Electromagnetic tensioning system suitable for piston engine aircraft transmission system

Abstract

The invention discloses an electromagnetic tensioning system suitable for a piston engine aircraft transmission system, and relates to the technical field of tensioning mechanisms, the electromagnetic tensioning system comprises a first fixing seat, a pressure sensor, an electromagnetic driving mechanism, a tensioning execution mechanism and a second fixing seat; the electromagnetic driving mechanism comprises an electromagnetic coil, an iron core, a telescopic guide cylinder and a telescopic guide cylinder fixing piece, the telescopic guide cylinder fixing piece is fixed to the first fixing base, the telescopic guide cylinder penetrates through the telescopic guide cylinder fixing piece and abuts against the pressure sensor, the pressure sensor is arranged between the telescopic guide cylinder and the first fixing base, and the iron core is fixed in the telescopic guide cylinder; the electromagnetic coil is sleeved on the iron core; the tensioning executing mechanism comprises an actuating sleeve and a permanent magnet armature, the actuating sleeve is arranged outside the telescopic guide cylinder in a sleeving mode and fixedly connected with the second fixing base, and the armature is fixed to the actuating sleeve and arranged opposite to the iron core. The system is high in response speed, can achieve the precise control of the tensioning force, better meets the space requirements of a helicopter transmission system, and is low in maintenance cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of tensioning mechanisms, in particular to an electromagnetic tensioning system suitable for a piston engine aircraft transmission system. BACKGROUND

[0002] Piston engines have become the core power solution for small and medium-sized unmanned helicopters and tiltrotors due to their low fuel consumption, high reliability and excellent adaptability to complex environments. However, piston engines have a key characteristic that they need to be completely disconnected from the load in the idle state, which requires the transmission system to have a reliable clutch function. Belt transmission can meet this core demand: during engine startup, the belt can remain relaxed, completely disconnecting the rotor from the engine and significantly reducing the load impact during startup. At the same time, by controlling the tensioning and relaxation of the belt, the power transmission can be flexibly disconnected or connected, easily achieving the disengagement effect. Therefore, in small and medium-sized unmanned helicopters and tiltrotors using piston engines, belt transmission has become the mainstream choice.

[0003] Currently, the clutch function of belt transmission is mainly achieved through a tensioning mechanism, and the mainstream solutions are divided into hydraulic and electric actuation types, but both have obvious shortcomings. The hydraulic tensioning mechanism is high in cost and complex in structure, requiring professional maintenance and strict requirements for the quality of hydraulic oil and system sealing, which increases the operating cost and failure risk of the equipment. The electric actuation type has a complex transmission chain, which relies on a mechanical self-locking structure. Long-term use or impact can easily cause the locking position to deviate. In addition, the multi-stage transmission design results in a slow response speed of the belt tension change, making it difficult to achieve timely and accurate adjustment in extreme working conditions. More notably, the internal space of the helicopter transmission system is extremely compact, with limited available installation space, which often poses a challenge for the placement of the above two types of tensioning mechanisms, further limiting their application effect in actual scenarios. SUMMARY

[0004] The purpose of the present application is to provide an electromagnetic tensioning system suitable for a piston engine aircraft transmission system to solve the problems of the prior art, with fast response speed, precise control of tensioning force, low requirement for installation space, good space demand for helicopter transmission system, and low maintenance cost.

[0005] To achieve the above purpose, the present application provides the following solutions: The present application provides an electromagnetic tensioning system suitable for a piston engine aircraft transmission system, comprising a first fixed seat, a pressure sensor, an electromagnetic driving mechanism, a tensioning execution mechanism and a second fixed seat. The first fixed seat is connected to a driven pulley support, and the second fixed seat is connected to a driving pulley support. The electromagnetic drive mechanism includes an electromagnetic coil, an iron core, a telescopic guide tube, and a telescopic guide tube fixing component. The telescopic guide tube fixing component is fixed to the first fixing base. One end of the telescopic guide tube passes through the telescopic guide tube fixing component and abuts against the pressure sensor. The pressure sensor is disposed between the telescopic guide tube and the first fixing base. The iron core is fixed inside the telescopic guide tube, and the electromagnetic coil is fixed inside the telescopic guide tube and sleeved on the iron core. The tensioning actuator includes an actuating sleeve and an armature. The armature is made of permanent magnet material. The actuating sleeve is sleeved on the other end of the telescopic guide tube and fixedly connected to the second fixed seat. The armature is fixed on the actuating sleeve and is arranged opposite to the iron core.

