CN102991714B - Method for manipulating connecting channel - Google Patents
Method for manipulating connecting channel Download PDFInfo
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- CN102991714B CN102991714B CN201210485563.5A CN201210485563A CN102991714B CN 102991714 B CN102991714 B CN 102991714B CN 201210485563 A CN201210485563 A CN 201210485563A CN 102991714 B CN102991714 B CN 102991714B
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Abstract
The invention provides a method for manipulating a boarding bridge. The method comprises the following steps of: starting laser range finders to measure distances from a flexible framework to an airplane body, and when the boarding bridge stretches and advances towards the airplane vertically and approaches the airplane to be docked by a certain distance, temporarily stopping the motion of the boarding bridge approaching the airplane; controlling the deformation of the flexible framework by using the distances measured by the plurality of laser range finders and by actuators so as to make the deformed flexible framework achieve the same surface curvature as that of a casing of the airplane body to be docked; continuously controlling the boarding bridge to advance, and braking the boarding bridge when the distance measured by the laser range finder at the front end of a floor reaches a preset value; and controlling a winding mechanism to release an energy storage device by a controller so as to tightly press a docking framework to fit the casing of the airplane body. By utilization of the method for manipulating the boarding bridge, disclosed by the invention, the tightness and safety are improved.
Description
Technical field
The present invention relates to a kind of interface channel method of operating, be specifically related to a kind of Aerobridge manipulation method, particularly relate to a kind of be included in dock with aircraft before just can have the method for operating of the connecting bridge of the docking framework of the profile of coincideing with aircraft surfaces radian adaptively.
Background technology
Boarding bridge is the airfield equipment that a modern passenger aircraft usually uses, and they are used as the entrance of boarding, can enter passenger plane inside for passenger from terminal.This connecting bridge all has an awning device in its end usually, and it is connected across in the space between connecting bridge and aircraft, thus boarding personnel can be protected not to be subject to the impact of adverse weather condition.
Patent documentation CN100355628C discloses a kind of birdman's gangway or boarding bridge sealing arrangement, comprise one and be stretched in vestibule diaphragm above a connection floor, wherein said vestibule diaphragm has a flexible frame on one open end, be arranged at its other end place on a door-shaped frame be used for fixing on birdman's gangway or boarding bridge, wherein said flexible frame is fitted on airplane skin when described vestibule diaphragm stretches out, and be wherein provided with one for the operating control of described vestibule diaphragm, to launch or to close up described vestibule diaphragm, wherein said operating control comprises wind2 and by energy storage equipment, the brake ac-tuating mechanism that multi link is formed.Patent documentation CN100528688C discloses a kind of shelter device, for the connecting bridge of aircraft, comprises flexible frame, is arranged on an open end of this shelter device, for fitting to the shell of this aircraft when this shelter device launches; Door-shaped frame, is arranged on another open end of this awning device, for being connected to this connecting bridge; Extensible folding paulin, be connected across between this flexible frame and this door-shaped frame, and be connected to top and the both sides of this flexible cross-over connection and this door-shaped frame, also comprise at least two steering units independent of each other, for driving this shelter device launch and/or close up, described steering unit is made up of wind2 and single energy storage equipment.Patent documentation CN101910001A discloses a kind of kiss connection device for portable connecting bridge, comprising: charging portion, and it is attached to the end of the shelter of described portable connecting bridge and can injects air; And padded coaming, it is arranged in described charging portion, even and if described padded coaming still keeps solid shape when discharging air from described charging portion.Patent documentation US5267368A discloses a kind of boarding bridge awning device, and it uses actuator to promote collapsible docking framework and realizes and the docking of aircraft door.
Therefore can find out, prior art all have employed energy storage equipment usually when realizing awning device and docking with fuselage, and such as gas spring etc. and wind2 are with the use of, or hydraulic actuator, and document CN100355628C also uses multiple connecting rod or cantilever design; And in order to make docking framework fit tightly fuselage as far as possible, and the injury that minimizing awning device may cause for aircraft fuselage cover, adopt flexible frame more than docking framework of the prior art, especially document CN101910001A also adopts the gas filled device with padded coaming.But, the difference each other of aircraft is now all comparatively large, and the Curvature varying of its outline is also all comparatively large, particularly sometimes also there is very large bent angle in prow transitional region, make existing boarding bridge awning device be difficult to accurately fit on airplane skin, and then retain gap.These gaps are totally unfavorable under severe conditions, particularly sleety weather, are easy to cause moisture enter interior of aircraft or drench passenger, also may cause wet and slippery risk at connecting bridge or fuselage interior.By energy storage equipment or actuator in aforementioned documents, such as gas spring, hydraulic actuator promote the top of docking flexible frame, awning device is made to fit to fuselage cover, due in such cases, docking framework passive is pushed on fuselage, actuating structure is comparatively complicated on the one hand, and flexible frame is when in the face of multiple curvature thereof on the other hand, is usually also difficult to very closely fit on fuselage cover.Moreover in order to realize fitting tightly, gas spring, hydraulic actuator generally also need to provide comparatively high thrust, therefore unavoidable fuselage cover to be caused damage.
