Multi-power vector propulsors and aircraft based on staggered layout

Abstract

This invention provides a multi-power vector thruster and aircraft based on a staggered layout, comprising two or more basic thruster units stacked longitudinally. Adjacent thruster units are connected by connectors, with a first interface and a second interface on opposite sides of the connectors. Each adjacent thruster unit is connected to both the first and second interfaces via a stator. The axes of the thruster units connected to the first interface and those connected to the second interface are parallel and spaced apart. This longitudinal stacking of multiple thruster units reduces the complexity of the control system design. Direct vector thrust control can be achieved through differences in thruster rotation speeds, avoiding the complex design and vulnerability of swashplate mechanisms. This design has fewer moving parts, making production and assembly more convenient. Furthermore, the multi-layered stacking design further utilizes longitudinal space, resulting in a smaller overall size after storage.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically, to a multi-power vector thruster and aircraft based on a staggered layout. Background Technology

[0002] With the widespread application of multirotor aircraft in aerial photography, logistics, and emergency rescue, achieving lightweighting and miniaturization of aircraft while ensuring power performance has become an important research direction in this field. The spatial layout of the propulsion system directly affects the size and weight of the aircraft, and compact arrangement of propulsion units is a key technical means to reduce the airframe volume and structural material usage.

[0003] Existing technologies have already introduced schemes for alternatingly stacked propeller units. For example, patent document CN218086020U discloses a quadcopter with longitudinally overlapping motor propellers, in which two sets of basic propeller units are arranged alternately. By raising one set of propellers, the two sets of basic propeller units are staggered in the vertical direction, achieving a compact arrangement of all propellers. However, this design still has significant shortcomings: 1) The propellers are connected to the fuselage via raised blocks, which can only achieve two-layer stacking, resulting in limited space compression efficiency and failure to fully utilize longitudinal space; 2) Foldable blades are not used, and the blades still require a large storage space.

[0004] Therefore, how to provide a thruster that can make full use of vertical space and achieve multi-layer stacking is a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide a multi-power vector thruster and aircraft based on a staggered layout.

[0006] The multi-power vector thruster based on a staggered layout provided by the present invention includes two or more thruster basic units, and the multiple thruster basic units are arranged in a longitudinal stack. Adjacent thruster basic units are connected by connectors, and the opposite sides of the connectors are respectively provided with a first interface and a second interface. Adjacent thruster basic units are connected to the first interface and the second interface respectively through stators. The first interface and the second interface are configured such that the axes of the thruster basic units connected to the first interface and the thruster basic units connected to the second interface are parallel and spaced apart.

[0007] Preferably, the basic unit of the propeller includes a stator, a rotor, and blades that can be folded and disposed on the outside of the rotor; Deployed state: The blades are deployed and extend radially along the rotor, with the blades of multiple propeller basic units stacked longitudinally. Collapsed state: The blades are folded up and extend vertically, with the blades of multiple basic propeller units staggered together.

[0008] Preferably, both the first interface and the second interface are hollow structures and are interconnected inside the connector to form a wiring channel; The stator of the basic thruster unit is a hollow structure. The power supply line of the basic thruster unit starts from the inner wall of the stator. The power supply line of the upper thruster unit passes through the wiring channel inside the connector and merges with the power supply line of the lower thruster unit. Then, in this manner, it passes through multiple connectors and the basic thruster unit from top to bottom and finally connects to the external body.

[0009] Preferably, the inner walls of both the first interface and the second interface are provided with at least one support lug; The lug extends inward from the inner wall of the first or second interface and has a connecting hole through it along the axial direction, which is used to fix the stator of the basic unit of the thruster to the first or second interface with fasteners.

[0010] Preferably, there are four basic thruster units, which are arranged in a spiral pattern when viewed from above.

[0011] Preferably, in the connector between the four basic thruster units, the included angle between the lines connecting the axes of the first and second interfaces on adjacent connectors is the same.

[0012] Preferably, the first interface and the second interface on the connector are coaxially connected to the corresponding basic thruster unit, and the axes of the first interface and the second interface are parallel to each other.

[0013] The aircraft provided by the present invention includes a fuselage, wherein the multi-force vectoring thruster based on a staggered layout is mounted on the upper surface of the fuselage; Among the plurality of said propulsion basic units, the lowest-level propulsion basic unit is connected to the body via a connector, the stator of the lowest-level propulsion basic unit is connected to one of the first interface and the second interface of the connector, and the body is connected to the other of the first interface and the second interface of the connector.

