Unmanned aerial vehicle and multi-rotor drone

Abstract

The present invention discloses an unmanned aerial vehicle body and a multi-rotor unmanned aerial vehicle. The unmanned aerial vehicle body includes n1 arc-shaped rods, n2 support rods, and n1 connecting members. The connecting member includes a first connecting end, at least two first connecting ends, and the first connecting end connects the n1 arc-shaped rods into a ring-shaped member. The support rods form an axisymmetric support member; the axis of symmetry of the support member passes through the center of the ring-shaped member, the support member is fixed in the ring-shaped member, and the ring-shaped member is a circular body with an inscribed support member. The multi-rotor unmanned aerial vehicle includes a fuselage, a wing, and a power assembly; the fuselage includes the annular fuselage described in any one of the above items. The wing includes m connecting members and m arms, and the arms are connected to the ring-shaped member in m equal parts through the connecting members, m≥3. The power assembly is installed on one or more support rods. The fuselage composed of the annular outer frame and the axisymmetric inner support members of the present invention can realize a platform-based multi-rotor agricultural drone structure with different rotors and different battery configurations; the structure is stable and the force transmission path is reasonable.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle body and a multi-rotor unmanned aerial vehicle. Background Art

[0002] Currently, most drone bodies are fully enclosed or semi-enclosed, which increases the difficulty during installation and disassembly; and the manufacturing cost is relatively high.

[0003] In addition, due to different operation objectives in the prior art, most agricultural drones have an axisymmetric four, six, or eight layout, and different numbers of rotors correspond to different fuselages. The operation objective is related to the number of battery configurations, and different battery configurations also require different fuselages. When it is necessary to change the rotor configuration, adjust the flight time, and then adjust the number of battery configurations according to the operation objective, it is difficult for the existing drone fuselage to be used as a platform. Summary of the invention

[0004] The object of the present invention is to provide an unmanned aerial vehicle that can solve one or more of the above-mentioned technical problems.

[0005] In order to achieve the above object, the technical solution proposed by the present invention is as follows:

[0006] The drone body comprises n1 arc-shaped rods, n2 support rods, and n1 connecting members. The connecting members comprise first connecting ends, and there are at least two first connecting ends, and the first connecting ends connect the n1 arc-shaped rods into a ring-shaped member. n1≥2; n2≥1.

[0007] The support rods form an axisymmetric support member; the symmetry axis of the support member passes through the center of the annular member, so that the support member is fixed in the annular member, and the annular member is a circular body with an inscribed support member.

[0008] Preferably, the connecting member further comprises a second connecting end, the second connecting end is at least one, and the second connecting end allows the support rod to be connected to the annular member. Preferably, the second connecting end is a triangle.

[0009] Preferably: the connecting member includes a base, a hoop and an upper cover; a connecting end is provided on the base, and at least one hoop is provided on each connecting end, and the hoop locks the arc rod or the support rod; the base and the upper cover are buckled to form a accommodating space and fix the hoop inside.

[0010] Preferably: the hoop member includes a hoop seat, a hoop strip, a protrusion and a through hole, the protrusion is located on the hoop seat and / or the hoop strip, and the through hole is arranged at the ends of the arc rod and the support rod; the protrusion cooperates with the through hole, and the hoop strip is fixed to the hoop seat by bolts to fix the arc rod or the support rod.

[0011] Preferably, the hoop seat is fixedly connected to the base via bolts.

[0012] Preferably, when n1=n2≥3, the connecting member has two first connecting ends and two second connecting ends; and the supporting member is a regular polygonal member inscribed in the annular member.

[0013] Preferably, the arc-shaped rod and / or the supporting rod is a hollow tube.

[0014] Another object of the present invention is to provide a multi-rotor drone that can solve one or more of the above-mentioned technical problems.

[0015] A multi-rotor drone comprises a fuselage, wings, and a power assembly; the fuselage comprises any one of the above-mentioned annular fuselages. The wings comprise m arm connectors and m arms, and the arms are connected to the annular member in m equal parts through the arm connectors, where m≥3. The power assembly is mounted on one or more support rods.

[0016] Preferably: the arm connector includes a main body, an arm clamping piece, and a fuselage clamping piece; the arm clamping piece is connected to the main body via bolts to clamp the arm, and a boss and a limiting hole are arranged between the arm and the clamping piece; the fuselage clamping piece is connected to the main body via bolts to clamp the arc rod.