Document CN202379091U discloses a kind of boarding bridge pickup range finding sensing device, comprise the buffering sebific duct being arranged on front edge of airport pickup port end, described buffering sebific duct is provided with range finding sensing device, the side of described buffering sebific duct has exploration hole, and the sensor probe of described range finding sensing device and described exploration hole are just to setting.It is mainly used in the deformation extent reacting buffering sebific duct, and notice control system sends speed-slackening signal in time, prevents from causing greater impact to fuselage.But the deployed configuration that it adopts still belongs to conventional prior art, and it also cannot solve the problem.Document CN101287649B disclose a kind of by connecting bridge automatic butt to the method on hatch door, it adopts laser rangefinder and Computer Control Unit to realize the automatic butt of connecting bridge and aircraft door.Above-mentioned two sections of documents are still more single for the using method of laser rangefinder.
Therefore, column defects under connecting bridge ubiquity of the prior art: due to energy storage equipment or the actuator point of application single, flexible frame is difficult to adapt to various aircraft surfaces curvature, and alerting ability and leak tightness are all poor; And in order to fuselage cover that flexible frame is closely fitted, the power of usual applying is all larger, easy infringement fuselage cover, in addition because energy storage equipment or actuator are just started working usually after awning device touches fuselage cover, therefore easily because faults itself or system error cause overload, heavy damage fuselage cover; Lack passenger's boarding process to detect in real time and alarm device, there is potential safety hazard.
Summary of the invention
In order to overcome the problems referred to above, the invention provides a kind of method of operating of connecting bridge, described connecting bridge comprises scalable bridge body passageway and awning device, awning device comprises door-shaped frame, stereoplasm frame and flexible frame, jack and energy storage equipment is connected with between door-shaped frame and stereoplasm frame, stereoplasm frame and flexible frame are articulated with non-telescoping floor respectively, wherein flexible frame is articulated with ground front edge of board, and two, floor layer front end side end and flexible frame both sides branch are also respectively arranged with apomecometer; Multiple actuator is connected with between stereoplasm frame and flexible frame, actuator hinge-point in the every side branch of flexible frame and apomecometer attachment point in the vertical direction should interlock and come, it is characterized in that the method comprises the steps: to open the distance that described laser rangefinder measures flexible frame distance airframe, before connecting bridge vertically retractable aircraft and then when close to the aircraft certain distance that will dock, temporarily stop awning device near the motion of aircraft; The Distance geometry actuator utilizing multiple laser rangefinder measurement to obtain controls flexible frame distortion: the distance value that controller receives measured by apomecometer generates the fuselage cover arc curve that will dock, generate based on this curve and there is flexible frame position data after the distortion of aforementioned radian, determine each actuator stroke further, and activate described actuator accordingly, thus the flexible frame after being out of shape is made to have identical surface curvature with the fuselage cover that will dock; Continue to control awning device to advance, when the laser rangefinder measuring distance of ground front edge of board reaches predetermined value, braking connecting bridge; Controller controls winding mechanism release energy storage equipment, makes it that docking framework is closely pressed on fuselage cover.
Preferably, described certain distance is preferably 1 meter.
Preferably, described anticipated value is relevant relative to the installation site at flexible frame edge with apomecometer.
Preferably, if awning device is relative to fuselage cover generation deflection or disengaging in passenger's boarding process, controller can control warning device accordingly and give the alarm, and laser rangefinder again starts wind2 release energy storage equipment or primer fluid hydraulic actuator, until can measure distance reenter safe range.
Aerobridge manipulation method tool according to the present invention has the following advantages: (1) multiple apomecometer and actuator carry out yielding flexibility framework because the present invention utilizes, therefore, it is possible to adapt to various different aircraft surfaces curvature well, and can possess good leak tightness; (2) because docking framework of the present invention completed distortion before touching fuselage cover, therefore, it is possible to prevent actuator from transshipping due to faults itself or system error; (3) distance measuring sensor of the present invention can detect docking situation in real time, and gives the alarm, therefore safer.