[0014] Preferably, the basic thruster unit is configured such that the outer envelope size formed in the retracted state is larger than the diameter of the body.

[0015] Preferably, the machine body has a base plate inside, the upper part of the base plate is equipped with a task load and control equipment, and the bottom of the base plate is fixedly equipped with a support frame.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention reduces the complexity of the control system design by using a design in which multiple basic thruster units are alternately stacked in the longitudinal direction. Vector direct thrust control can be achieved by using the difference in the rotation speed of different thrusters, avoiding the complex design and vulnerability of swashplate mechanism control. This design has fewer moving parts, making production and assembly more convenient. Moreover, the multi-layer stacking design can further utilize the longitudinal space, resulting in a smaller volume after storage.

[0017] 2. By adopting a folding blade structure, the blades can automatically unfold to provide propulsion when the rotor is rotating, and can also be naturally folded down and stored by gravity when the rotor stops rotating, or manually folded up. While ensuring storage, the size of the blades is increased to the maximum extent, thus improving the propulsion force. At the same time, folding and unfolding can be achieved without additional control mechanisms.

[0018] 3. By adopting a hollow design for the rotor, stator, and connecting parts, this invention solves the problem that the power supply line of the basic unit of the thruster must be external. Unlike the existing structure, this design can improve the simplicity of the overall appearance of the thruster, while avoiding the extra interference problem of external wiring. The thruster is smaller in size after folding, making it convenient for personal carrying. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of the thruster in this invention; Figure 2 This is a schematic diagram of the exploded structure of the thruster in this invention; Figure 3 This is a schematic diagram of the connector structure in this invention; Figure 4 This is a schematic diagram of the assembly of the connector and the basic unit of the thruster in this invention; Figure 5 This is a schematic diagram of the overall structure of the aircraft in its deployed state according to the present invention; Figure 6 This is a schematic diagram of the overall structure of the aircraft in its folded-up state according to the present invention.

[0020] The diagram shows: Detailed Implementation

[0021] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0022] This invention discloses a multi-power vector thruster and aircraft based on a staggered layout. Its main improvement lies in the design of multiple thruster basic units that are alternately stacked in the longitudinal direction, which reduces the complexity of the control system design. Vector direct thrust control can be achieved by using the difference in the rotational speed of different thrusters, avoiding the complex design and vulnerability of swashplate mechanism control. Moreover, the multi-layer stacking design can further utilize the longitudinal space, resulting in a smaller volume after storage.

[0023] The multi-force vectoring thruster based on a staggered layout provided by the present invention, such as Figure 1 As shown, it includes two or more basic thruster units, which are stacked vertically. Adjacent thruster units are connected by connectors 4, with a first interface 41 and a second interface 42 on opposite sides of each connector 4. Each adjacent thruster unit is connected to the first interface 41 and the second interface 42 via a stator 6, thus achieving a vertically stacked arrangement. Its structure is visible. Figure 3 The first interface 41 and the second interface 42 are configured such that the axes of the thruster basic units connected to the first interface 41 and the thruster basic units connected to the second interface 42 are parallel and spaced apart.

[0024] The connector 4 allows adjacent thruster basic units to be stacked longitudinally, and the number of stacks can be greater than two, making full use of the longitudinal space of the aircraft body. At the same time, the non-overlapping first interface 41 and second interface 42 design on the connector 4 allows the axes of two adjacent thruster basic units to be non-overlapping, enabling the thruster to achieve vector direct thrust control through the difference in the rotational speed of different thruster basic units.

[0025] In a preferred embodiment, the basic thruster unit includes a stator 6, a rotor 5, and blades 7 that can be folded and disposed on the outside of the rotor 5; such as Figure 5 , Figure 6As shown, the basic thruster unit has an deployed state and a retracted state. When the thruster is activated, the rotor 5 drives the blades 7 to rotate. The blades 7 automatically deploy as the rotor 5 rotates, thus providing thrust. At this time, the basic thruster unit is in the deployed state, with the blades 7 extending radially along the rotor 5. The blades 7 of multiple basic thruster units are stacked longitudinally. When the thruster is deactivated, the rotor 5 stops rotating, causing the blades 7 to stop rotating as well. The blades 7 can naturally fall downwards and be stored under gravity, or they can be manually retracted upwards. At this time, the basic thruster unit is in the retracted state, with the blades 7 extending vertically. The blades 7 of multiple basic thruster units are staggered circumferentially. Through the foldable connection between the blades 7 and the rotor 5, the size of the blades 7 can be maximized while ensuring storage, thus improving thrust. Furthermore, folding and unfolding can be achieved without additional control mechanisms, making it convenient to carry in small containers such as backpacks or suitcases.

