Heavy-duty webbing for arresting aircraft

Abstract

The application discloses a heavy-duty braid for blocking airplanes, relates to the technical field of braids, and comprises a bottom plate, traction boxes, a tightening mechanism, a main braid and an auxiliary braid. The bottom plate is fixed on the ground at the end of an airport runway through embedded steel bars. The two sides of the bottom plate are fixed with the traction boxes, and one side of the traction box is provided with the tightening mechanism. The heavy-duty braid for blocking airplanes is characterized in that the main braid is woven with a cable core, a steel strand and a tightening rope, the main braid for main interception is structurally reinforced, the main braid is used in cooperation with the auxiliary braid made of ultrahigh molecular polyethylene (PEPES), and the main braid can stably intercept airplanes with a large load. The main braid is straightened through the tightening mechanism, and the main braid is stored through cooperation of a movable pulley and a fixed pulley. When the airplane is blocked, double deceleration braking can be realized through cooperation of a gas rod and a double buffering assembly of a damping cylinder, so that the heavy-duty braid is prevented from being straightened and broken due to direct collision of the airplane with the braid.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of woven tape, in particular to a heavy woven tape for blocking airplanes. BACKGROUND

[0002] Woven tape is made of various yarns into a narrow fabric or tubular fabric. There are many varieties of tape fabrics, which are widely used in clothing, shoes, luggage, industry, agriculture, military supplies, transportation and other industrial departments. In the airport, during the take-off and landing process, the airplane may run off the runway due to failed take-off or excessive landing speed, causing immeasurable loss of life and property. The airplane blocking system, as an important safety protection device during the take-off or landing process of the airplane, can effectively block the airplane running off the runway, greatly improving the safety of the end of the airport runway. The airplane blocking system can be roughly divided into three types according to its blocking form: net type, cable type and pavement blocking system.

[0003] Due to the difficulty of the net type blocking and the cable type blocking to bear the heavy airplane, when the airplane loses control during landing and sliding on the airport runway, it cannot be smoothly intercepted by the conventional net type blocking and cable type blocking. The pavement blocking system needs to rely on the crushing strength of the material to ensure that the airplane landing gear is not damaged, and also needs to consider the speed of the airplane running off the runway, the depth of the blocking material, the wheel pressure, the landing gear structure and the strength of the front and main landing gear pillars. The operation mode of this pavement blocking requires extremely high, making it difficult to widely apply the operation of blocking airplanes. Therefore, we propose a heavy woven tape for blocking airplanes. SUMMARY

[0004] The purpose of the present application is to provide a heavy woven tape for blocking airplanes to solve the problems raised in the background.

[0005] To achieve the above purpose, the present application provides the following technical scheme: a heavy woven tape for blocking airplanes, comprising a bottom plate, a traction box, a tightening mechanism, a main woven tape and a secondary woven tape,

[0006] The bottom plate is fixed on the ground at the end of the airport runway by pre-embedded steel bars. The two sides of the bottom plate are fixed with traction boxes. The traction box is provided with a tightening mechanism on one side. The tightening mechanism is composed of a limiting roller, a rotating frame, an auxiliary wheel, a guide wheel and a gas rod. The limiting roller is installed on the inclined side of the traction box through a support. The limiting roller is provided with a rotating frame movably connected with the traction box on one side. The rotating frame is internally rotatably connected with an auxiliary wheel and a guide wheel at both ends. The limiting roller, the auxiliary wheel and the guide wheel are wound with a main woven tape. The main woven tape is horizontally provided with two groups, and the secondary woven tape is fixed at equal intervals between the two groups of main woven tapes.

[0007] Preferably, the main woven belt is composed of a cord core, a connecting line, a steel strand and a tightening rope, the inside of the main woven belt is embedded with the cord core woven with the cord core;

[0008] A plurality of the cord cores are connected by the connecting line, the outside of the cord core is provided with the steel strand, and the outer wall of the steel strand is provided with the tightening rope.

[0009] Preferably, the upper side of the traction box is connected with the top of the rotating frame through the air rod.

