Telescopic variable-pitch cross-medium propeller mechanism

Abstract

The utility model discloses a telescopic variable-pitch cross-medium propeller mechanism which comprises a vane seat shell, a supporting frame is arranged in the vane seat shell, an electric telescopic rod assembly is arranged on the supporting frame, vane assemblies are connected to the left end and the right end of the electric telescopic rod assembly in a threaded mode, each vane assembly is formed by sleeving a plurality of multi-section vanes, and the vanes are arranged on the vane seat shell. The front end of the electric telescopic rod assembly is connected with a wing piece at the foremost end of the wing piece assembly, and the wing piece assembly is driven by the electric telescopic rod assembly to stretch and retract. Proper lift force is provided for the cross-medium aircraft or the aircraft, modular design is adopted, the wing panel serialization design can be carried out according to the load requirement of the cross-medium aircraft or the aircraft, the wing panel extends into a large wingspan during air flight, the wing panel contracts into a small wingspan during underwater navigation, and the screw pitch of the propeller is increased.

Description

Technical Field

[0001] The utility model relates to the technical field of cross-medium aircraft or aircraft, and in particular to a retractable variable-pitch cross-medium propeller mechanism. Background Art

[0002] In recent years, the "New Quality Productivity" strategy has accelerated the development of new marine technologies. New unmanned aerial vehicles (UAVs) and aircraft have emerged in my country, and researchers have developed numerous submersible-to-air or air-to-submersible trans-medium aircraft or vehicles. However, most current trans-medium aircraft or vehicles are small and lightweight, with small wings and light payloads, making them incapable of carrying large payloads.

[0003] Large loads require aircraft or aircraft to have sufficient lift, and large lift requires a large wingspan and high rotation speed. However, cross-medium aircraft or aircraft often need to go through the movement process of two media: flying in the air and sailing underwater. Different media have different requirements for wingspan and rotation speed. Air flight requires a long wingspan and a reasonable high-efficiency rotation speed, while underwater navigation with a propeller that is too long will bring a large wingtip speed and cause cavitation of the winglets. The winglets will also be eroded by cavitation, greatly reducing the propeller efficiency and causing instability in underwater navigation. Therefore, underwater navigation requires a smaller propeller wingspan.

[0004] Therefore, how to make the wing have the ability to change shape, maintain a large wingspan when flying in the air and a small wingspan when sailing underwater, and have pitch adjustment to achieve lift control, is of great significance for cross-medium aircraft or aircraft to achieve stable flight or navigation. Utility Model Content

[0005] In view of this, in order to provide suitable lift for drones or unmanned helicopters moving in different media, the utility model can extend and rotate the propeller according to the different flight or navigation media, change parameters such as propeller shape and pitch in real time, and realize stable flight or navigation of aircraft or aircraft across media, provide technical support for new cross-media aircraft or aircraft, and propose a retractable variable-pitch cross-media propeller mechanism.

[0006] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0007] A retractable variable-pitch cross-medium propeller mechanism includes a wing seat housing, a support frame is provided inside the wing seat housing, an electric telescopic rod assembly is provided on the support frame, the left and right ends of the electric telescopic rod assembly are screwed with wing assemblies, the wing assembly is composed of a plurality of multi-section wing sets, the front end of the electric telescopic rod assembly is connected to the wing at the front end of the wing assembly, and the wing assembly is extended and shortened by the drive of the electric telescopic rod assembly.

[0008] As a further improvement of the above technical solution:

[0009] Preferably, the wing assembly includes a wing root portion threadedly connected to the electric telescopic rod assembly, a wing middle portion sleeved with the wing root portion, and a wingtip portion sleeved with the wing middle portion, and the front end of the electric telescopic rod assembly is fixedly connected to the front end of the wingtip portion.

[0010] Preferably, seals are used for dynamic sealing between the wing root and the wing seat shell, between the wing root and the wing middle, and between the wing middle and the wing tip.

[0011] Preferably, the electric telescopic rod assembly includes a reduction gearbox fixedly arranged on the support frame, a drive motor fixedly arranged on the support frame and connected to the input end of the reduction gearbox, a drive gear arranged on the output shaft of the reduction gearbox, a drive rack meshing with the drive gear, and a push rod connected to the front end of the drive rack, and the push rod is connected to the wing at the front end of the wing assembly.

[0012] Preferably, the push rod is sleeved in the sliding sleeve assembly, and the sliding sleeve assembly is composed of a plurality of sliding seats sleeve-connected with each other, and the sliding seat at the rear end of the sliding sleeve assembly is fixedly arranged on the wing assembly.

[0013] Preferably, a self-locking device is provided between adjacent slides.

