Belt tensioner structure and aircraft

Abstract

The utility model relates to an aircraft technical field especially relates to a belt compression wheel structure and aircraft. The belt compression wheel structure, including fixed frame, operating part and torsion spring, the fixed frame is used for fixing in the frame of aircraft, operating part with fixed frame articulates, the torsion spring is clamped between fixed frame with operating part, provides pressure to operating part through elastic deformation, operating part transmission pressure to the drive belt of aircraft. The utility model embodiment provides a belt compression wheel structure through the torsion spring clamped between fixed frame with operating part, provides pressure to operating part through elastic deformation, operating part transmission pressure to the drive belt of aircraft, thereby keeps the drive belt with normal occlusion of transmission wheel, so that need not be the frequent adjustment of the aircraft belt tightness, convenient to use.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a belt pressure wheel structure and an aircraft. Background Technology

[0002] In related technologies, aircraft include a main rotor and a tail rotor. To reduce costs, the main rotor and tail rotor are driven by the same motor. Specifically, the motor drives the main shaft to rotate the main rotor, and at the same time, the power is transmitted to the tail rotor through belt drive. However, after a period of use, the meshing between the belt and the gear will deteriorate, and the belt tension needs to be readjusted, which is inconvenient to use. Utility Model Content

[0003] This invention addresses the technical problem of transmission belts loosening after long-term use in aircraft, requiring readjustment of belt tension and causing inconvenience. It provides a belt pressure wheel structure and an aircraft.

[0004] This utility model provides a belt pressure wheel structure, including a fixed frame, an operating component, and a torsion spring. The fixed frame is used to fix to the frame of an aircraft. The operating component is hinged to the fixed frame. The torsion spring is sandwiched between the fixed frame and the operating component and provides pressure to the operating component through elastic deformation. The operating component transmits the pressure to the transmission belt of the aircraft.

[0005] In one embodiment, the mounting frame includes a fixed plate and a hinge plate connected together, the fixed plate being used to fix it to the frame of the aircraft.

[0006] In one embodiment, the operating component includes an abutment plate, a rotating plate, and a pressure rod connected in sequence. The rotating plate is hinged to the hinge plate, and the pressure rod is used to transmit pressure to the transmission belt of the aircraft.

[0007] In one embodiment, the torsion spring includes a first extended end, a spring body, and a second extended end connected together, the first extended end abutting against the fixed plate, and the second extended end abutting against the abutting plate.

[0008] In one embodiment, the system further includes a pivot shaft that extends through the hinge plate, the rotating plate, and the spring body.

[0009] In one embodiment, a pressure roller is also included, which is mounted on the pressure rod and is used to press against the transmission belt of the aircraft.

[0010] In one embodiment, the rotating plate includes a first rotating plate and a second rotating plate arranged at a relative interval, the abutment plate is connected between the first rotating plate and the second rotating plate, one end of the pressure rod is connected to the first rotating plate, and the other end is used to transmit pressure to the transmission belt of the aircraft.

[0011] In one embodiment, the rotating plate includes a hinge portion and a limiting portion connected together. The hinge portion is hinged to the hinge plate and has an arc-shaped edge arranged along the rotational circumference. The limiting portion is formed by extending from the hinge portion in a preset direction and cooperates with the abutment plate to limit the lower limit of the working angle of the torsion spring.

[0012] This utility model embodiment also provides an aircraft, including a frame, a drive mechanism, a belt drive assembly, and a propeller. The drive mechanism is fixed to the frame and drives the propeller to rotate through the belt drive assembly. The aircraft also includes a belt pressure roller structure, which includes a fixed frame, an operating member, and a torsion spring. The fixed frame is used to fix the aircraft to the frame. The operating member is hinged to the fixed frame. The torsion spring is sandwiched between the fixed frame and the operating member and provides pressure to the operating member through elastic deformation. The operating member transmits the pressure to the transmission belt of the aircraft.

[0013] In one embodiment, the fixing frame and the machine frame are an integral structure.

