WO2018082166A1 - Système de connexion électrique de composants électroniques - Google Patents

Système de connexion électrique de composants électroniques Download PDF

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Publication number
WO2018082166A1
WO2018082166A1 PCT/CN2016/111773 CN2016111773W WO2018082166A1 WO 2018082166 A1 WO2018082166 A1 WO 2018082166A1 CN 2016111773 W CN2016111773 W CN 2016111773W WO 2018082166 A1 WO2018082166 A1 WO 2018082166A1
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WO
WIPO (PCT)
Prior art keywords
support member
camera
uav
electronic component
electric motor
Prior art date
Application number
PCT/CN2016/111773
Other languages
English (en)
Inventor
Bin NIE
Original Assignee
XDynamics Limited
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
Priority claimed from PCT/CN2016/104535 external-priority patent/WO2018082004A1/fr
Priority claimed from PCT/CN2016/110055 external-priority patent/WO2018107416A1/fr
Application filed by XDynamics Limited filed Critical XDynamics Limited
Publication of WO2018082166A1 publication Critical patent/WO2018082166A1/fr

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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
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/02—Heads
    • F16M11/04—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
    • F16M11/06—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting
    • F16M11/10—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting around a horizontal axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
    • 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
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/02—Heads
    • F16M11/18—Heads with mechanism for moving the apparatus relatively to the stand
    • 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
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/20—Undercarriages with or without wheels
    • F16M11/2007—Undercarriages with or without wheels comprising means allowing pivoting adjustment
    • F16M11/2035—Undercarriages with or without wheels comprising means allowing pivoting adjustment in more than one direction
    • F16M11/2071—Undercarriages with or without wheels comprising means allowing pivoting adjustment in more than one direction for panning and rolling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2221/00—Electric power distribution systems onboard aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography

Definitions

  • the invention relates to a system for electrically connecting electronic components and particularly, but not exclusively, to a system for electrically connecting electronic components such as, for example, circuit boards located on opposing sides of an unmanned aerial vehicle (UAV) rotatable gimbal mechanism.
  • UAV unmanned aerial vehicle
  • UAVs are increasingly being used to shoot professional quality moving images.
  • the camera is supported under the UAV by a gimbal mechanism which allows the camera to be controlled to rotate (roll), pitch and yaw relative to the UAV body to capture action scenes or the like.
  • Such camera movements may be controlled manually or may be programmed in advance. Consequently, control and power electronic components including circuit boards are located either side of the gimbal mechanism connection to the UAV such that this poses challenges in routing electrical cables between to electrically connect the components.
  • An object of the present invention is to provide a mechanism for mechanically and electrically connecting and disconnecting parts of an unmanned aerial vehicle such as a drone or a multi-copter.
  • Another object of the present invention is to mitigate or obviate to some degree one or more problems associated with known unmanned aerial vehicles, or at least to provide a useful alternative.
  • the invention provides a system for electrically connecting electronic components.
  • the system comprises a first electronic component associated with a first support member and a second electronic component associated with a second support member.
  • the second support member is movable relative to the first support member via a motorised coupling mechanism movably connecting said first support member to said second support member.
  • An electric motor of said motorised coupling mechanism is provided with a hollow shaft whereby an electrical cable electrically connecting said first electronic component to said second electronic component is routed through said hollow shaft.
  • the invention provides an electric motor for a motorised coupling mechanism.
  • the electric motor comprises a stator adapted to be connected to a first support member and a rotor adapted to be connected to a second support member.
  • the second support member is movably coupled to the first support member by said motorised coupling mechanism.
  • the electric motor has a hollow shaft for receiving an electrical cable electrically connecting a first electronic component associated with the first support member and a second electronic component associated with the second support member.
  • the invention provides a method of electrically connecting electronic components.
  • the method comprises providing a first electronic component associated with a first support member and providing a second electronic component associated with a second support member.
  • the second support member is movable relative to the first support member via a motorised coupling mechanism movably connecting said first support member to said second support member.
  • An electric motor of said motorised coupling mechanism is provided with a hollow shaft.
