钉)，所以可以直接在弹性外衬套、管壁1102和连接部120上开设通孔，以减少加工流程和步骤以节省加工时间和成本。
进一步，可以在连接部120上形成一凸台1201，以使支撑管110开口端的管壁1102抵顶在该凸台1201的端面上从而限制支撑管110的轴向移动。比如，如图2所示，当连接部120包括一体成形的圆柱体和椭圆柱体时，可以将支撑管110开口端的管壁1102直接抵顶在圆柱体的右端，从而避免支撑管110的轴向移动，提高无人飞行器1的飞行稳定性。
本实施例的无人飞行器1，通过将连接部120套设在机架连接组件10的支撑管110开口端的空腔1101内，并在支撑管110开口端的管壁1102外侧设置辅助件130，可以简化机架连接组件10的结构，并且当连接部120为实心的一体结构时能够为无人飞行器1提供更优的结构强度，从而使无人飞行器1具有更好的飞行稳定性。而且，位于支撑管110开口端的空腔1101内的连接部120可以为开口端的管壁1102提供支撑力以进一步减少固定时管壁1102的变形，从而提高无人飞行器1飞行时的稳定性。同时，弹性垫片或者弹性外衬套的使用还能进一步减少支撑管110开口端的管壁1102的变形，进一步提高无人飞行器1的飞行稳定性。另外，通过螺丝固定支撑管110、辅助件130和连接部120还可以实现机架连接组件10的快速拆装，提高无人飞行器1的环境适应性和保存时占用的空间大小，也为不同旋翼动力装置30的更换提供了可能，从而可以使多旋翼无人飞行器1可以具有不同动力的旋翼动力装置30，以提供整体的飞行性能。
实施例13
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例10和实施例11提供的技术方案的基础上，在连接部120形成有容纳空腔1203，并将支撑管110套接在该容纳空腔1203内。辅助件130的右端伸入到支撑管110开口端的空腔1101内，从而将支撑管110开口端的管壁1102夹持在连接部120容纳空腔1203位置的侧壁1202和辅助件130之间。
具体的，在本实施例中，连接部120可以是带有容纳空腔1203并能与中 心架20连接且该容纳空腔1203内可以套接支撑管110开口端的任意结构，例如可以是半封闭的管材，当然这个半封闭的管材的两端可以具有不同的管径。优选地，大管径一端为封闭端，用于与中心架20连接，从而增大连接部120与中心架20之间的接触面积以提高二者的连接强度。小管径一端为套接端，支撑管110开口端的套接在该套接端的容纳空腔1203内，以使支撑管110开口端的管壁1102能夹持在容纳空腔1203的侧壁1202与辅助件130之间。
本实施例的无人飞行器1，通过在机架连接组件10的连接部120上形成容纳空腔1203，并将支撑管110的开口端套接在该容纳空腔1203内，同时还在支撑管110开口端的空腔1101内设置辅助件130，从而使得紧固件140固定连接部120和支撑管110时，可以将支撑管110开口端的管壁1102夹持在容纳空腔1203的侧壁1202和辅助件130之间，从而减少支撑管110的变形，提高无人飞行器1在空中的稳定性。并且，支撑管110开口端的管壁1102并不是与紧固件140的端部点接触，而是通过辅助件130和侧壁1202与紧固件140的两端面接触，进一步减少固定时管壁1102的变形，提高无人飞行器1的飞行稳定性。
进一步，为了限制支撑管110在轴向上的移动，还可以在辅助件130上形成凸起，并肩支撑管110开口端的管壁1102抵顶在该凸起的端面上。在本实施例中，对于上述凸起的形状和大小不作具体的限定，例如该凸起可以具有从辅助件130上表面往支撑管110开口端方向倾斜延伸的端面，这样，管壁1102可以插入凸起端面与辅助件130上表面之间，从而卡紧该支撑管110。
实施例14
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例13提供的技术方案的基础上，将辅助件130和连接部120制作成为一体成型结构，从而加强辅助件130和连接部120的连接强度，进而提高支撑管110和连接部120连接以后抗轴向剪切力的能力，从而使无人飞行器1在空中飞行更加稳定。
