12-axis contra-rotating 24-rotor unmanned aerial vehicle

Abstract

The utility model discloses a 12-axis contra-rotating 24-rotor unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a vehicle body and a plurality of rotor components, a loading component is arranged at the bottom of the vehicle body, the loading component comprises a plurality of support rods and two frame rods which are symmetrically arranged on two sides along the height direction, the support rods are respectively grouped by taking the side as a reference, and the support rods are arranged on two sides of the vehicle body. The two frame rods are respectively erected with the tail ends of the supporting rods which are grouped on the two sides as welding points, a load area is formed between the frame rods and the supporting rods in a surrounding manner, and the frame rods and the supporting rods in the load area can be used for fixing articles. The frame rods and the supporting rods can be matched and hung with hooks of matched boxes or bags; the stress stability of the loading assembly during loading is improved by means of a triangular stable structure formed between the reinforcing rods and the supporting rods, and the stability during loading is improved through center adjustment.

Description

Technical Field

[0001] The utility model discloses a UAV technology, in particular to a 12-axis counter-rotating 24-rotor UAV. Background Art

[0002] A drone is an aircraft controlled by a radio remote control device and a self-contained program control device. From a technical point of view, it can be divided into several categories: unmanned helicopters, unmanned fixed-wing aircraft, unmanned airships, and unmanned paragliders. It has the advantages of small size, low cost, and ease of use, and is widely used in people's daily production and life.

[0003] Multi-rotor drones have good flexibility and stability, and are capable of vertical lift and precise hovering. However, conventional multi-rotor drones do not have corresponding load-bearing structures, and their load-bearing capacity is relatively low. They can only carry lightweight loads such as camera components. Utility Model Content

[0004] The purpose of the utility model is to provide a 12-axis counter-rotating 24-rotor UAV in order to solve the above-mentioned problems.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a 12-axis counter-rotating 24-rotor UAV, including a body and a plurality of rotor assemblies, a load-bearing assembly is provided at the bottom of the body, and the load-bearing assembly includes a plurality of support rods and two racks symmetrically arranged along the height direction on both sides, the support rods are grouped based on the side they are located on, and the two racks are respectively installed with the ends of the support rods grouped on both sides as welding points, a load area is surrounded by the racks and the support rods, and the racks and support rods in the load area can be used to fix objects.

[0006] By adopting the above technical solution, a load area for placing objects is formed by the rack rods and the support rods, and the objects are fixed by means of the rack rods and the support rods.

[0007] Preferably, the support rods grouped on both sides are arranged obliquely and inclined toward the outside, and reinforcing rods are welded between the support rods on both sides, and a triangular stable structure is formed between the reinforcing rods and the support rods.

[0008] By adopting the above technical solution, the stability of the UAV when loaded is improved through the triangular stabilization structure.

[0009] Preferably, the connection point between the reinforcing rod and the support rod is located below the midpoint of the support rod.

[0010] By adopting the above technical solution, the center of gravity is adjusted to a position below the midpoint of the support rod by setting the connection point, thereby improving the balance performance of the drone.

[0011] Preferably, the rotor assembly includes a connecting rod and a power rotor installed on the connecting rod. The front and rear and left and right directions of the fuselage are respectively divided into front and rear rotor areas and left and right rotor areas. The rotor assemblies in the left and right rotor areas are symmetrically arranged according to the installation positions of the support rods, and the rotor assemblies in the front and rear rotor areas are arranged at equal angles in a 180° fan shape.

[0012] By adopting the above technical solution, the power and mass distribution of each component in each direction of the front and rear rotor areas and the left and right rotor areas are made consistent, thereby improving the mechanical balance performance of the UAV.

[0013] Preferably, the adjacent support rods and connecting rods extend toward one end of the machine body and intersect at one point.

[0014] By adopting the above technical solution, the torque of the UAV is concentrated on the fuselage, improving the flexibility and dynamic stability of the UAV flight.

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] A load area that can be used to load items is formed by the frame rods and support rods in the load-bearing assembly, and the frame rods and support rods can be hung in conjunction with hooks of matching boxes or bags; a triangular stabilizing structure is formed between the reinforcing rods and the support rods to improve the force stability of the load-bearing assembly when loaded, and the stability when loaded is improved through center adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the structure of a 12-axis counter-rotating 24-rotor UAV Figure 1 ;

[0018] Figure 2 A schematic diagram of the structure of a 12-axis counter-rotating 24-rotor UAV Figure 2 ;

[0019] Figure 3 It is a partial enlarged view of the front and rear rotor areas;

[0020] Figure 4 It is a front view of a 12-axis counter-rotating 24-rotor UAV;

[0021] Figure 5 A top view of a 12-axis counter-rotating 24-rotor UAV;

[0022] Figure numerals: 1, fuselage; 2, rotor assembly; 3, load-bearing assembly; 4, frame rod; 5, reinforcement rod; 6, support rod; 7, connecting rod. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model. In the description of the utility model, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, which are only for the convenience of describing the utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.