[0014] Preferably, two variable pitch motor assemblies are provided on the support frame, and the two variable pitch motor assemblies are respectively connected to the wing assemblies, and the flight or navigation attitude control is achieved by adjusting the connection pitch between the wing assembly and the electric telescopic rod assembly.

[0015] Preferably, the variable pitch motor assembly includes a brushless DC motor fixedly mounted on the support frame, a gear set fixedly mounted on the output shaft of the brushless DC motor and the wing assembly, and a transmission member mounted on the upper end of the gear set.

[0016] Preferably, the support frame is also provided with a power supply module for supplying power to various electrical components of the entire mechanism.

[0017] Preferably, a connector module is provided in the middle of the lower end of the wing seat housing, and the connector module is used to be connected to the UAV rotating shaft.

[0018] Compared with the existing technology, the beneficial effects of the utility model are:

[0019] The utility model provides suitable lift for a cross-medium aircraft or aircraft, adopts a modular design, and can carry out a series design of winglets according to the load requirements of the cross-medium aircraft or aircraft. When flying in the air, the winglets are extended to a large wingspan, and when sailing underwater, the winglets are contracted to a small wingspan and the propeller pitch is increased.

[0020] When a trans-medium aircraft or spacecraft enters the water from the air, the electric telescopic rod retracts and locks the wing blades according to the command, and the variable pitch motor rotates to adjust the propeller pitch in real time to maintain stability when entering the water. After entering the water, the propeller pitch is appropriately increased to increase underwater lift. When emerging from the water, according to the command, the electric telescopic rod unlocks and extends the wing blades after the wing blades emerge from the water, and locks them after the travel is in place. At the same time, the variable pitch motor rotates to adjust the propeller pitch to control the water exit posture.

[0021] It also has the following effects:

[0022] 1. It has the ability to reshape and deform the propeller blades across different media, and can adapt to both aerial and underwater navigation.

[0023] 2. It has a wide range of pitch adjustment capabilities, and the propeller pitch is changed by changing the blade angle through the pitch motor.

[0024] 3. It has the ability to carry large mass payloads, enrich the types of payloads, and greatly expand the use of cross-media aircraft or spacecraft.

[0025] 4. The use of high-strength slender retractable rod can reduce the thickness and resistance of the wing.

[0026] 5. Have certain posture control capabilities to ensure stable posture when entering and exiting the water.

[0027] 6. A large internal space is reserved for product counterweight or installation of instruments, which greatly improves the adaptability of the cross-medium propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the above-water structure of the propeller mechanism of the present utility model;

[0029] Figure 2 This is a schematic diagram of the underwater structure of the propeller mechanism of the utility model;

[0030] Figure 3 It is a schematic cross-sectional view of the wing assembly of the present invention.

[0031] In the figure: 1. Wing seat housing; 2. Connector module; 3. UAV shaft; 4. Wing root; 5. Wing mid-section; 6. Wing tip; 7. Reduction gearbox; 8. Drive motor; 9. Drive gear; 10. Drive rack; 11. Push rod; 12. Slide; 13. Self-locking device; 14. DC brushless motor; 15. Gear set; 16. Transmission parts; 17. Power module. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0033] In the description of this utility model, unless otherwise specified, "plurality" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of this utility model and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific direction, be constructed, or operate in a specific direction, and therefore should not be construed as limiting this utility model. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0034] In the description of this utility model, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integral connection; mechanical connection, electrical connection; direct connection, or indirect connection through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0035] As attached Figure 1 To the attached Figure 3 As shown, this technical solution includes the following parts:

[0036] 1. Adopts deformable, high-strength, lightweight carbon fiber wing components;

[0037] 2. Energy-saving high-strength electric telescopic rod assembly;

[0038] 3. Variable pitch motor assembly with stepless pitch adjustment;

[0039] 4. High-compatibility power module 17 with multi-voltage stabilization control output;

[0040] 5. A connector module 2 that achieves stable transmission and communication and prevents deep water leakage;

[0041] 6. The wing seat housing 1 provides high-strength structure and waterproof protection.

[0042] The wing seat housing 1 is mainly composed of a support frame (not shown in the figure, but the support frame is conventional technology), a power shaft, a housing, etc. It is made of high-strength aluminum alloy material and a sealed structure design. It can withstand the high-pressure environment underwater and provide high-strength waterproof protection for the interior of the cross-medium propeller structure.

[0043] The lower end of the wing seat shell 1 is connected to the drone shaft 3 through the connector module 2. The connector module 2 is mainly composed of a plug, a socket, a rotary connector and a cable, which can achieve reliable connection with the inside and the outside. A waterproof rotary connector that adapts to rotation is used to achieve stable data transmission and command communication. It adopts technologies such as rotary connection that adapts to rotating motors and connector anti-leakage at great water depths.