  • the method includes routing an electrical cable electrically connecting said first electronic component to said second electronic component through said hollow shaft.
  • the invention provides an unmanned aerial vehicle (UAV) having a camera carried by a gimbal mechanism of the UAV.
  • the camera comprises an integrated or dedicated peripheral device of the UAV.
  • the camera is rotatably mounted to at least one gimbal mechanism arm.
  • the arrangement is such that an electric motor for varying a pitch angle of the camera with respect to the gimbal mechanism arm is integrated within the housing of the camera.
  • the pitch motor has a stator fixedly connected to the gimbal mechanism arm and a rotor located within the camera housing to cause the camera and its housing to rotate about a pitch axis.
  • FIG. 1 is a side view of a UAV in accordance with an embodiment of the invention, but not including propellers;
  • FIG. 1 is a side-sectional view of the UAV of Fig. 1, but including propellers;
  • FIG. 1 is a plan view from below of the UAV of Fig. 1;
  • FIG. 1 is a plan view from below of the UAV of Fig. 1, but including propellers;
  • FIG. 1 is a perspective view from above of the UAV of Fig. 1, but not including propellers;
  • FIG. 1 is a perspective view from below of the UAV of Fig. 1, but not including propellers;
  • FIG. 1 is a perspective view showing an embodiment of a manually operable mechanism for mechanically and electrically connecting a peripheral electronic device with a body of a UAV in accordance with the present invention
  • FIG. 7 is a perspective view showing a first engaging means of the manually operable mechanism of Figure 7, with the first engaging means being adapted to associate with the body of the UAV;
  • FIG. 7 is a perspective view showing a second engaging means of the manually operable mechanism of Figure 7, with the second engaging means being adapted to associate with the peripheral electronic device;
  • FIG. 7 is a perspective view showing the first and the second engaging means of the manually operable mechanism of Figure 7 prior to connection;
  • FIG. 7 is a perspective view showing the first and the second engaging means of the manually operable mechanism of Figure 7 post connection;
  • FIG. 1 is a side view of an embodiment of a gimbal mechanism for a UAV in which an electrical cable is routed through a hollow shaft of an electric motor;
  • FIG. 1 is an exploded view of a part of another embodiment of a gimbal mechanism for a UAV in which an electrical cable is routed through a hollow shaft of an electric motor;
  • FIG. 13 is a schematic view of a rotor part of the electric motor for the embodiment of Fig. 13;
  • FIG. 13 is a perspective view of the gimbal mechanism of Fig. 13 showing a camera as a peripheral electronic device;
  • FIG. 13 is a schematic view of a camera mounting part of the gimbal mechanism of Fig. 13.
  • UAV unmanned aerial vehicle
  • a UAV 10 having a body 12 housing one or more of control circuitry 13, wireless communication circuitry 14 and a rechargeable power source 16 (Fig. 2) for the UAV 10.
  • the operation of the UAV 10 may be controlled wirelessly from a ground station (not shown) or it may operate automatically according to preprogrammed control instructions uploaded to its control circuitry 13.
  • a main part of the body 12 is preferably generally egg-shaped, although it will be understood that the shape of the UAV body may take any suitable form.
  • An advantage of an egg-shaped body 12 is that it is generally aerodynamically efficient whilst providing sufficient volume to house internal components 13, 14, 16 of the UAV 10. Furthermore, it provides a strong structural platform for supporting arms 18 for the UAV propellers.
  • the UAV 10 has a plurality of arms 18 extending outwardly from the body 12.
  • the arms 18 are also inclined upwardly with respect to the body 12.
  • a motor 20 having a rotor 22 on which is mounted a propeller 24.
  • the arms 18 preferably extend outwardly and upwardly from the body 12 such that a majority of an area A (Fig. 4) swept by a propeller 24 is substantially unimpeded by the main body part of the UAV body 12, i.e. the downward airflow of a propeller 24 is not significantly blocked by other structural parts of the UAV 10 such as the egg-shaped body 12.
  • the arms 18 are arranged around the body 12 such that they surround the body 12 and such that the areas A swept by the propellers 24 are closely adjacent to one another.