[0017] Preferably, it also includes a box, at least one of which is installed on one or more support rods.

[0018] Further: the power assembly includes a battery assembly and a flight control component.

[0019] The technical effects of the present invention are:

[0020] The fuselage composed of the annular outer frame and the axisymmetric inner support members of the present invention can realize a platform-based multi-rotor plant protection UAV structure with different rotors and different battery configurations; the structure is stable and the force transmission path is reasonable.

[0021] The installation position and quantity of the rotor can be adjusted along the annular circumference, and the position and quantity of the battery can be adjusted on the axisymmetric inner support. The installation position of other components can also be adjusted.

[0022] Here, the annular member adopts a plurality of arc-shaped rods, which can be completely replaced with each other, and have good versatility; the fuselage is connected to the support member, and the plurality of support rods can also be replaced with each other, and have good versatility;

[0023] The four-way transition connector is used for connection, which is simple in process and highly feasible; most of the different numbers of rotor arrangements can be realized;

[0024] The support rod can be used to install other accessories required for the drone (such as medicine boxes, batteries, flight control components, etc.);

[0025] The arc rod and support rod adopt hollow tubes, which can allow the layout lines to run inside the tubes, making the overall structure layout more concise, highly versatile, simple to assemble, and highly operable; at the same time, it reduces the weight of the fuselage;

[0026] Since the support is an axisymmetric multi-rod frame, it is more operable when configuring the components, has better counterweight stability, strong geometry, and the main weight of the medicine box and battery can be arranged reasonably. The center of gravity of the fuselage is stable and the force is evenly distributed. The arm arrangement is less restricted and the arrangement position is highly flexible. There are few restrictions on the design of the medicine box, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The drawings in the specification, which constitute a part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0028] In the attached picture:

[0029] Figure 1 The fuselage structure of the present invention is schematically shown in FIG. Figure 1 (connectors omitted);

[0030] Figure 2 The fuselage structure of the present invention is schematically shown in FIG. Figure 2 (connectors omitted);

[0031] Figure 3 The fuselage structure of the present invention is schematically shown in FIG. Figure 3 (connectors omitted);

[0032] Figure 4 The fuselage structure of the present invention is schematically shown in FIG. Figure 4 (connectors omitted);

[0033] Figure 5 The fuselage structure of the present invention is schematically shown in FIG. Figure 5 (connectors omitted);

[0034] Figure 6 It is a schematic diagram of the assembly of three arc rods and three support rods;

[0035] Figure 7 yes Figure 6 Schematic diagram of connection through connectors;

[0036] Figure 8 yes Figure 7 Schematic diagram of the local explosion structure in;

[0037] Fig. 9 It is a schematic diagram of the structure of the connecting parts;

[0038] Fig.10 It is an exploded schematic diagram of the connection between the connector and the end of the rod (arc rod or support rod);

[0039] Fig.11 yes Fig.10 Installation process diagram Figure 1 ;

[0040] Fig.12 yes Fig.10 Installation process diagram Figure 2 ;

[0041] Fig.13 It is a schematic diagram of the structure of a multi-rotor UAV;

[0042] Fig.14 It is a schematic diagram of the structure of a multi-rotor drone carrying a box;

[0043] Fig.15 It is a schematic diagram of the use of the arm connector;

[0044] Fig.16 It is a schematic diagram of the exploded structure of the machine arm joint;

[0045] Fig.17 It is a structural schematic diagram of the connection between the machine arm connector and the machine arm;

[0046] Fig.18 It is a structural schematic diagram of the main body in the arm connector;

[0047] Fig.19 It is a structural schematic diagram of a machine arm clamping part in a machine arm joint;

[0048] Fig. 20 It is a schematic diagram of the structure of the machine arm;

[0049] Fig.21 It is a schematic diagram of the structure of the fuselage pressing part in the arm joint;

[0050] Fig. 22 yes Fig.21 A partial enlarged schematic diagram of

[0051] Fig.23 This is a schematic diagram of a cabinet installation method;

[0052] Fig.24 This is a schematic diagram of a cabinet installation method.

