Launch pad tensioning and locking device and loading system

Abstract

The utility model discloses a launching pad pull locking device and loading system, including fixed launching pad and a plurality of pull locking devices, and pull locking device includes bearing mechanism, transmission mechanism and locking mechanism, and bearing mechanism includes pull hinged seat, pull pin and pull support seat, and transmission mechanism includes slewing bearing seat, pull rotation cover and nut rotation subassembly, and locking mechanism includes locking nut and locking pin, and bearing mechanism is used for transmitting the pull force of steel wire rope to pull pin, and transmission mechanism is used for transmitting the rotary power to locking nut, and locking mechanism is used for realizing mechanical locking. Through above -mentioned mode, the utility model discloses can adapt heavy load rocket, and the problem of uneven stress of each bearing point is effectively solved, and double locking avoids the rocket body to fall back when breaking down, and the modularization setting is more convenient to dismount.

Description

Technical Field

[0001] This utility model relates to the field of rocket launch technology, and in particular to a launch pad traction locking device and loading system. Background Technology

[0002] In the field of space launch, fixed launch pads are responsible for tasks such as rocket ignition tests and launch preparations. Precise load traction and reliable locking between the launch pad and the rocket core stage or booster are key to ensuring test safety and launch stability.

[0003] As my country's carrier rockets develop towards greater thrust, heavier weight, and modularity: the first-stage test rocket uses 7 engines, and the thrust generated by a single ignition test is close to 1,000 tons; after being combined and bundled with 3 universal core stage modules, its takeoff thrust can exceed 2,700 tons.

[0004] However, most of the traction and locking devices on mainstream launch pads at home and abroad currently use bolted connections. The load transfer path and load-bearing capacity of this type of device are fixed, making it difficult to adapt to the launch requirements of heavy-lift rockets.

[0005] At the same time, this type of traction locking device lacks dynamic load adjustment, which can easily lead to uneven stress on each load point during actual operation; in case of emergencies, it lacks emergency locking protection, and once a malfunction occurs and the locking fails, the rocket is at risk of falling back.

[0006] In addition, the components of the existing traction locking device are scattered and have a low degree of integration. When repairing or replacing it, a large number of components need to be disassembled one by one, which is cumbersome and time-consuming.

[0007] Based on the above problems, there is an urgent need to provide a launch pad traction and locking device that can adapt to high thrust and heavy load conditions and has dynamic load adjustment and emergency locking capabilities to meet the launch requirements of heavy rockets. Utility Model Content

[0008] The main technical problem solved by this utility model is to provide a launch pad traction locking device and loading system, with a single unit traction force exceeding 300t, which can be adapted to heavy-lift rockets; the deviation of multiple units coordinating loading is controlled within 1t, effectively solving the problem of uneven force on each load point; the double locking prevents the rocket body from falling back in case of failure; the modular design makes disassembly and assembly more convenient, and it can adapt to various scenarios such as test firing, traction, and emergency response.

[0009] To solve the above-mentioned technical problems, the present invention provides a launch pad traction locking device, comprising:

[0010] The load-bearing mechanism includes a traction hinge seat, a traction pin, and a traction support seat: the traction support seat is sleeved on the traction pin, the upper end of the traction pin is fixedly connected to the traction hinge seat, and the lower end of the traction pin passes through the central through hole of the traction support seat and is connected to the traction cylinder;

[0011] The transmission mechanism is located below the bearing mechanism and connected to the traction support seat. It includes a slewing bearing seat, a traction rotating sleeve, and a nut rotating assembly. The slewing bearing seat includes an inner ring and an outer ring. The inner ring is fixedly connected to the lower end of the traction support seat, and the outer ring is fixedly connected to the lower traction rotating sleeve. The nut rotating assembly is installed on one side of the outer ring of the traction support seat and is used to drive the outer ring of the slewing bearing seat to rotate.

[0012] The locking mechanism includes a locking nut and a locking pin; the locking nut is located between the pulling pin and the pulling rotating sleeve, and is threaded onto the pulling pin; one end of the locking pin is fixedly connected to the locking nut, and the other end is movably connected to the pulling rotating sleeve.

[0013] A hydraulic cylinder for pulling, including a piston rod, wherein the piston rod is fixedly connected to the lower end of the pulling pin.

