Aircraft deployment guide rope pay-off trolley

Abstract

The utility model provides an aircraft exhibition and place guide rope's pay -off trolley belongs to electric power equipment technical field. The utility model discloses through being provided with the automatic closing subassembly in the upper portion opening one side of hanger, automatic closing subassembly has the hinged plate of self lockable and unlocking, and the middle part of one end extension to the top baffle of the counterweight of another end in upper portion opening is hinged on the hinged plate, make guide rope can depress the top baffle and extend to the one end in upper portion opening and open upper portion opening, and can realize the automatic reset of top baffle through counterweight to seal up the upper portion opening, and can remove top baffle from the upper portion opening through unlocking hinged plate, and the lead wire is removed, need not high -precision structure cooperation to realize the action, simple structure and reliable, and automatic closing subassembly and the hanger's hanger plate have no acting force connection, will not cause the influence to the stress structure of hanger, and the security guarantee nature is higher, and the operation is more convenient, is favorable to aircraft pay -off operation.

Description

Technical Field

[0001] This utility model relates to the field of power equipment technology, specifically to a line-laying pulley for deploying guide ropes for aircraft. Background Technology

[0002] Conventional overhead power line construction requires clearing a ground path along the transmission line towers. The guide rope needs to be manually laid out in sections along the line, then passed through the grooves of the laying pulleys on the towers and connected. This method is suitable for relatively flat land areas. However, for areas with complex terrain such as large rivers, mountain ravines, etc., this ground-based laying method becomes very difficult and inefficient. Therefore, the industry uses helicopters or other aircraft to lay a tensioned guide rope into a laying pulley suspended on each transmission tower. The guide rope is then converted into a traction rope, which is used to complete the tension-based overhead power line construction for the conductors or ground wires. This method is known in the industry as aircraft-based overhead power line laying and is particularly suitable for overhead power line laying in areas with complex terrain.

[0003] Currently, equipment used in the industry for aircraft cable laying includes cable laying trolleys, the structure of which is exemplified by a helicopter cable laying trolley disclosed in patent CN200820083176.8. This trolley includes a trolley frame, a connecting plate, and pulleys, with one end of the trolley frame open. The end of the connecting plate corresponding to the opening of the trolley frame is rotatably connected to one end of a hanging plate. Simultaneously, the other end of the hanging plate is rotatably connected to the rotation center of an eccentric wheel. Furthermore, the radial plane of the eccentric wheel has a deep groove and a shallow groove on its outer periphery. The middle of the hanging plate is rotatably connected to a lever at one end, and the lever at one end engages with the shallow groove on the radial plane of the eccentric wheel. This interlocking structure allows the guide rope to be transferred from outside the cable laying trolley into the trolley without manual intervention, eliminating the need for manual climbing onto each cable laying trolley to thread the guide rope. While the aforementioned helicopter-mounted cable-laying pulleys can meet the requirements for aerial cable laying, the eccentric wheel, a key component for guiding the cable into the pulley, and the lever of the trigger mechanism that actuates the eccentric wheel, require high precision and sensitive operation. In field operations, dust can easily enter these components, causing malfunctions and preventing the guide rope from fully entering the eccentric wheel from the outside. This necessitates manual intervention by operators climbing the tower. Furthermore, removing the cable from the pulley groove after laying it is extremely difficult, requiring multiple people to work together to open one side of the pulley frame. Simultaneously, it's crucial to prevent potential injuries to personnel and the cable caused by structural changes after the pulley frame is opened. Therefore, there is an urgent need to develop an aircraft-mounted cable-laying pulley that is reliable, easy to operate, and simple to maintain. Summary of the Invention

[0004] To address the aforementioned problems in existing technologies, this invention aims to provide a cable-laying trolley for aircraft deployment. A lockable and unlockable hinged plate is installed at the upper end of one side frame. A top stop and a guide rod are mounted on the hinged plate, with a counterweight on the top stop. When the guide rope needs to be introduced into the pulley assembly, it is first guided to the top stop by the guide rod, and then the top stop flips to enter the pulley assembly. The top stop automatically resets and closes under the action of the counterweight. When the cable needs to be removed, the hinged plate can be unlocked to displace the top stop and guide rod, facilitating cable removal. This design eliminates the need for high-precision components, is simple and reliable, avoids structural changes after unlocking, provides higher safety, and simplifies operation, thus benefiting aircraft cable deployment.