具体的，在本实施例中，辅助件130可以是一端能够伸入支撑管110开 口端的空腔1101内并为开口端的管壁1102提供支撑的任意结构，例如可以是实心或者空心的圆柱块、椭圆柱块，或者其他具有弧形表面的块状结构或板状结构。
本实施例的无人飞行器1，通过将机架连接组件10中的辅助件130和连接部120制作成为一体成型结构，提高了支撑管110和连接部120以及辅助件130的连接强度，使得无人飞行器1飞行更加稳定。
实施例15
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例13提供的技术方案的基础上，将辅助件130和连接部120设置为分体结构，辅助件130的一端设置在支撑管110的开口端的空腔1101内，辅助件130的另一端设置在连接部120的容纳空腔1203内。
在本实施例中，辅助件130可以为任意单一结构的零件或者是多个零件组合在一起的组合结构，其仅需满足可以从内部支撑上述支撑管110开口端的管壁1102并一端位于开口端的空腔1101内、另一端位于连接部120的容纳空腔1203内即可。例如，该辅助件130可以是圆柱块、椭圆块或者两个具有曲面的支撑板所组成的组合结构。
本实施例的无人飞行器1，通过将机架连接组件10中的辅助件130和连接部120设置为分体结构，可以非常方便的控制支撑管110的管径并调整辅助件130的形状结构以使支撑管110、辅助件130和连接部120容纳空腔1203的侧壁1202具有更好的配合度以减少三者之间用紧固件140固定后的间隙，从而提高无人飞行器1在飞行时的稳定性。
实施例16
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例13、实施例14和实施例15的基础上，再辅助件130上形成凸条1306，并在支撑管110开口端的管壁1102上形成与该凸条1306相配合的卡槽1103，从而在装配时可以将凸条1306卡入该卡槽1103中，实现装配的快速定位并防止支撑管110的轴向移动。
在本实施例中，凸条1306的形状大小，可以根据实际需要进行设置，在此不作具体的限定。
需要说明的是，当支撑管110的管壁1102上设置有与上述凸条1306相配合的卡槽1103时，支撑管110和凸条1306可以在轴向上卡紧，因而可以省略上述实施例13中所述的凸起。
本实施例的无人飞行器1，通过在机架连接组件10中的辅助件130和支撑管110开口端的管壁1102上设置相互配合的凸条1306和卡槽1103，实现了机臂连接组件的快速定位安装和防止支撑管110的轴向移动，保证了无人飞行器1的飞行稳定性。
实施例17
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例13、实施例14、实施例15和实施例16的基础上，在连接部120容纳空腔1203的侧壁1202和辅助件130上形成有相互配合的卡接结构。例如，可以是在侧壁1202上形成凹槽1204并在辅助件130上形成的与该凹槽1204相配合的凸起或者凸条1306，从而组成上述卡接结构。当然也可以是在侧壁1202上形成的凸起并在辅助件130上形成与该凸起相配合的凹槽1204。
在本实施例中，凸起或者凸条1306的形状可以根据实际需要进行设置，在此不作具体的限定。
优选地，在辅助件130上形成凸条1306，并在侧壁1202上形成与该凸条1306相匹配的定位槽1205，从而使得凸条1306可以卡接在该定位槽1205中，从而防止辅助件130的轴向移动。
需要说明的是，当在辅助件130上形成凸条1306，并在侧壁1202上形成有与该凸条1306相配合的定位槽1205，以及在管壁1102上形成有与该凸条1306相配合的卡槽1103的情况下，凸条1306可以同时卡紧在定位槽1205和卡槽1103中，从而实现机架连接组件10的定位并防止其轴向移动。
另外，在本实施例中，当设置上述卡接结构时，支撑管110开口端的管壁1102可以抵顶在上述卡接结构上，从而可以省略上述实施例13所述的凸 起。尤其是当支撑管110的管壁1102上设置有与上述凸条1306相配合的卡槽1103时，支撑管110和凸条1306可以在轴向上卡紧，因此，更可以省略上述实施例13所述的凸起。
