CN103253378B - Frame and airplane jointing method - Google Patents
Frame and airplane jointing method Download PDFInfo
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- CN103253378B CN103253378B CN201310067040.3A CN201310067040A CN103253378B CN 103253378 B CN103253378 B CN 103253378B CN 201310067040 A CN201310067040 A CN 201310067040A CN 103253378 B CN103253378 B CN 103253378B
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Abstract
The invention provides a frame and airplane jointing method. The frame and airplane jointing method includes steps of starting laser range finders to measure the distance between a flexible frame to an airplane body, and temporarily stopping motion of a boarding bridge getting close to the airplane when the boarding bridge perpendicularly advances towards the airplane and gets close to the airplane to be jointed by a certain distance; controlling the flexible frame to deform by an actuator according to the distance measured by the laser range finder so as to enable the deformed flexible frame to be provided with surface curvature same with a housing of the airplane body to be jointed; keeping controlling the boarding bridge to advance and braking the boarding bridge when the distance measured by the laser range finders between the flexible frame and the airplane body reaches the preset value; controlling a first actuator to enable telescopic plates to extend to be fitted to the housing of the airplane body according to range finders on the telescopic plates; controlling a winding mechanism to release an energy storage device by a controller so that the jointed frame can be tightly pressed to the housing of the airplane body. By the aid of an unfolding method of a folding device, sealing property and safety are improved.
Description
Technical field
The present invention relates to the joint method of a kind of framework and aircraft, be specifically related to a kind of vestibule diaphragm device method of deploying, particularly relate to a kind of be included in dock with aircraft before just can have the method for deploying of the vestibule diaphragm device of the docking framework of the profile of coincideing with aircraft surfaces radian adaptively.
Background technology
Boarding bridge is the airfield equipment that a modern passenger aircraft usually uses, and they are used as the entrance of boarding, can enter passenger plane inside for passenger from terminal.This connecting bridge all has a vestibule diaphragm device in its end usually, and it is connected across in the space between connecting bridge and aircraft, thus boarding personnel can be protected not to be subject to the impact of adverse weather condition.
Patent documentation CN100355628C discloses a kind of birdman's gangway or boarding bridge sealing arrangement, comprise one and be stretched in vestibule diaphragm above a connection floor, wherein said vestibule diaphragm has a flexible frame on one open end, be arranged at its other end place on a door-shaped frame be used for fixing on birdman's gangway or boarding bridge, wherein said flexible frame is fitted on airplane skin when described vestibule diaphragm stretches out, and be wherein provided with one for the operating control of described vestibule diaphragm, to launch or to close up described vestibule diaphragm, wherein said operating control comprises wind2 and by energy storage equipment, the brake ac-tuating mechanism that multi link is formed.Patent documentation CN100528688C discloses a kind of shelter device, for the connecting bridge of aircraft, comprises flexible frame, is arranged on an open end of this shelter device, for fitting to the shell of this aircraft when this shelter device launches; Door-shaped frame, is arranged on another open end of this vestibule diaphragm device, for being connected to this connecting bridge; Extensible folding paulin, be connected across between this flexible frame and this door-shaped frame, and be connected to top and the both sides of this flexible cross-over connection and this door-shaped frame, also comprise at least two steering units independent of each other, for driving this shelter device launch and/or close up, described steering unit is made up of wind2 and single energy storage equipment.Patent documentation CN101910001A discloses a kind of kiss connection device for portable connecting bridge, comprising: charging portion, and it is attached to the end of the shelter of described portable connecting bridge and can injects air; And padded coaming, it is arranged in described charging portion, even and if described padded coaming still keeps solid shape when discharging air from described charging portion.Patent documentation US5267368A discloses a kind of 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, prior art is realizing usually all have employed energy storage equipment when vestibule diaphragm device docks with fuselage, and such as gas spring etc. and wind2 are with the use of, or hydraulic actuator, and document CN100355628C also uses multiple connecting rod or cantilever design; And in order to make docking framework fit tightly fuselage as far as possible, and the injury that minimizing vestibule diaphragm device may cause for aircraft fuselage cover, adopt flexible frame more than docking framework of the prior art, especially document CN101910001A also adopts the gas filled device with padded coaming.But, the difference each other of aircraft is now all comparatively large, and the Curvature varying of its outline is also all comparatively large, particularly sometimes also there is very large bent angle in prow transitional region, make existing connecting bridge vestibule diaphragm device be difficult to accurately fit on airplane skin, and then retain gap.These gaps are totally unfavorable under severe conditions, particularly sleety weather, are easy to cause moisture enter interior of aircraft or drench passenger, also may cause wet and slippery risk at connecting bridge or fuselage interior.By energy storage equipment or actuator in aforementioned documents, such as gas spring, hydraulic actuator promote the top of docking flexible frame, vestibule diaphragm device is made to fit to fuselage cover, due in such cases, docking framework passive is pushed on fuselage, actuating structure is comparatively complicated on the one hand, and flexible frame is when in the face of multiple curvature thereof on the other hand, is usually also difficult to very closely fit on fuselage cover.Moreover in order to realize fitting tightly, gas spring, hydraulic actuator generally also need to provide comparatively high thrust, therefore unavoidable fuselage cover to be caused damage.
Document CN202379091U discloses a kind of boarding bridge pickup range finding sensing device, comprise the buffering sebific duct being arranged on front edge of airport pickup port end, described buffering sebific duct is provided with range finding sensing device, the side of described buffering sebific duct has exploration hole, and the sensor probe of described range finding sensing device and described exploration hole are just to setting.It is mainly used in the deformation extent reacting buffering sebific duct, and notice control system sends speed-slackening signal in time, prevents from causing greater impact to fuselage.But the deployed configuration that it adopts still belongs to conventional prior art, and it also cannot solve the problem.Document CN101287649B disclose a kind of by connecting bridge automatic butt to the method on hatch door, it adopts laser rangefinder and Computer Control Unit to realize the automatic butt of connecting bridge and aircraft door.Above-mentioned two sections of documents are still more single for the using method of laser rangefinder.
