Telescopic variable-pitch cross-medium propeller mechanism

Abstract

The telescopic variable-pitch cross-medium propeller mechanism 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 vane seat shell and the electric telescopic rod assembly are connected in a threaded mode. 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. Appropriate lift force is provided for the cross-medium aircraft or the aircraft, modular design is adopted, 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 present invention relates to the technical field of cross-medium aircraft or spacecraft, and in particular to a retractable variable-pitch cross-medium propeller mechanism. Background Art

[0002] In recent years, new unmanned aerial vehicles or aircraft equipment have emerged in my country, and scientific researchers have developed a variety of submersible-air or air-submersible cross-medium aircraft or aircraft. However, most of the current cross-medium aircraft or aircraft are small and lightweight equipment with small wings and light loads, and cannot carry large mass loads.

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

[0005] In view of this, in order to provide suitable lift for UAVs or unmanned helicopters moving in different media, the present invention 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 the 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 object, the present invention adopts the following technical solutions:

[0007] A retractable variable pitch cross-medium propeller mechanism comprises a wing seat shell, a support frame is arranged inside the wing seat shell, an electric telescopic rod assembly is arranged 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 wing tip 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 wing tip 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 mounted on the support frame, a drive motor fixedly mounted 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, wherein 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 sleeved 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 slide seats.

[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 on the wing assembly, and a transmission member mounted on the upper end of the drive gear set.

[0016] Preferably, a power module is also provided on the support frame 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 shell, and the connector module is used to be connected to the UAV rotating shaft.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The present invention provides suitable lift for a cross-medium aircraft or spacecraft, adopts a modular design, and can perform a series of wing designs according to the load requirements of the cross-medium aircraft or spacecraft. The wings are extended to a large wingspan when flying in the air, and are contracted to a small wingspan and the propeller pitch is increased when sailing underwater.

[0020] When a trans-medium aircraft or spacecraft enters 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 the stability of entering the water. After entering the water, the propeller pitch is appropriately increased to increase the underwater lift; when emerging from underwater, according to the command, the electric telescopic rod unlocks and extends the wing blades after the wing blades emerge from the water surface, and locks them after the stroke is in place, and 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 reconstruct and deform the shape of propeller blades across media, and can adapt to both aerial flight 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-medium 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 It is a schematic diagram of the above-water structure of the propeller mechanism of the present invention;

[0029] Figure 2 It is a schematic diagram of the underwater structure of the propeller mechanism of the present invention;

[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 middle; 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 the present invention, unless otherwise specified, "plurality" means two or more than two; the orientations or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0034] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

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

[0036] 1. Adopts deformable high-strength and 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 adopts high-strength aluminum alloy material and a sealing structure design, can withstand underwater high-pressure environment, and provide high-strength waterproof protection for the inside of the cross-medium propeller structure;

[0043] The lower end of the wing seat shell 1 is connected to the UAV 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. The rotary connection that adapts to the rotating motor and the connector that prevents deep water leakage are adopted.

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

[0045] At the same time, the driving racks 10 of the two wings are designed to be symmetrical about the driving gear 9, and the two sets of push rods 11 are driven by a set of driving motors 8, which have the characteristics of compact structure, high precision, high speed, high reliability, etc. It adopts shared motors, high-precision sensors, real-time control port design, large stroke and fast telescopic technology.