[0014] Compared to related technologies, the belt pressure wheel structure provided in this embodiment of the utility model provides pressure to the operating member by clamping the torsion spring between the fixed frame and the operating member through elastic deformation. The operating member transmits the pressure to the transmission belt of the aircraft, thereby maintaining normal engagement between the transmission belt and the transmission wheel. This eliminates the need for frequent adjustment of the belt tension for the aircraft, making it convenient to use. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein:

[0016] Figure 1 A three-dimensional structural diagram of an aircraft provided for an embodiment of this utility model;

[0017] Figure 2 for Figure 1 A three-dimensional structural diagram of another configuration of the drive mechanism;

[0018] Figure 3 for Figure 1 A three-dimensional assembly diagram of the belt pressure roller structure shown;

[0019] Figure 4 for Figure 3 A three-dimensional structural diagram of another arrangement of the fixing bracket shown;

[0020] Figure 5 for Figure 3 An exploded three-dimensional structural diagram of the belt pressure roller structure shown.

[0021] Figure 6 for Figure 3 The cross-sectional view of the belt pressure roller structure shown;

[0022] Figure 7 for Figure 3 The cross-sectional view of the belt pressure roller structure shown from another direction. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0024] The terminology used in the embodiments of this utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. The singular forms "a" and "the" as used in the embodiments of this utility model and the appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise.

[0025] The terms "first" and "second" are used for descriptive purposes only to distinguish elements from one another, and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

[0026] Please see Figure 1 This is a three-dimensional structural diagram of an aircraft according to an embodiment of the present invention. The aircraft 10 includes a frame 11, a drive mechanism, a main shaft 13, a main rotor (not shown), a belt drive assembly 15, a tail rotor (not shown), and a belt pressure roller structure 17. The drive mechanism is fixed to the frame 11 and drives the main shaft 13 to rotate, thereby rotating the blades of the main rotor. The drive mechanism simultaneously drives the blades of the tail rotor to rotate via the belt drive assembly 15. The belt drive assembly 15 includes a drive pulley 151 and a drive belt 153. The belt pressure roller structure 17 applies pressure to the drive belt 153 to adjust the tension of the drive belt 153 and maintain the transmission efficiency of the drive pulley 151 and the drive belt 153.

[0027] It is understood that the drive mechanism can be a direct drive or a gear drive. See also... Figure 1 The diagram illustrates a gear-driven drive mechanism 12a, comprising a motor 121a, a first gear 123a, and a second gear 125a, which are sequentially driven. The second gear 125a is bearing-connected to the main shaft 13, driving the main shaft 13 to rotate, thereby rotating the main propeller. A transmission wheel 151 can be fixed to the main shaft 13 and / or the second gear 125a, and can be positioned above or below the second gear 125a. As long as the power from the motor 121a can be transmitted to the transmission wheel 151 to drive the tail propeller to rotate, the mechanism is sufficient.

[0028] It is also understood that in some embodiments, the drive mechanism drives the main propeller via a belt, and a belt pressure roller structure is set to apply pressure to the belt, so that the drive mechanism drives the blades of the main propeller to rotate normally.

[0029] Please see Figure 2 The diagram illustrates a direct-drive mechanism 12b, which includes a motor 121b. The output shaft of the motor 121b is connected to the main shaft 13, or the output shaft of the motor 121b and the main shaft 13 are integrally formed. The motor 121b drives the main shaft 13 to rotate, thereby rotating the main propeller. A transmission wheel 151 can be fixed to the housing of the main shaft 13 and / or the motor 121b, and can be positioned above or below the housing of the motor 121b. As long as the power from the motor 121b can be transmitted to the transmission wheel 151 to rotate the tail propeller, the desired effect is achieved.

[0030] Please see Figure 3 ,for Figure 1 The diagram shows a three-dimensional assembly of the belt pressure roller structure. The belt pressure roller structure 17 includes a fixed frame 171, an operating member 173, and a torsion spring 175. The fixed frame 171 is fixed to the frame 11. The middle part of the operating member 173 is hinged to the fixed frame 171. The torsion spring 175 is clamped between the fixed frame 171 and the first end of the operating member 173, providing pressure to the operating member 173 through elastic deformation. The second end of the operating member 173 transmits the pressure to the transmission belt 153, adjusting the tension of the transmission belt 153 to maintain normal engagement between the transmission belt 153 and the transmission pulley 151.

[0031] It is understood that the middle part of the operating member 173 is the middle part between the first end and the second end, and is not limited to the center of the operating member 173. The first end and the second end are the two sides of the middle part, and are not limited to the ends of the operating member 173. That is, the first end and the second end can be located on the two sides of the middle part.

[0032] The mounting bracket 171 includes a fixed plate 1711 and a hinge plate 1713 connected together. The fixed plate 1711 is fixed to the frame 11, and the hinge plate 1713 is hinged to the operating member 173. The hinge plate 1713 is formed by extending from the fixed plate 1711 in a direction away from the fixed plate 1711.

