Universal aircraft arresting equipment

Abstract

The utility model discloses universal aircraft arresting equipment which comprises a vertical net frame, a compound net body, an energy absorber, a brake band, a band guide wheel and a band collecting and pressing mechanism and further comprises a damping conversion device and an intelligent electrical control system. The utility model relates to the technical field of aircraft arresting equipment, and realizes effective arresting of aircrafts in a weight range of 5-80 tons through cooperation of a vertical net rack, a compound net body, an energy absorber and a damping conversion device. The damping conversion device is controlled through the intelligent electrical control system, working fluid in the energy absorbers is controlled through the damping conversion device, damping of the energy absorbers is adjusted, and when an airplane with the weight smaller than 40 tons and an airplane with the weight larger than 40 tons are blocked, the working states of the multiple energy absorbers are switched in a short time through the damping conversion device; and motion control is performed on the vertical net rack through a remote control box of the intelligent electrical control system.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft arresting equipment, in particular to a universal aircraft arresting equipment. Background Art

[0002] In recent years, the development of aircraft equipment has entered the fast lane. New fighters continue to emerge, and the weight chain formed has been greatly extended. In actual flight, the same aircraft type takes off and lands at multiple airports, and different aircraft types take off and land at the same airport. This makes the arresting nets with a smaller arresting weight span in use far from meeting the development of new flying weapons and the needs of actual combat training.

[0003] In view of this, a universal arresting device with multiple functions and uses came into being.

[0004] There may already be technical means to solve the above problems in the prior art, but this case intends to provide an alternative or replacement technical solution. Utility Model Content

[0005] In order to solve the problems raised in the background technology, the utility model is implemented through the following technical solutions: a universal aircraft arresting device, including a vertical grid frame, a compound grid body, an energy absorber, a brake belt, a guide pulley, and a belt collecting and pressing mechanism, characterized in that it also includes a damping conversion device and an intelligent electrical control system;

[0006] The vertical grid is arranged on both sides of the airport runway, the compound grid is connected to the vertical grid, the energy absorbers are arranged in pairs on both sides of the airport runway, one end of the brake belt is wound around the energy absorber, and the other end of the brake belt is connected to the compound grid after passing through the guide pulley, and the damping conversion device is connected to the energy absorber;

[0007] The damping conversion device includes an inlet valve and a discharge valve. The inlet valve is inserted into the upper side wall of the water tank part of the energy absorber, and the discharge valve is inserted into the lower side wall of the water tank part of the energy absorber. A filter is installed at one end of the inlet valve, an inlet pump is installed at one end of the filter, a discharge pump is installed at one end of the discharge valve, a liquid storage tank is installed at one end of the inlet pump and the discharge pump, and liquid level sensors are installed at both the upper and lower ends of the inner wall of the energy absorber.

[0008] Preferably, the vertical grid, compound grid body, energy absorber, brake belt, guide pulley, belt collection and pressing mechanism, damping conversion device and intelligent electrical control system are all installed on a concrete foundation.

[0009] Preferably, the vertical grid is formed by welding square tubes.

[0010] Preferably, the energy absorber is a water turbine structure.

[0011] Preferably, the belt taking-up and pressing mechanism comprises a base, a reduction motor is mounted on the top of the base, a belt taking-up wheel is mounted on the extended shaft of the reduction motor, and the belt taking-up wheel is connected to the energy absorber via a belt.

[0012] Preferably, the belt collecting and pressing mechanism further includes a belt pressing wheel, a tension spring and a spring fixing seat, the belt pressing wheel is close to the brake belt on the energy absorber, one end of the tension spring is connected to the belt pressing wheel, and the spring fixing seat is connected to the other end of the tension spring.

[0013] Preferably, the intelligent electrical control system includes a box, an AC contactor, a time relay, an intermediate relay, a phase sequence protector, a digital display, a PLC, a photoelectric converter, a signal light and a control button.