[0005] The specific technical solution is as follows: A guide rope deployment trolley for an aircraft, characterized by the following features: The hanger includes an inner cavity with an upper opening and a hanging plate on one side of the hanger; Pulley assembly, the pulley assembly is rotatably mounted in the inner cavity of the hanger; An automatic closing assembly is located at the upper opening of the inner cavity of the hanger. The automatic closing assembly includes a hinge plate, a top stop, a locking pin, and a connecting pin. The lower end of the hinge plate is hinged to the top of one side wall of the upper opening of the inner cavity of the hanger. A locking hole is provided in the middle of the hinge plate. A mating hole corresponding to the locking hole is provided on one side wall of the upper opening of the inner cavity of the hanger. The locking hole and the mating hole are locked together by a locking pin. The upper end of the hinge plate is hinged to the middle of the top stop through the connecting pin. One end of the top stop extends into the upper opening and selectively abuts against the other side of the upper opening. A counterweight is provided at the other end of the top stop.

[0006] The aforementioned aircraft deployment guide rope release trolley also includes a guide rod, one end of which is connected to a hinge plate. When the locking pin passes through the locking hole and the mating hole, the guide rod extends upwards and tilts away from the hanging plate.

[0007] The aforementioned aircraft deployment guide rope release trolley, wherein the guide rod and the hinge plate are hingedly connected, and a limit block is provided on the hinge plate, the limit block being located on the side of the hinge plate opposite to the upper opening.

[0008] The aforementioned aircraft deployment guide rope release trolley includes a gantry comprising a left side frame, a right side frame, a bottom beam, and a boom. The bottom beam is placed horizontally, and its two ends are fixedly connected to the bottom ends of the left side frame and the right side frame, respectively. One end of the boom is connected to the left side frame, and the other end of the boom extends toward the upper opening. Meanwhile, a suspension plate is set on the end of the boom that extends into the upper opening.

[0009] The aforementioned aircraft deployment guide rope release trolley further includes a left stop and a right stop, which are respectively located on both sides of the gantry, and the ends of the left and right stops opposite to the gantry extend to the two sides of the pulley of the pulley assembly.

[0010] The aforementioned aircraft deployment guide rope release trolley has an upper end of the left stop hinged to the boom, and the left stop swings along the direction of the guide rope.

[0011] The aforementioned aircraft deployment guide rope release trolley has a right stop lever rotatably mounted on the top of the right side frame, and the right stop lever swings along the direction of the guide rope.

[0012] The aforementioned aircraft deployment guide rope release trolley has a fixed block at the top of the right side frame, and the steering shaft of the right stop lever is inserted into the fixed block and keeps rotating.

[0013] The aforementioned aircraft deployment guide rope release trolley has an anti-loss hole at one end of the locking pin, a lifting hole on the hinge plate or suspender, and the two ends of a rope are respectively connected to the anti-loss hole and the lifting hole.

[0014] The positive effects of the above technical solution are: The aforementioned aircraft deployment guide rope release trolley features an automatic closing assembly on one side of the upper opening of the pylon. This assembly includes a lockable and unlockable hinged plate, which is hinged to the middle of a top stop. One end of the top stop extends into the upper opening and selectively abuts against the other end of the opening. A counterweight is located at the other end of the top stop. When the hinged plate is locked, the guide rope presses down on the end of the top stop extending into the upper opening, causing the top stop to deflect and open the upper opening, facilitating deployment. The guide rope enters, and after it does, the top stop automatically deflects and closes the upper opening under the action of the counterweight, preventing the guide rope and wire from coming out. In addition, the top stop can be removed from the upper opening by unlocking the hinge plate, which facilitates the removal of the wire. The structure is simple and easy to operate. Moreover, there is no high-precision structure to cooperate with the action, making the structure more reliable. At the same time, the automatic closing component does not contact the hanging plate of the gantry, and its action will not affect the change of the stress structure, thus ensuring higher safety and facilitating the deployment of the aircraft. Attached Figure Description

[0015] Figure 1 This is a structural diagram of an embodiment of a guide rope deployment trolley for an aircraft according to the present invention; Figure 2 This is a structural diagram of the hinged plate of a guide rope deployment trolley for an aircraft after the present invention has been unlocked. Figure 3This is a schematic diagram of the installation of the automatic closing assembly and right stop of the deployment trolley for deploying the guide rope of an aircraft according to the present invention.