  • the arms 18 are preferably integrally formed with the body 12.
  • a gimbal or gimbal mechanism 26 may be mounted under a forward portion of the body 12 for supporting a peripheral electronic device such as a camera 28.
  • the gimbal mechanism 26 comprises a first motor 26A for moving the camera 28 about a vertical axis, i.e. to effect yaw movements of the camera 28 with respect to the UAV body 12.
  • the first motor 26A is mounted to the UAV body 12.
  • the gimbal mechanism 26 includes a second motor 26B for moving the camera vertically about a horizontal pitch axis, i.e. to effect movement of the camera 28 about a horizontal axis that is normal to a forward direction of movement of the UAV 10 when the camera 28 is itself pointing in said forward direction of the UAV 10.
  • the gimbal mechanism 26 has a third motor 26C for effecting movement of the camera 28 about a horizontal axis, i.e. a roll axis, aligned with the forward direction of motion of the UAV 10 when the camera is pointing in said forward direction. Consequently, the gimbal mechanism 26 enables the camera 28 to be moved with three degrees of freedom relative to the UAV body 12.
  • the forward or front portion of the UAV body 12 preferably comprises the front 25% of the UAV body 12.
  • the gimbal mechanism 26 includes a gimbal arm 30 which connects at a first end to the first motor 26A at the forward part of the body 12 and extends downwardly and rearwardly from said point of connection.
  • a second end of the gimbal arm 30 mounts the second and third motors 26B, 26C and the camera 28. Consequently, the camera 28 is mounted in front of the arm 30 and an image view of the camera is always unimpeded by said arm 30.
  • the arm 30 is preferably curved.
  • the arm 30 may also carry electrical connections between the camera 28 and the second and third motors 26B, 26C and the internal components 13, 14, 16 housed in the UAV body 12.
  • the camera 28 is preferably permanently connected to the gimbal mechanism 26.
  • the camera 28 is preferably designed specifically for matched operation with the UAV 10.
  • This has at least the advantage that the characteristics such as the weight of the camera 28 are known when the UAV 10 is being designed such that the internal components 13, 14, 16 housed within the UAV body can be arranged so as to counterbalance the displacement of the camera 28 forward of a centre point of the UAV 10 which would normally comprise the UAVs centre of gravity.
  • knowing the weight of the camera enables not only the internal components housed in the body of the UAV to be arranged to counterbalance the forward placement of the camera, but to enable even the positioning of structural components such as the arms 18 to be arranged to provide some counterbalancing of the forward placement of the camera 28.
  • the gimbal mechanism 26 is preferably arranged such that a lens 28A of the camera is substantially in line with a front edge of the UAV body 12, although, in some embodiments, the camera may be positioned with its lens 28A forward of the front edge of the UAV body 12.
  • Displacing the camera 28 forward of the centre of the UAV body and below or lower than the UAV body 12 considerably reduces the likelihood of the camera image view being obstructed by structural components of the UAV such as the propeller arms 18 or even the propellers 24.
  • the forward placement of the camera 28 under the UAV body 12 greatly increases the range or degree of camera movements to capture images cleanly and without obstruction.
  • the gimbal mechanism 26 is arranged under the forward portion of the body 12 such that an angle of a forward vertical field of view X of the camera 28 is less than an angle of a forward vertical clearance field of view Z defined with respect to a forward tip or forward-most extent of at least one of the propellers 24.
  • a clearance angle Y comprising a difference on one side between the forward vertical clearance field of view angle Z and the camera forward vertical field of view angle X is preferably equal to or greater than a pitch angle of the camera on one side relative to the UAV body or the pitch angle of the UAV in forward motion.
  • the camera 28 can be pitched up by as much as the clearance angle Y before the image view is impeded to any degree by one of the UAV’s forward propellers 24.
  • the camera 28 can be pitched down by an angle greater than the clearance angle, because the forward placement of the camera 28 on the UAV 10 is such that the camera is generally forward of any structural components of the UAV 10 lower than the normal field of view X of the camera 28.
