CN103253377A - Method for curved docking with airplanes - Google Patents
Method for curved docking with airplanes Download PDFInfo
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- CN103253377A CN103253377A CN2013100667862A CN201310066786A CN103253377A CN 103253377 A CN103253377 A CN 103253377A CN 2013100667862 A CN2013100667862 A CN 2013100667862A CN 201310066786 A CN201310066786 A CN 201310066786A CN 103253377 A CN103253377 A CN 103253377A
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Abstract
The invention provides a method for curved docking with airplanes. The method includes the steps: turning on a laser distance meter to meter the distance between a flexible framework and an airframe, and when an aerobridge advances vertically towards an airplane and approaches to the airplane to be docked by a certain distance, temporarily discontinuing the movement of the aerobridge approaching to the airplane; controlling the flexible framework to deform by the aid of the metered distances of multiple laser distance meters and an actuator, and enabling the deformed flexible framework and a shell of the airframe to be docked to have the same surface curvature; continuing to control the aerobridge to advance, and when the metered distance of the laser distance meter of the flexible frame reaches a preset value, braking the aerobridge; according to a distance meter on an extensible floor section, controlling a first actuator to enable the extensible floor section to extend to be laminated with the shell of the airframe; and controlling a winding mechanism to release an energy storage device by a controller so as to closely laminate the docking framework to the shell of the airframe. By the aid of the canopy device unfolding method, sealability and safety are improved.
Description
Technical field
The present invention relates to a kind of method of docking with the aircraft bending, 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 the profile of coincideing with the aircraft surfaces radian before adaptively with aircraft that is included in.
Background technology
The aircraft boarding bridge is the usual airfield equipment that uses of a modern passenger aircraft, and they are used as the entrance of boarding, and can enter passenger plane inside from terminal for the passenger.This connecting bridge all has an awning device usually in its end, in the space of its cross-over connection between connecting bridge and aircraft, thereby can protect the personnel of boarding not to be subjected to the influence of adverse weather condition.
Patent documentation CN100355628C discloses a kind of birdman's gangway or aircraft 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 aircraft 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 constitute.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 tipping for portable connecting bridge and has put, and comprising: charging portion, its be attached to described portable connecting bridge shelter the end and can inject air; With the buffering material, 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 awning device, and it uses actuator to promote collapsible butt joint framework and realizes and the docking of aircraft door.
Therefore as can be seen, prior art is realizing that awning device has all adopted energy storage equipment usually when docking with fuselage, and for example gas spring etc. is used with wind2, perhaps hydraulic actuator, and document CN100355628C has also used a plurality of connecting rods or cantilever design; And in order to make the butt joint framework fit tightly fuselage as far as possible, and reduce the injury that awning device may cause for the airframe shell, adopt flexible frame more than the butt joint framework of the prior art, especially document CN101910001A also adopts the gas filled device that has padded coaming.But, the difference each other of aircraft now is all bigger, and the curvature of its outline changes also all greatly, particularly also has very big bent angle in the prow transitional region sometimes, make that existing connecting bridge awning device is difficult to accurately fit on the airplane skin, 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 butt joint flexible frame, make awning device fit to fuselage cover, because in such cases, the butt joint framework is passive being pushed on the fuselage, on the one hand actuating structure is comparatively complicated, 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 connecting bridge range finding sensing device that picks, comprise the buffering sebific duct that is installed in mouthful end that picks, 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, the following defective of 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 bigger, damage fuselage cover easily, in addition since energy storage equipment or actuator after awning device touches fuselage cover, just start working usually, 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, butt joint framework and scalable floor, scalable floor comprises the scalable portion that is positioned at front end, this scalable is utilized first actuator to realize stretching, described butt joint framework comprises stereoplasm frame and flexible frame, the height of flexible frame is greater than the height of stereoplasm frame, be connected with jack and energy storage equipment between door-shaped frame and the stereoplasm frame, stereoplasm frame is articulated in the outside, floor; Be connected with a plurality of second actuators between stereoplasm frame and the flexible frame, in a plurality of second actuators one is not fixedly connected on stereoplasm frame pivotly by means of support; Flexible frame both sides branch and scalable front end also are respectively arranged with apomecometer, it is characterized in that this 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 radian curve that will dock, generate flexible frame position data after the distortion with aforementioned radian based on this curve, further determine the second actuator stroke, and activate described second actuator accordingly, thereby make the flexible frame after the distortion have identical surface curvature with the fuselage cover that will dock; Continue the control awning device and advance, when flexible frame laser rangefinder measuring distance reaches predetermined value, the braking connecting bridge; Controlling the firstth actuator makes scalable floor section stretch the applying fuselage cover; 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 warning device accordingly and give the alarm, and start wind2 release energy storage equipment or primer fluid hydraulic actuator again, can measure distance until laser rangefinder and reenter safe range.
