WO2020237678A1 - Structure de raccordement, cadre et aéronef - Google Patents

Structure de raccordement, cadre et aéronef Download PDF

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Publication number
WO2020237678A1
WO2020237678A1 PCT/CN2019/089680 CN2019089680W WO2020237678A1 WO 2020237678 A1 WO2020237678 A1 WO 2020237678A1 CN 2019089680 W CN2019089680 W CN 2019089680W WO 2020237678 A1 WO2020237678 A1 WO 2020237678A1
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WO
WIPO (PCT)
Prior art keywords
elastic body
arm
rotating shaft
rotating
connection structure
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2019/089680
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English (en)
Chinese (zh)
Inventor
蒋李
吴利鑫
陈志强
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
Original Assignee
SZ DJI Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to PCT/CN2019/089680 priority Critical patent/WO2020237678A1/fr
Priority to CN201980004972.9A priority patent/CN111278729A/zh
Publication of WO2020237678A1 publication Critical patent/WO2020237678A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B64C1/069—Joining arrangements therefor
    • 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
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal

Definitions

  • This application relates to the technical field of aircraft vibration damping connection, in particular, to a connection structure, a frame, and an aircraft.
  • the power system is the main source of vibration of the fuselage, and the vibration of the fuselage will cause many problems, such as IMU over-range, aliasing, and structural fatigue.
  • the vibration effect of the fuselage is reduced by adding a vibration reduction system between the fuselage and the arm.
  • a vibration reduction system between the fuselage and the arm.
  • drones and other aircraft have volume requirements, and the addition of a vibration reduction system will undoubtedly increase
  • the overall size of the machine, and the existing fuselage and the arm need to achieve both a rotation function and a self-locking function, which leads to increased difficulty in setting the vibration reduction system and poor vibration reduction effect.
  • connection structure that can solve at least one of the above technical problems.
  • a connecting structure is used for the rotational connection of a machine arm and a fuselage, so that the machine arm can rotate relative to the fuselage and remain at a preset position relative to the fuselage
  • the connecting structure Including: an elastic body for connecting with one of the arm and the fuselage; a rotating shaft assembly connected with the elastic body and for connecting with the other of the arm and the fuselage Connected so that the rotation of the arm relative to the fuselage has at least one stroke interval; wherein the stroke interval has a first position, a second position, and is located between the first position and the second position In the third position, the shaft assembly is also used to abut and compress the elastic body when the arm is approaching the third position, and the elastic body is also used to when the arm exceeds the In the third position, the arm is automatically rotated to the first position or the second position.
  • a frame comprising: the connecting structure described in any of the above technical solutions; an arm connected to one of an elastic body and a rotating shaft assembly of the connecting structure; a body, connected to the elastic body and the The other one of the shaft assembly is connected.
  • An aircraft includes: the frame described in any one of the above technical solutions and a power system, the power system is arranged on an arm in the frame and used to provide flight power for the aircraft.
  • connection structure uses an elastic body to connect to one of the arm and the fuselage, the rotating shaft assembly is connected to the other of the arm and the fuselage, and the rotating shaft assembly is connected to the elastic body to realize the connection of the fuselage Assemble with the arm, and make the following three functions between the arm and the fuselage:
  • the use of the rotating shaft assembly enables relative rotation between the fuselage and the arm to meet the rotation requirements of the arm relative to the fuselage, and realize the function of the arm can be rotated relative to the fuselage to fold or unfold;
  • the elastic body can efficiently absorb vibration energy with its vibration-absorbing and buffering properties.
  • the elastic body By connecting the elastic body with one of the arm and the fuselage, the elastic body is in one of the arm and the fuselage and the shaft.
  • the components play a role of good vibration interception, thereby reducing the vibration energy transmitted to the fuselage, greatly reducing the impact of the arm and the power system on the arm on the vibration of the fuselage, and improving the vibration damping effect on the fuselage To improve the performance of the aircraft;
  • the rotating shaft assembly compresses the elastic body when the arm is close to the third position in the stroke interval so that the elastic body can accumulate energy. After the arm exceeds the third position, the elastic body releases elastic potential energy to drive the arm to reset to the first position or the second position in the stroke interval, thereby realizing the self-locking function between the arm and the body.
  • the elastic body of the connection structure can absorb vibration to prevent the vibration energy of the arm from being transmitted to the fuselage between the arm and the fuselage, and solve the problem of fuselage vibration.
  • the elastic body in this design can cooperate with the shaft assembly during the rotation of the arm, and compress to accumulate energy and elastically recover to respond to the release of energy. It is integrated into the self-locking and rotating process between the arm and the fuselage.
  • connection structure integrating vibration reduction, rotation, and self-locking functions is realized, which avoids separate establishment in the prior art
  • the poor compatibility of the damping system with the rotation and self-locking process leads to problems such as difficulty in setting the damping system and poor damping effect.
  • this also achieves the streamlining of product parts and is more conducive to the miniaturization of the aircraft. It is also more conducive to promotion and application in the field; on the other hand, unlike the traditional rotating shaft assembly that uses springs for energy storage and discharge, this application uses elastic bodies for energy storage and discharge.
  • the volume of the elastic body is much smaller than that of the spring, and compared with the spring, the compression stroke can be greatly reduced, which can save the internal space requirement of the product, which is more conducive to the compact design of the product and the reduction of the product size , In order to facilitate the miniaturized design of the aircraft.
  • FIG. 1 is a schematic diagram of a front view of a connection structure according to an embodiment of the present application
  • FIG. 2 is a schematic bottom view of the connection structure shown in FIG. 1;
  • Figure 3 is a schematic diagram of the B-B cross-sectional structure in Figure 2;
  • FIG. 4 is a schematic diagram of the three-dimensional structure of the connection structure shown in FIG. 1;
  • FIG. 5 is an exploded structure diagram of the connection structure shown in FIG. 1;
  • Fig. 6 is a schematic diagram of the assembly structure of the connecting structure and the arm in an embodiment of the present application.
  • FIG. 7 is a schematic diagram of the assembly structure shown in FIG. 6 from another perspective
  • FIG. 8 is a schematic bottom view of the assembled structure shown in FIG. 6;
  • Fig. 9 is a schematic diagram of the C-C cross-sectional structure in Fig. 8.
  • Fig. 10 is an exploded structural diagram of the assembly structure shown in Fig. 6;
  • FIG. 11 is a schematic diagram of the assembly structure of the connecting structure and the fuselage in an embodiment of the present application.
  • FIG. 12 is a schematic diagram of the assembly structure of the connecting structure and the fuselage in an embodiment of the present application.
  • Fig. 13a is a graph of the relationship between frequency and acceleration amplitude of the fuselage in an embodiment of the present application.
