CN117657971A

CN117657971A - Emergency rescue device for aircraft in pipeline

Info

Publication number: CN117657971A
Application number: CN202311600641.6A
Authority: CN
Inventors: 毛凯; 韩树春; 屈旭; 赵明; 谭浩; 马果垒; 冉剑
Original assignee: Shanxi Provincial Laboratory Of High Speed Racing; Casic Feihang Technology Research Institute of Casia Haiying Mechanical and Electronic Research Institute
Current assignee: Shanxi Provincial Laboratory Of High Speed Racing; Casic Feihang Technology Research Institute of Casia Haiying Mechanical and Electronic Research Institute
Priority date: 2023-11-28
Filing date: 2023-11-28
Publication date: 2024-03-08

Abstract

The invention relates to the technical field of fault rescue and discloses an emergency rescue device for an aircraft in a pipeline. The device comprises a portal frame unit, a guide sliding shoe sleeve, a tank and a tank pushing unit, wherein the portal frame unit comprises a plurality of portal frames, the guide sliding shoe sleeve comprises a base, limiting plates arranged on the upper surface of the base in multiple directions and a plurality of universal wheels arranged on the lower surface of the base, the portal frames are used for lifting an aircraft, after the aircraft is lifted, the guide sliding shoe sleeve is arranged at the guide sliding shoe of the aircraft, and the tank pushing unit is used for pushing the tank to the position below the support sliding shoe at the bottom of the aircraft. Thereby, rescue in the aircraft pipeline can be achieved.

Description

Emergency rescue device for aircraft in pipeline

Technical Field

The invention relates to the technical field of fault rescue, in particular to an emergency rescue device for an in-pipeline aircraft.

Background

The craft of the pipeline magnetic levitation transportation system runs in the vacuum pipeline at a speed of more than 1000km/h, and the craft sailing stage comprises the processes of running, accelerating, supporting the guide wheel to retract, stabilizing the levitation sailing, decelerating, supporting the guide wheel to descend, and the like. In the navigation process, the aircraft possibly parks abnormally in the pipeline due to the reasons of support guide wheel faults, superconducting magnet quench and the like, and a rescue device in the pipeline is required to be designed for rescue of the fault aircraft, and the fault aircraft is pulled to a maintenance base, so that the fault and maintenance of the aircraft are conveniently conducted.

Similar rescue scenes and rescue equipment at home and abroad, including subway vehicle rescue, tramcar derailment rescue, high-speed railway rescue, heavy object carrying field and the like, and no rescue device for high-speed galloping in a pipeline exists. In the field of subway vehicle fault rescue, if wheels cannot rotate, a lifting and wheel lifting device scheme is adopted to rescue, a bogie axle is firstly lifted by using a hydraulic device, and then a pair of wheel lifting devices are respectively arranged on the failed wheels to replace the rotation of the failed wheels. The field of tramcar derailment rescue adopts a re-track rescue device to realize the re-track of the vehicle. The utility model provides a high-speed railway vehicle trouble rescue field provides a high-speed railway rescue hoist, and this hoist can travel on the high-speed railway, possesses the ability of rescuing to the trouble vehicle under the open-air environment. In the heavy object carrying industry, a carrying small tank is used for replacing a traditional roller pad bottom carrying mode, so that heavy object movement of tens of tons or even thousands of tons is realized.

However, the existing rescue device can only be used in fixed scenes, such as high-speed rail rescue and subway rescue. In addition, the existing rescue device has the problems that the operation space is limited, the aircraft cannot be jacked, personnel operation safety risks are high, environmental adaptability is poor and the like. That is, existing rescue equipment cannot hoist an aircraft within a pipeline, and there is no special rescue equipment for an aircraft skid shoe touchdown scenario after an aircraft landing gear failure.

Disclosure of Invention

The invention provides an in-pipeline aircraft emergency rescue device which can solve the technical problems in the prior art.