[0010] Preferably, two groups of fixed pulleys are installed in the inside of the traction box, and every three horizontally arranged fixed pulleys form a group, a guide rod is arranged between the adjacent two fixed pulleys, and one end of the guide rod is connected with one side of the traction box in a penetrating mode.

[0011] Preferably, the other end of the guide rod is welded and fixed with the outside support of the movable pulley, and a connecting rod is welded between the upper and lower groups of guide rods, and the connecting rod is located on the outside of the traction box.

[0012] Preferably, the middle part of the connecting rod is welded with the end part of the piston rod, the piston rod is inserted into the inside of the damping cylinder, and the damping cylinder is arranged on the middle partition plate of the traction box.

[0013] Preferably, the inside of the damping cylinder is butted with a reset spring for resetting the movement of the piston rod, and the side surface of the damping cylinder is connected with a buffer pipe through a pipeline.

[0014] Preferably, a fixing sleeve is welded in the inside of the buffer pipe, and a flow guide channel is formed in the middle part of the fixing sleeve.

[0015] Preferably, sawtooth grooves are arranged on the two sides of the inner wall of the flow guide channel, and a valve plate is symmetrically connected with the middle part of the flow guide channel through a rotating pin.

[0016] Preferably, a magnet block is embedded in the inside of the valve plate, and a blocking rod is fixed on the inner wall of the flow guide channel, and the blocking rod is located on the outside of the valve plate.

[0017] Compared with the prior art, the heavy woven belt for blocking the airplane has the beneficial effects that the cord core, the steel strand and the tightening rope are woven in the main woven belt, the main woven belt for main interception is structurally reinforced, the main woven belt is cooperated with the auxiliary woven belt made of ultra-high molecular polyethylene PEPES material, the airplane with large load can be smoothly intercepted, the main woven belt is straightened by the tightening mechanism, the main woven belt is stored by the cooperation of the movable pulley and the fixed pulley, the double buffering assembly of the air rod and the damping cylinder is cooperated to realize double deceleration braking when the airplane is blocked, and the heavy woven belt is prevented from being straightened and broken due to the direct collision of the airplane with the woven belt.

[0018] 1. The heavy-duty braid for blocking the airplane, due to the equipment failure and other reasons, the airplane will lose control when landing, when the manned airplane loses control on the airport runway, the heavy airplane will slide a long distance to stop, but the general length of the airplane runway is not enough to provide the sliding to the stop state, and the conventional blocking cable is difficult to ensure the stable braking of the airplane, therefore, by weaving multiple cable cores in the main braid, and by wrapping the cable cores with steel wire and tightening rope, connecting the multiple cable cores through the connecting line, the intercepting rope composed of the cable core, the steel wire and the tightening rope can be folded, so as to ensure that the main braid which plays a leading role in interception is structurally reinforced, and the two groups of main braid have super strong anti-breaking effect, the main braid is used in cooperation with the auxiliary braid made of ultra-high molecular polyethylene PEPES material, so as to smoothly intercept the heavy airplane, and avoid the breaking of the heavy braid when blocking the heavy airplane;

[0019] 2. The heavy-duty braid for blocking the airplane, when the main braid cooperates with the auxiliary braid to intercept the airplane, the impact force generated by the inertia of the airplane acts on the middle region of the main braid, the two groups of transversely distributed main braid and the multiple groups of longitudinally distributed auxiliary braid are impacted, so that the main braid presents a "V" type traction state, when the main braid is bent and deformed, the main braid is straightened by the tightening mechanism, so as to ensure that the heavy braid has a preliminary buffering effect, after the airplane is preliminarily buffered, the main braid drives the movable pulley and the guide rod to pull the piston rod in the damping cylinder, at the same time, the piston part of the piston rod pushes the damping liquid in the damping cylinder into the buffer pipe, and the damping liquid impacts the valve plate inside the flow guide channel to achieve high-efficiency deceleration, so as to realize double deceleration braking, and prevent the single buffering from causing the heavy braid to be directly straightened and broken;