[0006] In one embodiment, the actuating sleeve is further provided with a return spring, which is located between the iron core and the armature, and the two ends of the return spring are respectively fixed to the actuating sleeve and the telescopic guide tube.

[0007] In one embodiment, the tensioning actuator further includes two anti-torsion plates. One end of the anti-torsion plate is fixedly connected to the actuating sleeve by a bolt, and the other end of the anti-torsion plate is fixedly connected to the telescopic guide tube fixing member by a bolt. The other ends of both anti-torsion plates are provided with bolt through holes. A long bolt passes through the two bolt through holes in sequence to connect the two anti-torsion plates. The anti-torsion plates can move axially relative to the long bolt. A limiting member is connected to the end of the long bolt opposite to its nut. The nut of the long bolt and the limiting member can limit the stroke of the two anti-torsion plates moving axially relative to each other. The long bolt and the two anti-torsion plates can prevent the actuating sleeve and the telescopic guide tube fixing member from twisting relative to each other.

[0008] In one embodiment, the system further includes a limiting mechanism and a controller. The limiting mechanism includes a micro switch and a traction rope. The micro switch, the pressure sensor, and the electromagnetic coil are all electrically connected to the controller. The micro switch is fixed to the telescopic guide tube fixing member. One end of the traction rope is connected to the micro switch, and the other end passes through a through hole on the actuating sleeve and is connected to the traction block. When the actuating sleeve moves relative to the telescopic guide tube to the tension limit position, the pressure value detected by the pressure sensor reaches a preset threshold, and the actuating sleeve pulls the traction rope through the traction block to trigger the micro switch. After receiving the detection signal from the pressure sensor and the trigger signal from the micro switch, the controller immediately cuts off the power supply to the electromagnetic coil.

[0009] In one embodiment, the first fixed seat is connected to the driven pulley support member via a spherical bearing, and the second fixed seat is connected to the driving pulley support member via a spherical bearing.

[0010] In one embodiment, the actuating sleeve and the telescopic guide tube are axially slidably connected via a slide rail structure.

[0011] In one embodiment, a positioning boss is fixedly provided on the actuating sleeve, and a limiting surface opposite to the positioning boss is provided on the telescopic guide tube fixing member. When the positioning boss and the limiting surface abut against each other, they are mutually axially limited.

[0012] In one embodiment, a pressure sensor housing is fixed on the first fixed base, and the pressure sensor is disposed inside the pressure sensor housing. The pressure sensor is pressed into the pressure sensor housing by the telescopic guide tube.

[0013] In one embodiment, the telescopic guide tube fixing member has a positioning pin groove at one end near the pressure sensor, and the telescopic guide tube has a positioning pin hole at one end near the pressure sensor. A positioning pin passes through the positioning pin hole and is disposed in the positioning pin groove. The positioning pin groove can limit the positioning pin in the circumferential direction of the telescopic guide tube to prevent the telescopic guide tube from rotating relative to the telescopic guide tube fixing member. The positioning pin groove can also limit the positioning pin in the axial direction of the telescopic guide tube to prevent the telescopic guide tube from moving away from the pressure sensor relative to the telescopic guide tube fixing member. The positioning pin groove also provides space for the positioning pin to move towards the pressure sensor along the axial direction of the telescopic guide tube.