[0014] Beneficial Effects

[0015] The utility model provides a universal aircraft arresting device, which has the following beneficial effects compared with the prior art:

[0016] 1. Through the coordination of vertical grid, compound grid, energy absorber and damping conversion device, it can effectively stop the aircraft with a weight range of 5 to 80 tons;

[0017] 2. The damping conversion device is controlled through an intelligent electrical control system. The working fluid in the energy absorber is controlled through the damping conversion device to adjust the damping of the energy absorber. When intercepting aircraft weighing less than 40 tons and aircraft weighing more than 40 tons, the damping conversion device can be used to switch the working states of multiple energy absorbers in a short time;

[0018] 3. The motion of the grid is controlled by the remote control box of the intelligent electrical control system. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 The utility model is a schematic diagram of the left side structure of a universal aircraft arresting device.

[0020] Figure 2 The utility model is a three-dimensional schematic diagram of a damping conversion device of a universal aircraft arresting equipment.

[0021] Figure 3 The utility model is a schematic diagram of the main sectional structure of a damping conversion device of a universal aircraft arresting equipment.

[0022] Figure 4 The utility model is a schematic diagram of the main structure of the belt collecting part of the belt collecting and pressing structure of a universal aircraft arresting device.

[0023] Figure 5 The utility model is a schematic diagram of the main structure of the belt pressing part of the belt collecting and pressing structure of a universal aircraft arresting device.

[0024] Figure 6 The utility model is a working principle diagram of the neutral network of an intelligent electrical control system of a universal aircraft arresting equipment.

[0025] Figure 7 The utility model discloses a working principle diagram of damping conversion in an intelligent electrical control system of a universal aircraft arresting device.

[0026] In the figure: 1. vertical grid, 2. compound grid body, 3. energy absorber, 4. brake belt, 5. guide wheel, 6. belt collection and pressing mechanism, 601. belt collection wheel, 602. belt, 603. reduction motor, 604. base, 605. belt pressing wheel, 606. tension spring, 607. spring fixing seat, 7. damping conversion device, 701. liquid inlet valve, 702. liquid discharge valve, 703. filter, 704. liquid inlet pump, 705. liquid discharge pump, 706. liquid storage tank, 707. liquid level sensor, 8. intelligent electrical control system. DETAILED DESCRIPTION

[0027] Based on the embodiments of the present utility model, all other embodiments obtained by ordinary technicians in the field without making any creative work shall fall within the scope of protection of the present utility model.

[0028] Embodiment: Through the personnel in this field, all the electrical components in this case are connected to their adapted power supplies through wires, and a suitable controller should be selected according to the actual situation to meet the control requirements. The specific connection and control sequence should refer to the following working principle, and the electrical connection between the electrical components is completed in the working order. The detailed connection means are well-known technologies in this field. The following mainly introduces the working principle and process, and does not explain the electrical control.

[0029] A universal aircraft arresting device, comprising a vertical grid frame 1, a compound grid body 2, an energy absorber 3, a brake belt 4, a belt guide wheel 5, a belt collecting and pressing mechanism 6, a damping conversion device 7 and an intelligent electrical control system;

[0030] Specifically, the vertical grid 1 is arranged on both sides of the airport runway, the compound grid body 2 is connected to the vertical grid 1, the energy absorbers 3 are arranged on both sides of the airport runway in pairs, one end of the brake belt 4 is wound around the energy absorber 3, and the other end of the brake belt 4 passes through the guide pulley 5 and is connected to the compound grid body 2, and the damping conversion device 7 is connected to the energy absorber 3;

[0031] It should be noted that Figure 1The left side structure of the present technical solution is shown (the right side structure is arranged symmetrically with the left side structure). The vertical grid 11, the energy absorber 33, the guide wheel 5, the belt collection and pressing mechanism 66, the damping conversion device 77, and the intelligent electrical control system 8 are all installed on the concrete foundation according to their positions. The vertical grid 11 is made of square tubes welded together. The compound grid body 22 is connected between the vertical grids 11 on both sides of the airport runway. One end of the brake belt 44 is wrapped around the energy absorber 33, and the other end passes through the guide wheel 5 and is connected to the compound grid body 22. When the aircraft hits the net, after the nose and wheels pass through the net body, the wing drags the net body forward, the net body detaches from the vertical net mechanism, and the upper horizontal belt naturally falls on the upper part of the fuselage. The net body wraps the aircraft forward, and the net body pulls the brake belt 44 through the net belt connector. The brake belt 44 drives the energy absorber 33 to rotate to generate damping, thereby causing the aircraft to slow down to a stop.