Awning device method of deploying according to the present invention has following advantage: (1) therefore can adapt to various aircraft surfaces curvature well, 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 butt joint 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 butt joint 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 butt joint framework 3, butt joint framework 3 is directly used in realizes docking of awning device 1 and airframe shell.Butt joint 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 padded coaming, inflatable packer or elastic variable pipe etc. further around the flexible frame.Flexible frame in height will be longer than stereoplasm frame, this flexible frame among the present invention is very favourable, because it has big length, even still can be for the passenger provides good space after therefore being out of shape, comparatively roomy flexible frame also more be conducive to butt joint certainly.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 two of two ends respectively, 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 front end sidepieces of awning 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.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 that for simplifying in the present embodiment, the number of hydraulic actuator herein is 5.These 5 actuators preferably are distributed on each side of flexible frame dispersedly, but preferably have 2 tops that are separately positioned on each side branch of flexible frame in a plurality of actuator at least, are beneficial to the applying of flexible frame and fuselage cover.That is to say that the flexible frame among the present invention breaks away from floor layer, it supports by stereoplasm frame and actuator fully, and this structure is very favourable for the distortion of flexible frame.Actuator one end and flexible frame 5 carry out hinged, the other end is then hinged with stereoplasm frame 4, a but actuator near middle (being preferably in stereoplasm frame 1/4th to 3/4ths altitude ranges), for example as shown in Figure 1, it is fixedly connected on stereoplasm frame 4 again by means of detachable fixed support 14, and whole like this flexible frame just can not move up and down; Certainly, directly this actuator is fixedly connected on stereoplasm frame and also is fine, but connect by means of detachable fixed support, the support that then is conducive to change different length is regulated flexible frame with respect to the height up and down of stereoplasm frame.Also be respectively arranged with a plurality of distance measuring sensors 10 in the branch of flexible frame both sides, 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.Apomecometer preferably disperses to be distributed on vertical height of flexible frame, and certainly, in order to measure accurately, they should be on same the vertical curve.The front end of the scalable portion of floor layer also is provided with apomecometer 13.Apomecometer quantity on the flexible frame can be identical with actuator quantity also can be different.Preferably, except the end of flexible frame, apomecometer installation site and the actuator hinge-point on flexible frame staggers as far as possible, so just can not cause too much infringement to flexible frame, is conducive to the use of apomecometer simultaneously.
Be equipped with vestibule diaphragm around the periphery in the space between flexible frame and the door-shaped frame.Vestibule diaphragm device 1 also comprises the controller (not shown) that is arranged on door-shaped frame 2 back upper lateral parts, is used for receiving signal that laser rangefinder obtains and the operation of control hydraulic actuator 9 and winding mechanism 8, goes back controller in addition 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 cause connecting bridge butt joint framework detachment machine body shell to give the alarm during big distance (for example being 10 centimetres) warning the passenger to postpone action, and start wind2 release energy storage equipment or primer fluid hydraulic actuator again, can measure distance until laser rangefinder and reenter safe range (sounding all clear).
At length introduce the method for operating of the awning device 1 among the present invention below.
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 stereoplasm frame apart from the distance of airframe, vertically advance towards aircraft at connecting bridge and (can utilize two apomecometers on the same horizon that is arranged on the flexible frame, 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 camber line shape, therefore the data of each laser rangefinder measurement are different, distance herein can be any data that measure in the laser rangefinder on the flexible frame) 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.