[0053] The above drawings include the following reference numerals:

[0054] Ring member 1, arc rod 101, support member 2, support rod 201;

[0055] Connecting member 3, base 301, upper cover 302, hoop member 303;

[0056] Hoop seat 3031, rod passage 3032, hoop groove 3033, hoop strip 3034, protrusion 3035, through hole 3036;

[0057] Arm 4, limiting hole 401;

[0058] Flight control components 5, battery frame 6, box 7;

[0059] The machine arm connecting part 8, the main body 801, the first fitting surface 8011, the machine body pressing part 802, the second fitting surface 8021, the machine arm pressing part 803, and the boss 8031. DETAILED DESCRIPTION

[0060] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments, wherein the illustrative embodiments and descriptions are only used to explain the present invention but are not intended to be improper limitations of the present invention.

[0061] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0062] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0063] The drone body comprises n1 arc-shaped rods 101, n2 support rods 201, and n1 connecting members 3. The connecting member 3 comprises at least two first connecting ends, and the first connecting ends connect the n1 arc-shaped rods into a ring member 1.

[0064] The support rods 201 form an axisymmetric support member 2; the axis of symmetry of the support member 2 passes through the center of the annular member, so that the support member is fixed in the annular member, and the annular member is a circular body with an inscribed support member.

[0065] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 Shown are five types of drone rings and internal support parts; O is the center of the ring, and L is the central symmetry axis of the support.

[0066] in Figure 1There is no connection between the support rods 201 constituting the support member 2, and each support rod becomes a chord of the ring member 1.

[0067] exist Figure 2 In FIG. 5 , the support rods 201 intersect in various forms to form an axisymmetric rod frame to be connected to the inside of the annular member to form the support member 2.

[0068] Here, the multiple arc-shaped rods 101 can also be connected by welding to form a ring member 1. Whether the support rod 201 and the ring member are connected by welding or by some kind of connecting member is not limited here.

[0069] In the present invention, the drone body is composed of a ring-shaped member 1 and a support member 2 located in the middle of the ring-shaped member, and the support member 2 is constructed by an axisymmetric rod frame.

[0070] The connection can be made through some kind of connection piece 3, either by welding or by bolts; there is no limitation.

[0071] The cross section of the rod constituting the annular member 1 or the supporting member 2 is circular or regular polygonal. The preferred cross-sectional shape is circular, because under the premise of the same thickness and circumference, the circular cross-section has the best anti-bending performance.

[0072] In some embodiments, the connecting member 3 preferably further includes a second connecting end, the second connecting end having at least one (eg, a T-shaped tee, a cross-shaped cross, etc.), and the second connecting end allows the support rod to be connected to the annular member.

[0073] In this way, the connection points of the support rod 201 and the arc rod 101 are together, and one connecting piece 3 can complete the connection during connection, thereby reducing assembly parts, improving assembly efficiency, and effectively reducing the possibility of actual assembly errors.

[0074] In some embodiments, the preferred connecting member 3 includes a base 301, a hoop 303, and an upper cover 302; a connecting end is provided on the base, and at least one hoop 303 is provided on each connecting end, and the hoop 303 locks and clamps the arc rod or the support rod; the base and the upper cover are buckled together to form a receiving space and fix the hoop inside.

[0075] Here, the base and the upper cover can be connected by bolts or by snap-fit ​​connection.

[0076] A limiting structure corresponding to the hoop is provided between the base and the upper cover to ensure that it does not separate along the extension direction of the rod, or the hoop is fixed between the base and the upper cover by bolts, without limitation. Preferably, the hoop is fixedly connected to the base by bolts.

[0077] In some embodiments, in order to ensure the stability of the connection, it is preferred that more than one hoop is provided on one end of the arc rod or the support rod. Figure 8 As shown, there are two hoops.

[0078] The hoop 303 serves as a transition part to connect the arc rod 101 or the support rod 201 to the base 301 to further form a whole.

[0079] The specific structure of the hoop 303 is not limited. The outer frame of the hoop is square for easy connection. The inner circle of the hoop is circumscribed to the rod (arc-shaped rod or support rod) and is set according to the cross-sectional shape of the rod (arc-shaped rod or support rod).

[0080] The hoop member preferably comprises a hoop seat and a corresponding hoop bar, and both ends of the hoop bar are connected to the hoop seat by bolts; or one end of the hoop bar is elastically connected to the hoop seat, and the other end is fixed to the hoop seat by bolts. After the hoop bar and the hoop seat are buckled together, an inner ring with the same cross section as the rod (arc-shaped rod or support rod) is formed to fix the rod (arc-shaped rod or support rod).