  • Figure 13b is a graph of the relationship between frequency and acceleration amplitude of the fuselage in the existing frame
  • Figure 14a is a graph of the relationship between frequency and acceleration amplitude of the arm in an embodiment of the present application.
  • Figure 14b is a graph of the relationship between frequency and acceleration amplitude of the arm in the existing frame.
  • connection structure the frame, and the aircraft according to some embodiments of the present application will be described with reference to FIGS. 1-12.
  • connection structure 10 provided by the embodiment of the first aspect of the present application is used for the rotational connection of the arm 20 and the body 30, so that the arm 20 can rotate relative to the body 30, and Keep in a preset position relative to the body 30.
  • the adaptation between the arm 20 and the fuselage 30 is such that the arm 20 can rotate relative to the fuselage 30 between the folded position and the unfolded position, so as to correspondingly realize the arm 20 relative to the fuselage. 30 folded or unfolded.
  • the aforementioned preset position of the middle arm 20 relative to the fuselage 30 may be specifically the folded position, the unfolded position, or even the one or more intermediate positions between the folded position and the unfolded position. Any intermediate position.
  • the connecting structure 10 includes an elastic body 100 and a rotating shaft assembly 200.
  • the elastomer 100 can be understood as a material that can be restored to its original shape after removal of external force, or it can be understood as a material that deforms significantly under stress and can quickly return to its original state after stress relaxation. And size of polymer materials.
  • the elastic body 100 is used to connect with one of the arm 20 and the body 30; the rotating shaft assembly 200 is connected to the elastic body 100 and is used to connect with the other of the arm 20 and the body 30 so that the arm 20 is opposite
  • the rotation movement of the fuselage 30 has at least one stroke interval; wherein the stroke interval has a first position, a second position, and a third position between the first position and the second position, and the rotating shaft assembly 200 is also used for the arm
  • the elastic body 100 is pressed against and compressed by the 20 approaching the third position, and the elastic body 100 is also used to automatically rotate the arm 20 to the first position or the second position when the arm 20 exceeds the third position.
  • the rotating shaft assembly 200 can abut against the elastic body 100 to make The elastic body 100 is compressed to store energy.
  • the elastic body 100 releases elastic potential energy and drives the arm 20 , So that the arm 20 rotates to the first position.
  • the elastic body 100 releases elastic potential energy and drives the arm 20 so that the arm 20 rotates to the second position.
  • the arm 20 is maintained at the first position or the second position relative to the body 30, that is, the self-locking function of the arm 20 relative to the body 30 is realized.
  • the process of the arm 20 approaching the third position from the second position can also be used to understand, so that the elastic body 100 does not exceed the third position when the arm 20 is removed.
  • the automatically driven machine arm 20 is reset to the second position; and when the machine arm 20 exceeds the third position and is between the third position and the first position, the automatically driven machine arm 20 is reset to the first position.
  • one of the first position and the second position can be understood as the folded position, and the other can be correspondingly understood as the unfolded position.
  • the aforementioned The preset position in can be adjusted in both the folded position and the unfolded position according to the product state.
  • the multiple travel intervals are arranged in sequence.
  • the first end of the travel interval The first position can be understood as the folded position
  • the second position of the trailing end of the stroke interval can be understood as the unfolded position.
  • the aforementioned preset position can be in the first position and the second position of multiple stroke intervals according to the product state ( Including the folding position of the head end and the unfolding position of the tail end) for adjustment.
  • the second position of the previous stroke section may be used as the first position of the next stroke section; of course, this solution is not limited to this, and Relatively independent relationships between adjacent stroke sections are also possible.
  • the elastic body 100 can absorb vibration to prevent the vibration energy of the arm 20 from being transmitted to the body 30 between the arm 20 and the body 30, so as to solve the vibration problem of the body 30, and Compared with the existing technology that additionally adds a vibration reduction system to reduce vibration, the elastic body 100 in the present design can cooperate with the shaft assembly 200 during the rotation of the arm 20 and compress to store energy and elastically recover Respond with energy, so as to integrate well with the self-locking and rotating process between the arm 20 and the fuselage 30. In this way, on the one hand, the integration of the connection structure 10 with the functions of vibration reduction, rotation and self-locking is realized.
  • the volume of the elastic body 100 is much smaller than that of the spring, and compared with the spring, the compression stroke can be greatly reduced, thereby saving the internal space of the product.
  • the demand is more conducive to the compact design of the product, and the reduction of product dimensions is conducive to the miniaturization of the aircraft.
  • the elastic body 100 is used for the connection of the body 30, and the rotating shaft assembly 200 is used for the connection of the arm 20.
  • the rotating shaft assembly 200 includes: a rotating shaft 210 and a rotating member 220, wherein the rotating shaft 210 is connected to the elastic body 100; the rotating member 220 is provided on the rotating shaft 210 And can rotate around the rotating shaft 210, the rotating member 220 is used to connect with the other of the arm 20 and the fuselage 30, and the rotating member 220 is in cooperation with the elastic body 100; wherein, the rotating member 220 rotates to make the machine
  • the elastic body 100 is compressed.
  • the elastic body 100 is released, and the elastic restoring force generated by the elastic body 100 makes the rotating member
  • the 220-driven arm 20 rotates to the first position or the second position.
  • the elastic body 100 is connected with the rotating shaft 210 for providing the rotation center to the rotating part 220, which is not only simple and convenient to assemble, but also can ensure the assembly stability of the rotating shaft 210, thereby improving the rotating part rotating around the rotating shaft 210 220, and the rotation stability of the arm 20 or the body 30 connected to the rotating member 220 and rotating with the rotating member 220 around the rotating shaft 210. It also allows the elastic body 100 to directly absorb vibrations on the rotating shaft 210 for providing the center of rotation. It can be understood that the rotating shaft 210 is a component for providing the center of rotation to the rotating member 220, which can be equivalent to the entire rotating shaft assembly 200. The base or foundation directly absorbs the vibration of the shaft 210.
  • the elastic body 100 faces the shaft assembly 200 in all directions.
  • the vibration energy can be well absorbed, so as to maximize the interception effect on the vibration energy between the arm 20 and the fuselage 30, the vibration reduction effect is better and more reliable, and the vibration impact of the fuselage 30 is further improved.
  • the elastic body 100 is provided with an elastic body shaft hole 110, and a part of the rotating shaft 210 is inserted into the elastic body shaft hole 110.
  • a shaft hole fit is formed between the elastic body 100 and the rotating shaft 210, so that the elastic body 100 can efficiently absorb vibration at any radial position of the rotating shaft 210.
  • the entire connecting structure 10 is not only compressed or released by the elastic body 100 for energy storage or
  • the direction of discharging energy can have better flexibility (it can also be said that the rigidity is less), and the entire connection structure 10 has better flexibility in any radial direction of the shaft 210, so that the connection structure 10 is in the arm 20 and the fuselage.
