CN102991714A - Method for manipulating connecting channel - Google Patents
Method for manipulating connecting channel Download PDFInfo
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- CN102991714A CN102991714A CN2012104855635A CN201210485563A CN102991714A CN 102991714 A CN102991714 A CN 102991714A CN 2012104855635 A CN2012104855635 A CN 2012104855635A CN 201210485563 A CN201210485563 A CN 201210485563A CN 102991714 A CN102991714 A CN 102991714A
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- flexible frame
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- connecting bridge
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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 connecting bridge method of operating, relate in particular to a kind of method of operating that docks the connecting bridge that docks framework that just can have adaptively the profile of coincideing with the aircraft surfaces radian before with aircraft that is included in.
Background technology
Boarding bridge is the usual airfield equipment that uses of a modern passenger aircraft, and the entrance that they are used as boarding can enter passenger plane inside from terminal for the passenger.This connecting bridge all has an awning device usually in its end, it is connected across in the space between connecting bridge and the aircraft, thereby can protect the personnel of boarding 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 that one is stretched in the vestibule diaphragm of top, a connection floor, wherein said vestibule diaphragm has a flexible frame at the one open end, being arranged on one at its other end place is used for fixing on the door-shaped frame on birdman's gangway or the boarding bridge, wherein said flexible frame is fitted on the airplane skin when described vestibule diaphragm stretches out, and wherein be provided with an operating control for described vestibule diaphragm, launching or to close up described vestibule diaphragm, wherein said operating control comprises wind2 and by energy storage equipment, the brake actuation mechanism that many connecting rods consist of.Patent documentation CN100528688C discloses a kind of shelter device, is used for the connecting bridge of aircraft, comprises flexible frame, is arranged on an open end of this shelter device, is used for fitting to when this shelter device launches the shell of this aircraft; Door-shaped frame is arranged on another open end of this awning device, is used 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 flexibility cross-over connection and this door-shaped frame, also comprise at least two steering units independent of each other, for driving this shelter device expansion and/or closing up, described steering unit is made of wind2 and single energy storage equipment.Patent documentation CN101910001A discloses a kind of kiss connection device for portable connecting bridge, comprising: charging portion, its be attached to described portable connecting bridge shelter the end and can inject air; And padded coaming, it is arranged in the described charging portion, even and described padded coaming when from described charging portion, discharging air, still keep solid shape.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 that prior art is realizing that awning device has all adopted energy storage equipment usually when docking with fuselage, be used with wind2 such as gas spring etc., perhaps hydraulic actuator, document CN100355628C has also used a plurality of connecting rods or cantilever design; And in order to fit tightly fuselage so that dock framework as far as possible, and reduce the injury that awning device may cause for the airframe shell, adopt flexible frame more than the 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 now is all larger, and the curvature of its outline changes also all greatly, particularly sometimes also has very large bent angle in the prow transitional region, accurately fit on the airplane skin so that existing boarding bridge awning device is very difficult, and then retain the slit.These slits are totally unfavorable under mal-condition, and sleety weather particularly is easy to cause moisture to enter interior of aircraft or drenches the passenger, also may cause wet and slippery risk at connecting bridge or fuselage interior.Pass through energy storage equipment or actuator in the aforementioned documents, for example gas spring, hydraulic actuator promote the top of docking flexible frame, make awning device fit to fuselage cover, because in such cases, the docking framework is passive being pushed on the fuselage, actuating structure is comparatively complicated on the one hand, and flexible frame also is difficult to very closely fit on the fuselage cover in the face of multiple fuselage curvature the time usually on the other hand.Moreover in order to realize fitting tightly, gas spring, hydraulic actuator generally also need to provide than high thrust, therefore unavoidably fuselage cover are caused damage.
Document CN202379091U discloses a kind of boarding bridge pickup range finding sensing device, comprise the buffering sebific duct that is installed in the front edge of airport pickup port end, on the described buffering sebific duct range finding sensing device is installed, have exploration hole on one side of described buffering sebific duct, the sensor probe of described range finding sensing device and described exploration hole are over against setting.It is mainly used in reacting the deformation extent of buffering sebific duct, and in time notifies control system to send speed-slackening signal, prevents from fuselage is caused greater impact.But the deployed configuration that it adopts still belongs to conventional prior art, and it also can't address the above problem.Document CN101287649B discloses a kind of with the method for connecting bridge automatic butt to the hatch door, and it adopts laser rangefinder and Computer Control Unit to realize the automatic butt of connecting bridge and aircraft door.Above-mentioned two pieces of documents are still more single for the using method of laser rangefinder.