[0081] Here, the hoop 303 is as Fig.10 , Fig.11 , Fig.12 As shown, in order to facilitate connection, in certain embodiments, it is more preferred that the hoop member includes a hoop seat 3031, a hoop strip 3034, a protrusion 3035 and a through hole 3036 (preferably an oblong shape).

[0082] The hoop seat has a rod channel 3032, a hoop groove 3033 is arranged above the channel, a hoop strip 3034 enters the hoop groove, the protrusion 3035 enters the through hole 3036 on the rod, the hoop strip fits with the rod, and the two ends of the hoop strip are fixed to the hoop seat by bolts so that the rod is pressed onto the hoop seat by the hoop strip.

[0083] The cooperation between the through hole and the protrusion has two advantages: 1. It ensures that the rod does not rotate, and 2. It ensures that the rod does not move along the extension direction of the rod.

[0084] In certain embodiments, Figure 6 — Fig.12 As shown, preferably: when n1=n2≥3, the connecting member has two first connecting ends and two second connecting ends (i.e., the connecting member is a four-way connection, and the number of the four-way connection is n1); the supporting member is a regular polygonal member (a regular n2-sided member) inscribed in the annular member. Preferably, it is a triangle. The triangular supporting member is more stable.

[0085] The four-way connector can achieve more deformable connections by adjusting the angle between the second connecting ends.

[0086] Preferably, the arc rod and / or the support rod is a hollow rod, which is convenient for overall wiring and makes the structure more concise.

[0087] like Fig.13 The present invention also provides a multi-rotor UAV, including a fuselage, wings 4, and a power assembly.

[0088] The fuselage comprises n1 arc-shaped rods 101, n2 support rods 201, and n1 connecting members 3. The connecting member comprises a first connecting end, and there are at least two first connecting ends, and the first connecting ends connect the n1 arc-shaped rods into a ring member 1.

[0089] The support rods 201 form an axisymmetric support member 2; the axis of symmetry of the support member 2 passes through the center of the annular member, so that the support member is fixed in the annular member, and the annular member is a circular body with an inscribed support member.

[0090] The wing comprises m connecting members 8 and m arms 4, and the arms are connected to the ring member in m equal parts through the connecting members, where m≥3. The power assembly is mounted on one or more supporting rods.

[0091] During use of the multi-rotor drone, the wings can be installed at any position on the ring member, the weight of the wings can be increased or decreased as needed, and the number of battery assemblies can be adjusted as needed.

[0092] In some embodiments, the power assembly includes a battery assembly and a flight control element 5. Fig.13 As shown, the flight control element 5 is connected between two support rods 201 .

[0093] The battery assembly is connected to the support rod through the battery frame. The battery frame is designed as a single entity, which can effectively reduce the dimension chain and improve the matching accuracy of the battery assembly. The battery frame assembly 6 (the battery frame assembly can also be installed through the hoop 301) is fixed to the support rod by the "hoop" method to achieve accurate assembly with the fuselage frame. This structure improves the matching accuracy of the battery from the perspective of the dimension chain and is a simple and reliable structural form.

[0094] In addition, the assembly position of the battery frame assembly can be determined by the earlier assembled fastener assembly, which greatly reduces assembly errors and reduces on-site disassembly instability, making it easier to adjust the battery pack.

[0095] The flight control element is preferably mounted on the symmetry axis L of the support.

[0096] like Fig.15 — Fig. 22As shown, preferably: the arm connector 8 includes a main body 801, an arm clamping member 803, and a fuselage clamping member 802; the arm clamping member 803 is connected to the main body 801 by bolts to clamp the arm 4, and a boss 8031 ​​and a limiting hole 401 are arranged between the arm and the clamping member; the fuselage clamping member 802 is connected to the main body 8 by bolts to clamp the arc rod 101.

[0097] like Fig.15 — Fig. 22 As shown, a boss and a limit hole are provided at the connecting part of the machine arm to prevent the machine arm from rotating;

[0098] As the two fitting surfaces of the fuselage connecting part (the first fitting surface 8011 located on the main body, and the second fitting surface 8021 located on the fuselage clamping piece) are fitted hyperbolic features with the same radius as the outer surface of the fuselage tube beam, the axis of the arc rod on the horizontal plane is non-straight. Therefore, based on the characteristics of the hyperbolic surface, it can only realize vertical rotation around the center O on the horizontal plane. Therefore, no additional limiting structure is required between the fuselage clamping piece and the main body to prevent the arm from rotating relative to the fuselage.