  • the vibration reduction effect between 30 and 30 is better, and the vibration effect of the fuselage 30 is further improved.
  • the rotating shaft 210 and the elastic body shaft hole 110 there is a transitional fit or an interference fit between the rotating shaft 210 and the elastic body shaft hole 110.
  • the rotation stability of the body 30 is correspondingly improved, and at the same time, the vibration absorption effect of the elastic body 100 on the rotating shaft 210 can be further improved.
  • the rotating shaft 210 is in transitional fit with the elastic body shaft hole 110, that is, there is a certain amount of clearance between the rotating shaft 210 and the elastic body shaft hole 110, or the two just fit, or there is a certain tightness between the two. In this way, it is more convenient to insert the rotating shaft 210 into the elastic body shaft hole 110 to realize assembly, and to ensure product assembly efficiency.
  • the ratio of the axial length of the part of the rotating shaft 210 in the elastic body shaft hole 110 to the total axial length of the rotating shaft 210 is greater than or equal to 1/4.
  • the axial direction of the rotating shaft 210 may refer to the direction indicated by ax in FIG. 1, FIG. 3, FIG. 4, FIG. 6 and FIG.
  • the axial length is also the length along the ax direction.
  • the stabilizing effect of the elastic body 100 on the rotating shaft 210 can be further improved, avoiding the deflection of the rotating shaft 210, and improving the rotation stability of the rotating member 220 rotating around the rotating shaft 210 and even the arm 20 or the body 30 connected to the rotating member 220.
  • the mating length of the rotating shaft 210 and the elastic body shaft hole 110 to account for more than 1/4 of the total length of the rotating shaft 210, it can also ensure that the elastic body 100 fully absorbs the vibration energy of the rotating shaft 210 and further improve the vibration influence of the fuselage 30.
  • the ratio of the axial length of the part of the shaft 210 in the elastic body shaft hole 110 to the total axial length of the shaft 210 is greater than or equal to 1/3.
  • the shape of the elastic body shaft hole 110 is adapted to the axial cross-sectional shape of the part of the shaft 210 located in the elastic body shaft hole 110, so that the opposite surface of the shaft 210 and the elastic body shaft hole 110 can be in uniform contact or Keeping the curvature equal, in this way, the elastic body 100 has a better vibration absorbing effect on the rotating shaft 210, and it is also more conducive to improving the stability of the elastic body 100 on the rotating shaft 210.
  • the elastic body shaft hole 110 may be designed as a circular hole, and the axial cross-sectional shape of the part of the rotating shaft 210 located in the elastic body shaft hole 110 is circular.
  • the elastic body shaft hole 110 can also be designed as an elliptical hole, a square hole, a rectangular hole, a trapezoidal hole, etc., and accordingly, the rotating shaft 210 is located in the elastic body shaft hole 110
  • the axial section shape of the part can also be designed as ellipse, square, rectangle, trapezoid, etc.
  • the shape of the inner peripheral surface of the elastic body shaft hole 110 and the axial cross-sectional shape of the part where the shaft 210 is located in the elastic body shaft hole 110 is circular, elliptical, square, rectangular, trapezoidal, or triangular , Pentagons, semicircles and other shapes not listed, should be macroscopically understood that their shapes are roughly round, elliptical, square, rectangular, trapezoidal, triangle, pentagon, semicircle, etc., rather than special It means that its shape must strictly conform to the standardized circular, oval, square, rectangular, trapezoidal, triangular, pentagonal, semicircular and other shapes.
  • a first stop portion 211 and a second stop portion 212 are provided on the rotating shaft 210, and the first stop portion 211 and the second stop portion 211
  • the stop portions 212 are distributed at intervals along the axial direction of the rotation shaft 210, and the portion of the rotation shaft 210 located between the first stop portion 211 and the second stop portion 212 is connected to the elastic body 100 and the rotation member 220, so that the elastic body 100 and The rotating member 220 is axially confined between the first stop portion 211 and the second stop portion 212.
  • the first stop part 211 and the second stop part 212 are arranged on both sides of the elastic body 100 and the rotating part 220 along the axial direction of the rotating shaft 210, so that the elastic body 100 and the rotating part 220 can be axially distributed. It is limited to be located between the first stop portion 211 and the second stop portion 212, so that, on the one hand, the vibration absorption effect of the elastic body 100 on the vibration of the rotating shaft 210 in the axial direction is ensured, thereby realizing the vibration absorption direction of the elastic body 100 on the rotating shaft 210 Comprehensive coverage (axial and arbitrary radial) to further strengthen the damping effect on the fuselage 30.
  • one of the first stop portion 211 and the second stop portion 212 is a stop structure 2111 integrally constructed on the rotating shaft 210, and the other is assembled and connected to the rotating shaft 210.
  • Fixing member 2121 That is, one of the first stop portion 211 and the second stop portion 212 is an integral structure with the rotating shaft 210, and the other is a fixing member 2121 that can be assembled or disassembled with the rotating shaft 210, so that the rotating shaft The assembly between 210 and the elastic body 100 and the rotating part 220 is more convenient.
  • the first stop portion 211 stops the stop structure 2111 and is integrally configured on the rotating shaft 210. More specifically, as shown in FIGS. 3 and 5, the stop structure 2111 is specifically a shoulder structure formed on the rotating shaft 210.
  • the second stop part 212 is a fixing member 2121, and the fixing member 2121 can be a nut or a threaded lock ring.
  • the rotating shaft 210 is provided with a threaded structure, and the fixing member 2121 is threadedly connected with the rotating shaft 210 for assembly.
  • first stop part 211 and the second stop part 212 may be both fixed parts 2121 that can be assembled or disassembled with the shaft 210.
  • the first stop portion 211 is located at one end of the shaft 210 in the axial direction and abuts against the elastic body 100. This makes the axial abutment position of the elastic body 100 and the rotating shaft 210 adjacent to the end of the rotating shaft 210, which can further strengthen the vibration absorption effect on the rotating shaft 210 and even the entire rotating shaft assembly 200, and further improve the vibration influence of the fuselage 30.
  • the first stop portion 211 has a stop end surface 2112, and the stop end surface 2112 is arranged along the outer circumference of the rotating shaft 210 and abuts against the elastic body 100.
  • the supporting stress of the stop end face 2112 to the elastic body 100 can be more evenly distributed along the circumferential direction of the elastic body 100, avoiding the concentrated stress of the elastic body 100, thereby reducing the risk of crushing of the elastic body 100 and extending the product life.
  • the elastic body 100 is configured with a first boss 121 at a location corresponding to the first stop part 211, and the first boss 121 of the elastic body 100 is The stop portion 211 abuts. This strengthens the elasticity of the elastic body 100 for the part that abuts the first stop portion 211, thereby further strengthening the vibration damping effect of the elastic body 100 on the rotating shaft 210.