本实施例的无人飞行器1，通过在机架连接组件10中容纳空腔1203的侧壁1202和辅助件130上设置相互配合的卡接结构，实现了辅助件130和连接部120的卡紧，从而提高了机架连接组件10与连接部120的连接强度，提高了无人飞行器1的飞行稳定性。
实施例18
本实施例提供一种无人飞行器。
继续参考图1-8，本实施例是在实施例3、实施例13、实施例14、实施例15、实施例6和实施例17的基础上，具体将辅助件130设置为包括支撑块，该支撑块设置在支撑管110开口端的空腔1101内，并且该支撑块与连接部120容纳空腔1203的侧壁1202一起将开口端的管壁1102夹持在这二者之间。同时，紧固件140的头部穿过侧壁1202和管壁1102固定在支撑块上，也即，紧固件140的两端分别与侧壁1202和支撑块接触。
具体的，本实施例的支撑块应做广义解释，例如可以是具有曲面的片状结构或者是实心或者空心的块状结构，本领域技术人员可以根据无人飞行器1的参数具体设置。上述无人飞行器1的参数例如可以是：无人飞行器1的重量、机架连接组件10的强度以及飞行速度和提升力、灵活度等。
本实施例的无人飞行器1，通过将机架连接组件10中的辅助件130具体设置成支撑块可以减少组件的结构数量，从而降低无人飞行器1的重量，以提高无人飞行器1的续航时间和飞行速度以及爬升能力等性能。
进一步，可以将支撑块设置成包括：第一支撑块1301和第二支撑块1302。这两个支撑块对称设置在支撑管110开口端的空腔1101的轴线两侧，从而将空腔1101轴线两侧的管壁1102分别夹持在第一支撑块1301和容纳空腔1203的侧壁1202之间，以及夹持在第二支撑块1302和容纳空腔1203的侧壁1202之间。具体来说，就是如图3所示的那样，右侧的管壁1102夹持在右侧侧壁1202和第一支撑块1301之间，左侧的管壁1102夹持在左侧侧壁1202和第 二支撑块1302之间。
同时，为了紧固上述第一支撑块1301和第二支撑块1302，将紧固件140设置成包括：第一紧固件140和第二紧固件140。第一紧固件140的头部穿过右侧的侧壁1202和右侧的管壁1102固定在第一支撑块1301上从而实现右侧的管壁1102的夹紧。第二紧固件140的头部穿过左侧的侧壁1202和左侧的管壁1102固定在第二支撑块1302上从而实现左侧的管壁1102的夹紧。
优选地，请参阅图4，紧固件140还可以包括：第三紧固件140和第四紧固件140。其中，第三紧固件140与第一紧固件140间隔一定距离，第四紧固件140与第三紧固件140对称，从而使得第一紧固件140和第二紧固件140的轴线与第三紧固件140和第四紧固件140的轴线平行。
在本实施例中，第一支撑块1301和第二支撑块1302可以为任意形状的能够为支撑管110开口端的管壁1102提供支撑的结构，例如，可以是，具有与管壁1102内表面形状匹配的曲面的板状结构。并且，可以优选地将第一支撑块1301和第二支撑块1302的形状设置成相同的以降低零部件的加工难度，提高加工效率。同时，第一紧固件140、第二紧固件140、第三紧固件140、第四紧固件140中的一个或者多个可以使用螺丝或者铆钉。例如，可以是如图3-7所示的使用四个螺丝，从而实现机架连接组件10的可快速拆装的目的。或者，也可以是如图7所示的使用四个铆钉，从而进一步降低管壁1102与侧壁1202和支撑块之间的间隙，提高无人飞行器1的飞行稳定性。
