Aviation propeller blade convenient to maintain

Abstract

The utility model discloses an aviation propeller blade convenient to maintain, which relates to the technical field of aviation flight, and comprises a blade, a connector, a power rod, a linear motor and a balancing weight, the left side of the blade is provided with the connector, the connector is arranged on the outer ring of the power rod, the linear motor is arranged in the center of the interior of the blade and the connector, and the balancing weight is arranged in the power rod. According to the equipment, the linear motor is installed at the position of the center point of the inner side of the connector and the inner side of the paddle, it can be guaranteed that the overall gravity center of the paddle is stable, after the linear motor is started, balance can be automatically adjusted under the action of the balancing weight, and the gravity center of the propeller can be changed; therefore, the operation vibration value of the propeller is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation flight, in particular to an aviation propeller blade which is convenient to maintain. Background Art

[0002] A propeller is a device that converts the engine's rotational power into propulsion by rotating the blades in the air or water. It may have two or more blades connected to the hub, and the rear side of the blade is a spiral surface or a propeller similar to a spiral surface. There are many types of propellers, and they are widely used, such as propellers for aircraft and ships, etc. However, existing aircraft propellers have shortcomings, such as:

[0003] A propeller as described in Publication No. CN208412129U comprises a hub and a plurality of blades connected to the hub, the plurality of blades being evenly distributed along the circumferential direction of the hub, the blades comprising a plurality of cross-sectional airfoils arranged side by side at equal intervals from the wing root to the wing tip, the plurality of cross-sectional airfoils being connected by a Bezier surface, the torsion angle of each cross-sectional airfoil decreasing successively from the root position along the span direction, but when the device is in use, the blades are susceptible to being hit by foreign objects, thus requiring local repair (local repairs are usually performed by filing, which causes a change in the center of gravity), and the repairs are bound to cause aerodynamic imbalance between the blades. Utility Model Content

[0004] The purpose of the utility model is to provide an aviation propeller blade that is easy to maintain, so as to solve the problem that the blades of the existing equipment on the market are easily hit by foreign objects when in use, so local repairs are required (local repairs usually adopt filing repairs, which will cause changes in the center of gravity), and the repairs will inevitably cause aerodynamic imbalance between the blades.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aviation propeller blade that is easy to maintain, comprising a blade, a connector, a power rod, a linear motor and a counterweight;

[0006] A connector is arranged on the left side of the blade, and the connector is installed on the outer ring of the power rod. A linear motor is arranged at the center position of the blade and the connector, and a counterweight is installed on the right side of the linear motor.

[0007] As a preferred technical solution of the utility model, the blade is arranged in a streamlined structure, and the blade is drop-shaped when viewed from the side, and there are three blades evenly arranged in a clockwise direction;

[0008] By adopting the above technical solution, the device reduces the drag coefficient when installing by setting the blades as a streamlined structure, and the blades face the same direction to maintain the consistency of the thrust generated.

[0009] As a preferred technical solution of the utility model, a connector is fixedly connected to the inner side of the blade, and the connector is a circular structure whose size gradually decreases along the outer side;

[0010] By adopting the above technical solution, the device can reduce the wind resistance by connecting the connector, and the circular structure can reduce the generation of wind noise, which is more conducive to installation.

[0011] As a preferred technical solution of the utility model, a power rod is fixedly connected to the inner side of the connector, the power rod has a conical round head, and a balance detection device is installed inside the power rod;

[0012] By adopting the above technical solution, the device can improve the circulation efficiency of the airflow and ensure sufficient thrust by setting the power rod as a conical round head, and a balance detection device is installed in the power rod to actively detect the posture of the device.

[0013] As the preferred technical solution of the utility model, a hole is opened at the center point of the inner side of the connector and the blade, and the connector and the blade hole are a two-section structure. The size of the hole on the left side of the connector and the blade hole is twice that of the right side, and a linear motor is fixedly connected to the hole on the left side of the connector and the blade hole, and a counterweight is installed on the right side of the linear motor.