[0014] In a preferred embodiment of the present invention, the nut rotating assembly includes a mounting base, a rotary gear, a connecting flange, and a motor. The mounting base is connected to a tension support base. The rotary gear is rotatably mounted on the mounting base. The motor is connected to the mounting base via the connecting flange, and the output shaft of the motor is drivenly connected to the rotary gear. The rotary gear is drivenly connected to the outer ring of the rotary support base.

[0015] In a preferred embodiment of the present invention, the outer ring of the slewing bearing is provided with a toothed ring, and the slewing gear meshes with the toothed ring.

[0016] In a preferred embodiment of the present invention, the outer peripheral wall of the traction rotating sleeve is provided with a long sliding groove along its axial direction, and the other end of the locking pin extends into the long sliding groove and can be displaced along the extension direction of the long sliding groove.

[0017] In a preferred embodiment of this utility model, there are two long sliding grooves, which are symmetrically arranged along the circumference of the traction rotating sleeve.

[0018] In a preferred embodiment of this utility model, the outer periphery of the pull pin is provided with a threaded section, the locking nut is sleeved on the threaded section and can move on the pull pin, and the movement stroke of the locking nut on the pull pin is ≥100mm.

[0019] In a preferred embodiment of this utility model, proximity switches for detecting the position of the locking nut are provided on the lower end face of the traction support seat and on the outer periphery of the piston rod end near the connection with the traction pin.

[0020] In a preferred embodiment of the present invention, the traction support seat is provided with a limiting step, and the traction pin is provided with a limiting protrusion corresponding to the limiting step. The limiting step and the limiting protrusion axially block each other to restrict the axial movement of the traction pin.

[0021] In a preferred embodiment of this utility model, a force sensor and a pressure sensor are also included. A steel wire rope is connected to the top of the traction hinge seat. The force sensor is installed between the steel wire rope and the traction hinge seat. The pressure sensor is installed in the rodless chamber oil circuit of the traction cylinder. The force sensor and the pressure sensor form a dual redundant load detection.

[0022] In a preferred embodiment of the present invention, a hydraulic control valve assembly is further included. The hydraulic control valve assembly includes a proportional directional valve, a balance valve, and a sequence valve. The proportional directional valve is located on the oil supply line of the traction cylinder, the balance valve is located at the rodless chamber oil port of the traction cylinder, and the sequence valve is located on the oil supply valve assembly of the motor.

[0023] In a preferred embodiment of the present invention, the proportional directional valve is electrically connected to a force sensor and a pressure sensor to perform closed-loop control of the traction cylinder based on the feedback signal of at least one of the force sensor and the pressure sensor.

[0024] To solve the above-mentioned technical problems, this utility model also provides a loading system, including a fixed launch platform and a plurality of launch platform pulling and locking devices symmetrically installed at the bottom of the fixed launch platform and evenly distributed around the rocket body, wherein the launch platform pulling and locking device is the launch platform pulling and locking device described above.

[0025] The beneficial effects of this utility model are:

[0026] Each traction and locking device has a traction force exceeding 300t, making it suitable for heavy-lift rockets. Each device is independently equipped with a proportional reversing valve, and multiple devices are synchronously loaded through closed-loop control using force sensors. The deviation between devices and the loading accuracy are controlled within 1t, effectively solving the problem of uneven force distribution at various load-bearing points. It adopts a double locking mechanism, so even if the hydraulic system is completely depressurized or the motor fails, the threaded self-locking mechanism can still maintain the locked state, preventing the rocket body from falling back unexpectedly. The whole system adopts a modular integrated structure and is connected to the launch pad by bolts, which greatly improves the efficiency of disassembly, assembly, and maintenance, and can adapt to various usage scenarios such as static testing, launch restraint, and emergency locking. Attached Figure Description

[0027] 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:

[0028] Figure 1 This is a schematic diagram of a preferred embodiment of the fixed launch platform of this utility model;

[0029] Figure 2 This is a schematic diagram of a preferred embodiment of the launch pad traction locking device of this utility model;

[0030] Figure 3 This is a cross-sectional view of a preferred embodiment of the launch pad traction locking device of this utility model;

[0031] Figure 4 yes Figure 3 A magnified view of a section at point A in the middle;

[0032] Figure 5 This is a schematic diagram of a preferred embodiment of the slewing bearing seat of this utility model;

[0033] Figure 6 This is a schematic diagram of a preferred embodiment of the nut rotating assembly of this utility model;

[0034] Figure 7 This is a schematic diagram of the launch pad traction locking device of this utility model in the locked state;

[0035] Figure 8 This is a structural schematic diagram of the launch pad traction locking device of this utility model in the unlocked state;

[0036] The components in the attached diagram are labeled as follows:

[0037] 100. Fixed launch platform; 200. Pull-locking device.

