WO2018152792A1 - 可折叠机架、机架组件及无人飞行器 - Google Patents
可折叠机架、机架组件及无人飞行器 Download PDFInfo
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- WO2018152792A1 WO2018152792A1 PCT/CN2017/074836 CN2017074836W WO2018152792A1 WO 2018152792 A1 WO2018152792 A1 WO 2018152792A1 CN 2017074836 W CN2017074836 W CN 2017074836W WO 2018152792 A1 WO2018152792 A1 WO 2018152792A1
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- frame
- carrier
- center frame
- motor
- propeller
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- 230000007246 mechanism Effects 0.000 claims description 136
- 239000000969 carrier Substances 0.000 claims description 7
- 238000000034 method Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/40—Modular UAVs
Definitions
- the present invention relates to the field of unmanned aerial vehicles, and more particularly to a foldable frame, a frame assembly, and an unmanned aerial vehicle.
- the frame of the commonly used multi-rotor UAV includes a center frame, a plurality of arms connected to the center frame, and a power device disposed on the arm.
- the current multi-rotor UAV frame can be equipped with a bending arm.
- the arm When storing and transporting, the arm can be folded or bent to the angle of the center frame to reduce the The overall occupancy of the human aircraft.
- the folding of the UAV frame is achieved by bending the arm. If the bending method is simple, the volume will still be occupied. If the bending method is more complicated, the folding and opening operations are performed. It is inconvenient and the implementation cost is high.
- the invention provides a foldable frame, a frame assembly and an unmanned aerial vehicle, which can realize the folding of the frame, has a simple structure and is convenient to operate.
- the present invention provides a foldable frame for use on an unmanned aerial vehicle comprising a center frame and at least one folding mechanism, the folding mechanism being disposed on a side of the center frame, each folding mechanism including at least three connecting members
- the two ends of each connecting member are hinged with the ends of the other connecting members or the center frame, and the connecting member and the center frame together form a variable shape polygon, and the connecting member away from the center frame serves as a carrier for setting the power device.
- the distance between the carrier and the center frame changes as the shape of the polygon changes.
- the present invention provides a frame assembly comprising a foldable frame as described above and The power unit, at least one power unit is disposed on each carrier of the foldable frame.
- the present invention provides an unmanned aerial vehicle comprising a frame assembly as described above, the center frame of the frame assembly being coupled to the body or the stand.
- the foldable frame comprises a center frame and at least one folding mechanism
- the folding mechanism is disposed at a side of the center frame
- each folding mechanism comprises at least three connecting members. Both ends of each connecting member are hinged with the ends or the center frame of the other connecting members, and the connecting member and the center frame together form a variable-shaped polygon, and the connecting member away from the center frame serves as a carrier for setting the power device.
- the distance between the carrier and the center frame changes as the shape of the polygon changes. This allows the foldable frame to be folded to achieve a smaller volume size, which is convenient for storage or transportation, and has a simple structure and convenient operation.
- FIG. 1 is a schematic structural view of a foldable rack according to Embodiment 1 of the present invention.
- FIG. 2 is a schematic structural view of a foldable frame when a folding mechanism is provided in a quadrangular shape according to Embodiment 1 of the present invention
- Figure 3 is a schematic view showing the structure of the foldable frame of Figure 2 when the folding mechanism is folded;
- FIG. 4 is a schematic structural view of a foldable frame when the folding mechanism is folded into a pentagon according to the first embodiment of the present invention
- FIG. 6 is a schematic structural view of a foldable mechanism when a folding mechanism is provided in a hexagonal shape according to Embodiment 1 of the present invention
- Figure 7 is a schematic view showing the structure of the foldable frame of Figure 6 when the folding mechanism is folded;
- FIG. 8 is a schematic structural view of a folding mechanism enclosing a parallelogram according to a first embodiment of the present invention
- FIG. 9 is a schematic structural view of a folding mechanism according to Embodiment 1 of the present invention when folded;
- FIG. 10 is a schematic structural view of another foldable frame according to Embodiment 1 of the present invention.
- FIG. 11 is a schematic structural view of a rack assembly according to Embodiment 2 of the present invention.
- FIG. 12 is a schematic structural view of a power unit in a rack assembly according to Embodiment 2 of the present invention.
- FIG. 13 is a schematic structural diagram of an unmanned aerial vehicle according to Embodiment 3 of the present invention.
- 1 folding mechanism
- 2 center frame
- 3 power unit
- 11 connector
- 12 auxiliary connector
- 31 first motor
- 32 second motor
- 33 first propeller
- 34 second propeller
- 35 connecting seat
- 11a bearing member
- 111 straight rod
- 112 hinged bracket
- 100 folding rack
- 200 rack assembly
- 300 unmanned aerial vehicle.
- FIG. 1 is a schematic structural view of a foldable frame according to Embodiment 1 of the present invention.
- the foldable rack 100 provided in this embodiment is generally applied to an unmanned aerial vehicle.
- the unmanned aerial vehicle generally includes a rack, a tripod, and a working device to be mounted. Power units or power components can be placed on the rack to drive the entire UAV and operating equipment for flight and takeoff and landing.
- the foldable frame 100 includes a center frame 2 and at least one folding mechanism 1 disposed on the side of the center frame 2, each folding mechanism 1 including at least three connecting members 11 at both ends of each connecting member 11 Coupling with the end of the other connecting member or the center frame 2, and the connecting member 11 and the center frame 2 together form a variable-shaped polygon, and the connecting member away from the center frame 2 serves as a carrier 11a for arranging the power unit, the carrier 11a
- the distance from the center frame 12 changes as the shape of the polygon changes.
- the center frame 2 of the foldable frame 100 can be used as a main structural part of the UAV, and can be used to connect the stand, and to mount work equipment and the like.
- the center frame 2 of the foldable frame 100 is generally located at the geometric center of the unmanned aerial vehicle, and the folding mechanism 1 of the foldable frame 100 is mainly used for connecting the center frame and the power unit.
- the arm structure is generally axially symmetric or centrally symmetric with respect to the center frame 2.
- Center frame 2 can be different shapes and shapes to meet different requirements.
- each folding mechanism 1 is included, and the folding mechanism 1 is disposed on the side of the center frame 2, and each folding mechanism 1 includes at least Three connectors 11.
- both ends of each connecting member 11 are connected with the ends of the other connecting members 11 or the center frame 2, and the connecting manners are all hinged, that is, the plane rotating pair is connected, and the connecting member connected with the center frame 2 11 , the ends of the different connecting members are hinged on different parts of the center frame 2, such that the connecting member 11 and the center frame 2 are connected end to end, together forming a closed polygonal shape, and the center frame 2 and the single connecting member 11 are respectively Make up a separate edge of the polygon.
- the connecting member 11 in the folding mechanism 1 has at least three, the polygonal shape of the connecting member 11 and the center frame 2 in the folding mechanism 1 is at least quadrangular. Further, since the end portion of each connecting member 11 is hingedly connected with other members, the connecting member 11 and the adjacent members are relatively rotatable, and between the sides of the enclosed polygon are It can be rotated relative to each other to become a different shape.
- each of the connecting members 11 of each folding mechanism 1 is connected to other members, and the folding mechanism 1 encloses a closed polygon, the entire folding mechanism 11 is a linkage mechanism, and at this time, one of the separate connecting members can be rotated. , the entire folding mechanism 11 can be driven to perform overall folding deformation, and the manipulation and driving manner are relatively simple. Specifically, the connecting member can be driven to rotate by providing a gear transmission member at the hinge point, and the connecting member can be rotated by other external components.
- each folding mechanism 1 there is at least one connecting member 11 which is away from the center frame 2 and which is not connected to the center frame 2 at both ends, and the connecting member 11 can be used for
- the carrier 11a of the power unit is disposed and carried, and the distance between the carrier 11a and the center frame 2 can be changed as the shape of the polygon changes, so that the distance between the power unit and the carrier 11a and the center frame 2 can be extended. Or shortened.
- the power device When the distance between the carrier 11a and the center frame 2 is the largest, the power device is away from the center frame 2, so that the components such as the propeller in the power device do not interfere with the structural components such as the center frame 2, and the normal and safe flight can be ensured;
- the distance between the carrier 11a and the center frame 2 is the smallest, the polygon of the foldable frame 100 is in a collapsed state, and the outline size thereof is the smallest, which can effectively reduce the outer dimensions of the unmanned aerial vehicle, and is beneficial to the unmanned aerial vehicle. Storage and transportation.