再进一步，可以在第一支撑块1301和第二支撑块1302的两端设置连接板，以将第一支撑块1301和第二支撑块1302连接在一起。这样，在使用紧固件140固定管壁1102和第一支撑块1301、第二支撑块1302时，第一支撑块1301和第二支撑块1302所受到的压紧力可以部分分散到连接板上，从而防止管壁1102和支撑块之间出现间隙，提高无人飞行器1飞行时的稳定性。优选地，如图3-7所示，连接板包括：第一连接板1303和第二连接板1304。其中，第一连接板1303和第二连接板1304间隔一段距离设置。通过设置第一连接板1303和第二连接板1304可以进一步分散第一支撑块1301和第二支撑块1302的压紧力，从而进一步减少管壁1102与第一支撑块1301、第二支 撑块1302之间的间隙，提高无人飞行器1的飞行稳定性。更优选地，第一连接板1303和第二连接板1304的弯曲方向相反，从而能更好的适应第一支撑块1301和第二支撑块1302所受到的压紧力的方向，使得二者受到的压紧力能更好的被分散以降低管壁1102与第一支撑块1301、第二支撑块1302之间的间隙，从而提高无人飞行器1的飞行稳定性。
更进一步，在第一支撑块1301上还可以设置加强筋1305，以提高第一支撑块1301对管壁1102的支撑能力。具体的，加强筋1305设置在第一支撑块1301的内侧表面，也即第一支撑块1301与远离管壁1102内表面的一侧表面，也即，图4中所示的右侧表面。在固定管壁1102和辅助件130时，第一紧固件140的头部穿过连接部120容纳空腔1203的侧壁1202、管壁1102和第一支撑块1301后固定在加强筋1305上。同理的，加强筋1305也可以设置在第二支撑块1302的内侧表面上。优选地，如图4、图6和图7所示，可以在第一支撑块1301的内侧表面以及第二支撑块1302的内侧表面均设置加强筋1305，同时设置两个分别与加强筋1305连接的第一连接板1303和第二连接板1304，从而形成一个与第一支撑块1301和第二支撑块1302的内侧表面连接的环状结构。当然，在具体制作时，可以将上述第一支撑块1301、第二支撑块1302、第一连接板1303、第二连接板1304以及加强筋1305一体制造从而形成一体结构以加强辅助件130的结构强度。
以上所述仅为本发明的实施例，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，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，或者对其中部分或者全部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发明各实施例技术方案的范围。

Claims (54)

  1. 一种用于无人飞行器的机架连接组件，其特征在于，包括：支撑管、辅助件和紧固件；
    所述支撑管用于连接所述无人飞行器的中心架，所述中心架设有用于与所述支撑管的开口端相互套接的连接部；所述辅助件设于所述支撑管的开口端内侧或外侧，以将所述支撑管的开口端的管壁夹持在所述辅助件与所述中心架的连接部之间；
    所述紧固件用于将所述辅助件、所述支撑管的开口端、以及所述中心架的连接部固定连接起来；
    其中，所述紧固件穿过所述支撑管的开口端的管壁，并且所述紧固件的两端分别与所述辅助件及所述中心架的连接部抵接。
  2. 根据权利要求1所述的机架连接组件，其特征在于，所述紧固件为多个，所述多个紧固件在所述管壁上均匀分布。
  3. 根据权利要求2所述的机架连接组件，其特征在于，所述多个紧固件对称设置在所述支撑管的轴线两侧。
  4. 根据权利要求1所述的机架连接组件，其特征在于，所述连接部套设在所述支撑管的开口端的空腔内，所述辅助件设置在所述开口端的管壁外侧。
  5. 根据权利要求4所述的机架连接组件，其特征在于，所述辅助件为弹性垫片或刚性垫片。
  6. 根据权利要求4所述的机架连接组件，其特征在于，所述辅助件为筒状的弹性衬套或刚性衬套。
  7. 根据权利要求4所述的机架连接组件，其特征在于，所述连接部上形成有凸台，所述支撑管的开口端的管壁抵顶在所述凸台的端面上以限制所述支撑管的轴向移动。
  8. 根据权利要求1所述的机架连接组件，其特征在于，所述连接部形成有容纳空腔，所述支撑管的开口端套设在所述容纳空腔内，所述辅助件伸入所述开口端的空腔内，以将所述管壁夹持在所述辅助件和所述容纳空腔的侧壁之间。
  9. 根据权利要求8所述的机架连接组件，其特征在于，所述辅助件上形 成有凸起，所述支撑管的开口端的管壁抵顶在所述凸起的端面上以限制所述支撑管的轴向移动。
