Multi-propeller aircraft
The multi-propeller vehicle with a seven-propeller design and hollow structure solves the problem of insufficient adaptability and maneuverability of traditional ROVs in complex underwater environments, and achieves high energy efficiency and omnidirectional movement capabilities.
Patent Information
- Application Number
- CN202423276448.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-30
- Publication Date
- 2025-10-28
- Estimated Expiration
- 2034-12-30
AI Technical Summary
Traditional ROV designs have limited adaptability and maneuverability in complex underwater environments. Although the six-propeller layout has high energy efficiency, it lacks flexibility, while the eight-propeller layout has redundant energy dispersion.
It adopts a seven-propeller design, with the propellers distributed in vertical triangles and 45° to control the movement of the aircraft. The speed is precisely adjusted through independent motors and control units. The hollow structure and flat design are combined to reduce water resistance and achieve omnidirectional movement.
The energy efficiency of the spacecraft has been improved, and efficient propulsion and flexible control have been achieved, including multi-directional movements such as forward, backward, ascent, descent, and left and right movement.
Smart Images
Figure CN223479299U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft technology, specifically to a multi-propeller aircraft. Background Technology
[0002] With the continuous development of marine resources and the increasing complexity of the marine environment, fields such as marine exploration, environmental monitoring, and underwater scientific research are becoming increasingly reliant on remotely operated vehicles (ROVs). As a device capable of long-duration, highly flexible underwater operations, ROVs have become an indispensable tool in these fields.
[0003] Traditional ROV designs typically use a combination of propellers and servos to achieve underwater movement. However, this design has limited adaptability and maneuverability in complex underwater environments. For example, under the same power input, a six-propeller layout exhibits a higher energy efficiency ratio than an eight-propeller layout. This is because the number of propellers is moderate, avoiding excessive energy dispersion and redundancy. However, its flexibility is reduced compared to an eight-propeller layout.
[0004] Therefore, in the above-mentioned technology, the layout and number of propellers are further improved and a multi-propeller aircraft is proposed. Utility Model Content
[0005] The purpose of this invention is to provide a multi-propeller aircraft. By reducing water resistance and simplifying the mechanical structure, the energy consumption of the aircraft is reduced, thus improving the energy efficiency ratio. At the same time, through the innovative seven-propeller design, the aircraft can achieve omnidirectional movement, including forward, backward, ascent, descent, and left and right movement, thereby achieving efficient propulsion and flexible control.
[0006] To achieve the above objectives, this utility model provides the following technical solution: a multi-propeller aircraft, comprising: a carrier body, wherein the carrier body is hollowed out; and a first propeller, a second propeller, and a third propeller disposed on the carrier body, wherein the first propeller, the second propeller, and the third propeller are assembled perpendicular to the carrier body and in a triangular distribution for controlling the up-down and tumbling movements of the carrier body; further comprising a fourth propeller, a fifth propeller, a sixth propeller, and a seventh propeller disposed on the carrier body, wherein the fourth propeller, the fifth propeller, the sixth propeller, and the seventh propeller are spatially distributed at 45° at the four corners of the carrier body for controlling the forward-backward and left-right movements of the carrier body.
[0007] Preferably, the first, second, third, fourth, fifth, sixth, and seventh propellers have the same structure and are each equipped with an independent motor and control unit, wherein the control unit controls the rotational speed and direction of the corresponding propeller.
[0008] Preferably, the aircraft body includes a first frame and a second frame disposed at the lower part of the first frame, and also includes several connecting fittings for detachably installing the second frame and the first frame.
[0009] Preferably, the first mounting cavity, the second mounting cavity, and the third mounting cavity are perpendicular to the first frame. The first mounting cavity, the second mounting cavity, and the third mounting cavity are triangularly distributed and are used for mounting the third propeller, the first propeller, and the second propeller respectively through mounting components.
[0010] Preferably, the support side rods fixed at the four corners of the second frame are used to install the fourth propeller, fifth propeller, sixth propeller and seventh propeller at the corresponding positions.
[0011] Preferably, the head and tail sections of the aircraft body are respectively provided with a head cabin and a tail fin, and the aircraft body adopts a regular symmetrical flat design.
[0012] Preferably, there are first and second hollowed-out grooves that are symmetrically distributed around the head of the aircraft carrier.
[0013] Preferably, depth sensors, attitude sensors, sonar systems, and high-definition cameras are evenly distributed on the second frame and the first frame where the navigation body is located.
[0014] Preferably, it also includes a fourth mounting cavity located at the stern of the aircraft body, wherein an electronic placement compartment is installed in the fourth mounting cavity. The electronic placement compartment has a streamlined design at the stern and integrates a control system, a communication module, a navigation system, and a sensor kit.