- the carrier 11a is a connection away from the center frame 2.
- the distance between the carrier 11a and the center frame 2 is minimized, and The folding mechanism 1 is caused to generate a large profile deformation.
- the carrier 11a can be placed in the polygon formed by the folding mechanism 1 at the farthest edge or vertex of the center frame 2. At this time, the carrier 11a is away from the center frame 2 The distance is the largest; while the polygons are folded and folded, all the connecting members 11 are close to each other and are approximately on the same straight line. At this time, the distance between the carrier 11a and its power unit and the center frame 2 is the smallest.
- each folding mechanism 1 can be surrounded by various shapes.
- all of the connecting members 11 and the center frame 2 collectively enclosing a variable shape may include one of the following shapes: a quadrangle, a pentagon or a hexagon.
- the folding frame 100 includes two folding mechanisms 1 as an example:
- each of the folding mechanisms 1 includes three connecting members 11, wherein the connecting member 11 away from the center frame 2 is a carrier 11a for arranging a power unit.
- the three connecting members 11 and the center frame 2 together form a quadrilateral, and the connecting member 11 or the center frame 2 constitutes a separate side of the quadrilateral. Since each of the sides of the quadrilateral can be rotated relative to the adjacent side, the shape of the quadrilateral can vary with the relative rotation of the connecting member 11.
- the folding mechanism 1 when the folding mechanism 1 is folded to the position shown in FIG. 3, the sides of the quadrilateral are close to each other and are arranged approximately in a straight line. At this time, the carrier 11a is adjacent to the center frame 2, and the folding mechanism 1 can be ensured to have a small outline size.
- each folding mechanism 1 includes four connecting members 11 away from the center.
- the two connecting members of the frame 2 can be used as the carrier 11a, and the power unit can be disposed on the two carriers 11a or at the hinge point between the two carriers 11a.
- the connecting member 11 and the center frame 2 each form a separate side, and when the connecting member 11 rotates relative to the hinge point, the angle between the sides of the pentagon becomes larger. Or become smaller to form different shapes.
- the angle between the sides of the pentagon is about 180°, the sides of the pentagon are arranged approximately on the same straight line and are in a collapsed state.
- FIG. 6 is a schematic structural view of a foldable mechanism when the folding mechanism is provided in a hexagonal shape according to the first embodiment of the present invention.
- Figure 7 is a schematic view showing the structure of the foldable frame of Figure 6 when the folding mechanism is folded.
- each of the folding mechanisms 1 may further include five connecting members 11, and the connecting member 11 and the center frame 2 collectively form a hexagon. Similar to the quadrilateral and the pentagon, the hexagon can also be formed into different shapes by the rotation between the adjacent connecting members 11, thereby being in an open or closed state.
- the polygon enclosed by the folding mechanism 1 is not limited to the above-mentioned quadrilateral, pentagonal and hexagonal shapes, but may be other polygonal shapes as long as the polygonal shape can be satisfied, and the carrier and the center frame are The distance between the two can be changed.
- the folding mechanism 1 on the side of the center frame may be the same polygon, such as a quadrilateral folding mechanism on both sides, or may be a different polygon, such as a side of the center frame.
- the folding mechanism 1 is a quadrangular folding mechanism, and the other side is a pentagonal folding mechanism or the like.
- the specific composition and structure of the folding mechanism 1 can be freely selected according to the structure and use requirements of the unmanned aerial vehicle.
- the folding mechanism 1 is generally surrounded by a quadrangle.
- all of the connecting members 11 and the center frame 2 in each folding mechanism 1 can be collectively formed into a parallelogram whose shape can be changed.
- FIG. 8 is a schematic structural view of a folding mechanism enclosing a parallelogram according to a first embodiment of the present invention.
- FIG. 9 is a schematic structural view of a folding mechanism according to Embodiment 1 of the present invention when folded. As shown in Figs.
- the center frame 2 and the carrier 11a constitute opposite sides, and the distance between the center frame 2 and the carrier 11a can be changed as the shape of the parallelogram changes. Reach the collapsible rack in flight and Switching between storage and shipping status.
- the hinge manner between the connecting members 11 in the folding mechanism 1 is bidirectional, that is, the connecting members 11 can be rotated and deformed in the direction of rotation in FIG. 8, or can be reversed in the direction of rotation in FIG. The direction is rotated and folded and deformed.
- the folding mechanism 1 includes the connecting member 11 and the center frame 2
- the connecting member 11 and the center frame 2 may have different shapes and sizes.
- the position of the hinge point can be defined. Specifically, the distance between the hinge points of the opposite ends of the two parallel connecting members can be In the same folding mechanism, the lines between the hinge points of the two connecting members 11 hinged to the center frame 2 are parallel to each other.
- the connecting member 11 and the center frame 2 together form a parallelogram, and the specific shape of the connecting member 11 and the center frame 2 can be unlimited, as long as There is no interference when deforming.
- the parallelogram can be made to have a larger deformation range.
- the angle formed between the carrier 11a and the other connectors 11 hinged to the carrier 11a can generally be between 0° and 180°.
- the angle between the connecting member 11 and the center frame 2 is 0° or approximately 0°
- the carrier 11a and the center frame 2 are approximately on the same straight line, such that the distance between the carrier 11a and the center frame 2 is the closest, and
- the foldable frame has the smallest profile for easy transport or storage.
- connection between the hinge points of the two ends of the connecting member 11 may be set to be parallel to the longitudinal direction of the center frame 2, and the carrier 11a is attached to the center frame 2, so that the loading can be performed.
- the minimum distance between the piece 11a and the center frame 2 is zero.
- the hinge axes of the end hinge points of all the connecting members 11 are parallel to each other.
- the deformation process of the entire folding mechanism 1 occurs in the same plane, which can effectively simplify the structural complexity of the folding mechanism 1 and increase the reliability of the folding mechanism 1 in deformation.
- the hinge axes of the hinge points can also be angled to meet different usage requirements. At this time, the deformation process of the folding mechanism 1 usually occurs in a spatial range.
- the connecting member 11 is generally a connecting rod, and the axial direction of the connecting rod is perpendicular to the axial direction of the hinge shaft of the connecting member 11. This makes it possible to form the deformable folding mechanism 1 by means of a simple rod.
- the carrier 11a may include the central frame 2 Straight rods 111 that are parallel in the longitudinal direction.
- the direction of the straight rod 111 is generally parallel to the axis of the center frame 2, so that when the carrier 11a and the center frame 2 are closed together, the straight rod 111 in the carrier 11a will fit on the side of the center frame 2, and the straight rod
- the extending direction of the 111 is consistent with the axial direction of the center frame 2, and the dimension of the carrier 11a perpendicular to the direction in which it extends is small, and the space occupied is also small, so that the structure is relatively compact.
- the supporting member 11a may further include a hinge bracket 112.
- the first end of the hinge bracket 112 is connected with the straight rod 111, and the second end of the hinge bracket 112 is hinged with the other connecting members 11 .
- the other connecting members 11 can be hinged to the carrier 11a through the hinge bracket 112.
- the position of the hinge bracket 112 is relatively flexible, and may be disposed at the end of the straight rod 111 in the carrier 11a or at a position near the middle of the straight rod 111, so that the structure of the carrier 11a and the position of the power unit have Greater flexibility.
- the hinge bracket 112 When the hinge bracket 112 is included on the carrier 11a, the distance between the two ends of the hinge bracket 112 can be set large, so that when the folding mechanism 1 is folded, the connecting members 11 connected to the hinge bracket 112 are located at the hinge bracket 112. Within the space between the ends.
- the parallelogram folding mechanism 1 is folded and folded, and the hinge points of both the connecting members 11 are parallel to the axial direction of the center frame 2, the straight rod 111 of the carrier 11a and the center frame 2 are hingedly supported.
- the support of 112 is not attached to the isolation, but has a certain gap between them. The width of the gap is equal to the distance between the two ends of the hinge bracket 112, and the connector 11 can be completely accommodated within the gap. This allows the connector 11 to be completely closed with the center frame 2, thereby minimizing the footprint of the folding mechanism 1 after folding and folding.
- the specific hinge manner may be various.
- the carrier 11a is located on the same plane as the other connectors 11.