  • the issue of obstruction by the forward propellers is more acute when the UAV 10 is moving forward at speed such that the UAV 10 itself is pitched downwardly at its front to obtain stable flight at speed.
  • the UAV 10 can be considered as having been pitched downwardly relative to the camera 28 (the camera 28 is pitched upwardly relative to the downwardly pitched UAV 10 to maintain its normal forward directed field of view X) by an amount as much as the clearance angle Y without obstructing the image view of the camera 28. It will be understood that forward motion of the UAV 10 will be relative to the surrounding air rather than relative to land. It will also be understood that the degree of pitch required during forward motion of the UAV 10 is dependent on the velocity of the UAV 10 relative to the surrounding air.
  • the novel arrangement of the UAV 10 as disclosed herein enables moving images to be captured by a UAV travelling forward at a predetermined velocity relative to air whilst the UAV 10 is pitched downwardly for forward motion and yet not have the rotating forward propellers 24 obstruct the normal forward vertical image view X of the camera 28.
  • the clearance angle Y may be as much as 19 degrees.
  • the forward vertical field of view X of the camera 28 may be as much as 64 degrees.
  • the UAV preferably has one or more feet 32 extending below the UAV body 12 and the gimbal mechanism 26.
  • the Y-shaped members 34 are formed integrally with the UAV body 12.
  • the Y-shaped members 34 respectively connect to the UAV body 12 at centre points on respective sides of the body 12. Consequently, the main structures of the Y-shaped members 34 save for the forward feet 32 are placed behind the gimbal 26 and camera 28.
  • the arrangement of the Y-shaped members 34 is such that the camera 28 may be rotated to shoot images to the rear of the UAV 10 when in forward flight having a generally unobstructed field of view backwards between the Y-shaped members 34.
  • the outer edges of the feet 32 define an imaginary square S (shown by dashed line S in Fig. 3) which provides a very stable landing support for the UAV 10.
  • the forward placement of the camera 28 on the UAV 10 is such that an angle of a forward horizontal field of view W of the camera is substantially less than an angle of a forward horizontal clearance field of view Q (Fig. 4) defined with respect to a forward edge or tip of at least one of the feet 32.
  • the camera 28 can be rotated to both sides in the horizontal field of view by a significant degree without its image view being obstructed by structural or other components of the UAV 10.
  • the camera 28 can be rotated to both sides in the horizontal field of view by as much as 57 degrees without its image view being obstructed by structural or other components of the UAV 10.
  • a difference between the forward horizontal clearance field of view angle Q and the camera forward horizontal field of view angle W is equal to or greater than a yaw angle of the camera 28 provided by gimbal motor 26A.
  • At least the lens 28A of the camera 28 is positioned forward of the front feet 32 of the UAV 10.
  • the forward placement of the camera 28 on a gimbal mechanism 26 supported below a front portion of the UAV body 12 is such that it enables a synergistic combination of at least pitch and yaw degrees of freedom of movement of the camera 28 when the UAV is in flight without the camera image view becoming obstructed by structural or other component parts of the UAV 10. This enables the UAV camera 28 to be operated to take high quality action scene moving images whilst in flight and whilst travelling at speed.
  • the gimbal mechanism 26 mechanically and electrically connects parts of the UAV 10 and may comprise a manually operable mechanism for mechanically and electrically connecting one or more peripheral devices with the UAV or part of the UAV.
  • the peripheral devices may include, but are not limited to, portable electronic devices such as mobile phones or smart phones; electronic optical instruments such as digital cameras and/or video recorders; audio recorders; and/or other electronic units or modules designed for specific purposes of the UAV.
  • the expression “manually operable” is generally used to describe the mechanism as being manipulatable for connecting and disconnecting parts of the UAV by only the user’s hand or hands without requiring the use of a tool such as, for example, a screwdriver, pliers or a wrench.
  • the manually operable mechanism of the present invention is beneficial in providing a quick and easy connection as well as release of such connection, both mechanically and electrically/electronically at the same time, for two or more parts of a UAV including one or more peripheral electronic devices with one or more parts of the UAV such as a drone.