[0014] By adopting the above technical solution, the device can ensure the stability of the overall center of gravity of the blade by installing the linear motor at the center point of the connector and the inner side of the blade. When the linear motor is started, it can automatically adjust the balance under the action of the counterweight block, and can change the center of gravity of the propeller, thereby reducing the vibration value of the propeller operation;

[0015] As a preferred technical solution of the utility model, three fixing grooves are evenly opened in the power rod, an offset rotating rod is installed at the center of the fixing groove, the offset rotating rod is a square columnar structure, and an offset rotating disk is fixedly connected to the inner side of the offset rotating rod, a rudder head is slidably connected in the offset rotating disk, the rudder head is connected to the aircraft control stick, and a cylindrical extension rod is installed at the edge of the offset rotating disk;

[0016] By adopting the above technical solution, the device can be connected to the blade by installing an offset rotating rod at the center position of the fixed groove, and the offset angle of the blade can be controlled to achieve different thrusts through the offset rotating disk fixedly connected to the inner side of the offset rotating rod.

[0017] Compared with the prior art, the beneficial effects of the utility model are:

[0018] The device can reduce the wind resistance of the connector and the circular structure can reduce the wind noise, which is more convenient for installation. The power rod is set to a conical round head, which can improve the circulation efficiency of the airflow and ensure sufficient thrust. In addition, a balance detection device is installed in the power rod to adjust the center of gravity of the propeller in real time according to the dynamic balance detection result of the propeller. No manual adjustment is required, which can achieve the effect of maintenance-free center of gravity, reduce the maintenance process, and improve maintenance efficiency.

[0019] The device can ensure the stability of the overall center of gravity of the blade by installing the linear motor between the connector and the inner center point of the blade. When the linear motor is started, it can automatically adjust the balance under the action of the counterweight block, which can change the center of gravity of the propeller and thus reduce the vibration value of the propeller operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a left-side perspective structural diagram of the utility model;

[0021] Figure 2 This is a front structural schematic diagram of the utility model;

[0022] Figure 3 This is a schematic diagram of the internal left-side stereoscopic structure of the power rod of the utility model;

[0023] Figure 4 This is a schematic diagram of the power rod structure from a top view of the utility model;

[0024] Figure 5 This is a front view structural diagram of the blade section of the utility model;

[0025] Figure 6 It is a schematic diagram of the three-dimensional structure of the blade of the utility model when viewed from the right side.

[0026] In the figure: 1. propeller blade; 2. connector; 3. power rod; 4. linear motor; 5. counterweight; 6. fixing slot; 7. offset turntable; 8. offset turntable. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0028] See also Figure 1-6 , the technical solution of the utility model: an aviation propeller blade that is easy to maintain, including a blade 1, a connector 2, a power rod 3, a linear motor 4, a counterweight block 5, a fixing slot 6, an offset turntable 7 and an offset turnbar 8;

[0029] A connector 2 is provided on the left side of the blade 1. The blade 1 is set to a streamlined structure, and the blade 1 is drop-shaped when viewed from the side. There are three blades 1 evenly arranged in a clockwise direction. The device reduces the wind resistance coefficient when installing by setting the blade 1 to a streamlined structure, and the blade 1 is in the same direction to maintain the consistency of the thrust generated. The connector 2 is installed on the outer ring of the power rod 3. The inner side of the blade 1 is fixedly connected with the connector 2. The connector 2 is a circular structure with a size that gradually decreases along the outer side. The device can reduce the wind resistance by connecting the connector 2. At the same time, the circular structure can reduce the generation of wind noise, which is more conducive to installation. A linear motor 4 is provided at the center position inside the blade 1 and the connector 2. A counterweight 5 is installed on the right side of the linear motor 4. The power rod 3 is fixedly connected to the inner side of the connector 2. The power rod 3 has a conical round head. The device can improve the circulation efficiency of the airflow and ensure sufficient thrust by setting the power rod 3 to a conical round head. A hole is opened at the center point of the connector 2 and the inner side of the blade 1, and the connector 2 and the hole of the blade 1 are a two-section structure. The size of the left side hole of the connector 2 and the blade 1 hole is twice that of the right side, and a linear motor 4 is fixedly connected to the left side hole of the connector 2 and the blade 1 hole, and a counterweight 5 is installed on the right side of the linear motor 4. The device can ensure the stability of the overall center of gravity of the blade 1 by installing the linear motor 4 at the center point of the connector 2 and the inner side of the blade 1. When the linear motor 4 is started, it can automatically adjust the balance under the action of the counterweight 5, and the center of gravity of the propeller can be changed, thereby reducing the vibration value of the propeller operation. Three fixed grooves 6 are evenly opened in the power rod 3, and an offset rotating rod 8 is installed at the center position of the fixed groove 6. The offset rotating rod 8 is a square columnar structure, and an offset turntable 7 is fixedly connected to the inner side of the offset rotating rod 8. A rudder head is slidably connected in the offset turntable 7, and the rudder head is connected to the aircraft control stick. A cylindrical extension rod is installed at the edge of the offset turntable 7. The device can be connected to the blade 1 by installing an offset rotating rod 8 at the center position of the fixed groove 6. The offset turntable 7 fixedly connected to the inner side of the offset rotating rod 8 can control the offset angle of the blade 1 to achieve different thrusts.