[0020] 3. The heavy-duty braid for blocking the airplane, when the airplane is intercepted and stopped from sliding, the airplane is moved to a safe position by the traction vehicle, at this time, when the return spring resets and extends, it can push the piston rod to reset to the original position in the damping cylinder, at this time, the damping liquid is reversely guided along the flow guide channel of the fixed sleeve, so that the damping liquid flows along the valve plates which are side by side and close to each other, so as to ensure that the damping liquid is not hindered by the valve plate when moving in the flow guide channel, and the air rod is used in cooperation to push the rotating frame to rotate, so that the main braid can be quickly retracted into the traction box, so as to ensure that the main braid can be quickly straightened and unfolded without the assistance of the staff, and ensure that the heavy braid can be repeatedly used for airplane blocking on the airport runway. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a schematic view of the main view cross-sectional structure of the present application;

[0022] Figure 2 It is a schematic view of the top view structure of the present application;

[0023] Figure 3The top view structure diagram of the main weaving belt being pulled and bent of the present application;

[0024] Figure 4 The top view structure diagram of the present application;

[0025] Figure 5 The top view structure diagram of the main weaving belt being pulled and bent of the present application;

[0026] Figure 6 The structure diagram of the main weaving belt of the present application;

[0027] Figure 7 The main view structure diagram of the damping cylinder of the present application;

[0028] Figure 8 The main view structure diagram of the fixed sleeve guiding the damping liquid in the positive direction of the present application;

[0029] Figure 9 The main view structure diagram of the fixed sleeve guiding the damping liquid in the reverse direction of the present application;

[0030] Figure 10 The left view structure diagram of the fixed sleeve of the present application.

[0031] In the figure: 1, bottom plate; 2, traction box; 21, fixed pulley; 22, guide rod; 23, movable pulley; 24, connecting rod; 25, piston rod; 26, damping cylinder; 27, return spring; 28, buffer pipe; 3, tightening mechanism; 31, limiting roller; 32, rotating frame; 33, auxiliary wheel; 34, guide wheel; 35, air rod; 4, main weaving belt; 41, cable core; 42, connecting wire; 43, steel strand; 44, tightening rope; 5, auxiliary weaving belt; 6, fixed sleeve; 61, guiding passage; 7, valve plate; 8, magnet block; 9, blocking rod. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0033] Please refer to Figures 1-5The application provides a technical scheme: a heavy-duty braid for blocking airplanes, which comprises a bottom plate 1, a traction box 2, a tightening mechanism 3, a main braid 4 and a secondary braid 5, the bottom plate 1 is fixed on the ground at the end of an airport runway through pre-embedded steel bars, so that the installation of the heavy-duty braid assembly is more stable, traction boxes 2 are fixed on the two sides of the bottom plate 1, the traction box 2 is provided with the tightening mechanism 3 on one side, the tightening mechanism 3 is composed of a limiting roller 31, a rotating frame 32, an auxiliary wheel 33, a guide wheel 34 and a gas rod 35, the limiting roller 31 is installed on the inclined side of the traction box 2 through a support, the limiting roller 31 is provided with the rotating frame 32 which is movably connected with the traction box 2 on one side, the rotating frame 32 is provided with two groups of upper and lower rotating frames 32, the upper and lower rotating frames 32 are butt-jointed through a support column, and the rotating frame 32 close to the bottom plate 1 is butt-jointed with the bottom plate 1 through a bearing seat, the two ends in the rotating frame 32 are rotatably connected with the auxiliary wheel 33 and the guide wheel 34 respectively, the upper side of the traction box 2 and the top of the rotating frame 32 are connected through the gas rod 35, the main braid 4 is wound between the limiting roller 31, the auxiliary wheel 33 and the guide wheel 34, the main braid 4 is horizontally provided with two groups, and the secondary braid 5 is fixed at equal intervals between the two groups of main braids 4, and the secondary braid 5 is made of ultra-high molecular polyethylene PEPES material, a plurality of secondary braids 5 are connected through elastic ropes, the secondary braids 5 connected through the elastic ropes can be regular, and the secondary braids 5 distributed at equal intervals can achieve the anti-winding effect between the two groups of main braids 4.

