CN102991709A - Method for stretching folding shed - Google Patents
Method for stretching folding shed Download PDFInfo
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- CN102991709A CN102991709A CN2012104850928A CN201210485092A CN102991709A CN 102991709 A CN102991709 A CN 102991709A CN 2012104850928 A CN2012104850928 A CN 2012104850928A CN 201210485092 A CN201210485092 A CN 201210485092A CN 102991709 A CN102991709 A CN 102991709A
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- vestibule diaphragm
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Abstract
The invention provides a method for stretching a folding shed. The method comprises the following steps of: starting laser distance measuring instruments to measure distances from a flexible frame to the body of an airplane; advancing an aerobridge perpendicular to the airplane and temporarily stopping the motion of the aerobridge for approaching the airplane to be butted when the aerobridge is at a certain distance away from the airplane; measuring the obtained distance by using the distances measured by the plurality of laser distance measuring instruments and an actuator, controlling the deformation of the flexible frame, thereby guaranteeing that the deformed flexible frame and the shell of the airplane body to be butted have the same surface curvature; continuously controlling the aerobridge to advance and braking the aerobridge when the distance measured by the laser distance measuring instrument at the front end of a floor reaches a predetermined value; and controlling a winding mechanism to release an energy storage device by a controller, so as to tightly press a butting frame on the shell of the airplane body. By using the method for stretching the folding shed, the sealing property and the safety are improved.
Description
Technical field
The present invention relates to a kind of method of launching vestibule diaphragm, relate in particular to a kind of method of deploying that docks the vestibule diaphragm 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 a vestibule diaphragm 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 vestibule diaphragm 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 connecting bridge vestibule diaphragm 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 the vestibule diaphragm 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 the vestibule diaphragm 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 connecting bridge vestibule diaphragm 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 the vestibule diaphragm 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 vestibule diaphragm 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 the vestibule diaphragm 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 vestibule diaphragm device, described vestibule diaphragm device comprises door-shaped frame and docking framework, 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 non-telescoping floor, flexible frame is fixed in the ground front edge of board, also be respectively arranged with apomecometer in two sidepieces of floor layer front end and the stereoplasm frame both sides branch, be connected with a plurality of actuators between stereoplasm frame and the flexible frame; The lateral branching of described stereoplasm frame will be wider than the lateral branching of flexible frame on width, apomecometer on the stereoplasm frame is installed on the described width that has more, 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 vestibule diaphragm device at the vestibule diaphragm 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 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 control vestibule diaphragm 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 the vestibule diaphragm 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.
Vestibule diaphragm 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 vestibule diaphragm device of the present invention;
Fig. 2 has schematically shown the installation relation of actuator and apomecometer;
Fig. 3 has schematically simulated the mode of texturing of the flexible frame of the vestibule diaphragm device among the present invention.
The specific embodiment
With reference to accompanying drawing 1, shown wherein that according to vestibule diaphragm device 1 of the present invention this vestibule diaphragm device 1 comprises door-shaped frame 2 and docking framework 3, docking framework 3 is directly used in realizes docking of vestibule diaphragm 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 vestibule diaphragm device 1 pivotally, and stereoplasm frame 4 also can comprise the shutoff device that can stop its pivot; And use energy storage equipment between door-shaped frame 2 and the stereoplasm frame 6 and reclaim winding mechanism 8, energy storage equipment for example can be gas spring 7.Flexible frame can be fixedly installed on the floor, but as a kind of selection, also can be articulated in the front end 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, 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 four, and on even keel is arranged between stereoplasm frame 4 and the flexible frame 5 respectively.These four actuators are preferably on each side that is distributed in dispersedly stereoplasm frame, but the rarest top that is arranged on each side branch of stereoplasm 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 11,10 in two sidepieces of floor layer front end and the stereoplasm frame 4 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 apomecometer that two sidepieces of floor layer front end are installed is very favourable for the later stage docking.The installation of apomecometer on stereoplasm frame 4 can be adopted well-known conventional means, for example can adopt the form of support to be installed on the stereoplasm frame 4, and this laser rangefinder also can be arranged among the perforate on the stereoplasm frame 4.Apomecometer quantity on the stereoplasm frame 4 can be identical from actuator quantity also can be different.The set laser rangefinder of floor layer front end sidepiece can be arranged in the boring of floor layer front end.Their setting position is such as schematically shown in Figure 2, the lateral branching of stereoplasm frame 4 outline on width is wider than flexible frame 5, actuator attachment point and apomecometer attachment point stagger at the width of framework branch like this, thereby so that flexible frame can not stop the light of apomecometer, if certainly the actuator attachment point on the stereoplasm frame is drawn a straight line, the words that the apomecometer attachment point also draws a straight line, these two straight lines also should be tried one's best close, are beneficial to the radian simulation in later stage.Except the bottom, apomecometer also should disperse (being preferably evenly) that (because the floor is equipped with apomecometer, so need not to install near the stereoplasm frame bottom) is installed again on stereoplasm frame as far as possible, is beneficial to obtain accurately the surperficial radian of fuselage cover.Apomecometer on the stereoplasm frame should be on the same vertical curve.Be equipped with vestibule diaphragm around the periphery in the space between stereoplasm frame, flexible frame and the door-shaped frame.Vestibule diaphragm 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, and controller is also controlled a warning device in addition.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 vestibule diaphragm device 1 among the present invention.