Therefore, column defects under the connecting bridge ubiquity of the prior art: because energy storage equipment or the actuator point of application are single, flexible frame is difficult to adapt to various aircraft surfaces curvature, and alerting ability and leak tightness are all relatively poor; And for fuselage cover that flexible frame is closely fitted, usually the power that applies is all larger, damage easily fuselage cover, in addition since energy storage equipment or actuator usually after awning device touches fuselage cover, just start working, therefore easily because faults itself or system's error cause overload, heavy damage fuselage cover; Lack passenger's process of boarding and detect in real time and alarm device, have 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, be connected with jack and energy storage equipment between door-shaped frame and the stereoplasm frame, stereoplasm frame and flexible frame are articulated in respectively non-telescoping floor, wherein flexible frame is articulated in the ground front edge of board, also is respectively arranged with apomecometer in two side ends of floor layer front end and the flexible frame both sides branch; Be connected with a plurality of actuators between stereoplasm frame and the flexible frame, actuator hinge-point in each 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 described laser rangefinder and measures flexible frame apart from the distance of airframe, vertically before retractable aircraft and then when approaching the aircraft certain distance that to dock, temporarily stop the motion of the close aircraft of awning device at connecting bridge; The distance and the distortion of actuator control flexible frame that utilize a plurality of laser rangefinders to measure: controller receives the measured distance value of apomecometer and generates the fuselage cover arc curve that will dock, generate flexible frame position data after the distortion with aforementioned radian based on this curve, further determine each actuator stroke, and activate accordingly described actuator, thereby so that the flexible frame after the distortion has identical surface curvature with the fuselage cover that will dock; Continue the control awning device and advance, when the laser rangefinder measuring distance of ground front edge of board reaches predetermined value, the braking connecting bridge; Controller control winding mechanism discharges energy storage equipment, makes it will dock framework and closely is pressed on fuselage cover.
Preferably, described certain distance is preferably 1 meter.
Preferably, described anticipated value is relevant with respect to the installation site at flexible frame edge with apomecometer.
Preferably, if awning device is with respect to fuselage cover generation deflection or disengaging in the passenger boards process, controller can be controlled accordingly warning device and give the alarm, and again start wind2 release energy storage equipment or primer fluid hydraulic actuator, until measuring distance, laser rangefinder reenters safe range.
Connecting bridge method of operating according to the present invention has following advantage: (1) therefore can adapt to well various aircraft surfaces curvature, and can possess good leak tightness because the present invention utilizes a plurality of apomecometers and actuator to be out of shape flexible frame; Therefore (2) because docking framework of the present invention had been finished distortion before touching fuselage cover, can prevent actuator because faults itself or system slip up transships; (3) distance measuring sensor of the present invention can detect the docking situation in real time, and gives the alarm, and is therefore safer.
Description of drawings
Fig. 1 has partly shown the longitdinal cross-section diagram according to connecting bridge of the present invention.
Fig. 2 has schematically simulated the mode of texturing of the flexible frame of the awning device among the present invention.
The specific embodiment
With reference to accompanying drawing 1, it has partly shown the retractable boarding bridge that comprises roller according to 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 realizes docking of awning device 1 and airframe shell.Docking framework 3 comprises stereoplasm frame 4 and the flexible frame 5 that will directly contact with fuselage cover, and flexible frame 5 is made by flexible material, but the ductility of this material is relatively poor, for example plastics.Also can comprise further padded coaming, inflatable packer or elastic variable pipe etc. around the flexible frame.Door-shaped frame 2 is fixedly connected on floor layer 6.Described floor layer is the non-telescoping formula flaggy regularly that can't change shape.4 of stereoplasm frames are articulated in the floor layer 6 of awning device 1 pivotally, and use energy storage equipment between door-shaped frame 2 and the stereoplasm frame 6 and reclaim winding mechanism 8, and energy storage equipment for example can be gas spring 7.Flexible frame can be articulated in the front end on floor, but as a kind of selection, also can be fixedly installed on the 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, be connected with a plurality of actuators between stereoplasm frame 4 and the flexible frame 5 (in order to adapt to various fuselage surface curvature, can accept in the scope at cost, the quantity of actuator is preferably The more the better), for example hydraulic actuator 9, consider for simplifying, in the present embodiment, the number of hydraulic actuator is three, and on even keel is arranged between stereoplasm frame 4 and the flexible frame 5 respectively.These three actuators are preferably on each side that is distributed in dispersedly flexible frame, but the rarest top that is arranged on each side branch of flexible frame preferably in a plurality of actuator is beneficial to the applying 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.Also be respectively arranged with distance measuring sensor 10 in two side ends of floor layer front end (floor and flexible frame hinge-point below) and the flexible frame 5 both sides branches, this apomecometer can for example be ultrasonic range finder, infrared