[0038] 210. Bearing mechanism; 211. Tension hinge seat; 212. Tension pin; 2121. Limiting protrusion; 213. Tension support seat; 2131. Limiting step.

[0039] 220. Transmission mechanism; 221. Slewing bearing seat; 2211. Inner ring; 2212. Outer ring; 2213. Gear ring; 222. Pulling slewing sleeve; 2221. Long slide groove; 223. Nut rotating assembly; 2231. Mounting base; 2232. Slewing gear; 2233. Connecting flange; 2234. Motor.

[0040] 230. Locking mechanism; 231. Locking nut; 232. Locking pin.

[0041] 240. Pulling cylinder; 241. Piston rod. Detailed Implementation

[0042] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0043] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0044] like Figure 1 As shown, this utility model provides a launch pad traction locking device, which is applied to a rocket loading system. The loading system includes a fixed launch pad 100 and a plurality of traction locking devices 200 symmetrically installed at the bottom of the fixed launch pad 100 and evenly distributed around the rocket body.

[0045] In one exemplary embodiment, four tension locking devices 200 are evenly distributed circumferentially along the fixed launch platform 100, symmetrically arranged in pairs to ensure uniform and stable loading of the rocket body. Each tension locking device 200 is rigidly connected to the base of the fixed launch platform 100 by bolts, forming a stable load-bearing foundation.

[0046] Each traction locking device 200 is arranged vertically and includes, from top to bottom, a bearing mechanism 210, a transmission mechanism 220, a locking mechanism 230, and a traction cylinder 240. The mechanisms are connected by detachable standard interfaces, which facilitates quick disassembly and maintenance.

[0047] The bearing mechanism 210 is used to transmit the tension of the wire rope to the pulling pin 212, the transmission mechanism 220 is used to transmit the rotational power to the locking nut 231, and the locking mechanism 230 is used to achieve mechanical locking. The maximum pulling force of the pulling and locking device of this utility model can reach more than 300t, which can be adapted to heavy launch vehicles with a takeoff mass of more than 2,000 tons and meet the pulling requirements of high thrust rockets.

[0048] The following combination Figure 2-6 The specific structure of each institution is explained in detail.

[0049] First is the load-bearing mechanism 210, which includes a tension hinge seat 211, a tension pin 212, and a tension support seat 213.

[0050] The traction hinge seat 211 is located at the very top of the entire traction locking device 200. The top of the traction hinge seat 211 is pinned to the wire rope, and the other end of the wire rope is connected to the arrow body, used to transmit external traction load to the traction locking device 200. Preferably, the traction hinge seat 211 is configured to withstand a traction force of not less than 300t.

[0051] The flexible connection of the wire rope is hinged with the tension hinge seat 211, which can withstand a load deflection angle of 0~20°. Even when the rocket body attitude deviates slightly at the moment of ignition, it can still maintain effective tension and avoid jamming failure caused by rigid connection.

[0052] The traction support 213 is sleeved on the traction pin 212. The traction hinge 211 is detachably and fixedly connected to the upper end of the traction pin 212 by multiple bolts. The lower end of the traction pin 212 vertically penetrates the central through hole of the traction support 213 and can slide freely along the axial direction of the central through hole. The outer periphery of the portion of the traction pin 212 extending out of the central through hole of the traction support 213 is provided with a threaded section. The lower end of the traction pin 212 is detachably and fixedly connected to the end of the piston rod 241 of the traction cylinder 240 by bolts.