[0016] In the attached diagram: 1. Hanger; 11. Hanging plate; 12. Left side frame; 13. Right side frame; 14. Bottom beam; 15. Boom; 131. Mating hole; 132. Fixing block; 2. Pulley assembly; 3. Automatic closing assembly; 31. Hinge plate; 32. Top stop bar; 33. Locking pin; 34. Connecting pin; 311. Locking hole; 321. Counterweight block; 4. Guide rod; 5. Left stop bar; 6. Right stop bar; 61. Steering shaft. Detailed Implementation

[0017] To make the technical means, creative features, objectives, and effects of this utility model easier to understand, the following embodiments are provided in conjunction with the appendix. Figure 1 To be continued Figure 3 The technical solution provided by this utility model is described in detail, but the following content is not intended to limit this utility model.

[0018] Figure 1 This is a structural diagram of an embodiment of a guide rope deployment trolley for an aircraft according to the present invention; Figure 2 This is a structural diagram of the hinged plate of a guide rope deployment trolley for an aircraft after the present invention has been unlocked. Figure 1 and Figure 2 As shown, the deployment trolley for the aircraft's guide rope provided in this embodiment includes: a gantry 1, a pulley assembly 2, an automatic closing assembly 3, and a guide rod 4.

[0019] Specifically, the suspender 1 has an inner cavity with an upper opening, which provides space for the installation and movement of the pulley assembly 2, and also provides conditions for the subsequent restraint of the guide rope and wire. Meanwhile, the upper opening of the inner cavity provides a passage for the guide rope to enter and the wire to exit. In addition, a hanging plate 11 is provided on one side of the suspender 1, which allows the wire-laying trolley to be suspended as a whole on the aircraft, meeting the requirements for in-flight wire laying.

[0020] Specifically, the pulley assembly 2 is rotatably installed in the inner cavity of the hanger 1. The pulley assembly 2 supports the guide rope and wire, reduces friction, facilitates wire laying, and also prevents wire wear, thus achieving safety protection. Preferably, the pulley assembly 2 includes a pulley and a rotating shaft. The two ends of the rotating shaft are respectively installed on the two side walls of the inner cavity of the hanger 1. The pulley is rotatably sleeved on the rotating shaft, which satisfies the rotatable installation of the pulley assembly 2 on the hanger 1.