Accompanying drawing explanation
Fig. 1 partially show the longitdinal cross-section diagram according to connecting bridge of the present invention.
Fig. 2 schematically simulates the mode of texturing of the flexible frame of the awning device in the present invention.
Detailed description of the invention
With reference to accompanying drawing 1, it partially show according to the retractable boarding bridge comprising roller of the present invention, it comprises scalable bridge body passageway and awning device 1, and this awning device 1 comprises door-shaped frame 2 and docking framework 3, and docking framework 3 is directly used in and realizes docking of awning device 1 and aircraft fuselage cover.The flexible frame 5 that docking framework 3 comprises stereoplasm frame 4 and directly will contact with fuselage cover, flexible frame 5 is made up of flexible material, but the ductility of this material is poor, such as plastics.Flexible frame surrounding also can comprise padded coaming, inflatable packer or elastic variable pipe etc. further.Door-shaped frame 2 is fixedly connected on floor layer 6.Described floor layer is the non-telescoping formula flaggy regularly that cannot change shape.Stereoplasm frame 4 is articulated with the floor layer 6 of awning device 1 pivotally, and uses energy storage equipment between door-shaped frame 2 and stereoplasm frame 6 and reclaim winding mechanism 8, and energy storage equipment can be such as gas spring 7.Flexible frame can be articulated with the front end on floor, but selects as a kind of, also can be fixedly installed on floor.In order to be added to open area, preferably, stereoplasm frame 4 and flexible frame also can be arranged on the lateral surface of floor layer.On each side, multiple actuator is connected with (in order to various fuselage surface curvature can be adapted between stereoplasm frame 4 and flexible frame 5, can accept in scope at cost, the quantity of actuator is preferably The more the better), such as hydraulic actuator 9, considers for simplification, in the present embodiment, the number of hydraulic actuator is three, and on even keel is arranged between stereoplasm frame 4 and flexible frame 5 respectively.These three actuators are preferably distributed on every side of flexible frame dispersedly, but the preferably the rarest top being arranged on every side branch of flexible frame in multiple actuator, be beneficial to the laminating of flexible frame and fuselage cover.Actuator one end and flexible frame 5 carry out hinged, and the other end is then hinged with stereoplasm frame 4.Two, floor layer front end side end (floor and flexible frame hinge-point below) and flexible frame 5 both sides branch are also respectively arranged with distance measuring sensor 10, this apomecometer can be such as ultrasonic range finder, infrared ambulator or laser rangefinder, prioritizing selection laser rangefinder in the present embodiment.The installation of apomecometer on flexible frame can adopt well-known conventional means, the form of support such as can be adopted to be arranged on flexible frame, and this laser rangefinder also can be arranged among the perforate on flexible frame 5, apomecometer can deflect along with flexible frame flexural deformation.Apomecometer quantity on flexible frame can identical from actuator quantity also can be different.The set laser rangefinder of floor layer front end can be arranged in the boring of floor layer front end.In an initial condition, distance measuring sensor 10 in the vertical direction that floor layer front end and flexible frame 5 are arranged should be alignment, and that is they should be arranged on same vertical straight line.Certainly, for the object of protection apomecometer, their edges slightly should retreat the edge in flexible frame or floor layer front end, can not cause shock like this when docking to apomecometer.Apomecometer in each branch of flexible frame is crisscross arranged relative to actuator, specifically, apomecometer should be tried one's best and is arranged at dispersedly on flexible frame, but should avoid being in very near the hinge-point of actuator on flexible frame, this use for apomecometer is very favourable, therefore described hinge-point often suffers stress, this is unsafe for apomecometer, consider it is also favourable from installing space in addition, simultaneously because they stagger installation, the infringement therefore for flexible frame is also less.The periphery in stereoplasm frame, space between flexible frame and door-shaped frame is equipped with awning.Awning device 1 also comprises the controller (not shown) being arranged on door-shaped frame 3 upper back, for receiving the signal and the operation of hydraulic control actuator 9 and winding mechanism 8 that laser rangefinder obtains, going back controller in addition and also controlling a warning device.Therefore this controller can have following function: when causing connecting bridge to tremble relative to airplane skin due to passenger's boarding, and then the warning passenger that gives the alarm when causing connecting bridge docking framework to depart from fuselage cover larger distance (being such as 10 centimetres) postpones action, and laser rangefinder again starts wind2 release energy storage equipment or primer fluid hydraulic actuator, until can measure distance reenter safe range (sounding all clear).