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 the flexible frame, generate the fuselage cover surface radian that will dock via the controller simulation, shown in mark 101; Then to butt joint framework this radian curve of translation attachment point intersection location on this camber line and flexible frame, that actuator that this attachment point namely can not pivot and the point of connection of flexible frame.
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 respectively the flexible frame in the representative simulations, initial position actuator and flexible after actuator.In this process, it is not flexible that actuator that can not pivot keeps.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 (not comprising that actuator that can not pivot) 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 use auxiliary actuator to come actuator between deflection flexible frame and the stereoplasm frame according to the angle of calculating.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 bigger 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 butt joint, 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 when moving closer to airframe (according to the comparison of the measured distance of apomecometer with anticipated value) the connecting bridge speed of advance slows down, (according to the comparison of laser rangefinder measuring distance and anticipated value, this value is relevant with the apomecometer installation site) namely brakes connecting bridge when flexible frame fits in fuselage cover.Afterwards, the apomecometer 13 of the stronghold scalable portion of flaggy front end, control actuator 12 elongation floor segments 11 are fitted until this floor segment and fuselage.
Controller control winding mechanism discharges energy storage equipment then, 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 bigger thrust like that 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 warning device accordingly and give the alarm, and start wind2 release energy storage equipment or primer fluid hydraulic actuator again, can measure distance until laser rangefinder and reenter 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 alarm in addition and revise the advantage of applying degree again.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), butt joint framework (3) and scalable floor (6), it is characterized in that scalable floor (6) comprises scalable (11) that are positioned at front end, this scalable is utilized first actuator (12) to realize stretching, described butt joint framework (3) comprises stereoplasm frame (4) and flexible frame (5), the height of flexible frame is greater than the height of stereoplasm frame, 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 the outside, floor (6), and flexible frame (5) is not directly connected in floor layer; Be connected with a plurality of second actuators (9) between stereoplasm frame (4) and the flexible frame (5), in a plurality of second actuators one is not fixedly connected on stereoplasm frame pivotly by means of support (14); Flexible frame both sides branch and scalable (11) front end also are respectively arranged with apomecometer, it is characterized in that this 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; Utilize a plurality of laser rangefinders measure on the flexible frame distance and the distortion of actuator control flexible frame: controller receives the measured distance value of apomecometer and generates the fuselage cover radian curve that will dock, generate flexible frame position data after the distortion with aforementioned radian based on this curve, further determine each second actuator stroke, and activate described second actuator accordingly, thereby make the flexible frame after the distortion have identical surface curvature with the fuselage cover that will dock; Continue the control awning device and advance, when flexible frame laser rangefinder measuring distance reaches predetermined value, the braking connecting bridge; According to the apomecometer on the section of scalable floor, control first actuator and make scalable floor section stretch the applying fuselage cover; 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. according to the method for deploying of any described awning device among the 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 warning device accordingly and give the alarm, and start wind2 release energy storage equipment or primer fluid hydraulic actuator again, can measure distance until laser rangefinder and reenter safe range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310066786.2A CN103253377B (en) | 2013-03-01 | 2013-03-01 | Method for curved docking with airplanes |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310066786.2A CN103253377B (en) | 2013-03-01 | 2013-03-01 | Method for curved docking with airplanes |
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| Publication Number | Publication Date |
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| CN103253377A true CN103253377A (en) | 2013-08-21 |
| CN103253377B CN103253377B (en) | 2015-02-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310066786.2A Active CN103253377B (en) | 2013-03-01 | 2013-03-01 | Method for curved docking with airplanes |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022206136A1 (en) * | 2021-03-30 | 2022-10-06 | 郑光普 | Automatic ramp |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
-
2013
- 2013-03-01 CN CN201310066786.2A patent/CN103253377B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
|---|---|---|---|---|
| WO2022206136A1 (en) * | 2021-03-30 | 2022-10-06 | 郑光普 | Automatic ramp |
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| CN103253377B (en) | 2015-02-25 |
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