[0014] The present invention achieves the following technical effects compared to the prior art: This invention provides an electromagnetic tensioning system suitable for piston engine aircraft transmission systems. Based on electromagnetic induction and force transmission, it utilizes the interaction between the electromagnetic force generated by electromagnetic components and the permanent magnet armature to directly drive the pulley, changing the belt tension. Simultaneously, a pressure sensor monitors the belt tension in real time, feeding feedback to the control system, which then adjusts the magnitude of the electromagnetic force to achieve precise tension control. This invention achieves dynamic adjustment of belt tension by driving the actuator with electromagnetic force, enabling precise control of the tension and ensuring the belt is always in optimal working condition. Due to the extremely fast generation and dissipation of electromagnetic force, the system has significant advantages in speed response and can better adapt to complex and changing environments. Compared to mechanical tensioning mechanisms, the electromagnetic tensioning mechanism mainly relies on the interaction between the electromagnetic components and the permanent magnet armature, reducing frequent mechanical friction, thereby reducing wear on mechanical components, extending the service life of the mechanism, and lowering maintenance costs. Furthermore, the electromagnetic tensioning mechanism has lower installation space requirements, better meeting the space requirements of helicopter transmission systems. Attached Figure Description

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

[0016] Figure 1 This is a schematic diagram of the installation and use of an electromagnetic tensioning system suitable for a piston engine aircraft transmission system in an embodiment of the present invention; Figure 2 This is a schematic diagram of the electromagnetic tensioning system applicable to the transmission system of a piston engine aircraft in an embodiment of the present invention; Figure 3 This is a front view of an electromagnetic tensioning system applicable to a piston engine aircraft transmission system according to an embodiment of the present invention; Figure 4 This is a cross-sectional view of an electromagnetic tensioning system applicable to a piston engine aircraft transmission system according to an embodiment of the present invention. Figure 5 This is an exploded structural diagram of the first fixed base, pressure sensor, telescopic guide tube, and telescopic guide tube fixing component in an embodiment of the present invention; Figure 6 This is an exploded cross-sectional view of the first fixed base, pressure sensor, telescopic guide tube, and telescopic guide tube fixing component in an embodiment of the present invention.

[0017] In the diagram: 1-First fixed seat, 2-Pressure sensor, 3-Second fixed seat, 4-Driven pulley support, 5-Driven pulley, 6-Driven pulley support, 7-Driven pulley, 8-Spherical bearing, 9-Electromagnetic coil, 10-Iron core, 11-Telescopic guide tube, 12-Telescopic guide tube fixing component, 13-Actuating sleeve, 14-Armature, 15-Reset spring, 16-Anti-torsion plate, 17-Micro switch, 18-Traction rope, 19-Pressure sensor housing, 20-Traction block, 21-Positioning pin groove, 22-Positioning pin hole, 23-Positioning pin, 24-Screw. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] The purpose of this invention is to provide an electromagnetic tensioning system suitable for piston engine aircraft transmission systems, in order to solve the problems existing in the prior art. It has a fast response speed, can achieve precise control of tension force, has low installation space requirements, can better meet the space requirements of helicopter transmission systems, and has low maintenance costs.

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] like Figures 1-6 As shown, this embodiment provides an electromagnetic tensioning system suitable for piston engine aircraft transmission systems, including a first fixed base 1, a pressure sensor 2, an electromagnetic drive mechanism, a tensioning actuator, and a second fixed base 3; The first fixed seat 1 is connected to the driven pulley support 4 via a spherical bearing 8. The driven pulley 5 is installed on the driven pulley support 4. The second fixed seat 3 is connected to the driving pulley support 6 via a spherical bearing 8. The driving pulley 7 is installed on the driving pulley support 6. The driven pulley 5 and the first fixed seat 1 can be installed on the wing spars for easy disassembly and belt replacement. The driving pulley support 6 is splined to engage with the engine output spline. The electromagnetic drive mechanism includes an electromagnetic coil 9, an iron core 10, a telescopic guide tube 11, and a telescopic guide tube fixing member 12. The telescopic guide tube fixing member 12 is fixed on the first fixing seat 1. One end of the telescopic guide tube 11 passes through the telescopic guide tube fixing member 12 and abuts against the pressure sensor 2. The pressure sensor 2 is disposed between the telescopic guide tube 11 and the first fixing seat 1. The iron core 10 is fixed inside the telescopic guide tube 11, and the electromagnetic coil 9 is fixed inside the telescopic guide tube 11 and sleeved on the iron core 10. The tensioning actuator includes an actuating sleeve 13 and an armature 14. The armature 14 is made of permanent magnet material. The actuating sleeve 13 is sleeved on the other end of the telescopic guide tube 11 and fixedly connected to the second fixed seat 3. The armature 14 is fixed on the actuating sleeve 13 and is arranged opposite to the iron core 10.