Introduce the method for operating of the awning device 1 in the present invention below in detail.
First, before awning device contacts with fuselage cover, the initial stage is used at connecting bridge, the laser rangefinder opened on awning device measures the distance of flexible frame distance airframe, connecting bridge vertically retractable aircraft advance (two apomecometers being arranged at floor layer leading section can be utilized, if their two distances measured are equal, connecting bridge just vertically aircraft advance is described), and when close to the aircraft certain distance that will dock, this distance is (because aircraft surfaces is arc line shaped, therefore the data of each laser rangefinder measurement are different, distance herein can be any one in laser rangefinder data of measuring) when can be arbitrary set point value between 0.5-5 rice, preferably 1 meter, temporary transient stopping connecting bridge is near the motion of aircraft, controller controls each actuator according to the distance value that each laser rangefinder measures and carries out respective stretching with yielding flexibility framework.Concrete operation method is as follows:
With reference to accompanying drawing 2, it schematically simulates the mode of texturing of the flexible frame of the awning device in the present invention.First utilizing the distance of the distance fuselage measured by the apomecometer on flexible frame and floor layer, generating the fuselage cover surface radian that will dock via controller simulation, as marked shown in 101; Because the flexible frame in the present invention is articulated with fixed type floor, therefore flexible frame position bottom remains unchanged after deformation, therefore according to the above-mentioned radian calculated, flexible frame after known distortion divides and prevaricates as marked as shown in 102 (translation radian 101, and in conjunction with flexible frame longitudinally height can draw); Because the stereoplasm frame 106 of simulation keeps motionless, and the hinge-point position of actuator on flexible frame is fixed, and flexible frame longitudinally extends negligible, and associated extension or the retracted length of the actuator therefore after distortion just can calculate.And then controller according to aforementioned calculated amount activate hydraulic actuator of the present invention can realize the flexible frame after being out of shape can have with will in conjunction with the identical radian of fuselage cover.Mark 103,104,105 in this figure flexible frame respectively in representative simulation, flexible after actuator and the actuator of initial position.In addition, in order to the distortion of flexible frame more accurately can be guaranteed, the present invention can also arrange auxiliary actuator (not shown) between actuator and stereoplasm frame, because the deflection angle of simulation actuator 104 in frame deformation process can calculate according to the method described above, auxiliary actuator therefore can be used according to calculated angle to deflect the actuator between flexible frame and stereoplasm frame.Described computation process can be completed by controller, and relevant mathematic calculation is all the common practise in affiliated field.
In this process, framework both sides independently operate, that is the distortion of flexible frame both sides can be different when needed, and this is for being very favorable during the corner that the appearance of hatch door periphery is larger, and therefore the present invention has very outstanding alerting ability in docking operation.And the actuator in the present invention just completed actuating before docking, therefore overload can not be there is due to the fault of self or because of control system error.
After this, namely continue to control connecting bridge to advance, and (the laser rangefinder measuring distance of stronghold front edge of board and comparing of anticipated value when moving closer to airframe, described anticipated value is relevant relative to the installation site at flexible frame edge with apomecometer) slow down connecting bridge speed of advance, until (the laser rangefinder measuring distance of stronghold front edge of board and comparing of anticipated value) brakes connecting bridge when flexible frame fits in fuselage cover.
Then controller controls winding mechanism release energy storage equipment, make it that docking framework is closely pressed on fuselage cover, because the flexible frame in the present invention is by actuator-operated distortion, therefore the energy storage equipment in the present invention, without the need to applying larger thrust in the prior art, therefore also just reduces the risk that awning device damages fuselage cover.
In passenger's boarding process, because the weight extruding of external conditions or passenger causes awning device relative to fuselage cover generation deflection or disengaging, because laser rangefinder can measure the change of distance, if therefore the distance of flexible frame and fuselage cover reaches a predetermined threshold (being such as 10 centimetres), controller can control warning device accordingly and give the alarm, and again start wind2 release energy storage equipment or primer fluid hydraulic actuator, until laser rangefinder can measure distance reenter safe range, sound all clear.
Because the engagement frame in the present invention was just provided with the surperficial radian of fuselage cover before laminating fuselage cover, therefore, it is possible to improve sealing property, reduce the hurtful risk of fuselage skin simultaneously.Also there is alarm in addition and again revise the advantage of laminating degree.What below do not elaborate is all the common practise in affiliated field.