  • the mechanism provides a simple one-step connecting and disconnecting, or closing and opening of the respective electrical connections or contacts, negating the need for any physical connection and disconnection of electrical wires or cables to thereby allow a quick attaching and detaching of any electrically linked parts to and from the UAV.
  • the easy disconnection of the parts from the UAV also allows a more compact structure and weight reduction in the design of the UAV for enhancing applicability of the UAV and user’s experience.
  • the mechanism 100 may comprise a first engaging means 120 adapted to be associated or connected with a first part of the UAV 10, such as a body of the UAV or part of the body of the UAV such as one or more of a printed circuit board (PCB), a motor and/or other electronic components.
  • the first engaging means 120 may include at least one first electrical contact or connector 122 adapted to establish an electrical contact or connection with a corresponding electrical counterpart.
  • the mechanism 100 may further comprise a second engaging means 130 adapted to be associated or connected with a second part of the UAV 10, such as another part of the UAV or one or more peripheral electrical devices operable cooperatively or independently with the UAV.
  • the second engaging means 130 may include at least one second electrical contact or connector 132 adapted to establish an electrical contact or connection with a corresponding electrical counterpart, such as the first electrical contact or connector 122.
  • the phrase “electrical contact” may relate to an electrical circuit component comprising one or more electrically conductive elements via which a close electric circuit can be achieved by bringing two or more of such conductive elements into contact.
  • the phase “electrical connector” may relate to an electro-mechanical component adapted to be physically or mechanically joined or connected with another electro-mechanical component to create an electric circuit.
  • first engaging means 120 and the second engaging means 130 are manually engageable to connect, both mechanically and electrically, said first and second parts of the UAV 10, and are manually releasable to disconnect, both mechanically and electrically, said first and second parts of the UAV.
  • the at least one first electrical contact or connector 122 is brought into electrical contact or connection with said at least one second electrical contact or connector 132 to form a closed circuit when the first and second engaging means 120, 130 are manually engaged to mechanically connect the first and second parts of the UAV together.
  • the at least one first electrical contact or connector 122 is brought into electrical contact or connection with the at least one second electrical contact or connector 132 by bringing or arranging the first engaging means 120 and the second engaging means 130 to a register position.
  • the first and the second electrical contact or connector 122, 132 may each comprise a plurality of contacts or connectors arranged or organised in a specific spatial arrangement such that, only by aligning the respective plurality of contacts or connectors 122, 132 relative to one another in a defined, registered manner, electrical contacts or connections can be established between the first and the second parts of the UAV 10.
  • the second engaging means 130 may comprise a plurality of second electrical contacts 132 in the form of twenty to thirty, preferably thirty-four, spaced apart electrical conducting pads 134 arranged in, or partially in, a concentric manner.
  • the plurality of electrical contacts 132 allow sufficient number of connections be available for conducting and/or transmitting electric power, as well as various forms of signals.
  • the conducting pads 134 can be provided in the form of gold plated pads for their lower electrical resistance.
  • the registration can be achieved by, for example, rotatably aligning the two engaging means 120, 130 and, alternatively or additionally, by aligning one or more indicia, marks or the like provided at one or more exterior surfaces of the two engaging means 120, 130.
  • At least one of the first and the second electrical contact or connector 122, 132 may comprise one or more movable members adapted to establish the electrical contact or connection with the corresponding other one of the first and the second electrical contact or connector 122, 132 when the first and the second parts of the UAV are mechanically connected together.
  • a plurality of movable members 124 can be provided at the first electrical contact 122, with the movable members 124 being movable along a longitudinal axis A-A about which the first and the second engaging means 120, 130 are, for example, rotatably moved to mechanically connect or lock the first and second parts of the UAV 10 via a lock connection arrangement, for example.
  • the plurality of movable members 124 are resiliently movable along the longitudinal axis A-A such that the first and the second electrical contacts or connectors 122, 124 can be brought into electrical contacts or connections under a resilient force to thereby enhance the electrical contacts or connections therebetween.