[0034] In specific implementation, when the out-of-control airplane slides along the airport runway, the heavy-duty braid at the end of the airport runway is used for interception, when the front part of the airplane contacts the main braid 4 between the two traction boxes 2, the two groups of parallelly distributed main braids 4 can pull the shell and landing gear of the airplane, and can cover each part of the airplane body with the cooperation of the secondary braids 5, so that each part of the front end of the airplane can be intercepted when passing through the heavy-duty braid, and the airplane can have the function of stable braking when decelerating.

[0035] Please refer to Figure 1 、 Figure 3 and Figure 5 , two groups of fixed pulleys 21 are installed in the traction box 2, and every three horizontally arranged fixed pulleys 21 form a group, a guide rod 22 is arranged between adjacent two fixed pulleys 21, one end of the guide rod 22 is connected with one side of the traction box 2 in a penetrating mode, the other end of the guide rod 22 is welded and fixed with the outer side support of a movable pulley 23, a connecting rod 24 is welded between the two groups of guide rods 22, and the connecting rod 24 is located on the outer side of the traction box 2, a channel is formed in the side of the traction box 2 close to the limiting roller 31, and the end of the main braid 4 is introduced into the fixed pulley 21 in the deepest part of the traction box 2 after penetrating through the channel.

[0036] In specific implementation, the three fixed pulleys 21 and the two movable pulleys 23 are arranged on the same horizontal plane, a main belt 4 is inserted along the passage of the traction box 2, the main belt 4 is arranged in S shape around the side of the fixed pulleys 21 and the movable pulleys 23, and the end of the main belt 4 is locked and fixed with the last fixed pulley 21 by a fastening bolt;

[0037] Referring to Figures 2-4 It can be seen that when the main belt 4 intercepts the airplane, the impact force generated by the inertia of the airplane acts on the middle region of the main belt 4, so that the two groups of transversely distributed main belts 4 and the multiple groups of longitudinally distributed auxiliary belts 5 are impacted, thereby the middle of the main belt 4 moves to one side, so that the main belt 4 presents a "V" shaped traction state, when the main belt 4 is subjected to bending deformation, a single main belt 4 can pull and drive the guide wheels 34 on the two groups of rotating frames 32, so that the guide wheels 34 rotate around the axis of the auxiliary wheels 33, the rotating frame 32 can be unloaded during the rotation operation, and the rotating rotating frame 32 can pull the air rod 35 to elongate, so that the airplane has a preliminary buffering effect when it collides on the heavy belt.

[0038] Conversely, by synchronously shortening the air rods 35 on the two groups of traction boxes 2, the output end of the air rod 35 drives the rotating frame 32 to rotate around the axis of the auxiliary wheel 33, so that the guide wheels 34 on the rotating frame 32 can straighten the main belt 4, and by arranging the rotating frame 32 in a symmetrical manner, the two groups of parallelly distributed main belts 4 can be straightened to a taut state.

[0039] Referring to Figure 1 and Figure 7 The middle of the connecting rod 24 is welded with the end of the piston rod 25, the piston rod 25 is inserted into the inside of the damping cylinder 26, and the damping cylinder 26 is arranged on the middle partition of the traction box 2; the inside of the damping cylinder 26 is connected with the reset spring 27 for resetting the movement of the piston rod 25, the side of the damping cylinder 26 is connected with the buffer pipe 28 through a pipeline, and the inside of the damping cylinder 26 and the buffer pipe 28 is filled with damping liquid, the inside of the buffer pipe 28 is welded with the fixing sleeve 6, and the middle of the fixing sleeve 6 is provided with the flow channel 61.

[0040] In specific implementation, when the airplane continues to slide out of control along the airport runway after being intercepted by the heavy belt, the main belt 4 is drawn out along the limiting roller 31, so that the main belt 4 is gradually pulled to a taut state between the three fixed pulleys 21, so that the main belt 4 generates extrusion force on the outside of the two groups of movable pulleys 23, thereby the guide rod 22 at one end of the two groups of movable pulleys 23 is telescoped and guided out along the side of the traction box 2.