  • the design of the first boss 121 can help extend the mating length of the elastic body shaft hole 110 and the rotating shaft 210 without increasing the volume of the elastic body 100 too much, and strengthen the stability of the rotating shaft 210.
  • the first boss 121 is a circular cylinder
  • the stop structure 2111 is a circular shoulder distributed around the outer circumference of the rotating shaft 210.
  • the outer contour line 221 of the cross section formed by the rotation member 220 being intercepted by a plane perpendicular to the center line of the rotation shaft 210 is non-circular, and the rotation The piece 220 is used to be inserted into the connecting hole 21 on the other of the arm 20 and the body 30; wherein the outer contour line 221 is adapted to the shape of the inner peripheral contour of the connecting hole 21.
  • This structural design makes the rotation The part 220 is not easy to slip between the arm 20 or the body 30, which has the advantages of efficient and reliable torque transmission, and also facilitates the assembly between the rotating part 220 and the connecting hole 21, for example, inserting the rotating part 220 into the connecting hole 21 Within.
  • the outer contour line 221 includes an unclosed arc line segment 221a and a connecting line segment 221b.
  • the arc line segment 221a and the connecting line segment 221b are alternately connected; wherein the connecting line segment 221b is a straight line segment, a broken line segment or a curvature different from that of a circular arc.
  • the arc segment of the line segment 221a is a straight line segment, a broken line segment or a curvature different from that of a circular arc.
  • the center line of the rotating shaft 210 is perpendicular to the paper surface and its vertical point can refer to the O point shown in FIG. 2, where the outer contour line 221 of the projection of the rotating member 220 along the center line of the rotating shaft 210 (or rotating The outer contour line 221) of the cross section perpendicular to the center line of the rotating shaft 210 of the piece 220 is non-circular.
  • the outer contour line 221 includes two arc line segments 221a and two connecting line segments 221b.
  • the connecting line segment 221b is selected as a straight line segment, and the two ends of one of the straight line segments correspond to the two circles.
  • Each end of the arc segment 221a is connected, and both ends of the other straight segment are connected to the other ends of the two arc segments 221a, so that the two straight segments and the two arc segments 221a alternately around the center line of the shaft 210 Arrange and enclose a closed outer contour line 221.
  • the two arc line segments 221a are relatively distributed, and the middle of the arc line segment 221a protrudes away from the center line of the rotating shaft 210; the two straight line segments are relatively distributed.
  • the two circular arc line segments 221a are distributed axisymmetrically or rotationally symmetrically, and the two straight line segments are distributed axisymmetrically or rotationally symmetrically.
  • Such a design can make the rotating member 220 receive more uniform and symmetrical force during the transmission process, which is more conducive to improving the carrying capacity of the rotating member 220 and improving product quality.
  • the number of arc line segments 221a may not be limited to the two listed, but can also be designed to be one, three, or more than three according to requirements. Accordingly, the number of connecting line segments 221b is not limited. Of the 2 items listed, it can be designed as 1, 3 or more than 3 according to requirements.
  • the rotating member 220 is provided with a rotating member shaft hole 222, and a part of the rotating shaft 210 penetrates the rotating member shaft hole 222, so that the rotating member 220 can rotate around the rotating shaft 210.
  • the rotation stability of the rotating part 220 is ensured, and after the vibration on the arm 20 is transmitted to the rotating part 220, the rotating part 220 will be radially transmitted to the rotating shaft 210 , And further radially transmitted to the elastic body 100 through the rotating shaft 210, so that the vibration energy is finally absorbed by the elastic body 100, thereby ensuring the absorption efficiency of the vibration energy of the rotating member 220, and further improving the vibration damping effect of the fuselage 30.
  • the elastic body 100 and the rotating member 220 respectively form a shaft hole fit with the rotating shaft 210, which can make the rotating member 220 transmit a small torque to the elastic body 100 through the rotating shaft 210, and reduce the wear of the elastic body 100.
  • the rotating shaft assembly 200 further includes a movable part 230, and the movable part 230 and the rotating part 220 form a cam drive cooperation, and the rotating part 220 It can rotate relative to the movable part 230 so that the movable part 230 compresses or releases the elastic body 100; wherein, when the contact point between the rotating part 220 and the movable part 230 reaches the highest point of the cam, the elastic body 100 is compressed. When the contact point of the member 230 avoids the highest point of the cam, the elastic body 100 is released, and the elastic restoring force generated by the elastic body 100 drives the rotating member 220 to rotate, so that the arm 20 automatically rotates to the first position or the second position.
  • the rotation movement of the rotating piece 220 can be converted into the displacement movement of the movable piece 230 for output, that is, the rotation of the rotating piece 220 is driven
  • the movable part 230 performs displacement movement and compresses the elastic body 100.
  • the elastic body 100 elastically returns and drives the movable part 230 to make displacement movement, so that the movable part 230 drives the rotating part 220 to rotate, and the rotating part 220 drives the arm 20 to rotate for resetting. .
  • the use of the movable part 230 to achieve the purpose of transmission while having the advantages of simple structure, compact layout, small size, convenient assembly, etc., and the cam driving fit formed between the movable part 230 and the rotating part 220 as a clutch-type fit, can play
  • the amount of vibration transmitted from the rotating part 220 to the movable part 230 is reduced, and then the vibration energy transmitted to the fuselage 30 is improved, and the stability of the fuselage 30 is improved.
  • the elastic body 100 is located on one side of the movable part 230 along the axial direction of the rotating shaft 210, and the rotating part 220 is located on the other side of the movable part 230 along the axial direction of the rotating shaft 210.
  • the movable part 230 corresponds to the rotating part 220.
  • a first cam structure 231 is configured on the surface of the rotating member 220
  • a second cam structure 223 is configured on the surface of the rotating member 220 corresponding to the movable member 230.
  • the first cam structure 231 and the second cam structure 223 form a cam drive fit.
  • the arrangement of the elastic body 100, the movable part 230, and the rotating part 220 along the axis of the rotating shaft 210 has the advantages of compact layout, accurate positioning and limiting of the movable part 230, and the movable part 230 is located between the elastic body 100 and Between the rotating parts 220, in this way, the movable stroke of the movable part 230 can be designed to be shorter, and the driving accuracy of the movable part 230 by the rotating part 220 and the elastic body 100 can be higher, thereby further improving the running accuracy of the product.
  • one of the first cam structure 231 and the second cam structure 223 includes a slider, the other includes a plurality of grooves, and the two opposite sidewall surfaces of the grooves are configured as slopes or arcs and make the grooves
  • the opening of ⁇ gradually increases, and the rotating member 220 rotates relative to the movable member 230 so that the slider slides along the side wall of the groove.
  • adjacent sidewall surfaces of adjacent grooves are connected to and define a convex peak structure 2311, and the apex of the convex peak structure 2311 is formed as the highest point of the cam.