[0022] In this embodiment, when the electromagnetic coil 9 is energized, the iron core 10 is magnetized. The magnetized iron core 10 generates an axial repulsive force on the permanent magnet armature 14 in the tensioning actuator, which is the original power of the mechanism. This force is used to overcome the reaction force of the component to be tensioned and drive the subsequent actuating sleeve 13 to move. When a reverse current is applied to the electromagnetic coil 9, the magnetized iron core 10 generates an axial attraction force with the permanent magnet armature 14, which can assist the actuating sleeve 13 in resetting. The permanent magnet armature 14 can be configured with an upper N pole and a lower S pole, or an upper S pole and a lower N pole. The actuating sleeve 13 moves axially relative to the telescopic guide cylinder 11, thereby changing the center distance between the driving pulley 7 and the driven pulley 5, causing the belt to loosen and tighten, thus realizing the clutch function. The belt tension is monitored in real time by the pressure sensor 2 and fed back to the control system. The control system then adjusts the magnitude of the electromagnetic force to achieve precise control of the tension. By driving the actuator with electromagnetic force, the belt tension can be dynamically adjusted, enabling precise control of the tension and ensuring that the belt is always in the optimal working state. Due to the extremely rapid generation and dissipation of electromagnetic force, the system exhibits significant advantages in speed response, allowing it to better adapt to complex and changing environments. Compared to mechanical tensioning mechanisms, electromagnetic tensioning mechanisms primarily rely on the interaction between electromagnetic components and permanent magnet armatures during operation, reducing frequent mechanical friction and thus lowering wear on mechanical parts, extending the mechanism's service life, and reducing maintenance costs. Furthermore, electromagnetic tensioning mechanisms have lower installation space requirements, better meeting the spatial needs of helicopter transmission systems.

[0023] In this embodiment, a return spring 15 is also provided inside the actuating sleeve 13. The return spring 15 is located between the iron core 10 and the armature 14, and its two ends are fixed to the actuating sleeve 13 and the telescopic guide tube 11, respectively. The return spring 15 is initially in a non-stretched state. When the tensioning mechanism is tensioned, the return spring 15 is stretched. When the tensioning mechanism is reset, the return spring 15 provides a reset force to pull the actuating sleeve 13 back to its original position. At the same time, it can also pass a reverse current to the electromagnetic coil 9, so that an attraction force is generated between the iron core 10 and the armature 14, and this attraction force provides the reset force.

[0024] In this embodiment, the tensioning actuator also includes two anti-torsion plates 16. One end of one anti-torsion plate 16 is fixedly connected to the actuating sleeve 13 by bolts, and the other end of the other anti-torsion plate 16 is connected to the telescopic guide tube fixing member 12 by bolts. The other ends of both anti-torsion plates 16 are provided with bolt through holes. A long bolt passes through the two bolt through holes in sequence to connect the two anti-torsion plates 16. The anti-torsion plates 16 can move axially relative to the long bolt. A limiting member is connected to the end of the long bolt opposite to its nut. The nut and the limiting member of the long bolt can limit the stroke of the axial relative movement of the two anti-torsion plates 16, that is, limit the axial movement stroke of the actuating sleeve 13 relative to the telescopic guide tube 11. The long bolt and the two anti-torsion plates 16 can prevent the actuating sleeve 13 and the telescopic guide tube fixing member 12 from twisting relative to each other, ensuring that the two only move relative to each other in the axial direction.