[0033] It is understood that the hinge plate 1713 and the fixing plate 1711 can be separate structures connected by a connecting mechanism, or they can be an integral structure; the fixing plate 1711 can also be an integral structure with the frame 11, or it can be the frame 11; the hinge plate 1713, the fixing plate 1711, and the frame 11 can be separate structures or an integral structure, such as... Figure 4 As shown.

[0034] Please see Figure 5 ,for Figure 3 The diagram shows an exploded three-dimensional view of the belt pressure roller structure. Specifically, the hinge plate 1713 can be hinged to the operating member 173 via a rotating shaft 177. In this embodiment, the fixing plate 1711 is C-shaped. The hinge plate 1713 includes a first hinge plate 17132 with a first through hole 17131 and a second hinge plate 17134 with a second through hole 17133. The first hinge plate 17132 and the second hinge plate 17134 are located at opposite ends of the C-shape. The first through hole 17131 and the second through hole 17133 are coaxial and spaced apart to allow the rotating shaft 177 to pass through. A bushing 178 is provided at the through hole.

[0035] It is understood that in some embodiments, the number of hinge plates may be one, three or more.

[0036] Please refer to the following: Figure 5 and Figure 6 ,in, Figure 6 for Figure 3 The diagram shows a cross-sectional view of the belt pressure roller structure. The operating component 173 includes an abutment plate 1731, a rotating plate 1733, and a pressure rod 1735 connected in sequence. A torsion spring 175 is clamped between the abutment plate 1731 and the fixed plate 1711, providing pressure to the abutment plate 1731 through elastic deformation. The rotating plate 1733 is hinged to the hinge plate 1713 and can rotate relative to the hinge plate 1713 under the pressure provided by the torsion spring 175, thereby rotating the pressure rod 1735 and transmitting pressure to the transmission belt 153.

[0037] It is understood that the transmission belt 153 simultaneously transmits pressure to the pressure rod 1735, and the transmission belt 153 and the torsion spring 175 maintain dynamic balance with the rotating shaft 177 as the fulcrum, thereby maintaining normal engagement between the transmission belt 153 and the transmission wheel 151.

[0038] The abutment plate 1731 includes a connecting part 17311 and an abutment part 17313 connected together, and the abutment part 17313 abuts against the torsion spring 175.

[0039] The rotating plate 1733 includes a hinge portion 1733a and a limiting portion 1733b connected together. The hinge portion 1733a is hinged to the hinge plate 1713 and has an arc-shaped edge arranged along the rotation circumference. The limiting portion 1733b is formed by extending the hinge portion 1733a in a preset direction and cooperates with the abutment plate 1731 to limit the lower limit of the working angle of the torsion spring 175.

[0040] Please see Figure 7 ,for Figure 3 The diagram shows a cross-sectional view of the belt pressure roller structure from another direction. Specifically, the rotating plate 1733 can be hinged to the hinge plate 1713 via the rotating shaft 177. In this embodiment, the rotating plate 1733 includes a first rotating plate 17331 and a second rotating plate 17332 arranged at relative intervals. The abutment plate 1731 connects between the first rotating plate 17331 and the second rotating plate 17332. One end of the pressure rod 1735 is connected to the first rotating plate 17331, and the other end transmits pressure to the transmission belt 153. The first rotating plate 17331 has a third through hole 17333, and the second rotating plate 17332 has a fourth through hole 17334. The first through hole 17131, the third through hole 17333, the fourth through hole 17334, and the second through hole 17133 are coaxially arranged so that the rotating shaft 177 passes through them sequentially. Bearings 176 are provided at the third through hole 17333 and the fourth through hole 17334.

[0041] It is understood that in some embodiments, the number of rotating plates may be one, three or more.

[0042] Please see again Figure 3 and Figure 4The pressure rod 1735 can be equipped with a pressure roller 179 at the end that transmits pressure to the transmission belt 153. Specifically, the pressure rod 1735 can be provided with a mounting hole to install the pressure roller 179. The wheel body 1791 of the pressure roller 179 is installed in the mounting hole through a bearing 1792 and a rotating shaft 1793. The wheel body 1791 of the pressure roller 179 abuts against the transmission belt 153, thereby reducing the impact on the normal transmission operation of the transmission belt 153 when the pressure roller 179 applies pressure to the transmission belt 153.

