Early warning device for preventing aircraft from settling when special vehicle operates by leaning against aircraft

Abstract

The utility model relates to the technical field of aviation support equipment, and discloses an early warning device for preventing an airplane from settling when a special vehicle operates by leaning against the airplane, which comprises a fixed seat and a fixed plate fixedly connected to the bottom end of the fixed seat, a disassembly and assembly mechanism is arranged on the fixed seat, an adjusting mechanism is arranged on the disassembly and assembly mechanism, and the adjusting mechanism is connected with the fixed seat. Stress blocks are extruded by pressing and pushing, so that the stress blocks on the two sides are pushed to move towards the two sides, a first supporting connecting rod and a positioning rod are driven to move, at the moment, the outer wall of the positioning rod is separated from the inner wall of a positioning hole, limiting of a positioning insertion plate is relieved, the positioning insertion plate is inserted into the inner wall of a clamping groove, and the positioning insertion plate is inserted into the clamping groove; the top end stress inclined face of the positioning rod is extruded, the positioning rod is driven to move, the positioning rod can be pushed to reset through springback of the spring so that the positioning rod can be clamped in the positioning hole, limiting is completed, the installation mode is rapid and convenient, a plurality of fastening bolts are not needed, and maintenance personnel can conveniently conduct disassembly, assembly and maintenance.

Description

Technical Field

[0001] This utility model belongs to the field of aviation support equipment technology, specifically, it relates to an early warning device for preventing aircraft from sinking when special vehicles are operating alongside them. Background Technology

[0002] In today's booming modern air transport industry, airports, as air transport hubs, must ensure the safe take-off and landing and efficient operation of a large number of flights every day. Special vehicles play an indispensable role in airport ground operations. Whether it is aircraft towing vehicles that are responsible for precisely towing aircraft to designated parking positions, refueling trucks that replenish aircraft fuel to ensure the continued flight range, or food supply vehicles and baggage towing vehicles that provide various services to passengers and ensure the transfer of baggage, they all need to frequently and closely approach aircraft for operations.

[0003] High-precision laser rangefinders will be used in the detection and early warning of aircraft settling. The laser beam emitted by the rangefinder is vertically pointed at a preset monitoring point on the bottom of the aircraft fuselage to measure the vertical distance between the special vehicle and the aircraft in real time. The rangefinder is complicated to disassemble and assemble, making it inconvenient for staff to disassemble and repair it later.

[0004] In view of this, this utility model is hereby proposed. Utility Model Content

[0005] To address the technical problem of the cumbersome disassembly and assembly of high-precision laser rangefinders used in aircraft settlement detection and early warning processes, where the emitted laser beam is vertically pointed at a preset monitoring point on the bottom of the aircraft fuselage to measure the real-time vertical distance between special vehicles and the aircraft, and the inconvenience of subsequent disassembly and maintenance by the rangefinders, the basic concept of this utility model is as follows:

[0006] A warning device for preventing aircraft from sinking when special vehicles are operating alongside them, including a fixed base;

[0007] A fixing plate is fixedly connected to the bottom end of the fixing base. The fixing base is provided with a disassembly and assembly mechanism, and the disassembly and assembly mechanism is provided with an adjustment mechanism. The disassembly and assembly mechanism includes a locking groove.

[0008] An adjusting mounting block is provided above the fixed base. The engaging groove is opened at the top of the adjusting mounting block. A sliding hole is opened in the inner wall of the engaging groove. A spring is fixedly connected to the inner wall of the sliding hole. A positioning rod is fixedly connected to the end of the spring away from the inner wall of the sliding hole. A force-bearing inclined surface is opened at the end of the positioning rod away from the spring. A positioning insert plate is engaged in the inner wall of the engaging groove. A positioning hole is opened in the outer wall of the positioning insert plate. A laser ranging sensor is installed on the outer wall of the positioning insert plate away from the inner wall of the engaging groove. A first supporting connecting rod is fixedly connected to the outer wall of the positioning rod. A force-bearing block is fixedly connected to the end of the first supporting connecting rod away from the outer wall of the positioning rod. A limit groove is opened at the bottom of the outer wall of the adjusting mounting block. A limit plate is movably provided in the inner wall of the limit groove. A second supporting connecting rod is fixedly connected to the outer wall of the limit plate. A push block is fixedly connected to the end of the second supporting connecting rod away from the limit plate.

[0009] In a preferred embodiment of this utility model, the adjustment mechanism includes a first support frame fixedly connected to the top of the fixed base. The bottom of the inner wall of the first support frame is provided with an installation groove, and a motor is fixedly installed on the inner wall of the installation groove. A lead screw is fixedly connected to the output end of the motor. A threaded hole is provided at the top of the adjustment mounting block, and the threaded hole is threadedly connected to the outer wall of the lead screw. A second support frame is fixedly connected to the top of the fixed base on one side of the first support frame, and a support slide rod is fixedly connected to the inner wall of the second support frame.