The invention provides an emergency rescue device for an in-pipeline aircraft, which comprises a portal frame unit, a guide shoe sleeve, a tank and a tank pushing unit, wherein the portal frame unit comprises a plurality of portal frames, the guide shoe sleeve comprises a base, limiting plates arranged on the upper surface of the base in multiple directions and a plurality of universal wheels arranged on the lower surface of the base, the portal frames are used for hoisting the aircraft, after the aircraft is hoisted, the guide shoe sleeve is arranged at the guide shoe of the aircraft, and the tank pushing unit is used for pushing the tank to the position below a support shoe at the bottom of the aircraft.

Preferably, the device further comprises a gantry transporting unit, the gantry transporting unit comprises a lifting module and a transporting vehicle, the lifting module comprises a plurality of jacks and a support, the jacks are arranged on the support, during transportation, the lifting module is arranged on the transporting vehicle, and the gantry is arranged on the jacks.

Preferably, the portal frame comprises a portal frame beam, a portal frame hanging point, a chain block, a portal frame supporting leg, a reinforced diagonal bracing base, a travelling wheel and a hand-operated screw rod, wherein the portal frame supporting leg is connected with the portal frame beam, the reinforced diagonal bracing base is connected with the portal frame supporting leg, the travelling wheel is connected with the reinforced diagonal bracing base, the hand-operated screw rod is arranged on the reinforced diagonal bracing base, the portal frame hanging point is arranged at the bottom of the portal frame beam and is matched with the position of the aircraft hanging point, and the chain block is arranged at the position of the portal frame hanging point.

Preferably, the portal frame hanging point is provided with a plurality of through holes, and a preset interval is reserved between every two adjacent through holes.

Preferably, the tank includes a vehicle body, limit baffles arranged in a plurality of directions on an upper surface of the vehicle body, and a plurality of wheels arranged on a lower surface of the vehicle body.

Preferably, the tank pushing unit comprises a limiting frame, a camera and a telescopic rod, wherein the telescopic rod is connected with the limiting frame, and the camera is arranged on the telescopic rod.

Preferably, the jack is a screw jack.

Preferably, the universal wheel is a bullseye bearing universal wheel.

Preferably, the wheels are PU wheels.

Through the technical scheme, the gantry crane which can be used in the pipeline can be used for hoisting the aircraft, so that the aircraft leaves the tubular beam supporting rail; and the tank is matched with the tank pushing unit, so that the tank is parked under the support skid shoe of the aircraft, and finally the guide skid shoe sleeve is arranged on the guide skid shoe of the aircraft, thereby realizing the lifting and moving of the aircraft in the limited space of the pipeline, and being matched with the comprehensive rescue vehicle or another aircraft, and realizing the rescue in the pipeline of the aircraft. The rescue device provided by the invention has the advantages of low cost, quick and effective rescue process, saving rescue time, reducing economic loss and providing quick rescue capability for the aircraft of the pipeline magnetic levitation transportation system.

Drawings

The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.

FIG. 1 shows a rescue schematic of an in-line aircraft emergency rescue device according to an embodiment of the invention;

FIG. 2 illustrates a gantry transport schematic of an in-line aircraft emergency rescue device according to an embodiment of the present invention;

FIG. 3 shows a schematic view of a gantry of an in-line aircraft emergency rescue device according to an embodiment of the invention;

FIG. 4 shows a schematic diagram of a tank of an in-pipeline aircraft emergency rescue device according to an embodiment of the present invention;

FIG. 5 shows a schematic diagram of a tank push-in unit of an in-pipeline aircraft emergency rescue device according to an embodiment of the present invention;

FIG. 6 shows a schematic view of a guide shoe sleeve of an in-line aircraft emergency rescue device according to an embodiment of the invention;

fig. 7 shows a schematic view of a lifting module of an in-line aircraft emergency rescue device according to an embodiment of the invention.