  • the movable member 230 is provided with a first cam structure 231
  • the first cam structure 231 includes two grooves
  • the rotating member 220 is provided with a second cam structure 223
  • the second cam structure 223 includes Take the slider as an example:
  • two peak structures 2311 are formed on the movable member 230, corresponding to the first peak structure and the second peak structure, the two grooves correspond to the first groove and the second groove, the first groove and The second grooves are arranged along the circumference of the rotating shaft 210, each groove has two side wall surfaces, and the first side wall surface of the first groove is adjacent to the first side wall surface of the second groove and defines a first convex peak Structure, the second side wall surface of the first groove is adjacent to the second side wall surface of the second groove and defines a second peak structure.
  • the first side wall surface and the second side wall surface of the first groove jointly form an arc-shaped recess with a gradually increasing opening
  • the first side wall surface and the second side wall surface of the second groove jointly form a gradually increasing opening. Large arc-shaped depressions to reduce sliding resistance.
  • the rotating part 220 is formed with a convex surface protruding toward the movable part 230.
  • the convex 233 structure defined by the convex surface serves as a slider.
  • the number of the sliders can be one or more.
  • the surface of the convex surface is convex. Curved to reduce sliding resistance.
  • the sliding block When the arm 20 is in the first position, the sliding block extends into the first groove to fit with the first groove.
  • the sliding block When the arm 20 is in the second position, the sliding block extends into the second groove to fit with the second groove.
  • the slider slides along the first side wall surface of the first groove and approaches the first peak structure, so that the movable part 230 is lifted up by the rotating part 220 and Compressed elastomer 100, where
  • the elastic body 100 releases elastic potential energy to push the movable part 230 to lean the movable part 230 against the rotating part 220.
  • the slider moves along the first position.
  • the first side wall surface of a groove slides away from the first convex peak structure, so that the rotating member 220 rotates relative to the movable member 230, until the slider returns to the position where the first groove fits, and the arm 20 is reset to the first groove accordingly.
  • the elastic body 100 releases elastic potential energy to push the movable part 230 to make the movable part 230 lean against the rotating part 220.
  • the slider slides along the first side wall surface of the second groove.
  • the rotating member 220 rotates relative to the movable member 230 until the sliding block reaches the position where it fits with the second groove, and the arm 20 is correspondingly reset to the second position.
  • the movable part 230 is provided with a movable part shaft hole 232, a part of the rotating shaft 210 is inserted into the movable part shaft hole 232, and the movable part 230 moves along the axial direction of the rotating shaft 210 to compress or Release the elastomer 100.
  • the movable part 230 and the rotating part 220 can be positioned by the rotating shaft 210. This ensures that the cam transmission between the movable part 230 and the rotating part 220 is efficient, Accurate and stable, to ensure the reliability of the self-locking function of the rotating shaft assembly 200.
  • the rotating shaft 210 can guide the movement of the movable part 230, so that the movable part 230 can compress or release the elastic body 100 along the axial direction of the rotating shaft 210, thereby corresponding control
  • the direction of expansion and contraction of the elastic body 100 is more conducive to ensuring the high efficiency of energy storage and discharging of the elastic body 100, while improving the force effect of the elastic body 100 and prolonging the service life of the elastic body 100.
  • the elastic body 100 is configured with a second boss 122 corresponding to the movable part 230, and the second boss 122 of the elastic body 100 abuts against the movable part 230.
  • the second boss 122 is used to abut against the movable part 230, which strengthens the elasticity of the part where the elastic body 100 abuts against the movable part 230, thereby further strengthening the vibration damping and vibration absorption of the elastic body 100 to the rotating shaft 210 effect.
  • the design of the second boss 122 can help extend the mating length of the elastic body shaft hole 110 and the rotating shaft 210 without excessively increasing the volume of the elastic body 100, and strengthen the stability of the rotating shaft 210.
  • the second boss 122 is a circular cylinder
  • the movable member 230 is located at and abuts against one end of the circular cylinder in the axial direction.
  • the movable part 230 is connected to the elastic body 100.
  • the elastic body 100 is connected to one of the arm 20 or the body 30, by connecting the movable part 230 with the elastic body 100, the movable part 230 and the one of the arm 20 or the body 30 can be further realized Relatively fixed, this not only enables the elastic body 100 to absorb and intercept the vibration transmitted by the movable part 230, and improves the vibration problem of the fuselage 30, but also restricts the rotation of the movable part 230 with the rotating part 220, and improves the movable part 230 and The cam matching accuracy between the rotating member 220 improves the self-locking effect between the arm 20 and the body 30.
  • the elastic body 100 is connected to the movable part 230 to limit the amount of movement of the movable part 230 relative to the elastic body 100, so as to limit the friction between the movable part 230 and the elastic body 100 and prevent the elastic body 100 from wearing.
  • Example 1 The movable part 230 is bonded to the elastic body 100.
  • the opposite surfaces of the movable part 230 and the elastic body 100 are bonded together using glue, double-sided tape and other adhesive materials to realize the fixing of the movable part 230 and the elastic body 100.
  • Example two as shown in FIG. 5, one of the movable member 230 and the elastic body 100 is provided with a protrusion 233, and the other is provided with a recess 124, and the protrusion 233 is inserted into the recess 124 to fix the movement.
  • Piece 230 and elastomer 100 are provided with a protrusion 233, and the other is provided with a recess 124, and the protrusion 233 is inserted into the recess 124 to fix the movement.
  • the number of protrusions 233 and the number of recesses 124 can be the same, so that the protrusions 233 and the recesses 124 can form a one-to-one corresponding plug-in assembly.
  • protrusions can also be designed.
  • the number of 233 is less than the number of recessed portions 124, so that the protrusion 233 is plugged and assembled with a part of the recessed portion 124.
  • the number of protrusions 233 can be one, the number of recesses 124 can be correspondingly designed as one, and the recesses 124 are arranged corresponding to the protrusions 233.
  • the protrusion 233 is eccentrically arranged with respect to the center line of the rotating shaft 210, so that the protrusion 233 and the recessed portion 124 can be inserted and fitted to transmit torque between the movable part 230 and the elastic body 100, and prevent the movable part 230 from being relative to the elastic body 100. Rotate.
  • this does not exclude the case where the protrusion 233 is arranged concentrically with the rotating shaft 210.
  • the only protrusion 233 When the only protrusion 233 is arranged concentrically with the rotating shaft 210, it can be designed to fit between the protrusion 233 and the recess 124 to restrict the protrusion 233 from being
  • the form of rotation in the recess 124 for example, designing the cross section of the protrusion 233 to be non-circular, can also prevent the movable part 230 from rotating relative to the elastic body 100.