[0053] Furthermore, the traction support 213 is provided with a limiting step 2131, and the traction pin 212 is provided with a corresponding limiting protrusion 2121. In this embodiment, the limiting step 2131 and the limiting protrusion 2121 are provided at the upper end surfaces of the traction support 213 and the traction pin 212. The limiting step 2131 and the limiting protrusion 2121 form a mutual blocking engagement in the axial direction to restrict the axial movement of the traction pin 212.

[0054] The traction support 213 is the intermediate load-bearing body of the entire traction locking device 200. The traction support 213 is connected to the fixed launch platform 100 by bolts. The lower end of the traction support 213 is fixedly connected to the slewing bearing 221, serving as the installation base for the transmission mechanism 220.

[0055] Secondly, there is a transmission mechanism 220, which includes a slewing bearing seat 221, a traction rotating sleeve 222, and a nut rotating assembly 223.

[0056] The slewing bearing 221 includes an inner ring 2211 and an outer ring 2212, which are connected by a bearing. The inner ring 2211 of the slewing bearing 221 is detachably and fixedly connected to the lower end of the tension support 213 by bolts, forming an installation base. The outer ring 2212 of the slewing bearing 221 has a toothed ring 2213 on its edge, and the tension rotating sleeve 222 is detachably and fixedly connected to the outer ring 2212 of the slewing bearing 221 by bolts, rotating together with the outer ring 2212.

[0057] Furthermore, there is a locking mechanism 230, which includes a locking nut 231 and a locking pin 232.

[0058] The locking nut 231 is located between the pulling pin 212 and the pulling rotating sleeve 222, and is threaded onto the threaded section of the pulling pin 212. One end of the locking pin 232 is fixedly connected to the locking nut 231, and the other end is movably connected to the pulling rotating sleeve 222.

[0059] Furthermore, the side wall of the pulling rotating sleeve 222 is provided with a long sliding groove 2221 along its axial direction, and the other end of the locking pin 232 extends into the long sliding groove 2221 and can be displaced along the extension direction of the long sliding groove 2221.

[0060] When the pulling rotating sleeve 222 rotates, the other end of the locking pin 232 is limited in the long slide groove 2221. The locking pin 232 rotates synchronously with the pulling rotating sleeve 222 and drives the locking nut 231 to rotate accordingly, so that the locking nut 231 moves axially along the threaded section of the pulling pin 212, and the locking pin 232 moves linearly along the long slide groove 2221 to compensate for axial displacement.

[0061] In this embodiment, the sliding stroke of the locking nut along the long slide groove 2221 is ≥100mm, that is, the locking stroke of the locking nut 231 along the threaded section of the pull pin 212 is not less than 100mm, ensuring the reliable and stable locking action.

[0062] The nut rotating assembly 223 is installed on one side of the outer ring of the tension support 213 and is used to drive the outer ring 2212 of the slewing bearing 221 to rotate.

[0063] Specifically, the nut rotating assembly 223 includes a mounting base 2231, a rotary gear 2232, a connecting flange 2233, and a motor 2234. The mounting base 2231 is connected to the tension support 213. The rotary gear 2232 is rotatably mounted on the mounting base 2231. The motor 2234 is connected to the mounting base 2231 via the connecting flange 2233, and the output shaft of the motor 2234 is driven by the rotary gear 2232. The rotary gear 2232 meshes with the gear ring 2213 of the rotary support 221.

[0064] In this embodiment, the motor 2234 is preferably a hydraulic motor, powered by a hydraulic power station. When the motor 2234 rotates, its output shaft drives the rotary gear 2232 to rotate. The rotary gear 2232 drives the outer ring 2212 of the slewing bearing 221 to rotate via the gear ring 2213, which in turn drives the pulling rotating sleeve 222 mounted on the outer ring 2212 to rotate. The pulling rotating sleeve 222 drives the locking nut 231 to rotate through the engagement of the long sliding groove 2221 and the locking pin 232.

[0065] Based on the above structure, the traction cylinder 240 is vertically mounted at the bottom of the entire traction locking device 200 to provide traction force. Its piston rod 241 is connected upward to the lower end of the traction pin 212, and the bottom of the cylinder body of the traction cylinder 240 is fixedly connected to the bottom of the fixed launch platform 100 by bolts. In this embodiment, the end of the piston rod 241 of the traction cylinder 240 is detachably fixedly connected to the traction pin 212 by bolts.