[0024] A 12-axis counter-rotating 24-rotor UAV, such as Figure 1-Figure 2 As shown, it includes a body 1 and a plurality of rotor assemblies 2. A load-bearing assembly 3 is provided at the bottom of the body 1. The load-bearing assembly 3 includes a plurality of support rods 6 and two rack rods 4 symmetrically arranged along the height direction on both sides. The support rods 6 are grouped based on the side they are located on, and the two rack rods 4 are respectively mounted with welding points on the ends of the support rods 6 grouped on both sides. A load area is formed between the rack rods 4 and the support rods 6. The rack rods 4 and the support rods 6 in the load area can be used to fix objects.

[0025] Articles can be contained in matching boxes or bags, which are provided with a plurality of hooks that can be hoisted and matched with the support rods 6, the frame rods 4 and the reinforcing rods 5, so as to realize the load.

[0026] like Figure 4 As shown, the support rods 6 grouped on both sides are inclined and inclined toward the outside, and reinforcing rods 5 are welded between the support rods 6 on both sides. A triangular stable structure is formed between the reinforcing rods 5 and the support rods 6. When the support rods 6, the frame rods 4 and the reinforcing rods 5 are loaded with boxes or bags for containing articles, the downward force received by the lower end frame rod 4 when loaded will pull the support rods 6 on both sides inward, and the presence of the reinforcing rods 5 will resist the thrust, thereby maintaining the force stability of the entire structure; the connection point between the reinforcing rods 5 and the support rods 6 is located below the midpoint of the support rods 6, and the center of gravity is adjusted to a lower position, which can improve the stability when loaded.

[0027] like Figure 3 and Figure 5As shown, the rotor assembly 2 includes a connecting rod 7 and a power rotor installed on the connecting rod 7. The front and rear directions and the left and right directions of the fuselage 1 are respectively divided into the front and rear rotor areas and the left and right rotor areas. The rotor assemblies 2 in the left and right rotor areas are symmetrically arranged according to the installation positions of the support rods 6. The number and positions of the connecting rods 7 are consistent with the installation positions of the support rods 6, which can maintain the balance of forces at various positions and thus improve the flight balance performance. The rotor assemblies 2 in the front and rear rotor areas are arranged at equal angles in a 180° fan shape. The equal angle arrangement can maintain the balanced flight power of the power rotors in the front and rear rotor areas during the vertical takeoff and landing flight of the UAV, thereby further improving the stability; the adjacent support rods 6 and connecting rods 7 extend close to one end of the fuselage 1 and intersect at one point, gathering the confluence points of the extension lines of the support rods 6 and connecting rods 7 in the front and rear rotor areas and the left and right rotor areas on the fuselage 1, further improving the flexibility and dynamic stability of the UAV flight.

[0028] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-restrictive from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

[0029] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A 12-axis counter-rotating 24-rotor UAV, comprising a body (1) and a plurality of rotor assemblies (2), characterized in that: A load-bearing assembly (3) is provided at the bottom of the machine body (1), and the load-bearing assembly (3) comprises a plurality of support rods (6) and two frame rods (4) symmetrically arranged along the height direction on both sides, the support rods (6) are respectively grouped based on the side where they are located, and the two frame rods (4) are respectively mounted at welding points with the ends of the support rods (6) in the group on both sides, and a load area is formed between the frame rods (4) and the support rods (6), and the frame rods (4) and the support rods (6) in the load area can be used to fix objects.

2. The 12-axis counter-rotating 24-rotor UAV according to claim 1, characterized in that: The support rods (6) grouped on both sides are arranged in an inclined manner and inclined toward the outside. A reinforcing rod (5) is welded between the support rods (6) on both sides, and a triangular stable structure is formed between the reinforcing rod (5) and the support rods (6).

3. The 12-axis counter-rotating 24-rotor UAV according to claim 2, characterized in that: The connection point between the reinforcing rod (5) and the supporting rod (6) is located below the midpoint of the supporting rod (6).

4. The 12-axis counter-rotating 24-rotor UAV according to claim 3, characterized in that: The rotor assembly (2) comprises a connecting rod (7) and a power rotor installed on the connecting rod (7); the front and rear directions and the left and right directions of the body (1) are respectively divided into a front and rear rotor area and a left and right rotor area; the rotor assemblies (2) in the left and right rotor areas are symmetrically arranged according to the installation positions of the support rods (6); and the rotor assemblies (2) in the front and rear rotor areas are arranged in a 180° sector shape at equal angles.

5. The 12-axis counter-rotating 24-rotor UAV according to claim 4, characterized in that: The adjacent support rods (6) and connecting rods (7) extend from one end close to the machine body (1) and intersect at one point.

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