[0041] The guide rod 22 leading out of the traction box 2 pushes the connecting rod 24 away from the traction box 2, so that the connecting rod 24 pulls the piston rod 25 in the damping cylinder 26, so that the piston rod 25 compresses the return spring 27, and at the same time, the piston part of the piston rod 25 pushes the damping liquid in the damping cylinder 26 into the buffer pipe 28, and the damping liquid flows forward along the flow channel 61 of the fixed sleeve 6 to complete deceleration;

[0042] Because the movable pulley 23 is arranged on the upper and lower sides of each traction box 2, when the movable pulley 23 is close to the fixed pulley 21, more bent main woven belts 4 can be stretched out of the traction box 2, so that the main woven belts 4 can be stretched continuously when the plane continues to slide.

[0043] Please refer to Figures 7-10 The inner wall of the flow channel 61 is provided with sawtooth grooves on both sides, the middle part of the flow channel 61 is symmetrically connected with the valve plate 7 through a rotating pin, the inside of the valve plate 7 is embedded with a magnet block 8, the inner wall of the flow channel 61 is fixed with a stop rod 9, and the stop rod 9 is located outside the valve plate 7, one end of the valve plate 7 away from the rotating pin is in a bevel structure, and the adjacent two groups of valve plates 7 are in a "V" shape structure when they are rotated and unfolded, and the magnet blocks 8 inside the adjacent two groups of valve plates 7 are of the same polarity.

[0044] In specific implementation, when the connecting rod 24 pulls the piston rod 25 to compress the return spring 27, the damping liquid will flow forward along the flow channel 61 inside the fixed sleeve 6, because the magnet blocks 8 of the same polarity are embedded in the adjacent two groups of valve plates 7, the adjacent two groups of valve plates 7 will be angularly opened, the damping liquid flowing forward will impact the adjacent two groups of valve plates 7 along the flow channel 61 of the sawtooth grooves, so that the adjacent two groups of valve plates 7 are unfolded in a "V" shape structure, and the valve plate 7 will be limited by the stop rod 9 when it is unfolded, so that there is a small gap between the valve plate 7 and the inner wall of the flow channel 61, and the damping liquid flowing forward can be slowed down by the unfolded valve plates 7 when it flows through the flow channel 61, so that the main woven belts 4 are greatly buffered and hindered when they are stretched;

[0045] When the plane is intercepted and stopped from sliding, the plane is moved to a safe position by the traction vehicle, at this time, the return spring 27 is reset and stretched, which can push the piston rod 25 to reset to the original position in the damping cylinder 26, at this time, the damping liquid flows reversely along the flow channel 61 of the fixed sleeve 6, so that the damping liquid passes through the valve plate 7, so that the damping liquid flows quickly along the valve plates 7 which are side by side and close to each other, so that the movable guide rod 22 and the movable pulley 23 are quickly reset to the original state, and the rotating frame 32 is pushed to rotate by the air rod 35, so that the main woven belts 4 can be quickly retracted into the traction box 2, so that the main woven belts 4 can be quickly stretched and unfolded without the assistance of the staff.

[0046] Please refer to Figure 6The main woven belt 4 is composed of a cord core 41, a connecting wire 42, a steel strand 43 and a tightening rope 44, the inside of the main woven belt 4 is embedded with the woven cord core 41; a plurality of cord cores 41 are connected through the connecting wire 42, the outer side of the cord core 41 is provided with the steel strand 43, the outer wall of the steel strand 43 is provided with the tightening rope 44, the connecting wire 42 is made of steel wire material, and the connecting wire 42 and the cord core 41 are welded and fixed.