[0066] In this embodiment, the motor 2234 is equipped with a mechanical brake. In the locked state, the locking nut 231 and the pull pin 212 are held in the locked position by the self-locking of the threaded pair, and the locking nut 231 and the pull support seat 213 are in contact to form a first layer of locking. At the same time, the mechanical brake brakes the output shaft of the motor, forming a second layer of locking. The locking stroke of the locking nut 231 on the pull pin 212 is not less than 100mm, and the braking torque reaches 2200N·m, which can reserve sufficient safety margin. When the system loses power or the hydraulic power is interrupted, the mechanical brake automatically brakes to ensure the reliability of the locked state.

[0067] With the above-mentioned double locking structure, even if the hydraulic system is completely depressurized or the motor fails, the locking state can still be maintained by the self-locking action of the threaded pair between the locking nut 231 and the pulling pin 212, effectively preventing the rocket body from falling back.

[0068] This utility model also includes a hydraulic control valve assembly, which is integrated into an explosion-proof control box. The explosion-proof control box is installed on the base of the fixed launch pad 100 to meet the explosion-proof safety requirements of the launch site.

[0069] The hydraulic control valve assembly includes a proportional directional valve, a balance valve, and a sequence valve, wherein the balance valve is installed on the cylinder body of the traction cylinder 240. The proportional directional valve is located on the oil supply line of the traction cylinder 240 and is used to regulate the flow and direction of the hydraulic oil entering the traction cylinder 240. The balance valve is located at the oil port of the rodless chamber of the traction cylinder 240 and is used to lock the oil in the rodless chamber of the traction cylinder 240 in the locked state to prevent the traction pin 212 from extending or retracting under external load. The sequence valve is located on the oil supply valve assembly of the motor 2234 and is used to distinguish the working circuit pressure in the unlocked state and the loaded state to prevent pressure misjudgment.

[0070] Each valve assembly is connected to the corresponding actuator via hydraulic lines. The hydraulic lines and valve assemblies are connected via quick-connect plugs, facilitating quick installation and disassembly on site.

[0071] This utility model also includes a force sensor, a pressure sensor, and a proximity switch. The force sensor is installed between the wire rope and the tension hinge seat 211 to directly collect the actual tension of the wire rope; the pressure sensor is installed in the rodless chamber oil circuit of the tension cylinder 240 to collect the working pressure of the tension cylinder 240.

[0072] In this embodiment, the force sensor and pressure sensor work together to monitor the load, forming a dual redundancy for overload protection. When either sensor fails, the data source can be automatically switched, eliminating the risk of downtime.

[0073] Two proximity switches are provided. One is located on the lower end face of the traction support 213 to determine whether the locking nut 231 is in the locked state. The other is located on the outer periphery of the piston rod 241 end, near the connection between the piston rod 241 and the traction pin 212, to determine whether the locking nut 231 is in the unlocked state.

[0074] When the proximity switch detects that the locking nut 231 has moved to the position where it is in contact with the lower end face of the traction support 213, it is determined that the locking nut 231 is in the locked position; when the proximity switch detects that the locking nut 231 has moved to the end of the traction pin 212 near the traction cylinder 240, it is determined that the locking nut 231 is in the unlocked position.

[0075] The proportional directional valve is electrically connected to the force sensor and the pressure sensor, and performs closed-loop control of the traction cylinder 240 based on the feedback signals from both sensors to adjust the traction force of the traction pin 212.

[0076] By using a proportional directional valve and a closed-loop feedback mechanism with force sensors, multiple devices can be loaded in a coordinated manner. The loading deviation between each device does not exceed 1 t, and the loading accuracy is controlled within 1 t, achieving high-precision synchronous control and solving the problem of uneven force distribution at the load-bearing points in existing solutions.

[0077] The working principle of the launch pad tensioning and locking device and loading system of this utility model is as follows:

[0078] In the initial state, the locking nut 231 is in the unlocked state, the piston rod 241 is in the fully retracted state, and at this time, the limiting protrusion 2121 at the upper end of the pulling pin 212 abuts against the limiting step 2131 of the pulling support seat 213.