[0015] Compared with the prior art, the beneficial effects of this utility model are as follows:
[0016] This invention utilizes a hollowed-out body design and a regularly symmetrical, flattened structure. By reducing water resistance and simplifying the mechanical structure, the energy consumption of the aircraft is reduced, thus improving its energy efficiency ratio. Furthermore, through an innovative seven-propeller design, the aircraft can achieve omnidirectional movement, including forward, backward, ascent, descent, and lateral movement, by independently controlling the speed and direction of each propeller. This results in efficient propulsion and flexible control. Attached Figure Description
[0017] Figure 1 This is a first-view perspective three-dimensional structural diagram of the present invention;
[0018] Figure 2 for Figure 1 A second-view 3D structural diagram;
[0019] Figure 3 for Figure 1 A schematic diagram of the third-person perspective stereoscopic structure;
[0020] Figure 4 This is a bottom view of the structure of this utility model;
[0021] Figure 5 This is a front view structural diagram of the present utility model;
[0022] Figure 6 This is a schematic diagram of the forward-moving structure of this utility model;
[0023] Figure 7 This is a schematic diagram of the left-shifting state structure of this utility model.
[0024] In the diagram: 111, Second frame; 112, First frame; 113, Head compartment; 114, First slot; 115, Second slot; 116, First mounting cavity; 117, Second mounting cavity; 118, Third mounting cavity; 119, Tail fin; 120, Fourth mounting cavity; 130, Support side rod; 150, Connecting assembly;
[0025] 211. First propeller; 212. Second propeller; 213. Third propeller;
[0026] 311. Fourth propeller; 312. Fifth propeller; 313. Sixth propeller; 314. Seventh propeller;
[0027] 411. Installation components;
[0028] 611. Electronic placement compartment. Detailed Implementation
[0029] In the description of this utility model, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. The various embodiments of this utility model are described in detail below with reference to the accompanying drawings. Example 1
[0030] Please see Figures 1 to 7The present invention preferably provides the following technical solution: a multi-propeller aircraft, comprising: a carrier body, the carrier body being hollowed out; and a first propeller 211, a second propeller 212, and a third propeller 213 mounted on the carrier body, the first propeller 211, the second propeller 212, and the third propeller 213 being assembled perpendicular to the carrier body and in a triangular distribution for controlling the up-down and flipping movements of the carrier body; further comprising a fourth propeller 311, a fifth propeller 312, a sixth propeller 313, and a seventh propeller 314 mounted on the carrier body, the fourth propeller 311, the fifth propeller 312, the sixth propeller 313, and the seventh propeller 314 being spatially distributed at 45° at the four corners of the carrier body for controlling the forward-backward and left-right movements of the carrier body;
[0031] Furthermore, the first propeller 211, the second propeller 212, the third propeller 213, the fourth propeller 311, the fifth propeller 312, the sixth propeller 313, and the seventh propeller 314 have the same structure and principle, and are each equipped with an independent motor and control unit. The control unit controls the speed and direction of the corresponding propeller.
[0032] In this application, the hollowed-out design of the aircraft body and the regular symmetrical flattened structure reduce water resistance and simplify the mechanical structure, thereby reducing the energy consumption of the aircraft and improving its energy efficiency ratio. At the same time, the innovative seven-propeller design, with the first propeller 211, the second propeller 212, the third propeller 213, the fourth propeller 311, the fifth propeller 312, the sixth propeller 313 and the seventh propeller 314 being existing mature technologies, is driven by independent brushless motors. These motors are controlled by precise electronic speed controllers (ESC). By independently controlling the speed and propulsion direction of each propeller, the aircraft can achieve omnidirectional movement, including forward, backward, ascent, descent and left and right movement, thereby achieving efficient propulsion and flexible control.
[0033] Specifically, if Figure 6 As shown, in the forward-moving state, the fourth propeller 311, the fifth propeller 312, the sixth propeller 313, and the seventh propeller 314 are operating and propulsing according to the arrows shown in the figure; as... Figure 7 The diagram shows the leftward movement in the forward direction. Similarly, the backward and rightward movements can also be performed.
[0034] When the operation of the first propeller 211, the second propeller 212, and the third propeller 213 is controlled and the propulsion direction is controlled, the machine can ascend and descend. When the propulsion directions of the second propeller 212 and the third propeller 213 are opposite, a torque will be generated, causing the machine to flip left and right.
[0035] Furthermore, the aircraft body includes a first frame 112 and a second frame 111 disposed below the first frame 112, and also includes several connecting fittings 150 for detachably mounting the second frame 111 and the first frame 112.
[0036] Furthermore, a first mounting cavity 116, a second mounting cavity 117, and a third mounting cavity 118 are perpendicular to the first frame 112. These three mounting cavities are triangularly distributed and are respectively used for mounting the third propeller 213, the first propeller 211, and the second propeller 212 via mounting members 411. Figure 1 As shown, the first mounting cavity 116, the second mounting cavity 117 and the third mounting cavity 118 are circular holes for embedding the third propeller 213, the first propeller 211 and the second propeller 212, which can be placed perpendicular to the ship body.
[0037] Furthermore, the support side rods 130 fixed at the four corners of the second frame 111 are used to install the fourth propeller 311, the fifth propeller 312, the sixth propeller 313 and the seventh propeller 314 at the corresponding positions. Example 2
[0038] As another embodiment of this utility model, the head and tail sections of the hull are respectively provided with a head compartment 113 and a tail fin 119, and the hull adopts a regular symmetrical flat design, which reduces the cross-sectional area and reduces the shear force formed by water flow on the surface of the vehicle, thereby reducing hydrodynamic drag.