[0032] Specifically, the damping conversion device 7 includes a liquid inlet valve 701 and a liquid discharge valve 702. The liquid inlet valve 701 is inserted into the upper side wall of the water tank portion of the energy absorber 3, and the liquid discharge valve 702 is inserted into the lower side wall of the water tank portion of the energy absorber 3. A filter 703 is installed at one end of the liquid inlet valve 701, a liquid inlet pump 704 is installed at one end of the filter 703, a liquid discharge pump 705 is installed at one end of the liquid discharge valve 702, and a liquid storage tank 706 is installed at one end of the liquid inlet pump 704 and the liquid discharge pump 705. Liquid level sensors 707 are installed at both the upper and lower ends of the inner wall of the energy absorber 3.

[0033] It should be noted that Figure 2-Figure 3 The damping conversion device 7 is shown, wherein the energy absorber 3 is a water turbine structure. The specific structure and working principle thereof can be referred to the energy absorption device and the energy absorption device in the aircraft arresting equipment with the publication number CN109110145B. The liquid is stored in the liquid storage tank 706. When it is necessary to intercept the aircraft, the liquid in the liquid storage tank 706 passes through the filter 703 and enters the energy absorber 3 through the opening of the liquid inlet pump 704 and the liquid inlet valve 701. The filter 703 is used to filter the impurities in the liquid to ensure the normal operation of the energy absorber 3. It works normally. When the liquid level sensor 707 located above the water tank in the energy absorber 3 detects that the liquid level has reached the highest value, the liquid inlet pump 704 and the liquid inlet valve 701 are closed, and the energy absorber 3 performs energy absorption work. When there is no need to intercept the aircraft, the liquid discharge pump 705 and the liquid discharge valve 702 are opened to make the liquid in the energy absorber 3 flow back into the liquid storage tank 706, so that the energy absorber 3 has no damping. When the liquid level sensor 707 located below the water tank in the energy absorber 3 detects that the liquid level has reached the lowest value, the liquid discharge pump 705 and the liquid discharge valve 702 are closed.

[0034] Figure 4The figure shows the belt collecting part in the belt collecting and pressing structure, the reduction motor 603 is fixed on the base 604, the belt collecting wheel 601 is installed on the extended shaft of the reduction motor 603, the belt 602 is installed on the belt collecting wheel 601, and the other end of the belt 602 is sleeved on the energy absorber 33. When the net body and the brake belt 44 move forward with the aircraft to a certain distance, the brake belt 44 is retracted by the operation of the reduction motor 603.

[0035] Figure 5 The figure shows the belt pressing part in the belt collecting and pressing structure, the belt pressing wheel 605 is close to the brake belt 44 of the energy absorber 33, one end of the tension spring 606 is fixed on the spring fixing seat 607, and the other end is connected to the belt pressing wheel 605. Under the action of the tension spring 606, the belt pressing wheel 605 applies a certain clamping force to the brake belt 44 of the energy absorber 33 to ensure that the brake belt 44 on the energy absorber 33 has no intermittent jumping during the movement.

[0036] Figure 6 This is the working principle diagram of the neutral network of the intelligent electrical control system. Figure 7 This is the working principle diagram of damping conversion in intelligent electrical control system. Intelligent electrical control system is divided into local control box and remote control box. Intelligent electrical control system is specially designed for the operation of aircraft arresting net, mainly composed of box, AC contactor, time relay, intermediate relay, phase sequence protector, digital display, PLC, photoelectric converter, signal light, control button, etc.