[0079] When loading is required, the hydraulic oil output from the hydraulic power station enters the rodless chamber of the traction cylinder 240 through the proportional directional valve. The piston rod 241 of the traction cylinder 240 extends, connecting the wire rope to the traction hinge seat 211. The proportional directional valve reverses, and the hydraulic oil enters the rod chamber of the traction cylinder 240, driving the piston rod 241 to retract. The traction pin 212 applies a traction force to the arrow body through the wire rope.

[0080] When the pulling force reaches the specified load, the piston rod 241 stops moving, i.e., the load is in place. At this time, the hydraulic power station supplies oil to the motor 2234, which drives the rotary gear 2232 to rotate. The rotary gear 2232 drives the outer ring 2212 of the slewing support 221 to rotate through the gear ring 2213, thereby causing the pulling rotating sleeve 222 to rotate as well. The pulling rotating sleeve 222, through the engagement of the long sliding groove 2221 and the locking pin 232, drives the locking nut 231 to rotate and rise along the threaded section of the pulling pin 212. When the locking nut 231 is in contact with the lower end face of the pulling support 213, the locking nut 231 reaches the locked state and cannot continue to rotate. The pulling pin 212 is axially limited by the locking nut 231 and cannot spring back, thus achieving mechanical locking. At this time, the oil supply to the motor 2234 can be cut off. The locking nut 231 remains in the locked position due to the self-locking characteristic of the threaded pair. Figure 7 As shown.

[0081] During the loading process, the force sensor collects the real-time tension of the wire rope, and the pressure sensor collects the pressure data of the traction cylinder 240 in real time. The two form redundant detection and feed back to the control system. When the actual traction load value reaches the preset value, the proportional reversing valve automatically cuts off the flow, so that the traction load is stably maintained within the set range.

[0082] In this embodiment, the tension load can be adjusted according to the operating conditions. When it is necessary to change the specified tension load, the motor 2234 rotates in the reverse direction, driving the locking nut 231 to rotate and descend along the threaded section of the tension pin 212, causing the locking nut 231 to disengage from the tension support 213, until the locking nut 231 reaches the unlocked state, as shown. Figure 8 As shown.

[0083] At this point, the piston rod 241 is extended or retracted again to make the pulling force reach the preset specified load. The piston rod 241 stops moving, and the locking nut 231 is adjusted again to reach the locking position. During this process, the sequence valve is used to distinguish the pressure of the locking circuit and the working circuit to avoid interference between the pressure signals of the unlocking action and the loading action.

[0084] When unloading is required, the proportional directional valve reverses, and hydraulic oil enters the rod chamber of the traction cylinder 240, pushing the piston rod 241 to retract and release the traction force.

[0085] Throughout the entire movement, the proximity switch detects in real time whether the locking nut 231 is in a locked or unlocked state and sends a feedback signal to the control system, allowing the next action to be performed.

[0086] The beneficial effects of the launch pad tensioning and locking device and loading system of this utility model are:

[0087] The maximum pulling force of a single traction locking device can reach over 300t, making it suitable for heavy-lift rockets.

[0088] Independently configured proportional directional valves are used to achieve coordinated loading of multiple units through closed-loop control of force sensors, with mutual deviation not exceeding 1t and loading accuracy also controlled within 1t, solving the problem of uneven force distribution at each load point in traditional solutions; double locking is adopted, so even if the hydraulic pressure is completely lost or the motor fails, the thread self-locking can still maintain the lock and prevent the rocket body from falling back.

[0089] The overall modular integration, connected to the launch pad with bolts, greatly improves the efficiency of disassembly, assembly and maintenance, and can adapt to different usage scenarios such as static testing, launch containment, and emergency locking.