Detailed Description

It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

As shown in fig. 1, 2 and 6, an embodiment of the present invention provides an in-pipeline aircraft emergency rescue device, wherein the device includes a gantry unit, a guide shoe sleeve 201, a tank 202 and a tank pushing unit 203, the gantry unit includes a plurality of gantries (rescue gantry) 2, the guide shoe sleeve 201 includes a base, a plurality of directional limiting plates 601 disposed on the upper surface of the base, and a plurality of universal wheels 602 disposed on the lower surface of the base, a plurality of the gantries are used for lifting an aircraft 4, after the aircraft 4 is lifted, the guide shoe sleeve 201 is disposed at a guide shoe of the aircraft 4, and the tank pushing unit 203 is used for pushing the tank 202 below a support shoe at the bottom of the aircraft 4.

Specifically, after the aircraft is lifted, the guide shoe sleeve is arranged at the guide shoe of the aircraft and plays a guiding role in the moving process of the aircraft. The guide shoe sleeve can change the sliding friction of the aircraft in the rescue process into rolling friction, so that the friction resistance is reduced, and the aircraft and the guide rail are protected.

For example, the number of the portal frames 2 may be two, the number of the limiting plates 601 in multiple directions may be three, the number of the universal wheels 602 may be ten, the thickness of the guide shoe sleeve 201 may be 25mm, and the thickness is less than 30mm of the gap between the aircraft and the track.

The guide sliding shoes are hung on the guide sliding shoes through the limiting plates in three directions, so that the guide sliding shoes sleeve can be prevented from falling off in the moving process of the aircraft.

The emergency rescue device for the aircraft in the pipeline is suitable for fault scenes such as the grounding of the sliding shoes of the aircraft and the failure of the superconducting magnet, and solves the problem that the fault scenes such as the failure of the aircraft in the limited space of the pipeline, the grounding of the sliding shoes, and the like, cannot be rescue.

According to one embodiment of the present invention, as shown in fig. 2 and 7, the apparatus further comprises a gantry transporting unit including a lifting module 1 and a transporting vehicle 3, the lifting module 1 includes a plurality of jacks 701 and a bracket 702, the plurality of jacks 701 are disposed on the bracket 702, the lifting module 1 is disposed on the transporting vehicle 3 during transportation, and the gantry 2 is disposed on the jacks 701.

For example, the number of jacks may be four. The rescue portal frame can be transported to the fault stopping point of the aircraft from the overhaul base by utilizing the comprehensive rescue vehicle and the portal frame transporting unit. Wherein, the lifting module sets up on the transportation vehicle (for example, is located the on-vehicle freight train of comprehensive rescue car), fixes portal frame and lifting module through the bolt, and then the ground altitude of accessible jack adjustment portal frame is convenient for transport in the pipeline.

According to one embodiment of the present invention, as shown in fig. 3, the gantry 2 includes a gantry beam 301, a gantry suspension point 302, a chain block 303, a gantry leg 304, a reinforced diagonal support base 305, a travelling wheel 306, and a hand screw 307, wherein the gantry leg 304 is connected to the gantry beam 301, the reinforced diagonal support base 305 is connected to the gantry leg 304, the travelling wheel 306 is connected to the reinforced diagonal support base 305, the hand screw 307 is disposed on the reinforced diagonal support base 305, the gantry suspension point 302 is disposed at the bottom of the gantry beam 301 and is matched with the position of the aircraft suspension point, and the chain block 303 is disposed at the position of the gantry suspension point 302.

For example, after the rescue gantry is transported near the aircraft, it may be pushed over the aircraft suspension point. The rescue portal frame can be fixed on the escape passage in the pipeline through the hand-operated screw rod. The rescue portal frame does not need to use electricity, an operator lifts the aircraft through the chain block, and the rescue portal frame has the lifting capacity in the pipeline of the aircraft.