[0010] In a preferred embodiment of this utility model, there are two positioning plates, which are distributed in a left-right symmetrical structure on the outer wall of the laser rangefinder.

[0011] In a preferred embodiment of this utility model, the outer wall of the positioning plate is fitted to the inner wall of the locking groove, and the inner wall of the positioning hole is fitted to the outer wall of the positioning rod.

[0012] In a preferred embodiment of the present invention, the outer wall of the adjusting mounting block is provided with a connecting groove, the inner wall of the connecting groove is connected to the inner wall of the sliding hole, and the outer wall of the first supporting connecting rod is movably disposed on the inner wall of the connecting groove.

[0013] In a preferred embodiment of this utility model, the outer wall of the adjusting mounting block is movably disposed on the inner wall of the first support frame and the second support frame.

[0014] In a preferred embodiment of the present invention, a through groove is provided at the top of one side of the adjusting mounting block, and the inner wall of the through groove is slidably connected to the outer wall of the supporting slide rod.

[0015] Compared with the prior art, the present invention has the following advantages:

[0016] This invention allows for the pressing and pushing of a force-bearing block, which in turn pushes the force-bearing blocks on both sides to move to the sides. This movement of the force-bearing blocks will cause the first support connecting rod and the positioning rod to move. At this time, the outer wall of the positioning rod will disengage from the inner wall of the positioning hole, thereby releasing the limitation on the positioning insert plate. During installation, simply insert the positioning insert plate into the inner wall of the locking groove, and then press the top force-bearing inclined surface of the positioning rod to move the positioning rod. As the positioning hole moves to the position of the positioning rod, the spring rebound will push the positioning rod back to its original position, thus locking it in the positioning hole and completing the limitation. This installation method is relatively quick and convenient, does not require the use of multiple fastening bolts, and is convenient for maintenance personnel to disassemble and repair.

[0017] This invention utilizes a motor that, when started, drives a lead screw to rotate. The forward and reverse rotation of the lead screw moves the adjusting mounting block up and down, which in turn moves the laser rangefinder sensor up and down. This ensures that the laser rangefinder sensor can be moved to the aircraft's monitoring point, even when facing various special vehicles at different altitudes, thus improving the applicability of the equipment.

[0018] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings. Attached Figure Description

[0019] In the attached diagram:

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 This is a schematic diagram of the rear structure of the present invention;

[0022] Figure 3 This is a schematic diagram of the disassembly and assembly mechanism of this utility model.

[0023] Figure 4 This is a schematic diagram of part of the disassembly and assembly mechanism of this utility model;

[0024] Figure 5 This is a cross-sectional view of the adjustment mechanism of this utility model.

[0025] In the diagram: 1. Fixed base; 2. Fixed plate; 31. Disassembly and assembly mechanism; 311. Engaging groove; 312. Spring; 313. Positioning rod; 314. Force-bearing inclined surface; 315. Positioning insert plate; 316. Positioning hole; 317. Laser rangefinder sensor; 318. First support connecting rod; 319. Limiting groove; 3110. Limiting plate; 3111. Second support connecting rod; 3112. Push block; 3113. Force-bearing block; 32. Adjustment mechanism; 321. First support frame; 322. Motor; 323. Lead screw; 324. Adjustment mounting block; 325. Second support frame; 326. Support slide rod. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate this utility model.

[0027] like Figures 1 to 5 As shown, a warning device for preventing aircraft from sinking during special vehicle-to-air operations includes a fixed base 1, a fixed plate 2 fixedly connected to the bottom of the fixed base 1, a disassembly and assembly mechanism 31 provided on the fixed base 1, and an adjustment mechanism 32 provided on the disassembly and assembly mechanism 31. The disassembly and assembly mechanism 31 includes a locking groove 311, and an adjustment mounting block 324 is provided above the fixed base 1. The locking groove 311 is located at the top of the adjustment mounting block 324. A sliding hole is provided on the inner wall of the locking groove 311, and a spring 312 is fixedly connected to the inner wall of the sliding hole. A positioning rod 313 is fixedly connected to the end of the spring 312 away from the inner wall of the sliding hole. A force-bearing inclined surface 314 is provided on the end of the positioning rod 313 away from the spring 312. The locking mechanism is equipped with a positioning plate 315, and a positioning hole 316 is provided on the outer wall of the positioning plate 315. A laser rangefinder sensor 317 is installed on the outer wall of the end of the positioning plate 315 away from the inner wall of the locking groove 311. A first support rod 318 is fixedly connected to the outer wall of the positioning rod 313. A force-bearing block 3113 is fixedly connected to the end of the first support rod 318 away from the outer wall of the positioning rod 313. A limit groove 319 is provided at the bottom of the outer wall of the adjusting mounting block 324. A limit plate 3110 is movably provided on the inner wall of the limit groove 319. A second support rod 3111 is fixedly connected to the outer wall of the limit plate 3110. A push block 3112 is fixedly connected to the end of the second support rod 3111 away from the limit plate 3110.