  • the number of the protrusions 233 may be multiple, and the number of the recesses 124 may be correspondingly designed to be multiple, so that the multiple protrusions 233 are inserted into the multiple recesses 124 one by one.
  • the movable part 230 is provided with a plurality of protrusions 233, and the plurality of protrusions 233 are arranged at intervals along the circumference of the movable part 230, so that the movable part 230 is separated from the elastic body 100.
  • the torque transmission is more uniform, thereby improving the force effect of the movable member 230 and the elastic body 100.
  • the protrusion 233 is a cylinder.
  • example 1 and example 2 can also be combined in a non-conflicting manner.
  • the present design is not limited to the above-mentioned example one and example two.
  • the connection between the movable part 230 and the elastic body 100 There are many ways to realize the connection between the movable part 230 and the elastic body 100.
  • the movable part 230 and the second The elastic body 100 is combined into one body in a secondary molding manner.
  • the connection forms of the elastic body 100 and the movable part 230 are not exhaustively listed here, but all belong to the protection scope of this solution without departing from the design concept.
  • the present design is not limited to the form of the above-mentioned embodiment 6.
  • the movable part 230 may not be designed, and the first cam is provided on the elastic body 100.
  • a second cam structure 223 is provided on the rotating member 220, so that the elastic body 100 and the rotating member 220 form a cam driving fit.
  • the rotating shaft 210 is a steel component.
  • the rotating shaft 210 is a carbon steel shaft type part. It has the advantages of low cost, strong rigidity, not easy to deform, etc., ensuring smooth rotation between the arm 20 and the body 30. At the same time, it also helps to ensure the accuracy of the matching between the rotating shaft 210 and the elastic body 100, thereby ensuring that the elastic body 100 is opposite to the rotating shaft 210.
  • the vibration-absorbing effect is also beneficial to ensure the matching accuracy of the rotating part 220 and the movable part 230, thereby ensuring the self-locking accuracy between the arm 20 and the body 30.
  • the elastic body 100 is a rubber body or a ULI colloid.
  • the rubber body and the Youli colloid can have good vibration absorption performance and resilience performance, thereby further improving the vibration damping effect on the fuselage 30, and further improving the self-locking accuracy and self-locking function between the arm 20 and the fuselage 30 Reliability.
  • the elastic body 100 is configured with a plurality of connecting portions 123, and the connecting portions 123 are used to connect with one of the arm 20 and the body 30 At least two of the plurality of connecting portions 123 are distributed axially symmetrically.
  • a plurality of connecting parts 123 are arranged so that at least two of them are axisymmetrically distributed.
  • the elastic body 100 can have at least two symmetrically distributed connecting positions, making it difficult for the elastic body 100 to be connected to the machine connected to it.
  • the relative rotation between the arm 20 or the body 30 improves the assembly stability of the elastic body 100 and further strengthens the vibration damping effect of the elastic body 100.
  • At least two of the plurality of connecting portions 123 form an angle shape with the center line of the rotating shaft assembly 200 as the vertex.
  • the rotating shaft assembly 200 includes a rotating shaft 210.
  • the center line of the rotating shaft assembly 200 can be understood as the center line or axis of the rotating shaft 210.
  • the rotating shaft 210 is arranged perpendicular to the paper surface, and its center line can refer to point O.
  • the elastic body 100 is provided with two connecting parts 123. A ray is drawn from the center of one connecting part 123 from point O, and a ray is drawn from the center of the other connecting part 123 from point O. Two rays form The angle A can be correspondingly understood as the shape of the angle A formed by the two connecting portions 123 roughly.
  • the shape design of the included angle shape can improve the stability of the elastic body 100, so that after the two connecting parts 123 are respectively connected to the arm 20 or the body 30, the elastic body 100 is not easy to move relative to the arm 20 along with the rotating member 220. Or the body 30 rotates to further strengthen the damping effect of the elastic body 100.
  • the connecting portion 123 includes a lug 1231, and the lug 1231 is located at the edge of the elastic body 100.
  • the lug 1231 is used to connect with the arm 20 or the fuselage 30.
  • the elastic body 100 is used for the part connected with the arm 20 or the fuselage 30 and the rotating shaft 210.
  • the center line has a certain distance to form a force arm. This can further strengthen the anti-rotation effect of the elastic body 100.
  • the lug 1231 is provided with a mounting hole 1232.
  • the mounting hole 1232 is used for assembling with a fastener 40 (such as a screw) to be fixed to One of the arm 20 and the body 30. Not only has the effect of simple structure, easy processing and assembly, but also can improve the fastening effect of the elastic body 100 and the arm 20 or the body 30, and avoid the shaking of the elastic body 100, thus improving the vibration absorption and damping effect of the elastic body 100 .
  • the embodiment of the second aspect of the present application provides a frame, including: the connecting structure 10 described in any of the above embodiments; the arm 20, and the elastic body of the connecting structure 10 100 is connected to one of the rotating shaft assembly 200; the body 30 is connected to the other of the elastic body 100 and the rotating shaft assembly 200.
  • one of the arm 20 and the body 30 used to connect with the elastic body 100 is provided with a fixing hole 33 and an avoiding hole 31.
  • the avoiding hole 31 is used to avoid the rotating shaft assembly.
  • 33 is opposite to the mounting hole 1232 of the elastic body 100, and the fastener 40 penetrates the fixing hole 33 and the mounting hole 1232, and locks one of the arm 20 and the body 30 for connecting with the elastic body 100 with the elastic body 100 together.
  • one of the arm 20 and the body 30 for connecting with the elastic body 100 is further provided with a positioning portion 32, and the positioning portion 32 is used to abut against the elastic body 100 so that the mounting hole 1232 and the fixing hole 33 are quickly aligned.
  • the positioning portion 32 is a convex rib, and the convex rib abuts against the side wall surface of the elastic body 100 to realize the positioning of the elastic body 100.
  • the convex rib is in an angled shape, and its apex is leaning against the concave corner formed by the two connecting parts 123, which has better positioning and guiding performance, and makes the convex rib itself have higher strength, which is resistant to elasticity to a certain extent.
  • the body 100 functions as an auxiliary limiter.
  • the rack provided in this embodiment includes: an arm 20, a body 30, and a connecting structure 10.
  • a set of connecting structures 10 may be provided between the arm 20 and the fuselage 30, or as shown in FIGS. 6, 9 and 10, multiple sets of connecting structures 10 may also be provided between the arm 20 and the fuselage 30.
  • each group of connecting structures 10 are respectively connected with the arm 20 and the body 30, so that the arm 20 can rotate relative to the body 30, and the rotation of the arm 20 relative to the body 30 has a first position and a second position.
  • two sets of connecting structures 10 are provided between the arm 20 and the fuselage 30, and preferably, the two sets of connecting structures 10 are arranged at intervals along the axis of the shaft 210. .