- all the connecting members 11 are located on the same plane, which can reduce the occupation space of the entire folding mechanism 1 in the direction along the hinge axis, and reduce the outer size of the foldable frame in this direction.
- a separate hinged bracket or other hinged member is typically utilized to effect articulation between the carrier 11a and other connectors.
- the carrier member 11a and the other connecting members may be arranged one above another in the axial direction of the hinge shaft at the hinge point.
- the articulated joints may be provided at corresponding positions of the ends of the carrier 11a and the other connecting members.
- a hole, and a separate hinged shaft is inserted into the hinge hole to achieve the hinge between the carrier 11a and the other connector; the hinge hole can also be opened in one of the carrier 11a or other connector, and the other
- the position of the corresponding hinge hole fixes the hinge shaft, and inserts the hinge shaft into the hinge hole to achieve the hinge between the two.
- the foldable frame 100 may further include a limit device, and the limiting device can be used to limit the parallelogram during deformation.
- the angle of deformation In general, when the parallelogram is deformed, the angle between two adjacent sides is usually varied between 0° and 90°, so this can be limited by the limiting device.
- the limiting device is usually disposed at the hinge point, and is generally a limiting portion or a limiting block disposed at the hinge point. When the connecting member 11 is rotated to a preset angle, the limiting portion at the hinge point or The limit block will abut against the connector 11 to prevent the connector 11 from continuing to rotate.
- the limiting portion and the limiting block may be disposed on the center frame 2 or other parts, or the limiting device of other principles may be used, and the invention is not limited thereto.
- FIG. 10 is a schematic structural view of another foldable frame according to Embodiment 1 of the present invention.
- each folding mechanism 1 there is further included at least one auxiliary connecting member 12, one end of the auxiliary connecting member 12 is connected to the center frame 2, and the other end is connected to the carrier 11a, and in order to secure the folding mechanism 1
- the side formed by the other connecting members 11 other than the carrier 12 in the auxiliary connecting member 12 and the parallelogram is parallel.
- the shape and length of the auxiliary connector 12 are consistent with the other connectors 11 except the carrier 11a.
- the auxiliary connecting member 12 can be improved.
- the structural strength of the folding mechanism 1 enhances its reliability.
- the connecting member 11 and the center frame 2 may be detachably connected.
- the quick release structure such as a thread or a snap can be provided, so that the connecting member 11 can be easily removed from the center frame 2 to further reduce the occupied space of the foldable frame 100, or to realize modularization of the connecting member. installation.
- the foldable frame 100 described above can be used as the main body of the UAV or as a separate structural accessory.
- the center frame 2 and the aircraft of the unmanned aerial vehicle The body is a one-piece or split structure.
- the center frame 2 and the unmanned aerial vehicle body are integrated, the center frame 2 serves as a main structural part of the unmanned aerial vehicle and is directly connected to the stand; and when the center frame 2 and the unmanned aerial vehicle body are in a split structure,
- the foldable frame 100 exists only as a separately detachable part of the structure of the UAV body.
- the center frame 2 can be detached from the body of the UAV or installed to a body without a frame and an arm. Up, thus enabling modular installation and replacement of the frame and arm.
- each of the connecting members can be closed to be close to or even attached to the center frame 2.
- the position of the joint, so the deformation ratio is large, enabling a smaller folding size for transportation and storage.
- the foldable frame comprises a center frame and at least one folding mechanism, and the folding mechanism is disposed at a side of the center frame, each folding mechanism includes at least three connecting members, and both ends of each connecting member are connected with other ends
- the end of the piece or the center frame is hinged, and the connecting piece and the center frame together form a variable shape polygon, and the connecting piece away from the center frame serves as a carrier for setting the power device, and the distance between the carrier and the center frame follows the polygon
- the shape changes and changes. This allows the foldable frame to be folded to achieve a smaller volume size, which is convenient for storage or transportation, and has a simple structure and convenient operation.
- FIG. 11 is a schematic structural diagram of a rack assembly according to Embodiment 2 of the present invention.
- the rack assembly 200 provided in this embodiment includes a foldable rack 100 and a power unit 3, and each of the carriers of the foldable rack 100 is provided with at least one power unit 3.
- the structure, function and working principle of the foldable frame 100 are the same as those of the foldable frame in the first embodiment, and are not described herein again.
- the power unit 3 is disposed on the carrier 11a of the foldable frame 100, and the power unit 3 can provide flight power for the unmanned aircraft, enabling the unmanned aircraft to perform operations such as take-off and landing. .
- At least one power unit 3 is disposed on each of the carriers 11a of the foldable frame 100. Since the number of folding mechanisms 1 in the foldable frame 100 is at least one, and usually an even number, the power unit 3 The number is usually also an even number.
- the power units 3 are generally arranged symmetrically with respect to the center frame 2 such that the torque generated by the power unit cancels each other out.
- two power units 3 are generally disposed on each of the carriers 11a of the foldable frame 100, and two power units are respectively disposed at opposite ends of the carrier 11a. This maximizes the distance between the power units 3 in each of the folding mechanisms 1, and maintains sufficient spacing between adjacent power units to improve stability and safety during flight.
- the power unit 3 includes a motor and a propeller, and the propeller hub is coupled to the shaft of the motor.
- the motor is used to drive the propeller to rotate to generate flight power.
- the power unit 3 generally also includes an electronic governor for adjusting the rotational speed of the motor.
- the electronic governor can adjust the rotational speed of the motor according to the control signal sent by the controller, and further control the rotational speed of the power components such as the propeller connected to the motor to control the adjustment and start-stop operation of the unmanned aerial vehicle into the flight attitude.
- each power unit 3 only one set of propellers or a double propeller may be provided to work together.
- different motors can be used to drive the corresponding propellers to operate.
- FIG. 12 is a schematic structural diagram of a power device in a rack assembly according to Embodiment 2 of the present invention.
- Each of the power units 3 may include a first motor 31, a second motor 32, a first propeller 33, and a second propeller 34.
- the hub of the first propeller 33 is coupled to the drive shaft of the first motor 31, and the second propeller 34 is connected.
- the hub is connected to the drive shaft of the second motor 32; at the same time, the first motor 31 and the second motor 32 are stacked on the same axis, and the first motor 31 and the second motor 32 are rotated in different directions, the first propeller 33 and the second propeller 34 are disposed away from each other.
- the airflows generated by the first propeller 33 and the second propeller 34 disposed away from each other are all oriented in the same direction, which can effectively enhance the power provided by the single power unit.
- the torque between the first motor 31 and the second motor 32 can also cancel each other, preventing the power unit 3 from generating a torque that affects the flight attitude of the UAV.
- each of the power devices may further include a connection support 35.
- the connection support 35 is fixed on the carrier 11a, and the opposite ends of the connection support 35 are respectively connected to the first The motor 31 and the second motor 32.
- the connecting bracket 35 and the carrier 11a can For a one-piece structure, it can also be a detachable structure.
- each of the power units includes a third motor, a third propeller and a fourth propeller, and the hub of the third propeller and the hub of the fourth propeller are both connected to the drive shaft of the third motor.
- the third propeller and the fourth propeller have the same steering, which can provide strong power for the unmanned aerial vehicle.
- the frame assembly includes a foldable frame and a power unit, and each of the carrier of the foldable frame is provided with at least one power unit; wherein the foldable frame includes a center frame and at least one folding mechanism, and is folded
- the mechanism is disposed at a side of the center frame, each folding mechanism includes at least three connecting members, and both ends of each connecting member are hinged with the ends or the center frame of the other connecting members, and the connecting member and the center frame together form a shape
- the variable polygon, the connector away from the center frame serves as a carrier for setting the power unit, and the distance between the carrier and the center frame changes as the shape of the polygon changes. This enables the foldable frame to be switched between the extended state and the folded and folded state, thereby allowing the foldable frame to be folded to achieve a smaller volume size, which is convenient for storage or transportation, and has a simple structure and convenient operation.
- FIG. 13 is a schematic structural diagram of an unmanned aerial vehicle according to Embodiment 3 of the present invention.
- the unmanned aerial vehicle 300 provided in this embodiment includes a rack assembly 200, and the center frame 2 of the rack assembly 200 is connected to a body or a tripod.
- the structure, function, and working principle of the rack assembly 200 are similar to those in the foregoing Embodiment 2, and therefore are not described herein again.