[0026] In a preferred embodiment, the rotor 5 and the stator 6 are connected by a bearing inside the rotor 5, and the blade 7 is connected by a fixing screw on the stator end side. The screw should be a lightweight and high-strength round-head screw, and a lock nut is used on the other side for fixing. The screw does not need to be tightened.

[0027] In a preferred example, such as Figure 4 As shown, both the first interface 41 and the second interface 42 are hollow structures and are interconnected inside the connector 4, forming a wiring channel; simultaneously, the stator 6 and rotor 5 of the basic thruster unit are both hollow structures, as shown... Figure 2 As shown, the power supply line 8 of the basic thruster unit starts from the inner wall of the stator 6. The power supply line 8 of the upper-level thruster basic unit passes through the wiring channel inside the connector 4 and merges with the power supply line 8 of the lower-level thruster basic unit. Then, in this manner, it passes through multiple connectors 4 and the basic thruster units from top to bottom, and finally connects to the external body 1. Through the hollow design of the rotor 5, stator 6, and connectors 4, the problem of the power supply line of the basic thruster unit having to be externally placed is solved. Unlike the existing structure, this design can improve the simplicity of the overall appearance of the thruster, while avoiding the additional interference problem of external wiring. This allows all the wiring to be hidden inside, and the thruster is smaller when folded, making it convenient for personal transport.

[0028] In a preferred example, such as Figure 4As shown, the inner walls of the first interface 41 and the second interface 42 are each provided with at least one lug; the lug extends inward from the inner wall of the first interface 41 or the second interface 42 and protrudes, and a connecting hole is provided through the lug along the axial direction, which is used to fix the stator 6 of the propeller basic unit to the first interface 41 or the second interface 42 with fasteners. The first interface 41 and the second interface 42 are coaxially connected to the corresponding propeller basic unit, and the axes of the first interface 41 and the second interface 42 are parallel to each other.

[0029] In a preferred embodiment, there are four basic thruster units arranged in a spiral pattern from a top view. In the connectors 4 between the four basic thruster units, the included angles between the lines connecting the axes of the first interface 41 and the second interface 42 on adjacent connectors 4 are the same. The connectors 4 are made of high-strength, lightweight aluminum alloy, and their two ends are respectively connected to the stator 6 of the upper-level and lower-level basic thruster units. Simultaneously, both the first interface 41 and the second interface 42 of the connectors 4 are coaxial with their corresponding basic thruster units, thus ensuring that the four basic thruster units are distributed counterclockwise in the horizontal direction, saving space while ensuring the normal function of the thruster.

[0030] This invention also discloses an aircraft, including a fuselage 1. The upper surface of the fuselage 1 is equipped with the aforementioned multi-power vector thrusters based on a staggered layout. Among the plurality of thruster basic units, the lowest-level thruster basic unit is connected to the fuselage 1 via a connector 4. The stator 6 of the lowest-level thruster basic unit is connected to one of the first interface 41 and the second interface 42 of the connector 4, and the fuselage 1 is connected to the other of the first interface 41 and the second interface 42 of the connector 4. The thruster basic units are configured such that the outer envelope size formed in the retracted state is larger than the diameter of the fuselage 1, so that when the propeller blades 7 are naturally folded and stored under gravity, they will not interfere with the fuselage 1.

[0031] The thruster assembly is connected to the main body 1 using connector 4, the same connector 4 used inside the basic thruster unit, thus minimizing the number of parts and improving production convenience. Furthermore, the main body 1 is not limited to using a fixed size and structure, such as... Figure 5 , Figure 6 The dimensions of the fuselage 1 shown are for reference only. Different weights, volumes, and functions of fuselage 1 can be quickly replaced via the standard connection interface of connector 4, significantly improving practicality and flexibility of use. It should be noted that the diameter of fuselage 1 and the subsequent base plate 2 should be smaller than the outer envelope size of all the propeller blades 7 after folding, thus ensuring that the propeller blades 7 can be completely folded, thereby maximizing space utilization efficiency.

