CN102963541A - Butting method for sealing device - Google Patents
Butting method for sealing device Download PDFInfo
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- CN102963541A CN102963541A CN2012104826613A CN201210482661A CN102963541A CN 102963541 A CN102963541 A CN 102963541A CN 2012104826613 A CN2012104826613 A CN 2012104826613A CN 201210482661 A CN201210482661 A CN 201210482661A CN 102963541 A CN102963541 A CN 102963541A
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Abstract
The invention discloses a butting method for a sealing device and provides an expanding method of an awning method. The expansion method comprises the following steps: laser distance meters are started to measure the distance from a flexible frame to an airframe of an airplane, when a boarding bridge moves towards the airplane in the vertical direction and approaches to the airplane to be butted with in a certain distance, the boarding bridge is temporally stopped from being close to the airplane; the flexible frame is controlled to be deformed by utilizing the distance measured by the multiple laser distance meters and actuators, and the deformed flexible frame is enabled to have the same curvature of the airplane skin to be butted; the boarding bridge is controlled to continuously move forwards, and when the laser distance meter at the front end of a floor measures that the distance reaches the preset value, the boarding bridge is braked; and a controller controls a winding mechanism to release an energy storage device, so that a butting frame is enabled to be tightly pressed on the airplane skin in a fitting manner through the energy storage device. With the adoption of the expanding method for the awning device, the air tightness and safety are improved.
Description
Technical field
The present invention relates to a kind of docking calculation of sealing arrangement, be specifically related to a kind of awning device method of deploying, relate in particular to a kind of method of deploying that docks the awning device 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 awning device method of deploying 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 deploying of awning device, described awning device comprises door-shaped frame, docking framework and Telescopic floor board, Telescopic floor board comprises the scalable section that is positioned at front end, this scalable is utilized the first actuator to realize stretching, described docking framework comprises stereoplasm frame and flexible frame, be connected with jack and energy storage equipment between door-shaped frame and the stereoplasm frame, stereoplasm frame is articulated in the floor, flexible frame is articulated in scalable front end, also is respectively arranged with apomecometer in two side ends of scalable front end of floor layer and the flexible frame both sides branch; Be connected with a plurality of the second 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 aircraft and then when approaching the aircraft certain distance that to dock, temporarily stop the motion of the close aircraft of awning device at awning device; 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 the first actuator and each second actuator stroke, and activate accordingly described the first and second actuators, 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.
Awning device method of deploying 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 is the longitdinal cross-section diagram according to awning device 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, shown wherein that according to awning device 1 of the present invention this awning device 1 comprises door-shaped frame 2 and docking framework 3, 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.Awning device also further comprises floor layer 6, wherein this floor layer is a kind of telescoping floor, it comprises one scalable 11, this scalable utilization for example is in the actuator of floor layer inside, for example hydraulic actuator 12 is realized fore and aft motion, this hydraulic actuator 12 is arranged at of floor layer midway location, also can be to be arranged at respectively two of two ends, and can certainly be other quantity.Door-shaped frame 2 is fixedly connected on floor layer 6.4 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 scalable 11 the front end on floor, but as a kind of selection, also can be fixedly installed on this expansion 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 herein is three, and on even keel is arranged between stereoplasm frame 4 and the flexible frame 5 respectively.These three actuators preferably are distributed on each side of flexible frame dispersedly, 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 the front end that floor layer is scalable 11 (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 installation site in each branch of flexible frame is crisscross arranged with respect to the actuator articulated position, 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 for example is arranged on door-shaped frame 3 rear upper lateral parts, be used for to receive signal that laser rangefinder obtains and control hydraulic actuator 9,12 and the operation of winding mechanism 8, go back in addition controller and also control 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 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 (comprising the whole apomecometers and the actuator that are arranged on floor layer and the flexible frame) and is carried out separately flexible with the distortion flexible frame.
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; Then to this arc curve of docking framework translation (because floor only horizontal extension) until put 107 intersection location on this camber line and the flexible frame, in fact this point is can be optional, for example be flexible frame mid point or 2/3rds At The Heights, preferred mode is to save the momentum of doing of actuator as far as possible.Therefore can learn that according to the length (because its extensibility is poor, ignoring spread length herein) of flexible frame branch the flexible frame after the distortion should be shown in mark 102 like that.And then after the distortion, (stereoplasm frame 106 of simulation keeps motionless) elongation or retracted length of associated actuator just can calculate.Subsequently 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, independent operation can be distinguished in the framework both sides, 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 (according to the laser rangefinder measuring distance of scalable the front end in floor 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 release energy storage equipment or primer fluid hydraulic actuator, until measuring distance, laser rangefinder reenters safe range.
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 deploying of an awning device, described awning device comprises door-shaped frame (2), docking framework (3) and Telescopic floor board (6), Telescopic floor board (6) comprises scalable (11) that are positioned at front end, this scalable is utilized the first actuator (12) to realize stretching, described docking framework (3) comprises 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) is articulated in floor (6), flexible frame (5) is articulated in scalable (11) front end, also is respectively arranged with apomecometer (10) in floor layer two side ends of scalable (11) front end and flexible frame (5) the both sides branch; Be connected with a plurality of the second 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 aircraft and then when approaching the aircraft certain distance that to dock, temporarily stop the motion of the close aircraft of awning device at awning device; 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 the first actuator and each second actuator stroke, and activate accordingly described the first and second actuators, 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 deploying of awning device according to claim 1 is characterized in that described certain distance is preferably 1 meter.
3. the method for deploying of awning device 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 deploying of any described awning device 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 |
|---|---|---|---|
| CN201210482661.3A CN102963541B (en) | 2012-11-23 | 2012-11-23 | Butting method for sealing device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210482661.3A CN102963541B (en) | 2012-11-23 | 2012-11-23 | Butting method for sealing device |
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| CN102963541A true CN102963541A (en) | 2013-03-13 |
| CN102963541B CN102963541B (en) | 2015-02-25 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104139864A (en) * | 2013-05-08 | 2014-11-12 | 深圳中集天达空港设备有限公司 | Awning device, boarding bridge and control method of awning device |
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| US3484883A (en) * | 1966-12-20 | 1969-12-23 | Aviolanda Maatschappij | End structure for airport gangways |
| US5257431A (en) * | 1990-08-15 | 1993-11-02 | Bridgetech, Inc. | Airplane loading bridge |
| US20030057360A1 (en) * | 1999-11-09 | 2003-03-27 | Nils-Eric Anderberg | Method and apparatus for positioning one end of a movable bridge in relation to a door of a craft |
| CN101148201A (en) * | 2006-09-22 | 2008-03-26 | 中国国际海运集装箱(集团)股份有限公司 | Awning device and its control method and embarking bridge with the awning device |
| 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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2012
- 2012-11-23 CN CN201210482661.3A patent/CN102963541B/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 |
| US5257431A (en) * | 1990-08-15 | 1993-11-02 | Bridgetech, Inc. | Airplane loading bridge |
| US20030057360A1 (en) * | 1999-11-09 | 2003-03-27 | Nils-Eric Anderberg | Method and apparatus for positioning one end of a movable bridge in relation to a door of a craft |
| CN101148201A (en) * | 2006-09-22 | 2008-03-26 | 中国国际海运集装箱(集团)股份有限公司 | Awning device and its control method and embarking bridge with the awning device |
| 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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104139864A (en) * | 2013-05-08 | 2014-11-12 | 深圳中集天达空港设备有限公司 | Awning device, boarding bridge and control method of awning device |
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