- the center frame 2 of the rack assembly 200 can be an integrated or split structure with the body, the center frame 2 can be connected as a separate component and a body, or can be used as the unmanned aerial vehicle 300.
- the main structural components are connected directly to the stand.
- the foldable frame in the frame assembly 200 enables folding deformation such that the distance between the carrier 11a and the center frame 2 in the foldable frame can be extended or shortened. In order to ensure normal and safe flight, or in a collapsed state, to effectively reduce the outer dimensions of the unmanned aerial vehicle 300, the storage and transportation of the unmanned aerial vehicle 300 is facilitated.
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Abstract
公开了一种可折叠机架（100）、机架组件（200）及无人飞行器（300）。可折叠机架（100）应用于无人飞行器（300）上，包括中心架（2）和至少一个折叠机构（1），折叠机构（1）设置在中心架（2）的侧方，每个折叠机构（1）包括至少三个连接件（11），每个连接件（11）的两端均与其它连接件（11）的端部或者中心架（2）铰接，且连接件（11）和中心架（2）共同围成形状可变的多边形，远离中心架（2）的连接件作为承载件（11a）用于设置动力装置（3），承载件（11a）与中心架（2）之间的距离随多边形形状的变化而改变。可折叠机架（100）能够实现机架的折叠，且结构简单，操作方便。
Description
本发明涉及无人飞行器领域，尤其涉及一种可折叠机架、机架组件及无人飞行器。
随着科技的不断发展进步，无人飞行器因使用方便、飞行速度较快等优点，得到了越来越广泛的应用。
目前，常用的多旋翼无人飞行器的机架包括有中心架，和中心架连接的多条机臂以及设置在机臂上的动力装置。为了方便运输，目前的多旋翼无人飞行器的机架可设置能够进行弯折的机臂，存储和运输时，可以将机臂折叠，或者弯折至和中心架靠拢的角度，以减小无人飞行器的整体占用体积。
然而，通过机臂弯折的方式实现无人飞行器机架的折叠，如果弯折方式较为简单，则仍然会占用较大的体积；而如果采用较为复杂的弯折方式，则折叠与打开操作均较为不便，且实现成本较高。
发明内容
本发明提供一种可折叠机架、机架组件及无人飞行器，能够实现机架的折叠，且结构简单，操作方便。
第一方面，本发明提供一种可折叠机架，应用于无人飞行器上，包括中心架和至少一个折叠机构，折叠机构设置在中心架的侧方，每个折叠机构包括至少三个连接件，每个连接件的两端均与其它连接件的端部或者中心架铰接，且连接件和中心架共同围成形状可变的多边形，远离中心架的连接件作为承载件用于设置动力装置，承载件与中心架之间的距离随多边形形状的变化而改变。
第二方面，本发明提供一种机架组件，包括如上所述的可折叠机架和
动力装置，可折叠机架的每个承载件上设置有至少一个动力装置。
第三方面，本发明提供一种无人飞行器，包括如上所述的机架组件，机架组件的中心架与机体或者脚架连接。
本发明的可折叠机架、机架组件及无人飞行器，可折叠机架包括中心架和至少一个折叠机构，折叠机构设置在中心架的侧方，每个折叠机构包括至少三个连接件，每个连接件的两端均与其它连接件的端部或者中心架铰接，且连接件和中心架共同围成形状可变的多边形，远离中心架的连接件作为承载件用于设置动力装置，承载件与中心架之间的距离随多边形形状的变化而改变。这样能够让可折叠机架通过折叠而实现较小的体积尺寸，便于进行存储或运输，且结构简单，操作方便。
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作一简单地介绍，显而易见地，下面描述中的附图是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1是本发明实施例一提供的可折叠机架的结构示意图；
图2是本发明实施例一提供的折叠机构围成四边形时可折叠机架的结构示意图；
图3是图2中的可折叠机架在折叠机构折叠时的结构示意图；
图4是本发明实施例一提供的折叠机构围成五边形时可折叠机架的结构示意图；
图5是图4中的可折叠机架在折叠机构折叠时的结构示意图；
图6是本发明实施例一提供的折叠机构围成六边形时可折叠机构的结构示意图；
图7是图6中的可折叠机架在折叠机构折叠时的结构示意图；
图8是本发明实施例一提供的围成平行四边形的折叠机构在展开时的结构示意图；
图9是本发明实施例一提供的折叠机构在折叠时的结构示意图；
图10是本发明实施例一提供的另一种可折叠机架的结构示意图；
图11是本发明实施例二提供的一种机架组件的结构示意图；
图12是本发明实施例二的机架组件中的一种动力装置的结构示意图；
图13是本发明实施例三提供的一种无人飞行器的结构示意图。
附图标记说明：
1—折叠机构；2—中心架；3—动力装置；11—连接件；12—辅助连接件；31—第一电机；32—第二电机；33—第一螺旋桨；34—第二螺旋桨；35—连接座；11a—承载件；111—直杆；112—铰接支架；100—可折叠机架；200—机架组件；300—无人飞行器。
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
图1是本发明实施例一提供的可折叠机架的结构示意图。如图1所示，本实施例提供的可折叠机架100通常应用于无人飞行器上，其中，无人飞行器一般包括有机架、脚架和需要挂载的作业设备等。机架上可设置动力装置或动力组件，以带动整个无人飞行器以及作业设备进行飞行和起降。
可折叠机架100包括中心架2和至少一个折叠机构1，折叠机构1设置在中心架2的侧方，每个折叠机构1包括至少三个连接件11，每个连接件11的两端均与其它连接件的端部或者中心架2铰接，且连接件11和中心架2共同围成形状可变的多边形，远离中心架2的连接件作为承载件11a用于设置动力装置，承载件11a与中心架12之间的距离随多边形形状的变化而改变。
具体的，可折叠机架100的中心架2可作为无人飞行器的主体结构部分，并可用于连接脚架，以及挂载作业设备等。一般的，为了便于进行平衡及配重，可折叠机架100的中心架2通常位于无人飞行器的几何中心位置，而可折叠机架100的折叠机构1主要作为用于连接中心架以及动力装置的机臂结构，一般相对于中心架2呈轴对称或者中心对称设置。中心架
2可以为不同的形状和外形，以满足不同的要求。
为了实现可折叠机架100的折叠与展开，在可折叠机架100中，包括有至少一个折叠机构1，折叠机构1设置在中心架2侧方，且每一个折叠机构1，都包括有至少三个连接件11。其中，每一个连接件11的两端，均与其它连接件11的端部，或者中心架2连接，且连接方式均为铰接，即平面转动副连接，而与中心架2所连接的连接件11中，不同连接件的端部铰接在中心架2的不同部位上，这样连接件11和中心架2首尾相接，共同围成了一个封闭的多边形形状，中心架2以及单个连接件11均组成该多边形的一条独立的边。由于折叠机构1中的连接件11至少有三个，因此折叠机构1中连接件11和中心架2所组成的多边形至少为四边形。进一步的，又由于每个连接件11的端部与其它部件之间均为铰接连接，所以连接件11和相邻的部件之间可相对转动，且围成的多边形的各条边之间均可相对旋转，从而变为不同的形状。