[0028] Furthermore, there are two positioning plates 315, which are distributed symmetrically on the outer wall of the laser rangefinder 317 to provide uniform support for the left and right sides of the laser rangefinder 317.

[0029] Furthermore, the outer wall of the positioning plate 315 is fitted to the inner wall of the engaging groove 311, and the inner wall of the positioning hole 316 is fitted to the outer wall of the positioning rod 313, thereby improving the insertion stability of the positioning plate 315 and the positioning rod 313.

[0030] Furthermore, the outer wall of the adjusting mounting block 324 is provided with a connecting groove, the inner wall of which is connected to the inner wall of the sliding hole. The outer wall of the first support rod 318 is movably disposed on the inner wall of the connecting groove, thus providing space for the first support rod 318 to move, so as to ensure that the positioning rod 313 can be moved and to facilitate disassembly.

[0031] The adjustment mechanism 32 includes a first support frame 321 fixedly connected to the top of the fixed base 1. The bottom of the inner wall of the first support frame 321 is provided with an installation groove. A motor 322 is fixedly installed on the inner wall of the installation groove. A lead screw 323 is fixedly connected to the output end of the motor 322. A threaded hole is provided at the top of the adjustment mounting block 324. The threaded hole is threadedly connected to the outer wall of the lead screw 323. A second support frame 325 is fixedly connected to the top of the fixed base 1 on one side of the first support frame 321. A support slide rod 326 is fixedly connected to the inner wall of the second support frame 325.

[0032] Furthermore, the outer wall of the adjusting mounting block 324 is movably disposed on the inner wall of the first support frame 321 and the second support frame 325. The first support frame 321 and the second support frame 325 can provide limiting support for the left and right outer walls of the adjusting mounting block 324.

[0033] Furthermore, a through groove is provided at the top of one side of the adjusting mounting block 324. The inner wall of the through groove is slidably connected to the outer wall of the support slide rod 326. The support slide rod 326 can support the adjusting mounting block 324 to ensure stability during movement.

[0034] The implementation principle of an early warning device for preventing aircraft from sinking during special vehicle docking operations in this embodiment is as follows: When the laser rangefinder sensor 317 needs to be disassembled for maintenance, the push block 3112 can be pushed inward to move it. At this time, the push block 3112 will drive the second support link 3111 to move inward, so the limiting plate 3110 will move within the inner wall of the limiting groove 319. The limiting groove 319 can limit the limiting plate 3110, preventing it from displacing out of its inner wall. At this time, the push block... The outer wall of 3112 will contact and press against the force-bearing block 3113. The pressed force-bearing block 3113 will move to the left and right. The movement of the force-bearing block 3113 will drive the first support connecting rod 318 and the positioning rod 313 to move. While the positioning rod 313 is moving, it will press against the spring 312. At this time, the outer wall of the positioning rod 313 will disengage from the inner wall of the positioning hole 316 opened on the outer wall of the positioning insert plate 315. In this way, the positioning insert plate 315 will be released from its limit and then pulled upward. The laser rangefinder 317 drives the positioning plate 315 to move upward, causing its outer wall to disengage from the inner wall of the engaging groove 311, thus completing the disassembly. During installation, simply insert the positioning plate 315 into the engaging groove 311. At this time, the bottom end of the positioning plate 315 will press against the force-bearing inclined surface 314 at the top of the positioning rod 313, thereby pushing the positioning rod 313 to move to both sides until the positioning hole 316 moves to the position of the positioning rod 313. Then, the spring 312 rebounds, pushing the positioning rod 313 to reset and engage with the inner wall of the positioning hole 316, completing the installation. This installation method is relatively quick and convenient, without the need for multiple fastening bolts, making it easy for maintenance personnel to disassemble and repair. When the aircraft experiences a settling phenomenon, the monitoring point on the aircraft will be out of the monitoring range of the laser rangefinder 317. This will cause the data monitored by the laser rangefinder 317 to become abnormal. Subsequently, after the controller calculates the deviation, it will activate the alarm device to complete the alarm warning, thereby alerting the staff in time and preventing high losses caused by the settling phenomenon.