According to one embodiment of the invention, the portal frame 2 can be provided with 6 traveling wheels 306, and any traveling wheel fails and still has lifting capability. The hand-operated screw rod 307 can ensure that the position of the portal frame 2 is fixed on the escape passage of the pipeline 5.

According to one embodiment of the present invention, the gantry crane point 302 is provided with a plurality of perforations, and adjacent perforations are spaced apart by a predetermined distance.

The positions of the gantry hanging points 302 are matched with those of the aircraft hanging points, each gantry hanging point can be provided with 3 through holes, the preset distance between each through hole is 100mm, and therefore the positions of the chain blocks can be flexibly adjusted. The rated hoisting of the chain block 303 is 5T, and a single person can hoist the aircraft only by using a pulling force of 50N. The rescue portal frame 2 does not need electricity, and the problem that no power supply exists in a pipeline is solved.

According to one embodiment of the present invention, as shown in FIG. 4, the tank 202 includes a vehicle body, a plurality of stopper plates 401 provided in a plurality of directions on an upper surface of the vehicle body, and a plurality of wheels 402 provided on a lower surface of the vehicle body.

After the aircraft lifts by crane, can push the tank under the aircraft bottom sprag skid shoe, bear the weight of aircraft, realized the removal of aircraft in the pipeline.

For example, the tank 202 includes four directional limit stops 401 and 12 wheels 402. The limit baffle 401 of the tank 202 is matched with the mechanical interface of the support skid shoe of the aircraft, so that the tank 202 is prevented from slipping in the moving process. The single tank 202 is rated to carry 9T with a safety factor of 2.8.

According to an embodiment of the present invention, as shown in fig. 5, the tank pushing unit 203 includes a stopper 501, a camera 502, and a telescopic link 503, the telescopic link 503 is connected to the stopper 501, and the camera 502 is disposed on the telescopic link 503.

The tank pushing unit can push the tank into the bottom of the aircraft supporting skid shoe, the tank pushing position can be checked through the camera of the tank pushing unit, personnel are not required to enter the bottom of the aircraft, and the safety of rescue personnel is ensured.

Wherein, the limit frame 501 can ensure the transverse accuracy of the tank pushing; the camera 502 can be connected with an upper computer, and the pushing position of the tank can be monitored in real time. The telescopic rod 503 can be telescopic and disassembled for convenient storage.

According to one embodiment of the present invention, the jack 701 is a screw jack.

The screw jack can lift the portal frame 2 in a hand-shaking mode, and the lifting stroke is 130mm. In actual use, the lifting height of the portal frame 2 is more than 50mm, so that the escape channel of the pipeline 5 can be prevented from interfering with the transportation process of the portal frame 2.

According to one embodiment of the invention, the universal wheel 602 is a bullseye bearing universal wheel.

The bearing capacity of a single bullseye bearing universal wheel can reach 60kg.

According to one embodiment of the invention, the wheel 402 is a PU wheel.

The following describes the use procedure of the in-pipeline aircraft emergency rescue device according to the present invention with reference to an example:

1. the portal frame transportation unit and the portal frame 2 are hoisted into a vehicle-mounted cargo compartment of the comprehensive rescue vehicle at the overhaul base and are reliably fixed;

2. the operator operates the screw jack 701 to make the height of the portal frame 2 from the escape passage greater than 50mm;

3. the comprehensive rescue vehicle is driven to transport the portal frame 2 to the accident site of the aircraft in the pipeline;

4. the operator lowers the portal frame onto the escape passage and moves the portal frame to the position above the lifting point of the aircraft;

5. an operator fixes the portal frame 2 on the escape passage in the pipeline by hand-shaking the screw rod 307;

6. the portal frame 2 is connected with a hanging point of the aircraft;

7. an operator operates a chain block of the portal frame 2 to enable the lifting height of the aircraft to be about 150mm;

8. pushing the tank 202 under the bottom support skid shoe of the aircraft by using the tank pushing unit 203;

9. mounting the guide shoe sleeve 201 on the aircraft guide shoe;

10. lowering the aircraft above the tank 202, and withdrawing the rescue portal frame 2 and the tank push rod 203;

11. and dragging the fault aircraft to a maintenance base for maintenance by using the comprehensive rescue vehicle.