[0090] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made using the content of this utility model specification, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A launch pad traction locking device, characterized in that, include: The bearing mechanism (210) includes a traction hinge seat (211), a traction pin (212), and a traction support seat (213): the traction support seat (213) is sleeved on the traction pin (212), the upper end of the traction pin (212) is fixedly connected to the traction hinge seat (211), and the lower end of the traction pin (212) passes through the central through hole of the traction support seat (213) and is connected to the traction cylinder (240); The transmission mechanism (220) is located below the bearing mechanism and connected to the traction support seat (213). It includes a slewing bearing seat (221), a traction rotating sleeve (222), and a nut rotating assembly (223). The slewing bearing seat (221) includes an inner ring (2211) and an outer ring (2212). The inner ring (2211) is fixedly connected to the lower end of the traction support seat (213), and the outer ring (2212) is fixedly connected to the lower traction rotating sleeve (222). The nut rotating assembly (223) is installed on one side of the outer ring of the traction support seat (213) and is used to drive the outer ring (2212) of the slewing bearing seat (221) to rotate. The locking mechanism (230) includes a locking nut (231) and a locking pin (232); the locking nut (231) is located between the pulling pin (212) and the pulling rotating sleeve (222), and is threaded onto the pulling pin (212); one end of the locking pin (232) is fixedly connected to the locking nut (231), and the other end is movably connected to the pulling rotating sleeve (222); The traction cylinder (240) includes a piston rod (241), which is fixedly connected to the lower end of the traction pin (212).

2. The launch pad traction locking device according to claim 1, characterized in that, The nut rotating assembly (223) includes a mounting base (2231), a rotary gear (2232), a connecting flange (2233), and a motor (2234). The mounting base (2231) is connected to the tension support (213). The rotary gear (2232) is rotatably mounted on the mounting base (2231). The motor (2234) is connected to the mounting base (2231) through the connecting flange (2233), and the output shaft of the motor (2234) is drivenly connected to the rotary gear (2232). The rotary gear (2232) is drivenly connected to the outer ring (2212) of the rotary support (221).

3. The launch pad traction locking device according to claim 2, characterized in that, The outer ring (2212) of the slewing bearing (221) is provided with a toothed ring (2213), and the slewing gear (2232) meshes with the toothed ring (2213).

4. The launch pad traction locking device according to claim 1, characterized in that, The outer peripheral wall of the traction rotating sleeve (222) is provided with a long sliding groove (2221) along its axial direction. The other end of the locking pin (232) extends into the long sliding groove (2221) and can be displaced along the extension direction of the long sliding groove (2221).

5. The launch pad traction locking device according to claim 4, characterized in that, There are two long slides (2221), and the two long slides (2221) are symmetrically arranged along the circumference of the traction rotating sleeve (222).

6. The launch pad traction locking device according to claim 1, characterized in that, The pull pin (212) has a threaded section on its outer periphery. The locking nut (231) is sleeved on the threaded section and can move on the pull pin (212). The movement stroke of the locking nut (231) on the pull pin (212) is ≥100mm.

7. The launch pad traction locking device according to claim 1, characterized in that, The lower end face of the traction support (213) and the outer periphery of the piston rod (241) near the connection with the traction pin (212) are provided with proximity switches for detecting the position of the locking nut (231).

8. The launch pad traction locking device according to claim 1, characterized in that, The traction support base (213) is provided with a limiting step (2131), and the traction pin (212) is provided with a limiting protrusion (2121) corresponding to the limiting step (2131). The limiting step (2131) and the limiting protrusion (2121) axially block each other to restrict the axial movement of the traction pin (212).

9. The launch pad traction locking device according to claim 1, characterized in that, It also includes a force sensor and a pressure sensor. A steel wire rope is connected to the top of the traction hinge seat (211). The force sensor is installed between the steel wire rope and the traction hinge seat (211). The pressure sensor is installed in the rodless chamber oil circuit of the traction cylinder (240). The force sensor and the pressure sensor form a dual redundant load detection.

10. The launch pad traction locking device according to claim 9, characterized in that, It also includes a hydraulic control valve assembly, which includes a proportional directional valve, a balance valve and a sequence valve. The proportional directional valve is located on the oil supply line of the traction cylinder (240), the balance valve is located at the rodless chamber oil port of the traction cylinder (240), and the sequence valve is located on the oil supply valve assembly of the motor (2234).

11. The launch pad traction locking device according to claim 10, characterized in that, The proportional directional valve is electrically connected to a force sensor and a pressure sensor to perform closed-loop control of the traction cylinder (240) based on feedback signals from at least one of the force sensor and the pressure sensor.

12. A loading system, characterized in that, It includes a fixed launch platform (100) and a plurality of launch platform traction and locking devices symmetrically installed at the bottom of the fixed launch platform (100) and evenly distributed around the rocket body, wherein the launch platform traction and locking device is the launch platform traction and locking device according to any one of claims 1-11.

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