At first, at the vestibule diaphragm device with before fuselage cover contacts, use the initial stage at connecting bridge, the laser rangefinder of opening on the vestibule diaphragm 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 (can be obtained by the apomecometer that is arranged at the floor layer leading section) is 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 3, it has schematically simulated the mode of texturing of the flexible frame of the vestibule diaphragm device among the present invention.At first utilize the measured distance apart from fuselage of apomecometer on stereoplasm frame and the floor layer (distance that laser rangefinder 11 measures should add when initial between the apomecometer 10 and 11 distance in the horizontal direction), 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 fixedly connected on the floor, therefore flexible frame bottom position after distortion remains unchanged, therefore according to the above-mentioned radian that calculates, flexible frame after the distortion divides and prevaricates shown in mark 102 like that (translation radian 101, and can draw in conjunction with the initial vertically height of flexible frame) as can be known; 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 and comformability 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 the vestibule diaphragm device damages fuselage cover.
In the passenger boards process, because the extruding of external conditions or passenger's weight causes the vestibule diaphragm 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 deploying of a vestibule diaphragm device, comprise door-shaped frame (2) and docking framework (3), it is characterized in that 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 non-telescoping floor (6), flexible frame (5) is fixed in floor (6) front end, also be respectively arranged with apomecometer (10 in two sidepieces of floor layer front end and stereoplasm frame (4) the both sides branch, 11), be connected with a plurality of actuators (9) between stereoplasm frame (4) and the flexible frame (5); The lateral branching of described stereoplasm frame (4) will be wider than the lateral branching of flexible frame (5) on width, apomecometer on the stereoplasm frame is installed on the described width that has more, 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 vestibule diaphragm device at the vestibule diaphragm 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 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 control vestibule diaphragm 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 vestibule diaphragm device according to claim 1 is characterized in that described certain distance is preferably 1 meter.
3. the method for deploying of vestibule diaphragm 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 vestibule diaphragm device according to claim 1-3, it is characterized in that if the vestibule diaphragm 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210485092.8A CN102991709B (en) | 2012-11-23 | 2012-11-23 | Method for stretching folding shed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210485092.8A CN102991709B (en) | 2012-11-23 | 2012-11-23 | Method for stretching folding shed |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102991709A true CN102991709A (en) | 2013-03-27 |
| CN102991709B CN102991709B (en) | 2015-07-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210485092.8A Active CN102991709B (en) | 2012-11-23 | 2012-11-23 | Method for stretching folding shed |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3484883A (en) * | 1966-12-20 | 1969-12-23 | Aviolanda Maatschappij | End structure for airport gangways |
| 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 |
-
2012
- 2012-11-23 CN CN201210485092.8A patent/CN102991709B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3484883A (en) * | 1966-12-20 | 1969-12-23 | Aviolanda Maatschappij | End structure for airport gangways |
| 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 |
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| CN102991709B (en) | 2015-07-15 |
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