[0046] A deformable high-strength and lightweight carbon fiber wing assembly is symmetrically arranged on the left and right sides of the energy-saving high-strength electric telescopic rod assembly, and its specific structure is: including a wing root portion 4 threadedly connected to a reduction gear box 7, and also including a wing middle portion 5 and a wing tip portion 6 which are sequentially sleeved with the wing root portion 4. Although only three-section wing pieces are shown in the figure, the wing pieces of the corresponding number of sections can be selected and increased or decreased during the production process according to actual needs. At the same time, a push rod 11 is located inside the wing assembly, and at the same time, 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 portion 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 waterproofing technology, etc.;

[0047] At the same time, a sliding sleeve assembly is arranged inside the wing assembly, and the push rod 11 is sleeved on the sliding sleeve assembly. At the same time, the sliding sleeve assembly adopts a plurality of slide seats 12 which are sleeved with each other. At the same time, self-locking devices 13 are arranged between adjacent slide seats 12 and between the slide seats 12 and the push rod 11. At the same time, it can be seen from the accompanying drawings that the number of sections of the slide seats 12 on the sliding sleeve assembly should be equal to the number of wing assemblies minus one, and the bottom slide seat 12 is fixedly arranged 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. 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, and can receive aircraft or spacecraft instructions in real time to achieve pitch change. It has the characteristics of complete interface, simple control, fast response, high efficiency, low cost, etc., and adopts technologies such as stepless pitch control and high-response brushless motor. The specific structure is: a DC brushless motor 14 fixedly arranged on the support frame, a gear set 15 fixedly arranged on the output shaft of the DC brushless motor 14 and on the wing assembly, and a transmission member 16 arranged on the upper end of the drive gear 9 group. A chain can be used for the transmission member 16.

[0049] A power module 17 is also provided inside the wing seat housing 1, which is used to power all the above-mentioned electrical components, such as the drive motor 8 and the DC brushless motor 14; it is mainly composed of a lithium battery pack, a cable assembly and an output interface, etc., which independently provides stable power for the entire mechanism. It can be powered by an external power supply during debugging, and has an internal and external power switching interface, which is convenient for debugging and flexible power use. High-density lithium batteries are selected, and the output power is strong. Technologies such as independent power supply, multi-voltage stabilization and output control are adopted.

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

[0051] 1. First, install and fix the electric telescopic rod assembly, variable pitch 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 retractable rod assembly and fix them;

[0053] 3. Then connect the root of the blade assembly to the variable pitch motor assembly, and use an O-ring for dynamic sealing at 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 air pressure test on the variable pitch propeller. After the air tightness test is passed, the variable pitch propeller can be installed on the power motor of the aircraft or aircraft that needs to be connected to achieve cross-medium flight.

[0055] The working process of this technical solution:

[0056] When a cross-medium aircraft or aircraft enters the water from the air, the electric telescopic rod retracts and locks the wing 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 is unlocked and the wing is quickly extended after the wing is exposed to the water surface, and locked after the stroke is in place, 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 flight or navigation attitude control can be achieved through the variable pitch motor assembly.

[0057] The above are only preferred specific implementation modes of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical solutions and inventive concepts of the present invention within the technical scope disclosed by the present invention, which 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 arranged inside the blade seat housing (1), characterized in that: The support frame is provided with an electric telescopic rod assembly, and the left and right ends of the electric telescopic rod assembly are screwed with wing assemblies, and 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.

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); 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: Sealing elements are used to dynamically seal between the wing root (4) and the wing seat shell (1), between the wing root (4) and the wing middle (5), and between the wing middle (5) and the wing tip (6).

4. The retractable variable pitch cross-medium propeller mechanism according to claim 1, characterized in that: The electric telescopic rod assembly comprises a reduction gear box (7) fixedly arranged on the support frame, a driving motor (8) fixedly arranged on the support frame and connected to the input end of the reduction gear box (7), a driving gear (9) arranged on the output shaft of the reduction gear box (7), a driving rack (10) meshing with the driving gear (9), and a push rod (11) connected to the front end of the driving 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 the 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 arranged between adjacent slide seats (12).

7. The retractable variable pitch cross-medium propeller mechanism according to claim 1, characterized in that: The support frame is provided with two variable pitch motor assemblies, which 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 5, 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 on the wing assembly, and a transmission member (16) mounted on the upper end of the drive gear (9) set.

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 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 arranged 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 drone rotating shaft (3).

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