由于每个折叠机构1中各个连接件11均和其它部件相连，且折叠机构1围成了封闭的多边形，所以整个折叠机构11为联动机构，此时，可通过驱动其中一个单独的连接件转动，即可带动整个折叠机构11进行整体折叠变形，操纵和驱动方式较为简单。具体的，可以通过在铰接点处设置齿轮传动件的方式驱动连接件转动，也可以通过其它外部部件带动连接件旋转。
为了在折叠机构1上设置动力装置，在每个折叠机构1中，均至少具有一个远离中心架2，且两端均不和中心架2连接的连接件11，该连接件11可作为用于设置并承载动力装置的承载件11a，且承载件11a与中心架2之间的距离能够随着多边形形状的变化而改变，这样动力装置和承载件11a与中心架2之间的距离可以伸长或缩短。当承载件11a和中心架2之间的距离最大时，动力装置远离中心架2，所以动力装置中的螺旋桨等元件不会和中心架2等结构部件发生干涉，可以保证正常安全的飞行；而当承载件11a和中心架2之间的距离最小时，此时可折叠机架100的多边形呈收拢状态，其轮廓尺寸最小，能够有效减小无人飞行器的外形尺寸，有利于无人飞行器的存储和运输。
通常的，由于可折叠机架100中，承载件11a为远离中心架2的连接
件，为了使无人飞行器在需要飞行时，让设置有动力装置的承载件11a尽量远离中心架2，且进行折叠存放时，使承载件11a和中心架2之间的距离尽量减小，需要让折叠机构1产生较大的轮廓变形，例如，可以让承载件11a位于折叠机构1所成的多边形中，离中心架2最远的边或者顶点上，此时，承载件11a距离中心架2的距离最大；而多边形在折叠收拢时，所有连接件11均相互靠拢，并近似在同一条直线上。此时，承载件11a及其动力装置与中心架2的距离最小。
具体的，通常为了保证平衡，无人飞行器的可折叠机架100包括偶数个折叠机构1，折叠机构1两两对称地设置在中心架2的两侧。这样可折叠机架100的重心会位于中心架2上，且优选的，可折叠机架100的重心可位于中心架2的中轴线上，这样有利于无人飞行器在飞行中保持平衡的姿态。其中，考虑到重量因素，可折叠机架100一般可以包括两个或者四个对称设置于中心架2两侧的折叠机构1。
具体的，每个折叠机构1均可以围成多种形状。例如在每个折叠机构1中，所有连接件11和中心架2共同围成形状可变的多边形可包括如下形状的一种：四边形、五边形或六边形。下面以可折叠机架100包括两个折叠机构1为例进行说明：
图2是本发明实施例一提供的折叠机构围成四边形时可折叠机架的结构示意图。图3是图2中的可折叠机架在折叠机构收拢时的结构示意图。如图2和图3所示，每个折叠机构1中，包括有三个连接件11，其中，远离中心架2的连接件11为用于设置动力装置的承载件11a。三个连接件11与中心架2共同构成了一个四边形，且连接件11或者中心架2均构成该四边形的一条独立的边。由于四边形中每个边均可相对相邻边产生旋转，所以四边形的形状可随着连接件11的相对转动而产生变化。例如当折叠机构1收拢至图3所示的位置时，四边形的各条边均相互靠拢，并近似排列在一条直线上。此时，承载件11a与中心架2相邻，可以保证折叠机构1具有较小的轮廓尺寸。
图4是本发明实施例一提供的折叠机构围成五边形时可折叠机架的结构示意图。图5是图4中的可折叠机架在折叠机构折叠时的结构示意图。如图4和图5所示，每个折叠机构1中包括有四个连接件11，而远离中心
架2的两个连接件可以作为承载件11a，动力装置可以设置在这两个承载件11a上，也可以设置于这两个承载件11a之间的铰接点上。和四边形类似，五边形的折叠机构中，连接件11和中心架2均形成一条独立的边，且连接件11相对铰接点转动时，可使该五边形各个边之间的角度变大或变小，从而构成不同的形状。当五边形的各条边之间的角度大约为180°时，五边形的各条边近似排列在同一条直线上，并呈收拢状态。
同样的，图6是本发明实施例一提供的折叠机构围成六边形时可折叠机构的结构示意图。图7是图6中的可折叠机架在折叠机构折叠时的结构示意图。如图6和图7所示，此外，每个折叠机构1中还可以包括五个连接件11，且连接件11和中心架2共同围成了一个六边形。和四边形以及五边形类似，六边形同样可以依靠相邻连接件11之间的转动而形成不同的形状，从而呈张开或收拢状态。
可以理解的是，折叠机构1所围成的多边形并不限于上述四边形、五边形及六边形，而是可以为其它多边形形状，只要能够满足多边形形状可变，且承载件与中心架之间的距离可变即可。
此外，在每个可折叠机架100中，位于中心架侧方的折叠机构1既可以为相同的多边形，如两侧均为四边形折叠机构；也可以为不同的多边形，例如中心架一侧的折叠机构1为四边形折叠机构，而另一侧为五边形折叠机构等。其折叠机构1的具体组成和结构均可以根据无人飞行器的结构和使用要求而自由选用。
在折叠机构1所围成的上述多边形中，为了减少机构复杂度，确保变形的顺畅性及可靠性，折叠机构1一般以围成四边形为主。例如，可以让每个折叠机构1中所有连接件11和中心架2共同围成形状可改变的平行四边形。图8是本发明实施例一提供的围成平行四边形的折叠机构在展开时的结构示意图。图9是本发明实施例一提供的折叠机构在折叠时的结构示意图。如图8和图9所示，由于平行四边形的结构不稳定性，所以可以通过驱动平行四边形中的某条边转动，以改变平行四边形的形状，使其呈矩形或者“压扁”的状态。而折叠机构1所围成的平行四边形中，中心架2和承载件11a构成了相对的两条边，中心架2和承载件11a之间的距离可以随着平行四边形形状的改变而变化，以达到可折叠机架在飞行状态和
存储及运输状态之间的切换。其中，折叠机构1中各个连接件11之间的铰接方式是双向的，即各连接件11既可以朝向图8中的转动方向旋转而进行折叠变形，也可以沿图8中的转动方向的反方向旋转而折叠变形。
进一步的，因为折叠机构1中包括连接件11以及中心架2，而连接件11及中心架2可能具有不同的形状和尺寸。为了确保连接件11和中心架2形成形状可变的平行四边形，可以对铰接点的位置进行限定，具体的，可以让平行四边形中相对的两个连接件的两端的铰接点之间的距离均相等，且同一折叠机构中，和中心架2所铰接的两个连接件11的两端铰接点之间的连线相互平行。这样，只要确定了连接件11和中心架2的铰接点的位置，即可保证连接件11和中心架2共同构成一个平行四边形，而连接件11以及中心架2的具体形状可不做限制，只要在变形时没有干涉即可。
可选的，由于平行四边形中，邻边所成的角度的变化范围较大，所以可让平行四边形具有较大的变形范围。具体的，承载件11a和与承载件11a铰接的其它连接件11之间形成的角度通常可在0°到180°之间。当连接件11和中心架2之间的角度为0°或者近似0°时，承载件11a和中心架2近似位于同一条直线上，这样承载件11a与中心架2之间的距离最近，而可折叠机架的外形轮廓也最小，便于进行运输或存放。进一步的，当折叠机构为平行四边形时，可以设置连接件11的两端的铰接点之间的连线与中心架2的长度方向平行时，承载件11a与中心架2贴合，这样可以使承载件11a和中心架2之间的最小距离为零。
具体的，在折叠机构1中，一般所有连接件11的端部铰接点的铰接轴均相互平行。这样整个折叠机构1的变形过程均发生在同一平面内，可以有效简化折叠机构1的结构复杂度，并增加折叠机构1在变形的可靠性。此外，也可以让铰接点的铰接轴之间呈一定角度，以满足不同的使用需求，此时，折叠机构1的变形过程通常发生在空间范围内。
作为一种可选的实施方式，为了简化结构，连接件11通常为连接杆，且连接杆的轴线方向与连接件11铰接轴的轴向垂直。这样通过简单的杆件即可组成可变形的折叠机构1。
同样的，连接件11为杆件结构时，承载件11a可包括与中心架2的
长度方向平行的直杆111。直杆111的方向一般与中心架2的轴线平行，这样当承载件11a和中心架2合拢在一起时，承载件11a中的直杆111会贴合在中心架2的侧方，且直杆111的延伸方向和中心架2的轴线方向保持一致，而承载件11a的垂直于自身延伸方向的尺寸较小，所占用的空间也会较少，这样结构较为紧凑。
进一步的，为了便于和其它连接件11实现铰接，承载件11a上还可以包括铰接支架112，铰接支架112的第一端与直杆111连接，铰接支架112的第二端和其它连接件11铰接。此时，其它连接件11即可通过铰接支架112与承载件11a实现铰接。铰接支架112的设置位置较为灵活，既可以设置在承载件11a中直杆111的端部，也可以设置在靠近直杆111中部的位置，这样承载件11a的结构和动力装置的设置位置均具有较大的灵活性。