  • Each connecting structure 10 includes: an elastic body 100 and a rotating shaft assembly 200.
  • the elastic body 100 is a rubber body or a Uniforce colloid, and the elastic body 100 is connected to the body 30.
  • the rotating shaft assembly 200 includes a rotating shaft 210, a rotating part 220 and a movable part 230.
  • the rotating shaft 210 is a steel part, and the rotating part 220 and the movable part 230 may be plastic parts.
  • the elastic body 100 is provided with an elastic body shaft hole 110
  • the movable part 230 is provided with a movable part shaft hole 232
  • the rotating part 220 is provided with a rotating part shaft hole 222
  • the rotating shaft 210 penetrates the elastic body shaft.
  • the movable part 230 is located between the elastic body 100 and the rotating part 220, and the movable part 230 is connected with the elastic body 100.
  • the protrusion 233 and the recess 124 are inserted between 230 and the elastic body 100.
  • the surface of the movable part 230 corresponding to the rotating part 220 is configured with a first cam structure 231
  • the surface of the rotating part 220 corresponding to the movable part 230 is configured with a second cam structure 223.
  • the first cam structure 231 and the second cam structure 223 form a cam transmission Cooperate.
  • the rotating part 220 can rotate relative to the movable part 230 so that the movable part 230 compresses or releases the elastic body 100. Specifically, when the contact point between the rotating part 220 and the movable part 230 reaches the highest point of the cam, the elastic body 100 is compressed, and when the contact point between the rotating part 220 and the movable part 230 avoids the highest point of the cam, the elastic body 100 is released.
  • the elastic restoring force generated by the elastic body 100 drives the rotating member 220 to rotate, so that the arm 20 automatically rotates to the first position or the second position.
  • first cam structure 231 may specifically refer to the groove shown in FIG. 5, and the second cam structure 223 may specifically refer to the slider shown in FIG. 5.
  • the two opposite side wall surfaces of the groove are configured as inclined surfaces or arc surfaces and make the opening of the groove gradually increase.
  • the rotating member 220 rotates relative to the movable member 230 so that the slider slides along the side wall surfaces of the groove.
  • adjacent side wall surfaces of adjacent grooves are connected to and define a convex peak structure 2311, and the apex of the convex peak structure 2311 is formed as the highest point of the cam.
  • the ratio of the axial length of the part of the rotating shaft 210 in the elastic body shaft hole 110 to the total axial length of the rotating shaft 210 is greater than or equal to 1/4.
  • One end of the shaft 210 in the axial direction is provided with a first stop part 211, and the other end in the axial direction is provided with a second stop part 212.
  • the elastic body 100, the movable part 230, and the rotating part 220 are limited to the first stop part 211 and Between the second stopper 212.
  • the elastic body 100 is configured with a first boss 121 at a location corresponding to the first stop part 211, and the first boss 121 of the elastic body 100 abuts against the first stop part 211.
  • the elastic body 100 is configured with a second boss 122 at a position corresponding to the movable part 230, and the second boss 122 of the elastic body 100 abuts against the movable part 230.
  • the outer contour line 221 of the cross-section formed by the rotating member 220 being cut by a plane perpendicular to the center line of the rotating shaft 210 is non-circular. As shown in FIG. 9, the rotating member 220 is inserted into the connecting hole 21 on the arm 20, wherein, The outer contour line 221 is adapted to the shape of the inner peripheral contour of the connecting hole 21.
  • the outer contour line 221 includes an unclosed arc line segment 221a and a connecting line segment 221b.
  • the arc line segment 221a and the connecting line segment 221b are alternately connected; wherein the connecting line segment 221b is a straight line segment, a broken line segment or a curvature different from that of a circular arc.
  • the arc segment of the line segment 221a is a straight line segment, a broken line segment or a curvature different from that of a circular arc.
  • the elastic body 100 is configured with a plurality of connecting portions 123, the connecting portion 123 is connected to the body 30, and at least two connecting portions 123 of the plurality of connecting portions 123 are distributed axially symmetrically. Further, at least two of the plurality of connecting portions 123 form an angle shape with the center line of the rotating shaft assembly 200 as the vertex.
  • the connecting portion 123 includes a lug 1231, and the lug 1231 is located at the edge of the elastic body 100.
  • the lug 1231 is provided with a mounting hole 1232, and the mounting hole 1232 is used for assembling with the fastener 40 to be fixed to the body 30.
  • the shaft assembly includes an upper cam, a lower cam, a spring, a cylinder, a shaft, and a fixed part.
  • the cam is connected with the body, the lower cam is sleeved on the rotating shaft and one end is against the upper cam, and the other end is against the spring.
  • the barrel is sleeved on the outside of the spring and the lower cam and connected with the arm.
  • positioning is achieved through the adaptation of upper and lower cams and springs.
  • the disadvantage is that: on the one hand, the use of springs to provide elastic force makes the structure of the rotating shaft assembly more complicated, and the structural size design is limited.
  • the existing rotating shaft assembly has low rigidity only in the folding direction and very high rigidity in other directions.
  • the vibration damping function of the rotating shaft assembly is poor.
  • the existing The technology realizes the vibration reduction of the fuselage by adding a vibration reduction system between the arm and the fuselage, but it will bring about the problem of increasing the volume of the fuselage.
  • the connecting structure 10 of the rack provided in this embodiment is different from the existing rotating shaft assembly.
  • the connecting structure 10 includes a rotating shaft 210, an elastic body 100 (such as rubber, uniglue, etc.), a rotating part 220, and a movable part 230.
  • the fixed part 2121, etc., the rotating part 220 is fixed to the arm 20, and rotates together with the arm 20.
  • the movable part 230 receives the force of the rotating part 220 to move upward to compress the elastic body 100, and the elastic body 100
  • the elastic force is generated after the deformation, and the elastic force reaches the maximum after rotating a certain angle (that is, when the contact point of the first cam structure 231 and the second cam structure 223 is at the highest point of the cam), then the elastic body 100 releases the elastic potential energy so that The rotating member 220 automatically rotates to a certain angle to complete the folding function or the unfolding function.
  • this structure adopts the elastic body 100 to absorb vibration and reduce vibration, and also perform energy storage and discharge, which can greatly reduce the size of the entire connecting structure 10 and reduce the number of parts of the entire connecting structure 10.
  • the elastic body 100 is installed on the fuselage 30 through the two mounting holes 1232 (or more) of the fastener 40, so that the fuselage 30 and the arm 20 are separated by the elastic body 100, In this way, designing through the size of the elastic body 100 can change the modal of the elastic system composed of the "arm 20 + elastic body 100" so as to better isolate the vibration of the arm 20 and reduce the vibration amplitude of the body 30. Improve the vibration performance of the body 30.
  • connection structure 10 The existing shaft assembly
  • vibration acceleration amplitude of the arm 20 and the fuselage 30 are detected respectively.