[0025] In this embodiment, a limiting mechanism and a controller are also included. The limiting mechanism includes a micro switch 17 and a traction rope 18. The micro switch 17, pressure sensor 2, and electromagnetic coil 9 are all electrically connected to the controller. The micro switch 17 is fixed on the telescopic guide tube fixing member 12. One end of the traction rope 18 is connected to the micro switch 17, and the other end passes through the through hole on the actuating sleeve 13 and is connected to the traction block 20. When the actuating sleeve 13 moves relative to the telescopic guide tube 11 to the tension limit position, the pressure value detected by the pressure sensor 2 reaches the preset threshold, and the actuating sleeve 13 pulls the traction rope 18 through the traction block 20 to trigger the micro switch 17. After receiving the detection signal from the pressure sensor 2 and the trigger signal from the micro switch 17, the controller immediately cuts off the power supply to the electromagnetic coil 9, and the actuating sleeve 13 stops moving, thus avoiding damage to the components due to overtravel.

[0026] In this embodiment, the actuating sleeve 13 and the telescopic guide tube 11 are axially slidably connected through a slide rail structure to ensure the stability and accuracy of the axial movement of the actuating sleeve 13.

[0027] In this embodiment, a positioning boss is fixedly provided on the actuating sleeve 13, and a limiting surface opposite to the positioning boss is provided on the telescopic guide tube fixing member 12. When the positioning boss abuts against the limiting surface, the two are mutually axially limited. The state when the positioning boss abuts against the limiting surface can be taken as the initial state. When the actuating sleeve 13 is reset, the positioning boss abuts against the limiting surface, which can limit the further movement of the actuating sleeve 13 and ensure the accuracy of the reset.

[0028] In this embodiment, a pressure sensor housing 19 is fixed on the first fixed base 1. The pressure sensor housing 19 is fixed to the first fixed base 1 by screws 24. The pressure sensor 2 is disposed inside the pressure sensor housing 19 and between the telescopic guide tube 11 and the pressure sensor housing 19.

[0029] In this embodiment, the telescopic guide tube fixing member 12 is provided with a positioning pin groove 21 at one end near the pressure sensor 2, and the telescopic guide tube 11 is provided with a positioning pin hole 22 at one end near the pressure sensor 2. A positioning pin 23 passes through the positioning pin hole 22 and is disposed in the positioning pin groove 21. The positioning pin groove 21 can limit the positioning pin 23 in the circumferential direction of the telescopic guide tube 11 to prevent the telescopic guide tube 11 from rotating relative to the telescopic guide tube fixing member 12. The positioning pin groove 21 can also limit the positioning pin 23 in the axial direction of the telescopic guide tube 11 to prevent the telescopic guide tube 11 from moving away from the pressure sensor 2 relative to the telescopic guide tube fixing member 12. The positioning pin groove 21 also provides a movement space for the positioning pin 23 to move towards the pressure sensor 2 in the axial direction of the telescopic guide tube 11. Thus, the telescopic guide tube 11 can transmit force to the pressure sensor 2, and the pressure sensor 2 can detect the belt tension.

[0030] The electromagnetic tensioning system for piston engine aircraft transmission systems, as described in this embodiment, achieves belt tensioning based on the combination of electromagnetic induction drive and mechanical transmission. Its working principle revolves around "converting electromagnetic force into mechanical tension force," and the working process is as follows: 1. Power generation When the electromagnetic coil 9 is energized, a magnetic field is generated around the coil according to the law of electromagnetic induction, which magnetizes the coaxially arranged iron core 10. The magnetized iron core 10 will generate an axial repulsive force on the permanent magnet armature 14 in the tensioning actuator, which is the original power of the mechanism. It is used to overcome the reaction force of the component to be tensioned and drive the subsequent actuating sleeve 13 to move.

[0031] 2. Tighten execution The armature 14 and the actuating sleeve 13 are fixedly connected. Therefore, the movement of the armature 14 directly drives the actuating sleeve 13 to move along the axis of the telescopic guide cylinder 11 and achieves precise guidance by relying on the slide rail built into the actuating sleeve 13. At the same time, the anti-torsion plate 16 is connected by a long bolt to restrict the actuating sleeve 13 from twisting during movement, ensuring that it only moves axially. During the tensioning process, the value detected by the pressure sensor 2 is compared with the force required for belt tensioning. When the value measured by the pressure sensor 2 reaches the preset value required for belt tensioning, it is considered that the belt has reached the required tension state. When the electromagnetic tensioning mechanism moves to the preset value position, the telescopic guide cylinder 11 extends until its end abuts against the actuating sleeve 13. The telescopic guide cylinder 11 can adopt a conventional electrically driven telescopic structure, and the actuating sleeve 13 is maintained in the corresponding position by mechanical limiting to ensure that the tension force does not decrease. After the limiting operation is completed, the electromagnetic tensioning mechanism is energized; or, the current flowing through the electromagnetic coil 9 is kept constant to maintain the actuating sleeve 13 in the corresponding position to ensure that the tension force does not decrease.