[0037] Here’s how it works:

[0038] 1. Power on: Connect 380V power supply to the U, V, W incoming line terminals, close the 0QF main switch, check the digital voltmeter PV and phase sequence protector BJ, observe whether the voltmeter displays the incoming line voltage and whether the phase failure protector alarms. If normal, proceed to the next operation.

[0039] 2. Control operation: The on-site control box and the remote tower control box are each equipped with a set of control operation buttons for erecting and releasing the net, energy absorption and drainage. The button switches with the same functions have the same operation level.

[0040] ① Left and right vertical grid: Before operation, close the sub-switches 1QF and 2QF to energize the main circuits of the left and right cubic grids.

[0041] Setting up the network: Press the network setting up button, the PLC central control system collects the button action signal, and immediately outputs the control signal to control the action of the intermediate relay, so that the coils of the network setting up main circuit contactors KM1 and KM3 are energized, the main contacts of the network setting up contactors KM1 and KM3 are connected, the network setting up motor runs forward, and the network setting up begins. When the grid touches the 85° stop travel switch SQ1 on the left and SQ5 on the right, the normally closed contacts of the travel switches SQ1 and SQ5 are disconnected, and the PLC controls the action of the intermediate relay to cut off the power supply to the network setting up main circuit contactors KM1 and KM3, and the network setting up is completed.

[0042] SQ2 on the left side of the 90° travel switch and SQ6 on the right side are limit protection switches. If the 85° travel switch is not cut off after the vertical net is in place, it will continue to run to SQ2 on the left side and SQ6 on the right side of the 90° travel switch. After the limit switch is actuated, the PLC is forced to stop the vertical net motor action output and perform secondary protective cutting.

[0043] Release the net: Press the release button, the PLC central control system collects the button action signal, immediately outputs the control signal, controls the intermediate relay to operate, energizes the coils of the release main circuit contactors KM2 and KM4, connects the release contactors KM2 and KM4, and the vertical release motor reverses to start releasing the net. During the release process, when the grid runs to the 6° left SQ3 and right SQ7 travel switch positions (normally closed contacts are disconnected), the PLC automatically controls the release to pause, and the pause time is the "Release 6° Delay Time Setting" (in milliseconds) on the "Parameter Setting" screen of the touch screen. After the pause time is reached, the release action continues to run. When the grid runs to the 0° travel switch SQ4 and SQ8 positions, the normally closed contacts of this switch are disconnected, and the PLC controls the intermediate relay to operate, respectively cut off the release main circuit contactors KM2 and KM4, and complete the release of the net.

[0044] Among them, the purpose of the system setting a 6° pause delay is to buffer the inertia of the continuous downward movement of the grid, reduce the impact force of the grid, and protect the equipment at the same time.

[0045] ② Add water and drain water to the left and right energy absorbers 3:

[0046] This device has an arresting force conversion function. By controlling one group (one on each side) of energy absorbers 3 to work, or two groups (all on the left and right sides) of energy absorbers 33 to work simultaneously, it can realize the load selection function of arresting aircraft of two weight groups of 5 to 40 tons and 40 to 80 tons.

[0047] When the weight of the arrested aircraft is 5 to 40 tons, only one set of energy absorbers 33 is needed to work. At this time, after pressing the 5 to 40 ton arresting button, the PLC controls the intermediate relay to energize the coils of the AC contactors KM6 and KM8, the main contact is connected, and an energy absorber 33 on each side starts to drain water.

[0048] When arresting an aircraft with a load of 41 to 80 tons, the 41 to 80 ton arresting button is pressed, and the PLC controls the intermediate relay to energize the coils of the AC contactors KM5 and KM7, the main contact is connected, and an energy absorber 33 on each side starts to add water.

[0049] Liquid level sensors 707 are installed at the upper and lower ends of the inner wall of the energy absorber 3. The liquid level sensor 707 uses a high-reliability electrode-type liquid level sensor 707 to detect the water level of each energy absorber 33 and transmit the water level signal to the PLC. It can realize the high and low water level automatic pump stop function during the operation of the liquid adding pump and the liquid discharging pump 705, and can monitor the water level status of each energy absorber 33 in real time, and has a water level alarm function.