ambulator or laser rangefinder, the preferential laser rangefinder of selecting in the present embodiment.The installation of apomecometer on flexible frame can be adopted well-known conventional means, for example can adopt the form of support to be installed on the flexible frame, and this laser rangefinder also can be arranged among the perforate on the flexible frame 5, and apomecometer can the deflection along with flexible frame flexural deformation.Apomecometer quantity on the flexible frame can be 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.Under initial condition, distance measuring sensor 10 in the vertical directions that arrange on floor layer front end and the flexible frame 5 should be alignments, that is to say that they should be arranged on the same vertical straight line.Certainly, for the purpose of protection apomecometer, their edges should slightly retreat in the edge of flexible frame or floor layer front end, can not cause bump to apomecometer like this when docking.Apomecometer in each branch of flexible frame is crisscross arranged with respect to actuator, specifically, apomecometer should be tried one's best and is arranged at dispersedly on the flexible frame, but should avoid being in the hinge-point of very close 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 also is favourable from installing space in addition, the simultaneously installation because they stagger, therefore also less for the infringement of flexible frame.Be equipped with awning around the periphery in the space between stereoplasm frame, flexible frame and the door-shaped frame.Awning device 1 also comprises the controller (not shown) that is arranged on door-shaped frame 3 rear upper lateral parts, be used for to receive signal that laser rangefinder obtains and the operation of control hydraulic actuator 9 and winding mechanism 8, goes back in addition controller and also controls a warning device.Therefore this controller can have following function: cause that when boarding owing to the passenger connecting bridge trembles with respect to airplane skin, and then give the alarm when causing the connecting bridge docking larger distance of framework detachment machine body shell (for example being 10 centimetres) and warn the passenger to postpone action, and again start wind2 release energy storage equipment or primer fluid hydraulic actuator, until measuring distance, laser rangefinder reenters safe range (sounding all clear).
The below at length introduces the method for operating of the awning device 1 among the present invention.
At first, at awning device with before fuselage cover contacts, use the initial stage at connecting bridge, the laser rangefinder of opening on the awning device is measured flexible frame apart from the distance of airframe, vertically advance towards retractable aircraft at connecting bridge and (can utilize two apomecometers that are arranged at the floor layer leading section, if the distance of their two measurements equates, illustrate that connecting bridge just vertically advances towards aircraft), and when approaching 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 data that measure in the laser rangefinder) in the time of can being the arbitrary set point value between the 0.5-5 rice, preferred 1 meter, temporarily stop connecting bridge near the motion of aircraft, the distance value that controller measures according to each laser rangefinder is controlled each actuator and is carried out separately flexible with the distortion flexible frame.Concrete operation method is as follows:
With reference to accompanying drawing 2, it has schematically simulated the mode of texturing of the flexible frame of the awning device among the present invention.At first utilize the measured distance apart from fuselage of apomecometer on flexible frame and the floor layer, generate the fuselage cover surface radian that will dock via the controller simulation, shown in mark 101; Because the flexible frame among the present invention is articulated in the fixed type floor, therefore flexible frame bottom position after distortion remains unchanged, therefore according to the above-mentioned radian that calculates, as can be known the flexible frame after the distortion divide and prevaricate shown in mark 102 like that (translation radian 101, and in conjunction with flexible frame vertically height can draw); Because it is motionless that the stereoplasm frame 106 of simulation keeps, and the hinge-point position of actuator on flexible frame fix, and the vertical extension of flexible frame can ignore, and therefore relevant elongation or the retracted length of the actuator after the distortion just can calculate.And then controller according to aforementioned calculated amount activate flexible frame after hydraulic actuator of the present invention can be realized being out of shape can have with will in conjunction with the identical radian of fuselage cover.Mark 103,104 among this figure, 105 is the flexible frame in the representative simulations, the actuator after flexible and the actuator of initial position respectively.In addition, in order more accurately to guarantee the distortion of flexible frame, the present invention can also arrange the auxiliary actuator (not shown) between actuator and stereoplasm frame, because the simulation deflection angle of actuator 104 in the frame deformation process can calculate according to the method described above, therefore can come actuator between deflection flexible frame and the stereoplasm frame according to the angle of calculating with auxiliary actuator.Described computation process can be finished by controller, and relevant mathematic calculation all is the common practise in affiliated field.
In this process, the framework both sides are independent operation respectively, the distortion that is to say the flexible frame both sides can be different when needed, and this is very favorable when larger corner occurring for the hatch door periphery, so the present invention has very outstanding alerting ability in docking operation.Therefore and the actuator among the present invention just finished actuating before docking, can not occur transshipping owing to the fault of self or because of the control system error.