[0030] Working principle: When using this kind of aviation propeller blade which is easy to maintain, first connect it with the aircraft through the power rod 3, open the power rod 3 and insert the offset rotating rod 8 into the connector 2, then align the connector 2 with the fixing groove 6, insert the column head of the offset rotating disk 7 into the groove of the rudder head, and then start the aircraft, the engine drives the power rod 3 to rotate, and at the same time the internal balance detection equipment starts to run, and the linear motor 4 adjusts the distance of the counterweight block 5 according to the balance data instruction;

[0031] When the propeller blade 1 is needed to provide thrust for takeoff, it is only necessary to pull the operating lever, which will push the rudder head forward under the action of the connecting rod, and the rudder head will drive the offset turntable 7 to rotate. The offset turntable 7 will change the angle of the offset lever 8 and the propeller blade 1, thereby greatly increasing the thrust to complete the takeoff.

[0032] Thereby completing a series of tasks, the contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0033] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aviation propeller blade that is easy to maintain, comprising a blade (1), a connector (2), a power rod (3), a linear motor (4), a counterweight (5), a fixing slot (6), an offset turntable (7) and an offset turnbar (8), characterized in that: A connector (2) is provided on the left side of the blade (1), the connector (2) is mounted on the outer ring of the power rod (3), a linear motor (4) is provided at the center position inside the blade (1) and the connector (2), a counterweight (5) is installed on the right side of the linear motor (4), a fixing groove (6) is provided in the power rod (3), an offset rotating rod (8) is installed in the fixing groove (6), and an offset rotating disk (7) is installed inside the offset rotating rod (8).

2. The aircraft propeller blade that is easy to maintain according to claim 1, characterized in that: The blade (1) is arranged in a streamlined structure, and the blade (1) is drop-shaped when viewed from the side, and there are three blades (1) evenly arranged in a clockwise direction.

3. The aircraft propeller blade that is easy to maintain according to claim 2, characterized in that: A connector (2) is fixedly connected to the inner side of the blade (1); the connector (2) is a circular structure whose size gradually decreases toward the outer side.

4. The aircraft propeller blade that is easy to maintain according to claim 3, characterized in that: A power rod (3) is fixedly connected to the inner side of the connector (2); the power rod (3) has a conical round head, and a balance detection device is installed inside the power rod (3).

5. The aircraft propeller blade that is easy to maintain according to claim 4, characterized in that: A hole is provided at the center point of the inner side of the connector (2) and the blade (1), and the hole of the connector (2) and the blade (1) is a two-stage structure, the size of the hole on the left side of the hole of the connector (2) and the blade (1) is twice that of the hole on the right side, and a linear motor (4) is fixedly connected to the hole on the left side of the hole of the connector (2) and the blade (1), and a counterweight block (5) is installed on the right side of the linear motor (4).

6. The aircraft propeller blade that is easy to maintain according to claim 5, characterized in that: Three fixing grooves (6) are evenly arranged in the power rod (3); an offset rotating rod (8) is installed at the center of the fixing groove (6); the offset rotating rod (8) is a square columnar structure; an offset rotating disk (7) is fixedly connected to the inside of the offset rotating rod (8); a rudder head is slidably connected to the inside of the offset rotating disk (7); the rudder head is connected to the aircraft control stick; and a cylindrical extension rod is installed at the edge of the offset rotating disk (7).

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