  10. 根据权利要求8所述的机架连接组件，其特征在于，所述辅助件和所述连接部为一体成型结构。
  11. 根据权利要求8所述的机架连接组件，其特征在于，所述辅助件与所述连接部为分体结构，所述辅助件的一端设在所述支撑管的开口端的空腔内，所述辅助件的另一端设在所述连接部的容纳空腔内。
  12. 根据权利要求11所述的机架连接组件，其特征在于，所述辅助件上形成有凸条，所述支撑管开口端的管壁上形成有卡槽，所述凸条卡接在所述卡槽内。
  13. 根据权利要求11所述的机架连接组件，其特征在于，所述连接部的容纳空腔的侧壁和辅助件形成有相互配合的卡接结构。
  14. 根据权利要求13所述的机架连接组件，其特征在于，所述卡接结构为所述侧壁上形成的凹槽以及所述辅助件上形成的凸条。
  15. 根据权利要求8所述的机架连接组件，其特征在于，所述辅助件包括支撑块，所述支撑管的开口端的管壁夹持在所述连接部的容纳空腔的侧壁与所述支撑块之间，所述紧固件的头部穿过所述侧壁和管壁固定在所述支撑块上。
  16. 根据权利要求15所述的机架连接组件，其特征在于，所述支撑块包括：第一支撑块和第二支撑块；所述第一支撑块和第二支撑块对称设置在所述空腔的轴线两侧；所述支撑管的开口端的管壁夹持在所述第一支撑块与所述侧壁之间，以及所述支撑管的开口端的管壁还夹持在所述第二支撑块与侧壁之间；
    所述紧固件包括：第一紧固件和第二紧固件；所述第一紧固件的头部穿过所述侧壁以及所述管壁固定在所述第一支撑块上；所述第二紧固件的头部穿过所述侧壁以及所述管壁固定在所述第二支撑块上。
  17. 根据权利要求16所述的机架连接组件，其特征在于，所述辅助件还包括连接板，所述连接板的两端分别连接所述第一支撑块和第二支撑块。
  18. 根据权利要求17所述的机架连接组件，其特征在于，所述连接板包括：第一连接板和第二连接板，所述第一连接板和第二连接板间隔一段距离 设置。
  19. 根据权利要求18所述的机架连接组件，其特征在于，所述第一连接板和第二连接板的弯曲方向相反。
  20. 根据权利要求16所述的机架连接组件，其特征在于，所述第一支撑块设置有加强筋，所述第一紧固件的头部穿过所述侧壁、所述管壁以及所述第一支撑块固定在所述加强筋上。
  21. 根据权利要求1所述的机架连接组件，其特征在于，所述连接部还用于与所述中心架固定连接。
  22. 根据权利要求1所述的机架连接组件，其特征在于，所述连接部还用于与所述中心架可转动连接。
  23. 根据权利要求1所述的机架连接组件，其特征在于，所述支撑管为所述无人飞行器的机臂或机臂组件。
  24. 根据权利要求1所述的机架连接组件，其特征在于，所述支撑管为所述无人飞行器的脚架或脚架组件。
  25. 根据权利要求1所述的机架连接组件，其特征在于，所述紧固件为螺丝或者铆钉。
  26. 根据权利要求1所述的机架连接组件，其特征在于，所述支撑管为碳纤维管。
  27. 根据权利要求1所述的机架连接组件，其特征在于，所述支撑管的横截面为椭圆环。
  28. 一种无人飞行器，其特征在于，包括：中心架及机架连接组件；
    所述机架连接组件包括：支撑管、辅助件和紧固件；
    所述支撑管用于连接所述中心架，所述中心架设有用于与所述支撑管的开口端相互套接的连接部；所述辅助件设于所述支撑管的开口端内侧或外侧，以将所述支撑管的开口端的管壁夹持在所述辅助件与所述中心架的连接部之间；
    所述紧固件用于将所述辅助件、所述支撑管的开口端、以及所述中心架的连接部固定连接起来；
    其中，所述紧固件穿过所述支撑管的开口端的管壁，并且所述紧固件的两端分别与所述辅助件及所述中心架的连接部抵接。
  29. 根据权利要求28所述的无人飞行器，其特征在于，所述紧固件为多个，所述多个紧固件在所述管壁上均匀分布。
  30. 根据权利要求29所述的无人飞行器，其特征在于，所述多个紧固件对称设置在所述支撑管的轴线两侧。
  31. 根据权利要求28所述的无人飞行器，其特征在于，所述连接部套设在所述支撑管的开口端的空腔内，所述辅助件设置在所述开口端的管壁外侧。