[0043] The torsion spring 175 includes a first protruding end 1751, a spring body 1753 and a second protruding end 1755 connected together. The first protruding end 1751 abuts against the fixed plate 1711, the spring body 1753 is hinged to the hinge plate 1713, and the second protruding end 1755 abuts against the abutting plate 1731.

[0044] In this embodiment, the first protruding end 1751 abuts against the fixing plate 1711, and the second protruding end 1755 abuts against the abutting plate 1731, thereby causing the torsion spring 175 to be clamped between the fixing frame 171 and the operating member 173. It is understood that in other embodiments, the first protruding end 1751 abuts against the frame 11, and the second protruding end 1755 abuts against the abutting plate 1731, which also allows the torsion spring 175 to be clamped between the fixing frame 171 and the operating member 173.

[0045] The torsion spring 175 described in this embodiment is clamped between the fixed frame 171 and the operating member 173. This includes the case where the first protruding end 1751 abuts against the fixed plate 1711, the case where the first protruding end 1751 abuts against the frame 11, and the case where the first protruding end 1751 abuts against the fixed plate 1711 and the frame 11. It is only necessary to provide a fulcrum for the first protruding end 1751 so that the second protruding end 1755 provides pressure to the abutting plate 1731.

[0046] It is understood that the transmission belt 153 transmits pressure to the pressure rod 1735, such that the angle between the first extended end 1751 and the second extended end 1755 is less than the free angle of the torsion spring 175. Preferably, the torsion spring 175 is a parallel double torsion spring, with two first extended ends 1751 and two spring bodies 1753, and the second extended end 1755 connects to the two spring bodies 1753.

[0047] Compared to related technologies, the belt pressure roller structure 17 provided in this embodiment of the utility model provides pressure to the operating member 173 by clamping the torsion spring 175 between the fixed frame 171 and the operating member 173 through elastic deformation. The operating member 173 transmits pressure to the transmission belt 153 of the aircraft 10, thereby maintaining the normal engagement between the transmission belt 153 and the transmission wheel 151. This eliminates the need for frequent belt tension adjustments for the aircraft 10, making it convenient to use.

Claims

1. A belt pressure roller structure, characterized in that, include: A mounting frame is used to secure an aircraft to its frame. The operating component is hinged to the fixed frame; A torsion spring, clamped between the fixed frame and the operating component, provides pressure to the operating component through elastic deformation, and the operating component transmits the pressure to the transmission belt of the aircraft.

2. The belt pressure roller structure as described in claim 1, characterized in that, The mounting frame includes a fixed plate and a hinge plate connected together, and the fixed plate is used to fix it to the frame of the aircraft.

3. The belt pressure roller structure as described in claim 2, characterized in that, The operating components include an abutment plate, a rotating plate, and a pressure rod connected in sequence. The rotating plate is hinged to the hinge plate, and the pressure rod is used to transmit pressure to the transmission belt of the aircraft.

4. The belt pressure roller structure as described in claim 3, characterized in that, The torsion spring includes a first extended end, a spring body, and a second extended end connected together. The first extended end abuts against the fixed plate, and the second extended end abuts against the abutting plate.

5. The belt pressure roller structure as described in claim 4, characterized in that, It also includes a pivot shaft that passes through the hinge plate, the rotating plate, and the spring body.

6. The belt pressure roller structure as described in claim 3, characterized in that, It also includes a pressure roller, which is mounted on the pressure rod and is used to press against the transmission belt of the aircraft.

7. The belt pressure roller structure as described in claim 3, characterized in that, The rotating plate includes a first rotating plate and a second rotating plate that are arranged at a relative interval. The abutment plate is connected between the first rotating plate and the second rotating plate. One end of the pressure rod is connected to the first rotating plate, and the other end is used to transmit pressure to the transmission belt of the aircraft.

8. The belt pressure roller structure as described in claim 3, characterized in that, The rotating plate includes a hinge portion and a limiting portion connected together. The hinge portion is hinged to the hinge plate and has an arc-shaped edge arranged along the rotation circumference. The limiting portion is formed by extending the hinge portion in a preset direction and cooperates with the abutment plate to limit the lower limit of the working angle of the torsion spring.

9. An aircraft, comprising a frame, a drive mechanism, a belt drive assembly, and propeller blades, wherein the drive mechanism is fixed to the frame and drives the propeller blades to rotate via the belt drive assembly, characterized in that, It also includes the belt pressure roller structure as described in any one of claims 1-8.

10. The aircraft as claimed in claim 9, characterized in that, The fixing frame and the machine frame are an integral structure.

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