  • the following is a comparison of the vibration conditions of the arm 20 and the fuselage 30 of this design with the vibration conditions of the existing arm and the fuselage based on the aforementioned test result data:
  • FIG. 13a it is a graph of the relationship between frequency and acceleration amplitude of the fuselage 30 in the frame of this embodiment.
  • the arm 20 and the fuselage 30 are connected by the connecting structure 10 of this embodiment;
  • FIG 13b it is a graph of the relationship between frequency and acceleration amplitude of the fuselage in the existing frame.
  • the arm and the fuselage are connected by an existing shaft assembly (also called a shaft).
  • the maximum value of the acceleration amplitude of the fuselage 30 of this embodiment shows a decreasing change in the x, y, and z directions compared to the maximum value of the acceleration amplitude of the existing fuselage.
  • the connecting structure 10 is used to connect the fuselage 30 and the arm 20 in this embodiment.
  • the comprehensive vibration amplitude of the fuselage 30 is reduced by at least 30%, which can greatly optimize the structure of the fuselage 30 and the performance of internal components, thereby greatly improving the performance of the aircraft.
  • the fuselage 30 is used to establish a coordinate system.
  • One of the length extension directions of the fuselage 30 points to the x direction, and one of the width directions of the fuselage 30 points to the y direction.
  • One of the up and down directions of the body 30 points to the z direction.
  • FIG. 14a it is a graph of the relationship between frequency and acceleration amplitude of the arm 20 in the frame of this embodiment.
  • the arm 20 and the fuselage 30 are connected by the connecting structure 10 of this embodiment;
  • FIG. 14b it is a graph of the relationship between frequency and acceleration amplitude of the arm 20 in the existing frame.
  • the arm 20 and the body 30 are connected by an existing shaft assembly (also called a shaft).
  • the maximum value of the acceleration amplitude of the arm 20 of the present embodiment shows a decreasing change in the x, y, and z directions compared to the maximum value of the acceleration amplitude of the existing arm.
  • the connecting structure 10 is used to connect the fuselage 30 and the arm 20 in this embodiment.
  • the machine The comprehensive vibration amplitude of the arm 20 is reduced by about 30%, which can reduce the shaking of the arm 20, improve flight stability and control accuracy, and further optimize the structure of the fuselage 30 and the performance of internal components.
  • the embodiment of the third aspect of the present application provides an aircraft, including a power system and the frame described in any of the above embodiments.
  • the power system is provided on the arm 20 in the frame for providing flight power for the aircraft. .
  • the arm 20 has a first end 22a and a second end 22b opposite to each other, the connecting structure 10 is connected to the first end 22a of the arm 20, and the power system is connected to the first end 22a.
  • the two ends 22b are connected.
  • the power system may include a motor and a rotor driven by the motor to rotate.
  • the aircraft is a drone.
  • the elastic body (such as rubber, uniglue, etc.) is used to provide elasticity to promote the automatic reset of the arm.
  • the elastic body can directly As a component connecting the shaft and the fuselage, the elastic body can intercept the vibration between the fuselage and the arm.
  • the overall length of the shaft or the connection structure is shortened, and the shaft or connection is reduced.
  • the overall volume of the structure makes the design of the connecting structure more free, and it is also more conducive to the miniaturization of the aircraft.
  • the elastic body as the connecting part of the connecting structure and the fuselage, has the function of damping in all directions. Compared with the existing structure with springs for energy storage and discharging and the structure with additional vibration reduction system, the product size is reduced while the vibration reduction effect on the fuselage is better.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

L'invention concerne une structure de raccordement, comprenant : un corps élastique (100), qui est utilisé pour se raccorder à un élément parmi un bras (20) et un fuselage (30) ; un ensemble arbre rotatif (200), qui est raccordé au corps élastique (100) et qui est utilisé pour se raccorder à l'autre élément parmi le bras (20) et le fuselage (30) de manière à amener la rotation du bras (20) par rapport au fuselage (30) à avoir au moins un intervalle de déplacement, l'intervalle de déplacement ayant une première position, une deuxième position et une troisième position qui est située entre la première position et la deuxième position. L'ensemble arbre rotatif (200) est également utilisé pour venir en butée contre le corps élastique (100) et le comprimer pendant un processus dans lequel le bras (20) s'approche de la troisième position et le corps élastique (100) est également utilisé pour faire tourner automatiquement le bras (20) vers la première position ou la deuxième position lorsque le bras (20) passe dans la troisième position. L'invention concerne en outre un cadre et un aéronef.
PCT/CN2019/089680 2019-05-31 2019-05-31 Structure de raccordement, cadre et aéronef Ceased WO2020237678A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/CN2019/089680 WO2020237678A1 (fr) 2019-05-31 2019-05-31 Structure de raccordement, cadre et aéronef
CN201980004972.9A CN111278729A (zh) 2019-05-31 2019-05-31 连接结构、机架及飞行器

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PCT/CN2019/089680 WO2020237678A1 (fr) 2019-05-31 2019-05-31 Structure de raccordement, cadre et aéronef

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Publication number Priority date Publication date Assignee Title
CN111674540B (zh) * 2020-06-18 2022-02-15 成都纵横大鹏无人机科技有限公司 一种转动机构
CN120902934A (zh) * 2025-08-12 2025-11-07 青鸾(深圳)无人机科技有限公司 一种电动垂直起降载人飞行器

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015050617A2 (fr) * 2013-07-15 2015-04-09 Design Intelligence Incorporated, LLC Véhicule aérien sans pilote (uav) à sections ailes d'inter-liaison
CN205675222U (zh) * 2016-02-22 2016-11-09 深圳市大疆创新科技有限公司 机架及使用该机架的无人机
CN206171791U (zh) * 2016-04-27 2017-05-17 零度智控（北京）智能科技有限公司 无人机
CN206685525U (zh) * 2017-04-28 2017-11-28 深圳市大疆创新科技有限公司 连接结构
CN208630850U (zh) * 2018-07-19 2019-03-22 深圳市大疆创新科技有限公司 无人飞行器及其机臂连接结构

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015050617A2 (fr) * 2013-07-15 2015-04-09 Design Intelligence Incorporated, LLC Véhicule aérien sans pilote (uav) à sections ailes d'inter-liaison
CN205675222U (zh) * 2016-02-22 2016-11-09 深圳市大疆创新科技有限公司 机架及使用该机架的无人机
CN206171791U (zh) * 2016-04-27 2017-05-17 零度智控（北京）智能科技有限公司 无人机
CN206685525U (zh) * 2017-04-28 2017-11-28 深圳市大疆创新科技有限公司 连接结构
CN208630850U (zh) * 2018-07-19 2019-03-22 深圳市大疆创新科技有限公司 无人飞行器及其机臂连接结构

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