[0032] Meanwhile, to enhance the safety of the mechanism, the electromagnetic tensioning mechanism features "limit protection" in its travel range. When the actuated sleeve 13 moves to its lower tension limit position due to tensioning requirements, it first triggers the pressure threshold of the pressure sensor 2 (at which point the sensor's monitored value reaches the preset threshold of the normal tension range). The pressure sensor 2 immediately reports an over-limit signal to the controller. Simultaneously, the extreme position movement of the actuated sleeve 13 pulls the traction rope 18, which in turn pulls the spring of the micro switch 17, triggering the micro switch 17 and sending a limit signal. Upon receiving the sensor over-limit signal and the micro switch trigger signal, the controller immediately cuts off the power to the electromagnetic coil 9, stopping the actuated sleeve 13 from continuing to move and preventing damage to components due to over-travel.

[0033] 3. Actuator reset When tension needs to be released, the controller supplies 0.5 times the rated reverse current to the electromagnetic coil 9, generating a reverse magnetic field in the iron core 10, which in turn generates a reverse axial force (attraction) on the permanent magnet armature 14, assisting in reset. Under the combined action of the attraction and the rebound force (tension) of the reset spring 15, the actuating sleeve 13 moves in the opposite direction along the axis of the telescopic guide tube 11, and the reset spring 15 gradually returns to its original length, with the spring force decreasing accordingly. When the actuating sleeve 13 returns to its initial position, the positioning boss at its end contacts the limiting surface of the telescopic guide tube fixing member 12, restricting further movement. When the pressure sensor 2 detects that the tension has dropped to the initial value, the mechanism completes the reset.

[0034] The electromagnetic tensioning system for piston engine aircraft transmission systems provided in this embodiment has the following advantages: First, the response speed is fast, which is attributed to the characteristic of "the generation and disappearance of electromagnetic force is extremely fast". The electromagnetic drive mechanism generates a magnetic field as soon as it is energized, magnetizes the iron core and generates an axial force between it and the permanent magnet armature. There is no need for a complex transmission chain to wait, and it can quickly respond to changes in the environment and working conditions to achieve timely tension adjustment.

[0035] Secondly, it has high control precision. It uses the magnetic force generated between the electromagnetic component and the permanent magnet armature to directly drive the pulley to move and change the belt tension. The belt tension is monitored in real time by the sensor, and the electromagnetic force can be precisely controlled. With the closed-loop feedback of the sensor, the tension can be precisely controlled to ensure the optimal working state of the belt.

[0036] Third, it boasts a long lifespan and low maintenance costs, based on the design principle that "the electromagnetic tensioning mechanism primarily relies on the interaction between the electromagnetic components and the permanent magnet armature during operation, reducing frequent mechanical friction." Compared to the complex mechanical structure of hydraulic systems and the mechanical self-locking and multi-stage transmission of electric actuators, electromagnetic action reduces mechanical losses, thereby extending lifespan and reducing maintenance.

[0037] Fourth, it has good spatial adaptability. Thanks to the electromagnetic tensioning mechanism being directly driven by electromagnetic force, the installation angle can be freely adjusted from 0° to 360° and has stable tension force. Moreover, the electromagnetic tensioning mechanism has no complex mechanical transmission structure inside, making the overall structure more compact and occupying less space. It can be adapted to the limited space of aircraft transmission systems and solve the layout problems of existing tensioning mechanisms.