当承载件11a上包括铰接支架112时，可以将铰接支架112的两端之间的距离设置的较大，以使折叠机构1收拢时，和铰接支架112连接的连接件11均位于铰接支架112的两端之间的空间范围内。这样当平行四边形的折叠机构1折叠合拢，且所有连接件11的两端铰接点连线均和中心架2的轴线方向平行时，承载件11a的直杆111以及中心架2之间在铰接支架112的支撑与隔离下并没有贴合，而是彼此之间具有一定的间隙，该间隙的宽度等于铰接支架112两端之间的距离，连接件11可以被完全容纳在该间隙之内。这样可以使连接件11完全与中心架2合拢，从而最大限度地减少折叠机构1在收拢折叠后的占用空间。
相邻两个连接件11之间在实现铰接时，其具体的铰接方式也可以有多种。例如，作为一种可选的实施方式，在每个折叠机构1中，承载件11a与其它连接件11位于同一平面上。这样使所有连接件11均位于同一平面，可以减少整个折叠机构1在沿着铰接轴方向上的占用空间，减小可折叠机架在该方向上的外形尺寸。此时，通常会利用独立的铰接支架或者其它铰接部件来实现承载件11a与其它连接件之间的铰接。
而作为另一种可选的实施方式，每个折叠机构中1，也可以让承载件11a与其它连接件在铰接点沿铰接轴的轴向方向上下相叠设置。具体的，可以在承载件11a和其它连接件的端部的对应位置均开设相互连通的铰接
孔，并将独立的铰接转轴穿入铰接孔中，以实现承载件11a与其它连接件之间的铰接；也可以在承载件11a或者其它连接件中的一者开设铰接孔，而另一者的对应铰接孔的位置固定铰接转轴，并将铰接转轴插入铰接孔中，实现两者之间的铰接。
此外，可选的，当折叠机构1进行变形时，为了防止连接件11转动至不合适的角度，可折叠机架100还可以包括有限位装置，限位装置能够用于限制平行四边形在变形时的变形角度。一般的，平行四边形在变形时，两条相邻边之间的角度通常在0°到90°之间变化，因此可以通过限位装置对此进行限制。具体的，限位装置通常设置在铰接点处，且一般为设置在铰接点处的限位部或者限位块等，当连接件11转动到预设角度时，铰接点处的限位部或者限位块会和连接件11相抵，以阻止连接件11继续转动。此外，也可以在中心架2上或者其它部位设置限位部及限位块，或者采用其它原理的限位装置等，本发明并不以此为限。
此外，在上述平行四边形折叠机构的基础上，为了提高折叠机构1的结构强度和变形可靠性，还可以设置辅助结构。图10是本发明实施例一提供的另一种可折叠机架的结构示意图。如图10所示，在每个折叠机构1中，还包括有至少一个辅助连接件12，辅助连接件12的一端与中心架2连接，另一端与承载件11a连接，且为了保证折叠机构1的正常变形，辅助连接件12与平行四边形中，除了承载件12之外的其它连接件11所构成的边平行。一般的，为了简化设计并降低成本，辅助连接件12的形状和长度均和除承载件11a外的其它连接件11保持一致。当中心架2以及承载件11a的长度较长，或者单个连接件11的承力能力较弱，再或者可折叠机架所承受的负载较大时，均可以通过设置辅助连接件12，来提高折叠机构1的结构强度，增强其可靠性。
可选的，连接件11与中心架2之间可以为可拆卸连接。此时，可以通过设置螺纹或者卡扣等快拆结构，使连接件11可以较为容易地从中心架2上取下，以进一步减少可折叠机架100的占用空间，或者实现连接件的模块化安装。
此外，上述可折叠机架100，既可以作为无人飞行器的主要机体，也可以作为一个单独的结构附件存在。相应的，中心架2和无人飞行器的机
体为一体式或者分体式结构。当中心架2和无人飞行器的机体为一体时，中心架2作为无人飞行器的主体结构部分，并和脚架直接连接；而当中心架2和无人飞行器的机体为分体式结构时，可折叠机架100仅作为无人飞行器机体结构的一个可以独立拆卸的部分存在，此时，可以将中心架2从无人飞行器的机体上拆下或安装至没有设置机架和机臂的机体上，从而实现机架和机臂的模块化安装和更换。
由于本发明中是通过多边形的形状改变而进行折叠变形，且在折叠机构1的形状以及各连接件11的尺寸比例合理的情况下，能够使各连接件均合拢至和中心架2靠近甚至贴合的位置，所以变形比例较大，能够实现较小的折叠尺寸，便于运输和存放。
本实施例中，可折叠机架包括中心架和至少一个折叠机构，折叠机构设置在中心架的侧方，每个折叠机构包括至少三个连接件，每个连接件的两端均与其它连接件的端部或者中心架铰接，且连接件和中心架共同围成形状可变的多边形，远离中心架的连接件作为承载件用于设置动力装置，承载件与中心架之间的距离随多边形形状的变化而改变。这样能够让可折叠机架通过折叠而实现较小的体积尺寸，便于进行存储或运输，且结构简单，操作方便。
图11是本发明实施例二提供的一种机架组件的结构示意图。如图11所示，本实施例提供的机架组件200，包括可折叠机架100和动力装置3，可折叠机架100的每个承载件上设置有至少一个动力装置3。其中，可折叠机架100的结构、功能和工作原理均和前述实施例一中的可折叠机架相同，此处不再赘述。
具体的，机架组件中，动力装置3设置在可折叠机架100的承载件11a上，动力装置3可以为无人飞行器提供飞行用的动力，让无人飞行器能够实现起降和飞行等操作。在可折叠机架100的每个承载件11a上均设置有至少一个动力装置3，由于可折叠机架100中的折叠机构1的数量为至少一个，且通常呈偶数个，所以动力装置3的数量通常也为偶数个。动力装置3通常相对于中心架2对称设置，这样可以使动力装置所产生的转矩相互抵消。
可选的，为了提供较为充足的动力，在可折叠机架100的每个承载件11a上一般设置有两个动力装置3，且两个动力装置分别设置在承载件11a的相对两端。这样在可以让每一个折叠机构1中的动力装置3之间的距离最大，能够保持相邻动力装置之间具有足够的间隔，提高飞行时的稳定性和安全性。
具体的，为了为无人飞行器提供动力，动力装置3包括电机和螺旋桨，螺旋桨的桨毂和电机的转轴连接。电机用于驱动螺旋桨转动，以产生飞行动力。
此外，可选的，动力装置3一般还包括用于调节电机的转速的电子调速器。电子调速器可以根据控制器所发出的控制信号，调整电机的转速，并进一步控制电机连接的螺旋桨等动力元件的转速，以控制无人飞行器进飞行姿态的调整和启停等操作。
通常的，每个动力装置3中，既可以只设置有一套螺旋桨，也可以设置为双螺旋桨共同进行工作。当每个动力装置3中具有两套螺旋桨时，作为其中一个可选的实施方式，可以分别利用不同的电机驱动对应的螺旋桨进行工作。
具体的，图12是本发明实施例二的机架组件中的一种动力装置的结构示意图。每个动力装置3中可包括有第一电机31、第二电机32、第一螺旋桨33和第二螺旋桨34，第一螺旋桨33的桨毂和第一电机31的驱动轴连接，第二螺旋桨34的桨毂和第二电机32的驱动轴连接；同时，第一电机31和第二电机32上下叠放在同一轴线上，且第一电机31和第二电机32的转动方向不同，第一螺旋桨33和第二螺旋桨34相互背离设置。这样，由于第一电机31和第二电机32的转向不同，所以相互背离设置的第一螺旋桨33和第二螺旋桨34所产生的气流均朝向同一方向，这样可以有效增强单个动力装置所提供的动力，同时，第一电机31和第二电机32之间的转矩也能够相互抵消，避免动力装置3产生影响到无人飞行器飞行姿态的转矩。
为了安放第一电机31和第二电机32，每个动力装置中一般还可以包括连接支座35，连接支座35固定在承载件11a上，且连接支座35的相对两端分别连接第一电机31和第二电机32。连接支座35与承载件11a可以
为一体式结构，也可以为可拆卸式结构。
此外，作为另一种可选的实施方式，当动力装置中具有两套螺旋桨时，也可以利用一个电机带动不同的螺旋桨进行工作。此时，每个动力装置中包括第三电机，第三螺旋桨和第四螺旋桨，第三螺旋桨的桨毂和第四螺旋桨的桨毂均与第三电机的驱动轴连接。此时，第三螺旋桨和第四螺旋桨的转向相同，可以为无人飞行器提供较强的动力。