  • the resiliency can be provided by any known resilient means, such as but not limited to, one or more elastic members or spring members utilised to resiliently bias the movable members to their extended configuration to enhance the electrical contacts or connections.
  • the movable members 124 may each comprise a protruding member adapted to resiliently and movably engage a corresponding terminal member 134 of the second electrical contact or connector 132 to thereby establish the electrical contract or connection when the first and the second engaging means 120, 130 are engaged to mechanically connect the first and the second parts of the UAV 10.
  • the one or more movable members 124 can be or may comprise one or more pogo pins, as shown in Figure 8.
  • the plurality of movable members 124 may comprise 34 pogo pins adapted to conduct and/or transmit one or more of the electric power, HDMI signals, control signals and sensor signals for the peripheral electronic device, e.g. camera.
  • the pogo pins 124 provided at the first engaging means 120 will be compressed by the opposing engaging surface of the second engaging means 130, with the spring means (not shown) arranged at each of the pogo pins 124 exerting a biasing force against the compression to thereby enhance the overall electrical contacts between the pogo pins 124 and the corresponding electrical terminals 134 at the second engaging means 130 when the pogo pins 124 and the corresponding electrical terminals 34 are aligned, i.e. have reached the register position.
  • Figure 9 shows an embodiment of a mount or a support arm 140 having the second engaging means 130 at one end, and a means 142 for mounting or supporting a peripheral electronic device such as a camera at the other, opposing end.
  • the support arm 140 can be, comprise or is adapted to be connected with, a gimbal for pivotally mounting the peripheral electronic device to the body of the UAV 10.
  • the support arm 140 comprises one embodiment of the gimbal arm 30 of Fig. 1.
  • the second engaging means 130 may comprise at its peripheral edges one or more protrusions and/or recesses 136 having a complementary configuration with one or more recesses and/or protrusions 126 provided at corresponding positions of the first engaging means 120 to thereby allow the first and the second engaging means 120, 130 to be engageable via a mechanical connection, for example, a screw-lock connection.
  • the connection may be a lockable connection.
  • the first and the second engaging means 120, 130 may also be engaged via one or more other known types of connections, for example, push-fitting or snap-fitting, etc. and can be released by one or more switches or press buttons.
  • one of the first or the second engaging means 120, 130 can be mounted with a spring member 128 such that a biasing force along the longitudinal axis A-A is applied against the screw connection to thereby enhance the mechanical connection therebetween.
  • Figures 10 and 11 show the screw connection between the first and the second engaging means 120, 130 under the biasing effect of the spring member 128 positioned at the first engaging means 120.
  • the second engaging means 130 will be brought towards and into engagement with the first engaging means 120, with their corresponding protrusions and recesses 126 and 136 aligned with one another.
  • the support arm 140 and thus the second engaging means 130 will then be pushed towards the first engaging means 120 to compress the spring member 128 arranged at the first engaging means 120, and subsequently, rotated angularly about the longitudinal axis A-A to lock the two engaging means 120, 130 in position.
  • the locking will be subjected to the biasing force of the spring member 128 to enhance the mechanical connection therebetween.
  • the support arm 140 will first be pushed towards the first engaging means 120, and subsequently, counter-rotated about the longitudinal axis A-A to unlock the two engaging means 120, 130.
  • Fig. 12 provides a view of an embodiment of a gimbal mechanism 150 supporting an electronic peripheral device 152 for a UAV 10.
  • the peripheral device 152 comprises a camera 154.
  • the gimbal mechanism 150 comprises a yaw motor 156 mounted to the UAV body 158.
  • the yaw motor 156 is an electric motor with a limited reciprocal rotational range of less than 360 degrees optionally less than 270 degrees and more preferably less than 180 degrees.
  • a gimbal arm 160 is fixedly connected at its first end to a rotor 156A of the motor 156 such that the gimbal arm 160 rotates within the limited reciprocal rotation range with the rotor 156A.
  • a second end of the arm 160 has rotatably mounted thereto a pair of peripheral device support arms 162A,B which between them rotatably support the camera 154.