[0050] At the same time, according to the selected different blocking loads of 5 to 40 tons or 41 to 80 tons, the intelligent electrical control system automatically monitors the water level based on the liquid level sensor 707 and intelligently controls the water adding and draining actions of the corresponding liquid adding pump and liquid draining pump 705 through the logical operation of the PLC.

[0051] ③Left and right net closing:

[0052] When the aircraft hits the net, the composite net body 22 is completely separated from the net and needs to be retrieved, so the net collection system needs to be activated.

[0053] In the electric control box, the 5QF circuit breaker switch is the power switch of the left and right net collecting main circuits. Turning on this switch connects the left and right net collecting main circuits and the left and right net collecting works. Turning off this switch turns off the net collecting work.

[0054] When the flight mission is completed, the composite net body 22 is released and restored to its original state, and then all control box power supplies are cut off and the box doors are locked to prevent non-professionals from operating and accidentally touching, ensuring that the control box is always in good condition.

[0055] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A universal aircraft arresting device, comprising a vertical grid frame (1), a compound grid body (2), an energy absorber (3), a brake belt (4), a belt guide wheel (5), and a belt collecting and pressing mechanism (6), characterized in that: It also includes a damping conversion device (7) and an intelligent electrical control system; (8) The vertical grid frame (1) is arranged on both sides of the airport runway, the compound grid body (2) is connected to the vertical grid frame (1), the energy absorbers (3) are arranged in pairs on both sides of the airport runway, one end of the brake belt (4) is wound around the energy absorber (3), and the other end of the brake belt (4) passes through the guide pulley (5) and is connected to the compound grid body (2), and the damping conversion device (7) is connected to the energy absorber (3); The damping conversion device (7) comprises a liquid inlet valve (701) and a liquid discharge valve (702); the liquid inlet valve (701) is inserted into the upper side wall of the water tank portion of the energy absorber (3); the liquid discharge valve (702) is inserted into the lower side wall of the water tank portion of the energy absorber (3); a filter (703) is installed at one end of the liquid inlet valve (701); a liquid inlet pump (704) is installed at one end of the filter (703); a liquid discharge pump (705) is installed at one end of the liquid discharge valve (702); a liquid storage tank (706) is installed at one end of the liquid inlet pump (704) and the liquid discharge pump (705); and liquid level sensors (707) are installed at both the upper and lower ends of the inner wall of the energy absorber (3).

2. A universal aircraft arresting device according to claim 1, characterized in that: The vertical grid frame (1), the compound grid body (2), the energy absorber (3), the brake belt (4), the belt guide wheel (5), the belt collection and pressing mechanism (6), the damping conversion device (7) and the intelligent electrical control system are all installed on a concrete foundation.

3. A universal aircraft arresting device according to claim 1, characterized in that: The vertical grid (1) is formed by welding square tubes.

4. A universal aircraft arresting device according to claim 1, characterized in that: The energy absorber (3) is a water turbine structure.

5. The universal aircraft arresting device according to claim 1, characterized in that: The belt taking-up and pressing mechanism (6) comprises a base (604), a reduction motor (603) is installed on the top of the base (604), a belt taking-up wheel (601) is installed on the extended shaft of the reduction motor (603), and the belt taking-up wheel (601) is connected to the energy absorber (3) via a belt (602).

6. A universal aircraft arresting device according to claim 5, characterized in that: The belt collecting and pressing mechanism (6) further comprises a belt pressing wheel (605), a tension spring (606) and a spring fixing seat (607), wherein the belt pressing wheel (605) is close to the brake belt (4) on the energy absorber (3), one end of the tension spring (606) is connected to the belt pressing wheel (605), and the spring fixing seat (607) is connected to the other end of the tension spring (606).

7. The universal aircraft arresting device according to claim 1, characterized in that: The intelligent electrical control system comprises a box, an AC contactor, a time relay, an intermediate relay, a phase sequence protector, a digital display, a PLC, a photoelectric converter, a signal lamp and a control button.

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