本实施例中，机架组件包括可折叠机架和动力装置，可折叠机架的每个承载件上设置有至少一个动力装置；其中，可折叠机架包括中心架和至少一个折叠机构，折叠机构设置在中心架的侧方，每个折叠机构包括至少三个连接件，每个连接件的两端均与其它连接件的端部或者中心架铰接，且连接件和中心架共同围成形状可变的多边形，远离中心架的连接件作为承载件用于设置动力装置，承载件与中心架之间的距离随多边形形状的变化而改变。这样能够使可折叠机架在伸展状态与折叠合拢状态之间切换，从而让可折叠机架通过折叠而实现较小的体积尺寸，便于进行存储或运输，且结构简单，操作方便。
图13是本发明实施例三提供的一种无人飞行器的结构示意图。如图13所示，本实施例提供的无人飞行器300包括有机架组件200，机架组件200的中心架2与机体或者脚架连接。其中，机架组件200的结构、功能和工作原理均和前述实施例二中的类似，故此处不再赘述。
本实施例的无人飞行器300，机架组件200的中心架2由于和机体可以为一体式或者分体式结构，所以中心架2既可以作为独立部件和机体连接，也可以作为无人飞行器300的主要结构部件，而直接和脚架连接。机架组件200中的可折叠机架能够实现折叠变形，使可折叠机架中承载件11a与中心架2之间的距离可以伸长或缩短。以保证正常安全的飞行，或者呈收拢状态，以有效减小无人飞行器300的外形尺寸，便于无人飞行器300的存储和运输。
本实施例中，无人飞行器包括有机架组件，机架组件的中心架与机体或者脚架连接，机架组件中包括有可折叠机架，可折叠机架的每个承载件上设置有至少一个动力装置；其中，可折叠机架包括中心架和至少一个折
叠机构，折叠机构设置在中心架的侧方，每个折叠机构包括至少三个连接件，每个连接件的两端均与其它连接件的端部或者中心架铰接，且连接件和中心架共同围成形状可变的多边形，远离中心架的连接件作为承载件用于设置动力装置，承载件与中心架之间的距离随多边形形状的变化而改变。这样能够使可折叠机架在伸展状态与折叠合拢状态之间切换，从而让可折叠机架通过折叠而实现较小的体积尺寸，便于进行存储或运输，且结构简单，操作方便。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分或者全部技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。
Claims (66)
- 一种可折叠机架，应用于无人飞行器上，其特征在于，包括中心架和至少一个折叠机构，所述折叠机构设置在所述中心架的侧方，每个所述折叠机构包括至少三个连接件，每个所述连接件的两端均与其它所述连接件的端部或者所述中心架铰接，且所述连接件和所述中心架共同围成形状可变的多边形，远离所述中心架的连接件作为承载件用于设置动力装置，所述承载件与所述中心架之间的距离随所述多边形形状的变化而改变。
- 根据权利要求1所述的可折叠机架，其特征在于，包括偶数个折叠机构，所述折叠机构两两对称地设置在所述中心架的两侧。
- 根据权利要求1或2所述的可折叠机架，其特征在于，每个所述折叠机构中，所有所述连接件和所述中心架共同围成形状可变的多边形包括如下形状的一种：四边形、五边形或六边形。
- 根据权利要求1或2所述的可折叠机架，其特征在于，每个所述折叠机构中所有所述连接件和所述中心架共同围成形状可改变的平行四边形。
- 根据权利要求4所述的可折叠机架，其特征在于，所述平行四边形中相对的两个所述连接件的两端的铰接点之间的距离均相等，且同一折叠机构中，与所述中心架铰接的两个所述连接件的两端铰接点之间的连线相互平行。
- 根据权利要求4所述的可折叠机架，其特征在于，所述连接件的两端的铰接点之间的连线与所述中心架的长度方向平行时，所述承载件与所述中心架贴合。
- 根据权利要求1或2所述的可折叠机架，其特征在于，所有所述连接件的端部铰接点的铰接轴均相互平行。
- 根据权利要求1或2所述的可折叠机架，其特征在于，所述连接件为连接杆，所述连接杆的轴线方向与所述连接件和所述承载件的铰接轴的轴向垂直。
- 根据权利要求8所述的可折叠机架，其特征在于，所述连接件与所述中心架之间为可拆卸连接。
- 根据权利要求4所述的可折叠机架，其特征在于，所述承载件包括与所述中心架的长度方向平行的直杆。
- 根据权利要求10所述的可折叠机架，其特征在于，所述承载件还包括铰接支架，所述铰接支架的第一端与所述直杆连接，所述铰接支架的第二端和其它连接件铰接。
- 根据权利要求11所述的可折叠机架，其特征在于，所述折叠机构收拢时，和所述铰接支架连接的连接件均位于所述铰接支架两端之间。
- 根据权利要求11或12所述的可折叠机架，其特征在于，每个所述折叠机构中，所述承载件与其它连接件位于同一平面上。
- 根据权利要求11或12所述的可折叠机架，其特征在于，每个所述折叠机构中，所述承载件与其它连接件在所述铰接点沿所述铰接轴的轴向方向上下相叠设置。
- 根据权利要求1或2所述的可折叠机架，其特征在于，还包括限位装置，所述限位装置用于限制所述平行四边形在变形时的变形角度。
- 根据权利要求4所述的可折叠机架，其特征在于，所述承载件和与所述承载件铰接的连接件之间形成的角度在0°到180°之间。
- 根据权利要求4所述的可折叠机架，其特征在于，每个所述折叠机构中，还包括有至少一个辅助连接件，所述辅助连接件的一端与所述中心架连接，另一端与所述承载件连接，且所述辅助连接件与所述平行四边形中，所述承载件之外的连接件所构成的边平行。
- 根据权利要求1或2所述的可折叠机架，其特征在于，所述中心架和所述无人飞行器的机体为一体式或者分体式结构。
- 一种机架组件，其特征在于，包括可折叠机架和动力装置，所述可折叠机架的每个承载件上设置有至少一个所述动力装置；其中，所述可折叠机架包括中心架和至少一个折叠机构，所述折叠机构设置在所述中心架的侧方，每个所述折叠机构包括至少三个连接件，每个所述连接件的两端均与其它所述连接件的端部或者所述中心架铰接，且所述连接件和所述中心架共同围成形状可变的多边形，远离所述中心架的连接件作为承载件用于设置动力装置，所述承载件与所述中心架之间的距离随所述多边形形状的变化而改变。
- 根据权利要求19所述的机架组件，其特征在于，所述可折叠机架包括偶数个折叠机构，所述折叠机构两两对称地设置在所述中心架的两侧。
- 根据权利要求19或20所述的机架组件，其特征在于，每个所述折叠机构中，所有所述连接件和所述中心架共同围成形状可变的多边形包括如下形状的一种：四边形、五边形或六边形。
- 根据权利要求19或20所述的机架组件，其特征在于，每个所述折叠机构中所有所述连接件和所述中心架共同围成形状可改变的平行四边形。
- 根据权利要求22所述的机架组件，其特征在于，所述平行四边形中相对的两个所述连接件的两端的铰接点之间的距离均相等，且同一折叠机构中，与所述中心架铰接的两个所述连接件的两端铰接点之间的连线相互平行。
- 根据权利要求22所述的机架组件，其特征在于，所述连接件的两端的铰接点之间的连线与所述中心架的长度方向平行时，所述承载件与所述中心架贴合。
- 根据权利要求19或20所述的机架组件，其特征在于，所有所述连接件的端部铰接点的铰接轴均相互平行。
- 根据权利要求19或20所述的机架组件，其特征在于，所述连接件为连接杆，所述连接杆的轴线方向与所述连接件和所述承载件的铰接轴的轴向垂直。
- 根据权利要求26所述的机架组件，其特征在于，所述连接件与所述中心架之间为可拆卸连接。
- 根据权利要求22所述的机架组件，其特征在于，所述承载件包括与所述中心架的长度方向平行的直杆。
- 根据权利要求28所述的机架组件，其特征在于，所述承载件还包括铰接支架，所述铰接支架的第一端与所述直杆连接，所述铰接支架的第二端和其它连接件铰接。
- 根据权利要求29所述的机架组件，其特征在于，所述折叠机构收拢时，和所述铰接支架连接的连接件均位于所述铰接支架两端之间。
- 根据权利要求29或30所述的机架组件，其特征在于，每个所述折叠机构中，所述承载件与其它连接件位于同一平面上。
- 根据权利要求29或30所述的机架组件，其特征在于，每个所述折叠机构中，所述承载件与其它连接件在所述铰接点沿所述铰接轴的轴向方向上下相叠设置。
- 根据权利要求19或20所述的机架组件，其特征在于，还包括限位装置，所述限位装置用于限制所述平行四边形在变形时的变形角度。
- 根据权利要求22所述的机架组件，其特征在于，所述承载件和与所述承载件铰接的连接件之间形成的角度在0°到180°之间。