  32. 根据权利要求31所述的无人飞行器，其特征在于，所述辅助件为弹性垫片或刚性垫片。
  33. 根据权利要求31所述的无人飞行器，其特征在于，所述辅助件为筒状的弹性衬套或刚性衬套。
  34. 根据权利要求31所述的无人飞行器，其特征在于，所述连接部上形成有凸台，所述支撑管的开口端的管壁抵顶在所述凸台的端面上以限制所述支撑管的轴向移动。
  35. 根据权利要求28所述的无人飞行器，其特征在于，所述连接部形成有容纳空腔，所述支撑管的开口端套设在所述容纳空腔内，所述辅助件伸入所述开口端的空腔内，以将所述管壁夹持在所述辅助件和所述容纳空腔的侧壁之间。
  36. 根据权利要求35所述的无人飞行器，其特征在于，所述辅助件上形成有凸起，所述支撑管的开口端的管壁抵顶在所述凸起的端面上以限制所述支撑管的轴向移动。
  37. 根据权利要求35所述的无人飞行器，其特征在于，所述辅助件和所述连接部为一体结构。
  38. 根据权利要求35所述的无人飞行器，其特征在于，所述辅助件与所述连接部为分体结构，所述辅助件的一端设在所述支撑管的开口端的空腔内，所述辅助件的另一端设在所述连接部的容纳空腔内。
  39. 根据权利要求38所述的无人飞行器，其特征在于，所述辅助件上形成有凸条，所述支撑管开口端的管壁上形成有卡槽，所述凸条卡接在所述卡槽内。
  40. 根据权利要求38所述的无人飞行器，其特征在于，所述连接部的容 纳空腔的侧壁和辅助件形成有相互配合的卡接结构。
  41. 根据权利要求40所述的无人飞行器，其特征在于，所述卡接结构为所述侧壁上形成的凹槽以及所述辅助件上形成的凸条。
  42. 根据权利要求35所述的无人飞行器，其特征在于，所述辅助件包括支撑块，所述支撑管的开口端的管壁夹持在所述连接部的容纳空腔的侧壁与所述支撑块之间，所述紧固件的头部穿过所述侧壁和管壁固定在所述支撑块上。
  43. 根据权利要求42所述的无人飞行器，其特征在于，所述支撑块包括：第一支撑块和第二支撑块；所述第一支撑块和第二支撑块对称设置在所述空腔的轴线两侧；所述支撑管的开口端的管壁夹持在所述第一支撑块与所述侧壁之间，以及所述支撑管的开口端的管壁还夹持在所述第二支撑块与侧壁之间；
    所述紧固件包括：第一紧固件和第二紧固件；所述第一紧固件的头部穿过所述侧壁以及所述管壁固定在所述第一支撑块上；所述第二紧固件的头部穿过所述侧壁以及所述管壁固定在所述第二支撑块上。
  44. 根据权利要求43所述的无人飞行器，其特征在于，所述辅助件还包括连接板，所述连接板的两端分别连接所述第一支撑块和第二支撑块。
  45. 根据权利要求44所述的无人飞行器，其特征在于，所述连接板包括：第一连接板和第二连接板，所述第一连接板和第二连接板间隔一段距离设置。
  46. 根据权利要求45所述的无人飞行器，其特征在于，所述第一连接板和第二连接板的弯曲方向相反。
  47. 根据权利要求43所述的无人飞行器，其特征在于，所述第一支撑块设置有加强筋，所述第一紧固件的头部穿过所述侧壁、所述管壁以及所述第一支撑块固定在所述加强筋上。
  48. 根据权利要求28所述的无人飞行器，其特征在于，所述连接部还用于与所述中心架固定连接。
  49. 根据权利要求28所述的无人飞行器，其特征在于，所述连接部还用于与所述中心架可转动连接。
  50. 根据权利要求28所述的无人飞行器，其特征在于，所述支撑管为所述无人飞行器的机臂或机臂组件。
  51. 根据权利要求28所述的无人飞行器，其特征在于，所述支撑管为所述无人飞行器的脚架或脚架组件。
  52. 根据权利要求28所述的无人飞行器，其特征在于，所述紧固件为螺丝或者铆钉。
  53. 根据权利要求28所述的无人飞行器，其特征在于，所述支撑管为碳纤维管。
  54. 根据权利要求28所述的无人飞行器，其特征在于，所述支撑管的横截面为椭圆环。
PCT/CN2016/078287 2016-04-01 2016-04-01 用于无人飞行器的机架连接组件及无人飞行器 WO2017166275A1 (zh)

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