[0047] In specific implementation, by weaving a plurality of cord cores 41 in the main woven belt 4, and by tightly wrapping the cord core 41 with the steel strand 43 and the tightening rope 44, and by connecting the plurality of cord cores 41 through the connecting wire 42, the intercepting rope composed of the cord core 41, the steel strand 43 and the tightening rope 44 can be folded, so that the two groups of main woven belts 4 have super strong anti-breaking effect, and the internal reinforcing assembly is protected by the main woven belt 4, so that the main woven belt 4 cooperates with the auxiliary woven belt 5 made of ultra-high molecular polyethylene PEPES material, and can smoothly intercept the aircraft with large load, and prevent the heavy woven belt from breaking to cause blocking failure.

[0048] In summary, the heavy woven belt and the matching buffer assembly are installed at the end of the airport runway, when the out-of-control aircraft slides along the airport runway, the main woven belt 4 and the auxiliary woven belt 5 of the heavy woven belt are intercepted, each part of the front end of the aircraft can be intercepted when passing through the heavy woven belt, and the aircraft has the function of stable braking when decelerating, the contents not described in detail in the description belong to the prior art known to those skilled in the art.

[0049] Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art can modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part of the technical features, any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A heavy-duty webbing for arresting aircraft, comprising a base plate (1), a traction box (2), a tightening mechanism (3), a main webbing (4), and a secondary webbing (5), characterized in that: The base plate (1) is fixed to the ground at the end of the airport runway by pre-embedded steel bars. The base plate (1) is fixed with traction boxes (2) on both sides. The traction box (2) is provided with a tightening mechanism (3) on one side. The tightening mechanism (3) consists of a limiting roller (31), a rotating frame (32), an auxiliary wheel (33), a guide wheel (34), and a pneumatic rod (35). The limiting roller (31) is installed on the inclined side of the traction box (2) by a bracket. The limiting roller (31) is provided with a rotating frame (32) that is movably connected to the traction box (2) on one side. The two ends of the rotating frame (32) are rotatably connected to the auxiliary wheel (33) and the guide wheel (34) respectively. The limiting roller (31), the auxiliary wheel (33), and the guide wheel (34) are wound with a main webbing (4). The main webbing (4) is horizontally arranged in two sets, and the two sets of main webbing (4) are fixed with secondary webbing (5) at equal intervals. The upper side of the traction box (2) is connected to the top of the rotating frame (32) via a pneumatic rod (35); Each traction box (2) is equipped with movable pulleys (23) on both the upper and lower sides. The traction box (2) is equipped with two sets of fixed pulleys (21), and three horizontally arranged fixed pulleys (21) form a group. A guide rod (22) is provided between two adjacent fixed pulleys (21). One end of the guide rod (22) is connected through to one side of the traction box (2), and the other end of the guide rod (22) is welded and fixed to the outer support of the movable pulley (23). A connecting rod (24) is welded between the upper and lower sets of guide rods (22), and the connecting rod (24) is located on the outside of the traction box (2). The middle part of the connecting rod (24) is welded to the end of the piston rod (25). The piston rod (25) is inserted into the inside of the damping cylinder (26). The damping cylinder (26) is set on the middle partition of the traction box (2). The inside of the damping cylinder (26) is connected to a return spring (27) for the piston rod (25) to return to its original position. The side of the damping cylinder (26) is connected to a buffer tube (28) through a pipe. The inside of the buffer tube (28) is welded with a fixing sleeve (6). A flow channel (61) is opened in the middle of the fixing sleeve (6). The inner wall of the flow channel (61) is provided with serrated grooves on both sides. A valve plate (7) is symmetrically connected to the middle of the flow channel (61) by a rotating pin. A magnet block (8) is embedded in the valve plate (7). A stop bar (9) is fixed to the inner wall of the flow channel (61), and the stop bar (9) is located on the outside of the valve plate (7).

2. The heavy-duty webbing for stopping aircraft according to claim 1, characterized in that: The main webbing (4) is composed of a core (41), connecting wires (42), steel strands (43) and a tightening rope (44), and the core (41) is embedded in the interior of the main webbing (4). Multiple cable cores (41) are connected by connecting lines (42). Steel strands (43) are provided on the outer side of each cable core (41), and a tightening rope (44) is wound around the outer wall of each steel strand (43).

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