[0035] When the height position of the laser rangefinder 317 needs to be adjusted, the motor 322 can be started. Its output end will drive the lead screw 323 to rotate in both directions. As the lead screw 323 rotates forward, it will drive the adjusting mounting block 324 to move upward. At the same time, the other end of the adjusting mounting block 324 will slide on the outer wall of the support slider 326. The support slider 326 can support the adjusting mounting block 324 to ensure stability and stability of movement. As the adjusting mounting block 324 moves, it can drive the laser rangefinder 317 to move up and down, thereby completing the height position adjustment operation. This ensures that the laser rangefinder 317 can be moved to the monitoring point of the aircraft, thus improving its applicability.

Claims

1. An early warning device for preventing aircraft subsidence during special vehicle approach operation, comprising a fixing seat (1); A fixed plate (2) is fixedly connected to the bottom end of the fixed seat (1), characterized in that, A dismounting mechanism (31) is arranged on the fixing seat (1), and an adjusting mechanism (32) is arranged on the dismounting mechanism (31); the dismounting mechanism (31) comprises a clamping groove (311); An adjusting mounting block (324) is arranged above the fixing seat (1), the clamping groove (311) is arranged at the top end of the adjusting mounting block (324), a sliding hole is arranged in the inner wall of the clamping groove (311), a spring (312) is fixedly connected to the inner wall of the sliding hole, a positioning rod (313) is fixedly connected to the end of the spring (312) away from the inner wall of the sliding hole, a stress inclined surface (314) is arranged at the end of the positioning rod (313) away from the spring (312), a positioning plug plate (315) is clamped on the inner wall of the clamping groove (311), a positioning hole (316) is arranged on the outer wall of the positioning plug plate (315), a laser ranging sensor (317) is mounted on the outer wall of the end of the positioning plug plate (315) away from the inner wall of the clamping groove (311), a first supporting connecting rod (318) is fixedly connected to the outer wall of the positioning rod (313), a stress block (3113) is fixedly connected to the end of the first supporting connecting rod (318) away from the outer wall of the positioning rod (313), a limiting groove (319) is arranged at the bottom end of the outer wall of the adjusting mounting block (324), a limiting plate (3110) is movably arranged in the inner wall of the limiting groove (319), a second supporting connecting rod (3111) is fixedly connected to the outer wall of the limiting plate (3110), and a push block (3112) is fixedly connected to the end of the second supporting connecting rod (3111) away from the limiting plate (3110).

2. A warning device for preventing the sinking of an aircraft during the operation of a special vehicle according to claim 1, characterized in that The adjusting mechanism (32) comprises a first supporting frame (321) fixedly connected to the top end of the fixing seat (1), a mounting groove is arranged in the inner wall of the bottom end of the first supporting frame (321), a motor (322) is fixedly mounted in the inner wall of the mounting groove, a lead screw (323) is fixedly connected to the output end of the motor (322), a threaded hole is arranged at the top end of the adjusting mounting block (324), and the threaded hole is threadedly connected to the outer wall of the lead screw (323); a second supporting frame (325) is fixedly connected to one side of the top end of the fixing seat (1) and located on the side of the first supporting frame (321), and a supporting sliding rod (326) is fixedly connected to the inner wall of the second supporting frame (325).

3. A warning device for preventing the sinking of an aircraft during the operation of a special vehicle according to claim 1, characterized in that, The number of the positioning plug plates (315) is two, and the positioning plug plates (315) are symmetrically arranged on the outer wall of the laser ranging sensor (317).

4. The warning device for preventing the aircraft from sinking during the operation of the special vehicle according to claim 1, characterized in that, The outer wall of the positioning plug plate (315) is matched with the inner wall of the clamping groove (311), and the inner wall of the positioning hole (316) is matched with the outer wall of the positioning rod (313).

5. The warning device for preventing the aircraft from sinking during the operation of the special vehicle according to claim 1, characterized in that, A communication sliding groove is arranged on the outer wall of the adjusting mounting block (324), the inner wall of the communication sliding groove is in communication with the inner wall of the sliding hole, and the first supporting connecting rod (318) is movably arranged on the inner wall of the communication sliding groove.

6. A warning device for preventing the sinking of an aircraft during the operation of a special vehicle according to claim 2, characterized in that The outer wall of the adjusting mounting block (324) is movably arranged on the inner walls of the first supporting frame (321) and the second supporting frame (325).

7. A warning device for preventing the sinking of an aircraft during the operation of a special vehicle according to claim 2, characterized in that, The adjusting mounting block (324) is provided with a through sliding groove at one side top end, and the inner wall of the through sliding groove is slidably connected to the outer wall of the supporting sliding rod (326).

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