[0044] An energy-saving and high-strength electric telescopic rod assembly is provided inside the wing seat housing 1, and its specific structure is: a reduction gearbox 7 fixedly arranged on the support frame, a drive motor 8 fixedly arranged on the support frame and connected to the input end of the reduction gearbox 7, a drive gear 9 arranged on the output shaft of the reduction gearbox 7, a drive rack 10 meshing with the drive gear 9, and a push rod 11 connected to the front end of the drive rack 10. The forward and reverse rotation of the drive motor 8 is converted into a telescopic action of the push rod 11 by the cooperation between the drive gear 9 and the drive rack 10, thereby realizing the extension and shortening of the wing connected thereto. The push rod 11 is designed to be a slender rod to adapt to thin winglets. Although the accompanying drawings do not show a corresponding limit design for the rack, it is a conventional technology to drive the drive rack 10 to move left and right by the forward and reverse rotation of the drive gear 9, and to limit the drive rack 10 in a direction perpendicular to the direction of movement.

[0045] The drive racks 10 of the two wings are designed to be symmetrical about the drive gear 9. The two sets of push rods 11 are driven by a set of drive motors 8. They have the characteristics of compact structure, high precision, high speed and high reliability. They adopt technologies such as shared motor, high-precision sensor, real-time control port design, and large-stroke and fast extension.

[0046] A deformable, high-strength, lightweight carbon fiber wing assembly is symmetrically arranged on the left and right sides of the energy-saving, high-strength electric telescopic rod assembly. Its specific structure is as follows: it includes a wing root portion 4 threadedly connected to a reduction gear box 7, and also includes a wing middle portion 5 and a wing tip portion 6 which are sequentially sleeved with the wing root portion 4. Although the figure only shows a three-section wing assembly, the wing of the corresponding number of sections can be selected and reduced during the production process according to actual needs. At the same time, the push rod 11 is located inside the wing assembly, and the front end of the push rod 11 is fixedly connected to the wing tip portion 6. Seals are used for dynamic sealing between the wing root portion 4 and the wing seat housing 1, between the wing root portion 4 and the wing middle portion 5, and between the wing middle portion 5 and the wing tip 6. Therefore, the wing assembly as a whole adopts a three-section suit and a high lift-to-drag ratio airfoil design, dynamic sealing and waterproof technology, etc.

[0047] At the same time, a sliding sleeve assembly is provided inside the wing assembly, and the push rod 11 is sleeved on the sliding sleeve assembly. At the same time, the sliding sleeve assembly is composed of several slides 12 that are sleeved with each other. At the same time, self-locking devices 13 are provided between adjacent slides 12 and between the slides 12 and the push rods 11. At the same time, it can be seen from the accompanying drawings that the number of sections of the slides 12 on the sliding sleeve assembly should be equal to the number of wing assemblies minus one, and the bottom slide 12 is fixedly set on the wing root 4.

[0048] A variable pitch motor assembly with stepless pitch adjustment is also provided inside the wing seat shell 1. There are two variable pitch motor assemblies, which are responsible for adjusting the wing pitch. The lift control is mainly achieved by rotating to change the wing pitch. At the same time, it has the ability to control the stable attitude when entering and exiting the water. It can receive aircraft or vehicle instructions in real time to achieve pitch change. It has the characteristics of complete interface, simple control, fast response, high efficiency and low cost. It adopts technologies such as stepless pitch control and high-response brushless motor. The specific structure is: a DC brushless motor 14 fixedly set on the support frame, a gear set 15 fixedly set on the output shaft of the DC brushless motor 14 and on the wing assembly, and a transmission member 16 arranged at the upper end of the gear set 15. A chain can be used for the transmission member 16.

[0049] A power module 17 is also located within the vane housing 1 to power all of the aforementioned electrical components, such as the drive motor 8 and brushless DC motor 14. Composed primarily of a lithium battery pack, cable assembly, and output interface, it independently provides stable power to the entire mechanism. During commissioning, it can be powered by an external power source. A switch interface between internal and external power allows for flexible power usage and convenient commissioning. High-density lithium batteries provide robust output power. Technologies such as independent power supply and multi-voltage stabilization control output are employed.

[0050] The installation process of each component of this technical solution:

[0051] 1. First, install and fix the electric telescopic rod assembly, pitch-changing motor assembly, power module 17, connector module 2 and other components on the support frame of the wing seat housing 1 (6) in sequence;

[0052] 2. Then screw the two wing assemblies from the left and right into the electric retracting rod assembly and secure them;

[0053] 3. Then connect the root of the blade assembly to the variable pitch motor assembly. Use an O-ring to dynamically seal the connection between the blade assembly and the blade seat housing 1. After all the components are installed in place, a variable pitch propeller mechanism is formed.