[0021] Figure 3 This is a schematic diagram illustrating the installation of the automatic closing assembly and right stop lever of a guide rope deployment trolley for an aircraft according to this utility model. Figures 1 to 3As shown, the automatic closing component 3 is installed at the upper opening of the inner cavity of the hanger 1. The automatic closing component 3 enables the opening or closing of the upper opening of the inner cavity, which facilitates the entry of the guide rope and the removal of the wire. At the same time, it also ensures the closure of the upper opening during the wire laying process, thus ensuring normal wire laying operation. At this time, the automatic closing assembly 3 includes a hinge plate 31, a top stop bar 32, a locking pin 33, and a connecting pin 34. The lower end of the hinge plate 31 is hinged to the top of the side wall of the upper opening of the inner cavity of the hanger 1 by a pivot pin. A locking hole 311 is provided in the middle of the hinge plate 31. A mating hole 131 corresponding to the locking hole 311 is provided on the side wall of the upper opening of the inner cavity of the hanger 1. The locking hole 311 and the mating hole 131 can be locked by a locking pin 33. In the locked state, there are two spaced connection points between the hinge plate 31 and the hanger 1, so that the hinge plate 31 can maintain a stable state. In the unlocked state after the locking pin 33 is pulled out, only the lower end of the hinge plate 31 is hinged to the hanger 1, so that the hinge plate 31 can be flipped on the hanger 1, providing conditions for the subsequent removal of the wire. At this time, the upper end of the hinge plate 31 is hinged to the middle part of the top stop bar 32 by the connecting pin 34, allowing the top stop bar 32 to swing on the hinge plate 31. This provides conditions for the guide rope to press down on the top stop bar 32 and enter the hanger 1, and for the top stop bar 32 to automatically reverse and reset under the action of the counterweight 321. One end of the top stop bar 32 extends into the upper opening and selectively abuts against the other side of the upper opening. The other end of the top stop bar 32 is provided with a counterweight 321, so that in the natural state, the top stop bar 32, under the action of the counterweight 321, can abut against the other side of the upper opening, thereby locking the upper opening. When the guide rope needs to pass through the upper opening, the guide rope, under its own weight, presses down on the end of the top stop bar 32 located in the upper opening, causing the top stop bar 32 to overcome the gravity of the counterweight 321 and flip to open the upper opening, allowing the guide rope to pass through. The rope enters the inner cavity of the hanger 1 through the upper opening. After the guide rope passes through, the counterweight 321 presses down on the top stop 32, causing the top stop 32 to flip in the opposite direction and reset. The upper opening is sealed by one end of the top stop 32 abutting against the other end of the upper opening, achieving automatic closure. The structure is simple, requires no manual intervention, and is more convenient to use. It also does not require high-precision parts to cooperate with the action, making it more reliable. Furthermore, the automatic closing component 3 has no force connection with the hanging plate 11, so there will be no problem of changes in the overall force structure of the hanger 1 after unlocking, thus ensuring higher safety.

[0022] More specifically, a guide rod 4 is also connected to the hinge plate 31. At this time, the lower end of the guide rod 4 is connected to the hinge plate 31, and when the locking pin 33 passes through the locking hole 311 and the mating hole 131, the guide rod 4 extends upward towards the side away from the hanging plate 11. The guide rod 4 expands the edge of the upper opening, so that the guide rope contacts the guide rod 4 first, and moves to the upper opening through the guidance of the guide rod 4 to trigger the top stop bar 32, making it more convenient to use.

[0023] More specifically, the guide rod 4 is hinged to the hinge plate 31, allowing the position of the guide rod 4 on the hinge plate 31 to change. This ensures that when the hinge plate 31 is unlocked, the guide rod 4 can naturally droop under its own weight, avoiding the problem that the guide rod 4, when fixed to the hinge plate 31, would affect the flipping angle of the hinge plate 31 due to the end of the guide rod 4 abutting against the hanger 1 or pulley assembly 2. This ensures that after the hinge plate 31 is unlocked, the opening of the upper part can be larger, facilitating the removal of the wire. It is worth noting that a limiting block is provided on the hinge plate 31. The limiting block is located on the side of the hinge plate 31 away from the upper opening, so that when the hinge plate 31 is locked, the side of the guide rod 4 away from the upper opening can be held by the limiting block, thereby maintaining the guide rod 4 in an upward tilted state. After the hinge plate 31 is unlocked and flipped, the guide rod 4 hangs down under its own weight, causing the guide rod 4 to deflect towards the side away from the limiting block, and is no longer restricted by the limiting block. This allows the guide rod 4 and the hinge plate 31 to rotate naturally, thereby ensuring that the guide rod 4 does not affect the flipping of the hinge plate 31 when it hangs down naturally, so that the upper opening can be opened to the maximum extent, and the structural design is more reasonable.