Those skilled in the art can make replacement or modification according to content disclosed by the invention and the art technology grasped to content of the present invention; but these replacements or modification should not be considered as disengaging the present invention design, and these replacements or modification are all in the interest field of application claims protection.
Claims (1)
1. the method for operating of a connecting bridge, described connecting bridge comprises scalable bridge body passageway and awning device (1), awning device comprises door-shaped frame (2), stereoplasm frame (4) and flexible frame (5), jack (8) and energy storage equipment (7) is connected with between door-shaped frame (2) and stereoplasm frame (4), stereoplasm frame (4) and flexible frame (5) are articulated with non-telescoping floor (6) respectively, wherein flexible frame (5) is articulated with floor (6) front end, two, floor layer front end side end and flexible frame (5) both sides branch are also respectively arranged with laser rangefinder (10), multiple actuator (9) is connected with between stereoplasm frame (4) and flexible frame (5), actuator hinge-point in the every side branch of flexible frame and laser rangefinder attachment point in the vertical direction should interlock and come, it is characterized in that the method comprises the steps: to open the distance that described laser rangefinder measures flexible frame distance airframe, the distance that two laser rangefinders being arranged at floor layer leading section are measured is equal, connecting bridge just vertically aircraft advance is described, before connecting bridge vertically retractable aircraft and then when close to the aircraft certain distance that will dock, temporary transient stopping awning device is near the motion of aircraft, the Distance geometry actuator utilizing multiple laser rangefinder measurement to obtain controls flexible frame distortion: the distance value that controller receives measured by laser rangefinder generates the fuselage cover arc curve that will dock, generate based on this curve and there is flexible frame position data after the distortion of aforementioned radian, determine each actuator stroke further, and activate described actuator accordingly, thus the flexible frame after being out of shape is made to have identical surface curvature with the fuselage cover that will dock, continue to control awning device to advance, when the laser rangefinder measuring distance of ground front edge of board reaches predetermined value, braking connecting bridge, controller controls winding mechanism release energy storage equipment, makes it that docking framework is closely pressed on fuselage cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210485563.5A CN102991714B (en) | 2012-11-23 | 2012-11-23 | Method for manipulating connecting channel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210485563.5A CN102991714B (en) | 2012-11-23 | 2012-11-23 | Method for manipulating connecting channel |
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| Publication Number | Publication Date |
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| CN102991714A CN102991714A (en) | 2013-03-27 |
| CN102991714B true CN102991714B (en) | 2015-07-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210485563.5A Active CN102991714B (en) | 2012-11-23 | 2012-11-23 | Method for manipulating connecting channel |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| ES2412607B1 (en) * | 2013-05-06 | 2014-05-12 | Thyssenkrupp Airport Systems, S.A. | Stop system for the cockpit of aircraft and ships drive gateways |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3484883A (en) * | 1966-12-20 | 1969-12-23 | Aviolanda Maatschappij | End structure for airport gangways |
| US3641604A (en) * | 1970-05-27 | 1972-02-15 | Boothe Airside Services | Closure apparatus |
| DE3023885A1 (en) * | 1980-06-26 | 1982-01-14 | Trepel Ag, 6200 Wiesbaden | Bellows for aircraft access gangway - has sliding extension on guide rollers, with pivoted hydraulic ram and bumper |
| US5257431A (en) * | 1990-08-15 | 1993-11-02 | Bridgetech, Inc. | Airplane loading bridge |
| CN202379091U (en) * | 2011-11-07 | 2012-08-15 | 蒂森克虏伯机场系统(中山)有限公司 | Pickup and ranging sensing device for boarding bridge |
-
2012
- 2012-11-23 CN CN201210485563.5A patent/CN102991714B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3484883A (en) * | 1966-12-20 | 1969-12-23 | Aviolanda Maatschappij | End structure for airport gangways |
| US3641604A (en) * | 1970-05-27 | 1972-02-15 | Boothe Airside Services | Closure apparatus |
| DE3023885A1 (en) * | 1980-06-26 | 1982-01-14 | Trepel Ag, 6200 Wiesbaden | Bellows for aircraft access gangway - has sliding extension on guide rollers, with pivoted hydraulic ram and bumper |
| US5257431A (en) * | 1990-08-15 | 1993-11-02 | Bridgetech, Inc. | Airplane loading bridge |
| CN202379091U (en) * | 2011-11-07 | 2012-08-15 | 蒂森克虏伯机场系统(中山)有限公司 | Pickup and ranging sensing device for boarding bridge |
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| CN102991714A (en) | 2013-03-27 |
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