[0039] Furthermore, the first hollowed-out groove 114 and the second hollowed-out groove 115, which are symmetrically distributed around the head of the aircraft body, are used to reduce weight and reduce drag caused by turbulence. Example 3
[0040] In other embodiments of this utility model, depth sensors, attitude sensors, sonar systems and high-definition cameras are evenly distributed on the second frame 111 and the first frame 112 where the vehicle body is located. Through the set sensing units and camera modules, real-time underwater environmental data can be provided to help the operator better understand the situation around the vehicle.
[0041] Furthermore, it also includes a fourth mounting cavity 120 located at the tail of the aircraft body. The fourth mounting cavity 120 is equipped with an electronic placement compartment 611. The electronic placement compartment 611 has a streamlined design at the tail and integrates a control system, a communication module, a navigation system, and a sensor suite for comprehensive remote control and data transmission of the aircraft.
[0042] The internal structure of the electronic storage compartment 611 is divided into upper and lower layers. The lower layer is specifically used to house heavier electrical components to ensure stability and maneuverability during underwater operations. The remaining related electrical components are rationally placed in the upper space, maximizing space utilization. In the communication system, this invention adopts a high-bandwidth, low-latency communication system to ensure stable and reliable data transmission between the vehicle and the operator. The communication system supports multiple communication protocols, including wireless and wired communication, to adapt to different operating environments.
[0043] In this utility model, unless otherwise explicitly specified and limited, the terms "installation", "connection", "fixation" and other terms should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral part. There are various ways to install detachably, such as by using a plug-in and snap-fit method, or by using a bolt connection, etc.
[0044] The above description of the specific embodiments of this utility model is only used to further illustrate this utility model and should not be construed as limiting the scope of protection of this utility model. Any non-essential improvements and adjustments made to this utility model by technical engineers based on the above description of the utility model shall fall within the scope of protection of this utility model.
Claims
1. A multi-propeller aircraft, characterized in that, include: The hull of the vessel is designed with a hollow structure. The first propeller (211), the second propeller (212), and the third propeller (213) are mounted on the hull of the aircraft. The first propeller (211), the second propeller (212), and the third propeller (213) are assembled perpendicular to the hull of the aircraft and in a triangular arrangement to control the up-down and flipping movements of the hull of the aircraft. It also includes a fourth propeller (311), a fifth propeller (312), a sixth propeller (313), and a seventh propeller (314) installed on the vehicle body. The fourth propeller (311), the fifth propeller (312), the sixth propeller (313), and the seventh propeller (314) are spatially distributed at 45° at the four corners of the vehicle body to control the forward, backward, left, and right movements of the vehicle body.
2. The multi-propeller aircraft according to claim 1, characterized in that: The first propeller (211), the second propeller (212), the third propeller (213), the fourth propeller (311), the fifth propeller (312), the sixth propeller (313), and the seventh propeller (314) have the same structure and are each equipped with an independent motor and control unit. The control unit controls the rotation speed and direction of the corresponding propeller.
3. A multi-propeller aircraft according to claim 1, characterized in that: The aircraft body includes a first frame (112) and a second frame (111) disposed under the first frame (112), and also includes several connecting fittings (150) for detachably mounting the second frame (111) and the first frame (112).
4. A multi-propeller aircraft according to claim 3, characterized in that: A first mounting cavity (116), a second mounting cavity (117), and a third mounting cavity (118) are opened perpendicular to the first frame (112). The first mounting cavity (116), the second mounting cavity (117), and the third mounting cavity (118) are triangularly distributed and are respectively used for the installation of the third propeller (213), the first propeller (211), and the second propeller (212) through mounting parts (411).
5. A multi-propeller aircraft according to claim 3, characterized in that: The support side rods (130) fixed at the four corners of the second frame (111) are used to install the fourth propeller (311), the fifth propeller (312), the sixth propeller (313) and the seventh propeller (314) at the corresponding positions.
6. A multi-propeller aircraft according to claim 1, characterized in that: The aircraft body is provided with a head compartment (113) and a tail fin (119) at the head and tail, respectively, and the aircraft body adopts a regular symmetrical flat design.
7. A multi-propeller aircraft according to claim 1, characterized in that: And the first hollowed-out groove (114) and the second hollowed-out groove (115) are symmetrically distributed around the head of the ship's body.
8. A multi-propeller aircraft according to claim 3, characterized in that: Depth sensors, attitude sensors, sonar systems, and high-definition cameras are also evenly distributed on the second frame (111) and the first frame (112) where the aircraft body is located.
9. A multi-propeller aircraft according to claim 1, characterized in that: It also includes a fourth mounting cavity (120) located at the tail of the aircraft body, wherein an electronic placement compartment (611) is installed in the fourth mounting cavity (120), and the tail of the electronic placement compartment (611) is streamlined.