[0024] More specifically, the main load-bearing structure, the hanger 1, includes a left side frame 12, a right side frame 13, a bottom beam 14, and a boom 15. The bottom beam 14 is placed horizontally, and its two ends are fixedly connected to the bottom ends of the left side frame 12 and the right side frame 13, respectively, forming an approximately "U"-shaped structure, thus creating an inner cavity with an upper opening. At this time, one end of the boom 15 is connected to the left side frame 12, and the other end of the boom 15 extends into the upper opening. Simultaneously, a hanging plate 11 is placed on the end of the boom 15 extending into the upper opening, ensuring that the hanging plate 11 is on the central axis of the hanger 1. This allows the hanging plate 11 to coincide with the center of gravity of the hanger 1 in the vertical direction, maintaining the stability of the hanger 1 in its suspended state. It is worth noting that the pulley assembly 2 is located between the left side frame 12 and the right side frame 13, and the two ends of the pulley assembly 2's rotating shaft are respectively installed on the left side frame 12 and the right side frame 13. Furthermore, the hinge plate 31 of the automatic closing assembly 3 is installed on the top of the right side frame 13, and one end of the top stop bar 32 extending into the upper opening selectively abuts against one end of the boom 15 extending into the upper opening, thereby reducing the total length of the top stop bar 32, saving materials, and lowering manufacturing costs. It is worth noting that the various structures of the hanger 1 are preferably welded connections, resulting in higher structural strength and stronger load-bearing capacity.

[0025] More specifically, the hanger 1 is also provided with a left stop bar 5 and a right stop bar 6 on both sides. Furthermore, the ends of the left stop bar 5 and the right stop bar 6 that are away from the hanger 1 extend to the two sides of the pulley of the pulley assembly 2, so that after the guide rope enters the inner cavity of the hanger 1, it can fall smoothly into the middle groove of the pulley of the pulley assembly 2 through the guiding action of the left stop bar 5 and the right stop bar 6. The structural design is more reasonable.

[0026] More specifically, the upper end of the left stop 5 is hinged to the boom 15, allowing the left stop 5 to swing relative to the hanger 1, facilitating the subsequent passage of the plank. Additionally, the left stop 5 is deflected along the direction of the guide rope, ensuring that the deflection direction is in the direction the plank passes. It is worth noting that the left stop 5 may be hinged to the boom 15 using a hinge pin, as long as the hinged installation requirements are met; the specific structure will not be elaborated upon here.

[0027] More specifically, the right stop lever 6 is rotatably mounted on the top of the right side frame 13, and the right stop lever 6 swings along the direction of the guide rope, so that the swing direction of the right stop lever 6 is the direction in which the walkway passes, facilitating the passage of the walkway. At this time, including but not limited to, a steering shaft 61 is installed at one end of the right stop lever 6, and the steering shaft 61 is rotatably mounted on the top of the right side frame 13 in the vertical direction to meet the swing requirements.

[0028] More specifically, a fixing block 132 is also provided on the top of the right side frame 13. Preferably, the fixing block 132 is bolted to the right side frame 13. The fixing block 132 strengthens the structural strength of the top of the right side frame 13 and provides a stable support. The steering shaft 61 of the right stop lever 6 is inserted into the fixing block 132 and keeps rotating, ensuring that the right stop lever 6 can maintain stability. It is worth noting that a rotating hole is opened on the fixing block 132 in the vertical direction. The lower end of the steering shaft 61 of the right stop lever 6 is inserted into the rotating hole and then protrudes. A retaining ring is provided on the protruding end of the steering shaft 61. The retaining ring forms a limiting structure at the end of the steering shaft 61, preventing the steering shaft 61 from accidentally falling off the fixing block 132. The structural design is more reasonable.

[0029] More specifically, an anti-loss hole is provided at one end of the locking pin 33, and a lifting hole is provided on the hinge plate 31 or the hanger 1. The two ends of a rope are connected to the anti-loss hole and the lifting hole respectively. That is, the locking pin 33 is connected to the hinge plate 31 or the hanger 1 through the rope, realizing the anti-loss design after the locking pin 33 is pulled out, and the structural design is more reasonable.