[0032] In a preferred embodiment, the body 1 has a base plate 2 inside, on which the mission payload and control equipment are mounted. A support frame 3 is fixedly mounted at the bottom of the base plate 2. Specifically, the body 1 and the base plate 2 are connected by lightweight aluminum alloy screws. Various control equipment and mission payloads can be mounted on the base plate 2, and all equipment payloads are completely hidden inside the body 1 without external mounting or wiring. The base plate 2 provides a mounting platform for all payloads while ensuring simple installation and overall compactness of the thruster, making it ideal for deployment in space-constrained environments. The support frame 3 is connected to the base plate 2 by four high-strength screws. This structure is load-bearing and primarily ensures the overall stability of the thruster in a static state. The support frame 3 is made of lightweight aluminum alloy and has limited outward extension while ensuring the overall stability of the thruster. This ensures both support functionality and minimizes the overall structural envelope, maximizing overall space utilization efficiency.

[0033] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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. Therefore, they should not be construed as limitations on this application.

[0034] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A multi-force vectoring thruster based on a staggered layout, characterized in that, It includes two or more basic thruster units, with multiple basic thruster units stacked vertically. The adjacent thruster basic units are connected by a connector (4). The connector (4) has a first interface (41) and a second interface (42) on opposite sides. The adjacent thruster basic units are connected to the first interface (41) and the second interface (42) respectively through a stator (6). The first interface (41) and the second interface (42) are configured such that the axis of the thruster basic unit connected to the first interface (41) and the axis of the thruster basic unit connected to the second interface (42) are parallel and spaced apart.

2. The multi-force vectoring thruster based on a staggered layout according to claim 1, characterized in that, The basic unit of the propulsion includes a stator (6), a rotor (5), and blades (7) that can be folded and disposed on the outside of the rotor (5). Deployed state: The blades (7) are deployed and extend radially along the rotor (5), and the blades (7) of multiple propeller basic units are stacked longitudinally; Collapsed state: The blades (7) are collapsed and extended in the vertical direction, and the blades (7) of multiple propeller basic units are staggered.

3. The multi-force vectoring thruster based on a staggered layout according to claim 1, characterized in that, Both the first interface (41) and the second interface (42) are hollow structures and are interconnected inside the connector (4) to form a wiring channel; The stator (6) of the basic thruster unit is a hollow structure. The power supply line (8) of the basic thruster unit starts from the inner wall of the stator (6). The power supply line (8) of the upper-level basic thruster unit passes through the wiring channel inside the connector (4) and merges with the power supply line (8) of the lower-level basic thruster unit. Then, in this manner, it passes through multiple connectors (4) and the basic thruster unit from top to bottom and finally connects to the external body (1).

4. The multi-force vectoring thruster based on a staggered layout according to claim 1, characterized in that, The inner walls of both the first interface (41) and the second interface (42) are provided with at least one support lug; The lug extends inward from the inner wall of the first interface (41) or the second interface (42), and a connecting hole is provided through the lug along the axial direction for use with fasteners to fix the stator (6) of the basic unit of the propeller to the first interface (41) or the second interface (42).

5. The multi-force vectoring thruster based on a staggered layout according to claim 1, characterized in that, The thruster consists of four basic units, which are arranged in a spiral pattern when viewed from above.

6. The multi-force vectoring thruster based on a staggered layout according to claim 5, characterized in that, In the connector (4) between the four basic thruster units, the included angle between the lines connecting the axes of the first interface (41) and the second interface (42) on adjacent connectors (4) is the same.

7. The multi-force vectoring thruster based on a staggered layout according to claim 1, characterized in that, The first interface (41) and the second interface (42) on the connector (4) are coaxially connected to the corresponding basic thruster unit, and the axes of the first interface (41) and the second interface (42) are parallel to each other.

8. An aircraft, characterized in that, Includes a body (1), the upper surface of which is equipped with a multi-power vector thruster based on a staggered layout as described in any one of claims 1-7; Among the multiple propulsion basic units, the lowest-level propulsion basic unit is connected to the body (1) via a connector (4). The stator (6) of the lowest-level propulsion basic unit is connected to one of the first interface (41) and the second interface (42) of the connector (4), and the body (1) is connected to the other of the first interface (41) and the second interface (42) of the connector (4).

9. The aircraft according to claim 8, characterized in that, The basic unit of the thruster is configured such that the outer envelope size formed in the retracted state is greater than the diameter of the body (1).

10. The aircraft according to claim 8, characterized in that, The body (1) has a base plate (2) inside, and a task load and control device are installed on the upper part of the base plate (2). A support frame (3) is fixedly installed at the bottom of the base plate (2).

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