[0038] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. An electromagnetic tensioning system suitable for piston engine aircraft transmission systems, characterized in that: It includes a first fixed base, a pressure sensor, an electromagnetic drive mechanism, a tensioning actuator, and a second fixed base; The first fixed base is connected to the driven pulley support, and the second fixed base is connected to the driving pulley support; The electromagnetic drive mechanism includes an electromagnetic coil, an iron core, a telescopic guide tube, and a telescopic guide tube fixing component. The telescopic guide tube fixing component is fixed to the first fixing base. One end of the telescopic guide tube passes through the telescopic guide tube fixing component and abuts against the pressure sensor. The pressure sensor is disposed between the telescopic guide tube and the first fixing base. The iron core is fixed inside the telescopic guide tube, and the electromagnetic coil is fixed inside the telescopic guide tube and sleeved on the iron core. The tensioning actuator includes an actuating sleeve and an armature. The armature is made of permanent magnet material. The actuating sleeve is sleeved on the other end of the telescopic guide tube and fixedly connected to the second fixed seat. The armature is fixed on the actuating sleeve and is arranged opposite to the iron core.

2. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: The actuating sleeve is also provided with a return spring, which is located between the iron core and the armature. The two ends of the return spring are respectively fixed to the actuating sleeve and the telescopic guide tube.

3. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: The tensioning actuator also includes two anti-torsion plates. One end of the anti-torsion plate is fixedly connected to the actuating sleeve by a bolt, and the other end of the anti-torsion plate is fixedly connected to the telescopic guide tube fixing component by a bolt. The other ends of both anti-torsion plates are provided with bolt through holes. A long bolt passes through the two bolt through holes in sequence to connect the two anti-torsion plates. The anti-torsion plates can move axially relative to the long bolt. A limiter is connected to the end of the long bolt opposite to its nut. The nut of the long bolt and the limiter can limit the stroke of the two anti-torsion plates moving axially relative to each other. The long bolt and the two anti-torsion plates can prevent the actuating sleeve and the telescopic guide tube fixing component from twisting relative to each other.

4. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: It also includes a limiting mechanism and a controller. The limiting mechanism includes a micro switch and a traction rope. The micro switch, the pressure sensor, and the electromagnetic coil are all electrically connected to the controller. The micro switch is fixed to the telescopic guide tube fixing component. One end of the traction rope is connected to the micro switch, and the other end passes through a through hole on the actuating sleeve and is connected to the traction block. When the actuating sleeve moves relative to the telescopic guide tube to the tension limit position, the pressure value detected by the pressure sensor reaches a preset threshold, and the actuating sleeve pulls the traction rope through the traction block to trigger the micro switch. After receiving the detection signal from the pressure sensor and the trigger signal from the micro switch, the controller immediately cuts off the power supply to the electromagnetic coil.

5. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: The first fixed seat is connected to the driven pulley support member via a spherical bearing, and the second fixed seat is connected to the driving pulley support member via a spherical bearing.

6. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: The actuating sleeve and the telescopic guide tube are axially slidably connected via a slide rail structure.

7. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: The actuating sleeve is fixedly provided with a positioning boss, and the telescopic guide tube fixing component is provided with a limiting surface opposite to the positioning boss. When the positioning boss and the limiting surface abut against each other, the two are mutually axially limited.

8. The electromagnetic tensioning system for piston engine aircraft transmission systems according to claim 1, characterized in that: A pressure sensor housing is fixed on the first mounting base, and the pressure sensor is disposed inside the pressure sensor housing.

9. The method for use in piston engine aircraft according to claim 1 The electromagnetic tensioning system of the transmission system is characterized by: The telescopic guide tube fixing component has a positioning pin groove at one end near the pressure sensor, and a positioning pin hole at the other end of the telescopic guide tube near the pressure sensor. A positioning pin passes through the positioning pin hole and is positioned in the positioning pin groove. The positioning pin groove can limit the positioning pin in the circumferential direction of the telescopic guide tube to prevent the telescopic guide tube from rotating relative to the telescopic guide tube fixing component. The positioning pin groove can also limit the positioning pin in the axial direction of the telescopic guide tube to prevent the telescopic guide tube from moving away from the pressure sensor relative to the telescopic guide tube fixing component. The positioning pin groove also provides space for the positioning pin to move towards the pressure sensor along the axial direction of the telescopic guide tube.

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