[0099] A groove 8022 is provided on the mating surface between the fuselage pressing piece 802 and the end surface of the main body 8. The groove 8022 is designed to reduce the contact of the mating surface and reduce the matching problem caused by the manufacturing tolerance.

[0100] In certain embodiments, such as Fig.14 The figure also includes a box 7, at least one of which is mounted on one or more support rods. Fig.14 The upper box is a medicine box, which is a regular hexagon and has a matching limit relationship with the three support rods. Since there are few restrictions around the box, a structure with simple shape and simple process can be achieved.

[0101] When the support is an inscribed regular polygon of a ring, the box (medicine box) is designed with a specific limit and the fastener assembly on the arm cooperates to achieve a vertically pluggable structure. The regular polygon design of the fuselage inner frame limits the movement of the medicine box in all horizontal directions. Moreover, since the center of gravity is designed below the fuselage frame, the box can be stable when the drone is flying without other forms of fixation. This plug-in form of the box is simple to operate on site and has a stable state. For other uses such as seed boxes, the shape of the reference box can also perfectly apply to this fuselage structure.

[0102] Here, the cabinet can be one or more cabinets, and multiple cabinets can be assembled into a large cabinet, which can also adopt the above connection method.

[0103] The installation between the box and the support rods is adjusted according to the arrangement of the support rods.

[0104] like Fig.23 , 24 As shown in the figure, the installation methods of different numbers of boxes.

[0105] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. Unmanned aerial vehicle, characterized in that: It comprises n1 arc-shaped rods, n2 support rods, and n1 connecting members, wherein the connecting member comprises a first connecting end, and there are at least two first connecting ends, and the first connecting end connects the n1 arc-shaped rods into a ring-shaped member; the support rods form an axisymmetric support member; the symmetry axis of the support member passes through the center of the ring-shaped member, and the support member is fixed in the ring-shaped member, so that the ring-shaped member is a circular body with an inscribed support member; the connecting member also comprises a second connecting end, and there is at least one second connecting end, and the second connecting end connects the support rod in the ring-shaped member; the connecting member comprises a base, a hoop, and an upper cover; A connecting end is arranged on the base, and at least one hoop is arranged on each connecting end on the base, and the hoop locks the arc rod or the support rod; the base and the upper cover are buckled to form a accommodating space and fix the hoop inside; the hoop includes a hoop seat, a hoop strip, a protrusion and a through hole, the protrusion is located on the hoop seat and / or the hoop strip, and the through hole is arranged on the end of the arc rod and the support rod; the protrusion cooperates with the through hole, and the hoop strip is fixed to the hoop seat by bolts to fix the arc rod or the support rod, and a power assembly is installed on the support rod, and the power assembly includes a battery assembly and a flight control element.

2. The drone fuselage according to claim 1, characterized in that: The hoop seat is fixedly connected to the base through bolts.

3. The drone fuselage according to claim 1, characterized in that: When n1=n2≥3, the connecting member has two first connecting ends and two second connecting ends; and the supporting member is a regular polygonal member inscribed in the annular member.

4. The drone fuselage according to claim 1, characterized in that: The arc rod and / or the support rod are hollow tubes.

5. Multi-rotor drone, characterized by: Including fuselage, wings, and power components; The fuselage comprises the unmanned aerial vehicle fuselage according to any one of claims 1 to 4; The wing comprises m arm connectors and m arms, and the arms are connected to the ring member in m equal parts through the arm connectors, where m≥3; the power assembly is installed on one or more support rods.

6. The multi-rotor UAV according to claim 5, characterized in that: The arm connector includes a main body, an arm clamping piece, and a fuselage clamping piece; the arm clamping piece is connected to the main body by bolts to clamp the arm, and a boss and a limiting hole are arranged between the arm and the clamping piece; the fuselage clamping piece is connected to the main body by bolts to clamp the arc rod.

7. The multi-rotor UAV according to claim 6, characterized in that: It also includes a box, at least one of which is installed on one and / or more support rods.

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