As can be seen from the above embodiments, the in-pipeline aircraft emergency rescue device according to the present invention has at least the following advantages:

1) The space required by rescue is small: the emergency rescue device can rescue in the pipeline, and the pipeline rescue clearance area is only 15 square meters. The distance between two sides of the aircraft and the guide rail of the U-shaped pipeline is only 30mm, and the guide shoe sleeve is only 25mm thick, so that the guidance of the aircraft rescue process can be realized.

2) The rescue speed is high: the emergency rescue device can reach an accident site 2km away from the overhaul base within 5 min. The rescue process only needs 30min, and the aircraft can be towed to the overhaul base for maintenance.

3) The rescue process does not need electricity: because no power supply exists near the accident site in the pipeline, the rescue portal frame disclosed by the invention adopts the chain block as a lifting device, and electricity is not required in the rescue process.

4) Rescue personnel safety: the tank pushing unit has the functions of video monitoring and telescoping, and after the aircraft is lifted, rescue can be carried out without personnel entering the bottom of the aircraft, so that the safety of the personnel is ensured.

In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.

The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an in-pipeline aircraft emergency rescue device, its characterized in that, the device includes portal frame unit, direction shoe cover (201), tank (202) and tank push unit (203), the portal frame unit includes a plurality of portal frames (2), direction shoe cover (201) include the base, set up limiting plate (601) and the setting of a plurality of directions at the base upper surface are in a plurality of universal wheels (602) of base lower surface, a plurality of the portal frame is used for lifting by crane the aircraft after lifting by crane the aircraft, direction shoe cover (201) set up the direction shoe department of aircraft, tank push unit (203) are used for with tank (202) push to the support shoe below of aircraft bottom.

2. The device according to claim 1, further comprising a gantry transport unit comprising a lifting module (1) and a transport vehicle (3), the lifting module (1) comprising a plurality of jacks (701) and a support (702), a plurality of the jacks (701) being arranged on the support (702), the lifting module (1) being arranged on the transport vehicle (3) during transport, the gantry (2) being arranged on the jacks (701).

3. The device according to claim 2, characterized in that the gantry (2) comprises a gantry beam (301), a gantry suspension point (302), a chain block (303), a gantry leg (304), a reinforcement diagonal support base (305), a travelling wheel (306) and a hand screw (307), the gantry leg (304) is connected with the gantry beam (301), the reinforcement diagonal support base (305) is connected with the gantry leg (304), the travelling wheel (306) is connected with the reinforcement diagonal support base (305), the hand screw (307) is arranged on the reinforcement diagonal support base (305), the gantry suspension point (302) is arranged at the bottom of the gantry beam (301) and is matched with the position of the aircraft suspension point, and the chain block (303) is arranged at the position of the gantry suspension point (302).

4. A device according to claim 3, characterized in that the gantry suspension point (302) is provided with a plurality of perforations, adjacent perforations being spaced apart by a predetermined distance.

5. The apparatus according to claim 4, wherein said tank (202) comprises a vehicle body, a plurality of directional stopper plates (401) provided on an upper surface of the vehicle body, and a plurality of wheels (402) provided on a lower surface of the vehicle body.

6. The apparatus according to claim 5, wherein the tank pushing unit (203) includes a stopper (501), a camera (502), and a telescopic link (503), the telescopic link (503) is connected to the stopper (501), and the camera (502) is disposed on the telescopic link (503).

7. The device according to any one of claims 2-6, wherein the jack (701) is a screw jack.

8. The device according to any one of claims 1-6, wherein the castor (602) is a bullseye bearing castor.

9. The apparatus of claim 5, wherein the wheel (402) is a PU wheel.