  • the pair of support arms 162A,B are configured to rotate about a roll axis whereas the camera 154 is configured to rotate relative to said support arms 162A,B about a pitch axis.
  • Rotation of the pair of support arms 162A,B about a roll axis is effected by a roll motor 164 connected through the second end of the gimbal arm 160 to the pair of support arms 162A,B.
  • Rotation of the camera 154 about a pitch axis is effected by a pitch motor which is located within a housing 168 of the camera 154.
  • a stator of the pitch motor is fixed to one of the support arms 162A,B and a rotor of the pitch motor is connected to the camera housing from with to thereby effect movement of the camera 154 about the pitch axis.
  • each of the roll motor and the pitch motor preferably has a limited reciprocal rotation range of less than 360 degrees, optionally less than 270 degrees and more preferably less than 180 degrees.
  • an electrical cable 170 connecting an electronic component in the UAV 10 to an electronic component on the gimbal mechanism 150 and/or an electronic component in the camera 154 is routed through a hollow shaft comprising the rotor of the yaw motor 156 and may also be routed through a hollow shaft of the pitch motor located within the camera housing 168.
  • a gimbal mechanism 226 enabling the routing of an electrical power and/or signal cable 280 through a hollow shaft 226D (Fig. 14) of at least a yaw motor 226A.
  • Fig. 13 provides an exploded view of a topmost part of the gimbal mechanism 226 as well as components of the UAV 10.
  • the dashed horizontal line in Fig. 13 is indicative of a bottom wall of a housing of the UAV 10. It will be seen therefore that the yaw motor 226A is largely accommodated within the UAV housing with its shaft/rotor 226D/E connected with the first gimbal mechanism manually releasable engagement means 220.
  • An electronic component in the form of a circuit board 282 is provided within the UAV housing (i.e. above the dashed horizontal line in Fig. 13). Also provided is a motor fixing base 283 for fixing the yaw motor 226A to the UAV housing and a gimbal mechanism damping mechanism 286.
  • the electrical cable 280 has a first connector block 280A which, in use, connects to a connector block 282A of the circuit board 282.
  • the cable 280 has a second connector block 280B which connects to a connector block 284A of a second circuit board 284.
  • the second circuit board is located on an opposing side of the moveable coupling formed by the connection of the first end of the gimbal arm 230 (Fig.
  • the rotor shaft 226D is hollow, i.e. of a tubular form. It is therefore possible to route the cable 280 connecting the first and second circuit boards 282, 284 via the hollow rotor shaft 226D as illustrated by dashed line 280 in Fig. 13. As the rotor shaft 226D does not fully rotate, but is limited to a reciprocal rotational range less than 360 degrees and even less so in some embodiments, there is minimal risk that rotation of the rotor shaft 226D will cause damage or wear to a normal electrically insulating cover of the cable 280.
  • the cable 280 does not require any additional wear protective layer or coating. It has been found that it is possible to make the hole through the yaw motor rotor shaft 262D large enough that the cable 280 can be routed therethough without unduly contacting an inner surface of the bore of the hollow shaft. Also shown in Fig. 13 is the first electrical contact or connector 222 of the first engaging means 220 and a base 288 for the second circuit board 284.
  • Routing of the cable 280 through the hollow shaft 226D of the yaw motor 226A overcome a number of technical issues by providing a novel route for the cable. This negates the need to provide a separate conduit/route for the cable from the first circuit board to the second circuit board through a bottom wall of the UAV housing.
  • Fig. 15 provides an exploded view of gimbal mechanism 226 showing both the first engaging means 220 and the second engaging means 230 which together comprise the manually releasable coupling between the gimbal mechanism 226 and the UAV body.
  • the gimbal arm 230 carries at its lower end the roll motor 226C which effects reciprocal rotation of the gimbal support arms 262A, B.
  • the gimbal support arms 262A,B mount the camera 254 in such a manner that it is rotatable about the pitch axis.
  • Fig. 16 provides a schematic view of the camera 254 mounted between the support arms 262A, B.
  • the camera housing 268 accommodates the camera 254 and the pitch motor 226B.