[0054] 4. Perform an air tightness and pressure test on the variable pitch propeller. Once the air tightness test is passed, the variable pitch propeller can be installed on the power motor of the aircraft or vehicle to be connected to achieve cross-medium flight.

[0055] The working process of this technical solution:

[0056] When a trans-medium aircraft or aircraft enters the water from the air, the electric telescopic rod retracts and locks the wings according to the command, while the variable pitch motor rotates to adjust the propeller pitch in real time to maintain stability when entering the water. After entering the water, the propeller pitch is appropriately increased to increase underwater lift. When emerging from the water, according to the command, the electric telescopic rod unlocks and quickly extends the wings after the wings emerge from the water. The wings are locked after the travel is completed, and the variable pitch motor rotates to adjust the propeller pitch to control the attitude when emerging from the water. During flight or navigation, the variable pitch motor assembly can achieve flight or navigation attitude control.

[0057] The above are only preferred specific implementation methods of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and utility model concept of the present invention, should be covered by the protection scope of the present invention.

Claims

1. A retractable variable pitch cross-medium propeller mechanism, comprising a blade seat housing (1), wherein a support frame is provided inside the blade seat housing (1), characterized in that: An electric telescopic rod assembly is provided on the support frame, and wing assemblies are screwed on the left and right ends of the electric telescopic rod assembly. The wing assembly is composed of a plurality of multi-section wings. The front end of the electric telescopic rod assembly is connected to the wing at the front end of the wing assembly, and the wing assembly is extended and shortened by the drive of the electric telescopic rod assembly.

2. The retractable variable-pitch cross-medium propeller mechanism according to claim 1, characterized in that: The wing assembly comprises a wing root portion (4) threadedly connected to the electric telescopic rod assembly, a wing middle portion (5) sleeved with the wing root portion (4), and a wing tip portion (6) sleeved with the wing middle portion (5), and the front end of the electric telescopic rod assembly is fixedly connected to the front end of the wing tip portion (6).

3. The retractable variable-pitch cross-medium propeller mechanism according to claim 2, characterized in that: Dynamic sealing is performed between the wing root portion (4) and the wing seat housing (1), between the wing root portion (4) and the wing mid-portion (5), and between the wing mid-portion (5) and the wing tip portion (6) using sealing elements.

4. The retractable variable-pitch cross-medium propeller mechanism according to claim 1, characterized in that: The electric telescopic rod assembly comprises a reduction gearbox (7) fixedly arranged on the support frame, a drive motor (8) fixedly arranged on the support frame and connected to the input end of the reduction gearbox (7), a drive gear (9) arranged on the output shaft of the reduction gearbox (7), a drive rack (10) meshing with the drive gear (9), and a push rod (11) connected to the front end of the drive rack (10), wherein the push rod (11) is connected to the wing at the front end of the wing assembly.

5. The retractable variable-pitch cross-medium propeller mechanism according to claim 4, characterized in that: The push rod (11) is sleeved in a sliding sleeve assembly, and the sliding sleeve assembly is composed of a plurality of sliding seats (12) sleeved with each other, and the sliding seat (12) at the rear end of the sliding sleeve assembly is fixedly arranged on the wing assembly.

6. The retractable variable-pitch cross-medium propeller mechanism according to claim 5, characterized in that: A self-locking device (13) is provided between adjacent slide seats (12).

7. The retractable variable-pitch cross-medium propeller mechanism according to claim 1, characterized in that: Two variable pitch motor assemblies are provided on the support frame, and the two variable pitch motor assemblies are respectively connected to the wing assemblies. The flight or navigation attitude control is achieved by adjusting the connection pitch between the wing assemblies and the electric telescopic rod assembly.

8. The retractable variable-pitch cross-medium propeller mechanism according to claim 7, characterized in that: The variable pitch motor assembly comprises a brushless DC motor (14) fixedly mounted on the support frame, a gear set (15) fixedly mounted on the output shaft of the brushless DC motor (14) and the wing assembly, and a transmission member (16) mounted on the upper end of the gear set (15).

9. The retractable variable-pitch cross-medium propeller mechanism according to any one of claims 1 to 6, characterized in that: The support frame is also provided with a power supply module (17) for supplying power to various electrical components of the entire mechanism.

10. The retractable variable-pitch cross-medium propeller mechanism according to claim 1, characterized in that: A connector module (2) is provided in the middle of the lower end of the wing seat housing (1), and the connector module (2) is used to be connected to the UAV rotating shaft (3).

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