[0030] The aircraft deployment guide rope deployment trolley provided in this embodiment includes a gantry 1, a pulley assembly 2, and an automatic closing assembly 3. The pulley assembly 2 is installed in the inner cavity of the gantry 1 with an upper opening. Simultaneously, an automatic closing assembly 3 is provided on one side of the upper opening of the gantry 1. The automatic closing assembly 3 has a self-locking and self-unlocking hinge plate 31. A top stop bar 32, with one end extending into the upper opening and the other end having a counterweight 321, is hinged to the middle of the hinge plate 31. This allows the guide rope to press down on the top stop bar 32 when the hinge plate 31 is locked. The top stop bar 32 is automatically reset by the counterweight 321 after the guide rope passes through, thus sealing the top opening. The top stop bar 32 can be removed from the top opening by unlocking the hinge plate 31, which facilitates the removal of the wire. The action is simple and reliable without the need for a high-precision structure. Furthermore, the automatic closing component 3 is not forcefully connected to the hanging plate 11 of the gantry 1, so it will not affect the stress structure of the gantry 1. The safety is higher, the operation is more convenient, and it is beneficial for the aircraft to lay the wire.

[0031] The above are merely preferred embodiments of the present utility model and are not intended to limit the implementation methods and protection scope of the present utility model. Those skilled in the art should realize that any equivalent substitutions and obvious changes made based on the description and illustrations of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A release trolley for deploying a guide rope in an aircraft, characterized in that, include: A hanger, the hanger including an inner cavity with an upper opening, and a hanging plate provided on one side of the hanger; A pulley assembly, which is rotatably mounted in the inner cavity of the hanger; An automatic closing assembly is disposed at the upper opening of the inner cavity of the hanger. The automatic closing assembly includes a hinge plate, a top stop, a locking pin, and a connecting pin. The lower end of the hinge plate is hinged to the top of one side wall of the upper opening of the inner cavity of the hanger. A locking hole is provided in the middle of the hinge plate. A mating hole corresponding to the locking hole is provided on one side wall of the upper opening of the inner cavity of the hanger. The locking hole and the mating hole are locked together by a locking pin. The upper end of the hinge plate is hinged to the middle of the top stop through the connecting pin. One end of the top stop extends into the upper opening and selectively abuts against the other side of the upper opening. A counterweight is provided at the other end of the top stop.

2. The deployment pulley for the guidance rope of an aircraft according to claim 1, characterized in that, It also includes a guide rod, one end of which is connected to the hinge plate, and when the locking pin is inserted to lock the locking hole and the mating hole, the guide rod extends upward at an angle away from the hanging plate.

3. The deployment pulley for the guidance rope of an aircraft according to claim 2, characterized in that, The guide rod is hinged to the hinge plate, and a limit block is provided on the hinge plate. The limit block is located on the side of the hinge plate opposite to the upper opening.

4. The deployment pulley for the guidance rope of an aircraft according to claim 1, characterized in that, The hanger includes a left side frame, a right side frame, a bottom beam, and a boom. The bottom beam is placed horizontally, and its two ends are fixedly connected to the bottom ends of the left side frame and the right side frame, respectively. One end of the boom is connected to the left side frame, and the other end of the boom extends toward the upper opening. Meanwhile, the hanging plate is disposed on the end of the boom that extends into the upper opening.

5. The deployment pulley for the guidance rope of an aircraft according to claim 4, characterized in that, It also includes a left stop and a right stop, which are respectively disposed on both sides of the hanger, and the left stop and the right stop extend from the end connected to the hanger to the two sides of the pulley of the pulley assembly.

6. The deployment pulley for the guidance rope of an aircraft according to claim 5, characterized in that, The upper end of the left stop is hinged to the boom, and the left stop swings along the direction of the guide rope.

7. The deployment pulley for the guidance rope of an aircraft according to claim 5, characterized in that, The right stop lever is rotatably mounted on the top of the right side frame, and the right stop lever swings along the direction of the guide rope.

8. The deployment pulley for the guidance rope of an aircraft according to claim 7, characterized in that, A fixing block is provided on the top of the right side frame, and the steering shaft of the right stop lever is inserted into the fixing block and keeps rotating.

9. The deployment pulley for the guidance rope of an aircraft according to claim 1, characterized in that, One end of the locking pin is provided with an anti-loss hole, and the hinge plate or the hanger is provided with a lifting hole. The two ends of a rope are respectively connected to the anti-loss hole and the lifting hole.

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