  • a stator 290 of the pitch motor 226B extends through a wall of the camera housing 268 and is fixed to a motor block plate 292 provided in one (262B) of the support arms.
  • a stator coil 294 is mounted on the stator within the motor housing 268 and, in use drives the rotor 296 of the motor 226B.
  • the rotor 296 is fixed or connected to the camera housing such that the camera 254 and its housing 268 rotate with the rotor 294.
  • the camera 254 is rotatably mounted to the other one (262A) of the support arms 262A,B.
  • a first power and signal cable 298 may be routed through the arm 262B to provide power and control signals to the pitch motor 226B. It will be noted that the cable 298 is able to be routed along a side of the stator 290 to extend into the camera housing 268.
  • a second power and signal cable 299 may be routed through the arm 262A to provide power and control signals to the camera 254. The second cable 299 may be routed so as to enter the camera housing 268 via an aperture in the housing adjacent to the rotational support between the camera housing 268 and the arm 262A.
  • the stator 290 of the pitch motor 226B comprises a shaft of said motor 226B and, as such, the stator shaft may be formed to be hollow to provide a cable routing passage into the camera housing 268.
  • any element expressed as a means for performing a specified function is intended to encompass any way of performing that function.
  • the invention as defined by such claims resides in the fact that the functionalities provided by the various recited means are combined and brought together in the manner which the claims call for. It is thus regarded that any means that can provide those functionalities are equivalent to those shown herein.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Accessories Of Cameras (AREA)

Abstract

Système permettant de connecter électriquement des composants électroniques. Le système comprend un premier composant électronique associé à un premier élément de support et un second composant électronique associé à un second élément de support. Le second élément de support est mobile par rapport au premier élément de support par l'intermédiaire d'un mécanisme de couplage motorisé reliant de façon mobile ledit premier élément de support audit second élément de support. Un moteur électrique (156) dudit mécanisme de couplage motorisé est pourvu d'un arbre creux, moyennant quoi un câble électrique (170) connectant électriquement ledit premier composant électronique audit second composant électronique est acheminé à travers ledit arbre creux.
PCT/CN2016/111773 2016-11-04 2016-12-23 Système de connexion électrique de composants électroniques WO2018082166A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
PCT/CN2016/104535 WO2018082004A1 (fr) 2016-11-04 2016-11-04 Véhicule aérien sans pilote
CNPCT/CN2016/104535 2016-11-04
PCT/CN2016/110055 WO2018107416A1 (fr) 2016-12-15 2016-12-15 Mécanisme actionnable manuellement destiné à connecter des parties d'un véhicule aérien sans pilote (uav)
CNPCT/CN2016/110055 2016-12-15

Publications (1)

Publication Number Publication Date
WO2018082166A1 true WO2018082166A1 (fr) 2018-05-11

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109973791A (zh) * 2019-04-02 2019-07-05 嘉兴古辛达贸易有限公司 一种楼宇监控系统

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030103770A1 (en) * 2001-11-30 2003-06-05 Pelco Slip ring assembly and method
CN205402146U (zh) * 2016-02-18 2016-07-27 武汉智能鸟无人机有限公司 一种360度旋转的手持云台
CN105992903A (zh) * 2015-05-15 2016-10-05 深圳市大疆创新科技有限公司 云台
CN106043723A (zh) * 2016-07-25 2016-10-26 武汉大势智慧科技有限公司 一种固定翼无人机摇摆式倾斜摄影系统及方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030103770A1 (en) * 2001-11-30 2003-06-05 Pelco Slip ring assembly and method
CN105992903A (zh) * 2015-05-15 2016-10-05 深圳市大疆创新科技有限公司 云台
CN205402146U (zh) * 2016-02-18 2016-07-27 武汉智能鸟无人机有限公司 一种360度旋转的手持云台
CN106043723A (zh) * 2016-07-25 2016-10-26 武汉大势智慧科技有限公司 一种固定翼无人机摇摆式倾斜摄影系统及方法

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109973791A (zh) * 2019-04-02 2019-07-05 嘉兴古辛达贸易有限公司 一种楼宇监控系统

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