After this, namely continuing the control connecting bridge advances, and (the laser rangefinder measuring distance of stronghold front edge of board and the comparison of anticipated value when moving closer to airframe, described anticipated value is relevant with respect to the installation site at flexible frame edge with apomecometer) the connecting bridge speed of advance that slows down, until flexible frame when fitting in fuselage cover (the laser rangefinder measuring distance of stronghold front edge of board and the comparison of anticipated value) brake connecting bridge.
Then controller control winding mechanism discharges energy storage equipment, make it will dock framework and closely be pressed on fuselage cover, because the flexible frame among the present invention is by actuator-operated distortion, therefore the energy storage equipment among the present invention need not to apply like that larger thrust in prior art, has therefore also just reduced the risk that awning device damages fuselage cover.
In the passenger boards process, because the extruding of external conditions or passenger's weight causes awning device with respect to fuselage cover generation deflection or disengaging, because laser rangefinder can measure the variation of distance, if therefore the distance of flexible frame and fuselage cover reaches a predetermined threshold (for example being 10 centimetres), controller can be controlled accordingly warning device and give the alarm, and again start wind2 and discharge energy storage equipment or primer fluid hydraulic actuator, reenter safe range until laser rangefinder can measure distance, sound all clear.
Because the engage frame among the present invention had just had the surperficial radian of fuselage cover before the applying fuselage cover, therefore can improve sealing property, reduced simultaneously the hurtful risk of fuselage skin.Also have in addition alarm and again revise the advantage of applying degree.What below do not elaborate all is the common practise in affiliated field.
Those skilled in the art can make replacement or modification to content of the present invention according to content disclosed by the invention and the art technology of grasping; but these replacements or modification should not be considered as breaking away from the present invention's design, and these replacements or modification are all in the claimed interest field of the present invention.
Claims (4)
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), be connected with jack (8) and energy storage equipment (7) between door-shaped frame (2) and the stereoplasm frame (4), stereoplasm frame (4) and flexible frame (5) are articulated in respectively non-telescoping floor (6), wherein flexible frame (5) is articulated in floor (6) front end, also is respectively arranged with apomecometer (10) in two side ends of floor layer front end and flexible frame (5) the both sides branch; Be connected with a plurality of actuators (9) between stereoplasm frame (4) and the flexible frame (5), actuator hinge-point in each 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 described laser rangefinder and measures flexible frame apart from the distance of airframe, vertically before retractable aircraft and then when approaching the aircraft certain distance that to dock, temporarily stop the motion of the close aircraft of awning device at connecting bridge; The distance and the distortion of actuator control flexible frame that utilize a plurality of laser rangefinders to measure: controller receives the measured distance value of apomecometer and generates the fuselage cover arc curve that will dock, generate flexible frame position data after the distortion with aforementioned radian based on this curve, further determine each actuator stroke, and activate accordingly described actuator, thereby so that the flexible frame after the distortion has identical surface curvature with the fuselage cover that will dock; Continue the control awning device and advance, when the laser rangefinder measuring distance of ground front edge of board reaches predetermined value, the braking connecting bridge; Controller control winding mechanism discharges energy storage equipment, makes it will dock framework and closely is pressed on fuselage cover.
2. the method for operating of connecting bridge according to claim 1 is characterized in that described certain distance is preferably 1 meter.
3. the method for operating of connecting bridge according to claim 1 and 2 is characterized in that described anticipated value is relevant with respect to the installation site at flexible frame edge with apomecometer.
4. the method for operating of any described connecting bridge according to claim 1-3, it is characterized in that if awning device is with respect to fuselage cover generation deflection or disengaging in the passenger boards process, controller can be controlled accordingly warning device and give the alarm, and again start wind2 release energy storage equipment or primer fluid hydraulic actuator, until measuring distance, laser rangefinder reenters safe range.
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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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| 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 true CN102991714A (en) | 2013-03-27 |
| CN102991714B 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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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260898A (en) * | 2013-05-06 | 2015-01-07 | 蒂森克虏伯机场系统股份有限公司 | Stopping System For A Cab Of Boarding Bridges For Accessing Aircraft And Ships |
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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260898A (en) * | 2013-05-06 | 2015-01-07 | 蒂森克虏伯机场系统股份有限公司 | Stopping System For A Cab Of Boarding Bridges For Accessing Aircraft And Ships |
| CN104260898B (en) * | 2013-05-06 | 2018-05-15 | 蒂森克虏伯机场系统股份有限公司 | Pass in and out the braking system in the cabin of the connecting bridge of aircraft or ship |
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| CN102991714B (en) | 2015-07-15 |
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