- 根据权利要求22所述的机架组件，其特征在于，每个所述折叠机构中，还包括有至少一个辅助连接件，所述辅助连接件的一端与所述中心架连接，另一端与所述承载件连接，且所述辅助连接件与所述平行四边形中，所述承载件之外的连接件所构成的边平行。
- 根据权利要求19或20所述的机架组件，其特征在于，所述中心架和所述无人飞行器的机体为一体式或者分体式结构。
- 根据权利要求19所述的机架组件，其特征在于，每个所述承载件上设置有两个所述动力装置，两个所述动力装置分别设置在所述承载件的相对两端。
- 根据权利要求19或20所述的机架组件，其特征在于，所述动力装置包括电机和螺旋桨，所述螺旋桨的桨毂和所述电机的转轴连接。
- 根据权利要求38所述的机架组件，其特征在于，每个所述动力装置中包括有第一电机、第二电机、第一螺旋桨和第二螺旋桨，所述第一螺旋桨的桨毂和所述第一电机的驱动轴连接，所述第二螺旋桨的桨毂和所述第二电机的驱动轴连接；所述第一电机和所述第二电机上下叠放在同一轴线上，且所述第一电机和所述第二电机的转动方向不同，所述第一螺旋桨和所述第二螺旋桨相互背离设置。
- 根据权利要求39所述的机架组件，其特征在于，每个所述动力装置中还包括连接支座，所述连接支座固定在所述承载件上，且所述连接支座的相对两端分别连接所述第一电机和所述第二电机。
- 根据权利要求38所述的机架组件，其特征在于，每个所述动力装置中包括第三电机，第三螺旋桨和第四螺旋桨，所述第三螺旋桨的桨毂和所述第四螺旋桨的桨毂均与所述第三电机的驱动轴连接。
- 根据权利要求19或20所述的机架组件，其特征在于，所述动力装置还包括用于调节所述电机的转速的电子调速器。
- 一种无人飞行器，其特征在于，包括机架组件，所述机架组件的中心架与机体或者脚架连接；所述机架组件包括可折叠机架和动力装置，所述可折叠机架的每个承载件上设置有至少一个所述动力装置；其中，所述可折叠机架包括中心架和至少一个折叠机构，所述折叠机构设置在所述中心架的侧方，每个所述折叠机构包括至少三个连接件，每个所述连接件的两端均与其它所述连接件的端部或者所述中心架铰接，且所述连接件和所述中心架共同围成形状可变的多边形，远离所述中心架的连接件作为承载件用于设置动力装置，所述承载件与所述中心架之间的距离随所述多边形形状的变化而改变。
- 根据权利要求43所述的无人飞行器，其特征在于，所述可折叠机架包括偶数个折叠机构，所述折叠机构两两对称地设置在所述中心架的两侧。
- 根据权利要求43或44所述的无人飞行器，其特征在于，每个所述折叠机构中，所有所述连接件和所述中心架共同围成形状可变的多边形包括如下形状的一种：四边形、五边形或六边形。
- 根据权利要求43或44所述的无人飞行器，其特征在于，每个所述折叠机构中所有所述连接件和所述中心架共同围成形状可改变的平行四边形。
- 根据权利要求46所述的无人飞行器，其特征在于，所述平行四边形中相对的两个所述连接件的两端的铰接点之间的距离均相等，且同一折叠机构中，与所述中心架铰接的两个所述连接件的两端铰接点之间的连线相互平行。
- 根据权利要求46所述的无人飞行器，其特征在于，所述连接件的两端的铰接点之间的连线与所述中心架的长度方向平行时，所述承载件 与所述中心架贴合。
- 根据权利要求43或44所述的无人飞行器，其特征在于，所有所述连接件的端部铰接点的铰接轴均相互平行。
- 根据权利要求43或44所述的无人飞行器，其特征在于，所述连接件为连接杆，所述连接杆的轴线方向与所述连接件和所述承载件的铰接轴的轴向垂直。
- 根据权利要求50所述的无人飞行器，其特征在于，所述连接件与所述中心架之间为可拆卸连接。
- 根据权利要求46所述的无人飞行器，其特征在于，所述承载件包括与所述中心架的长度方向平行的直杆。
- 根据权利要求52所述的无人飞行器，其特征在于，所述承载件还包括铰接支架，所述铰接支架的第一端与所述直杆连接，所述铰接支架的第二端和其它连接件铰接。
- 根据权利要求53所述的无人飞行器，其特征在于，所述折叠机构收拢时，和所述铰接支架连接的连接件均位于所述铰接支架两端之间。
- 根据权利要求53或54所述的无人飞行器，其特征在于，每个所述折叠机构中，所述承载件与其它连接件位于同一平面上。
- 根据权利要求53或54所述的无人飞行器，其特征在于，每个所述折叠机构中，所述承载件与其它连接件在所述铰接点沿所述铰接轴的轴向方向上下相叠设置。
- 根据权利要求43或44所述的无人飞行器，其特征在于，还包括限位装置，所述限位装置用于限制所述平行四边形在变形时的变形角度。
- 根据权利要求46所述的无人飞行器，其特征在于，所述承载件和与所述承载件铰接的连接件之间形成的角度在0°到180°之间。
- 根据权利要求46所述的无人飞行器，其特征在于，每个所述折叠机构中，还包括有至少一个辅助连接件，所述辅助连接件的一端与所述中心架连接，另一端与所述承载件连接，且所述辅助连接件与所述平行四边形中，所述承载件之外的连接件所构成的边平行。
- 根据权利要求43或44所述的无人飞行器，其特征在于，所述中心架和所述无人飞行器的机体为一体式或者分体式结构。
- 根据权利要求43所述的无人飞行器，其特征在于，每个所述承载件上设置有两个所述动力装置，两个所述动力装置分别设置在所述承载件的相对两端。
- 根据权利要求43或44所述的无人飞行器，其特征在于，所述动力装置包括电机和螺旋桨，所述螺旋桨的桨毂和所述电机的转轴连接。
- 根据权利要求62所述的无人飞行器，其特征在于，每个所述动力装置中包括有第一电机、第二电机、第一螺旋桨和第二螺旋桨，所述第一螺旋桨的桨毂和所述第一电机的驱动轴连接，所述第二螺旋桨的桨毂和所述第二电机的驱动轴连接；所述第一电机和所述第二电机上下叠放在同一轴线上，且所述第一电机和所述第二电机的转动方向不同，所述第一螺旋桨和所述第二螺旋桨相互背离设置。
- 根据权利要求63所述的无人飞行器，其特征在于，每个所述动力装置中还包括连接支座，所述连接支座固定在所述承载件上，且所述连接支座的相对两端分别连接所述第一电机和所述第二电机。
- 根据权利要求62所述的无人飞行器，其特征在于，每个所述动力装置中包括第三电机，第三螺旋桨和第四螺旋桨，所述第三螺旋桨的桨毂和所述第四螺旋桨的桨毂均与所述第三电机的驱动轴连接。
- 根据权利要求43或44所述的无人飞行器，其特征在于，所述动力装置还包括用于调节所述电机的转速的电子调速器。
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| CN111473992A (zh) * | 2020-04-17 | 2020-07-31 | 河北工程大学 | 一种地质工程用地质勘测器 |
| CN113734434A (zh) * | 2020-05-30 | 2021-12-03 | 京飞(菏泽)航天科技有限公司 | 一种垂直起降飞行器 |
| WO2023035236A1 (zh) * | 2021-09-10 | 2023-03-16 | 深圳市大疆创新科技有限公司 | 用于无人飞行器的机架、无人飞行器及套件 |
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| CN205770119U (zh) * | 2016-05-20 | 2016-12-07 | 天津大学 | 用于改变机翼翼展的折叠机构 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021053406A1 (en) | 2019-09-18 | 2021-03-25 | Uab "Sg Consulting Baltics & By" | Folding drone |
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| Publication number | Publication date |
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| CN108513555A (zh) | 2018-09-07 |
| CN108513555B (zh) | 2021-11-05 |
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