Therefore, column defects under vestibule diaphragm device method of deploying ubiquity of the prior art: due to energy storage equipment or the actuator point of application single, flexible frame is difficult to adapt to various aircraft surfaces curvature, and alerting ability and leak tightness are all poor; And in order to fuselage cover that flexible frame is closely fitted, the power of usual applying is all larger, easy infringement fuselage cover, in addition because energy storage equipment or actuator are just started working usually after vestibule diaphragm device touches fuselage cover, therefore easily because faults itself or system error cause overload, heavy damage fuselage cover; Lack passenger's boarding process to detect in real time and alarm device, there is potential safety hazard.
Summary of the invention
In order to overcome the problems referred to above, the invention provides a kind of method of deploying of vestibule diaphragm device, described vestibule diaphragm device comprises door-shaped frame, docking framework and Telescopic floor board, Telescopic floor board comprises the telescoping section being positioned at front end, it is flexible that this telescoping section utilizes the first actuator to realize, described docking framework comprises stereoplasm frame and flexible frame, the height of flexible frame is greater than the height of stereoplasm frame, jack and energy storage equipment is connected with between door-shaped frame and stereoplasm frame, slide-bar on the chute that stereoplasm frame utilizes self to offer and outside portion, floor matches and merges by means of the 3rd actuator thus realize stereoplasm frame and can move up and down a segment distance relative to floor, flexible frame is not directly connected in floor layer, be connected with multiple second actuator between stereoplasm frame and flexible frame, one in multiple second actuator is non-pivotally fixedly connected to stereoplasm frame again by means of shelf support, flexible frame both sides branch and telescoping section front end are also respectively arranged with apomecometer, the method comprises the steps: to open the distance that described laser rangefinder measures flexible frame distance airframe, before vestibule diaphragm device vertically aircraft and then when close to the aircraft certain distance that will dock, temporarily stop vestibule diaphragm device near the motion of aircraft, whether detection or artificial observation docking framework are on suitable height relative to hatch door, if not then needing to utilize the 3rd actuator up-down adjustment docking framework one segment distance, the Distance geometry actuator that on flexible frame, multiple laser rangefinder measurement obtains is utilized to control flexible frame distortion: the distance value that controller receives measured by apomecometer generates the fuselage cover arc curve that will dock, generate based on this curve and there is flexible frame position data after the distortion of aforementioned radian, determine each second actuator stroke further, and activate described second actuator accordingly, thus the flexible frame after being out of shape is made to have identical surface curvature with the fuselage cover that will dock, continue to control vestibule diaphragm device to advance, when flexible frame laser rangefinder measuring distance reaches predetermined value, braking connecting bridge, according to the apomecometer in Telescopic floor board section, control the first actuator and make Telescopic floor board section stretch laminating fuselage cover, controller controls winding mechanism release energy storage equipment, makes it that docking framework is closely pressed on fuselage cover.
Preferably, described certain distance is preferably 1 meter.
Preferably, described anticipated value is relevant relative to the installation site at flexible frame edge with apomecometer.
Preferably, if vestibule diaphragm device is relative to fuselage cover generation deflection or disengaging in passenger's boarding process, controller can control warning device accordingly and give the alarm, and laser rangefinder again starts wind2 release energy storage equipment or primer fluid hydraulic actuator, until can measure distance reenter safe range.
Vestibule diaphragm device method of deploying tool according to the present invention has the following advantages: (1) multiple apomecometer and actuator carry out yielding flexibility framework because the present invention utilizes, therefore, it is possible to adapt to various different aircraft surfaces curvature well, and can possess good leak tightness; (2) because docking framework of the present invention completed distortion before touching fuselage cover, therefore, it is possible to prevent actuator from transshipping due to faults itself or system error; (3) distance measuring sensor of the present invention can detect docking situation in real time, and gives the alarm, therefore safer.
Accompanying drawing explanation
Fig. 1 is the longitdinal cross-section diagram according to vestibule diaphragm device of the present invention;
Fig. 2 schematically simulates the mode of texturing of the flexible frame of the vestibule diaphragm device in the present invention.
Detailed description of the invention
With reference to accompanying drawing 1, which show according to vestibule diaphragm device 1 of the present invention, this vestibule diaphragm device 1 comprises door-shaped frame 2 and docking framework 3, and docking framework 3 is directly used in and realizes docking of vestibule diaphragm device 1 and aircraft fuselage cover.The flexible frame 5 that docking framework 3 comprises stereoplasm frame 4 and directly will contact with fuselage cover, flexible frame 5 is made up of flexible material, but the ductility of this material is poor, such as plastics.Flexible frame surrounding also can comprise padded coaming, inflatable packer or elastic variable pipe etc. further.Flexible frame in height will be longer than stereoplasm frame, this flexible frame in the present invention is very favourable, because it has greater depth, even if still can provide good space for passenger after being therefore out of shape, certainly comparatively roomy flexible frame is also more conducive to docking.Vestibule diaphragm device also comprises floor layer 6 further, wherein this floor layer is a kind of telescoping floor, it comprises a telescoping section 11, this telescoping section utilizes the actuator being such as in floor layer inside, such as hydraulic actuator 12 realizes fore and aft motion, this hydraulic actuator 12 is arranged at one of floor layer midway location, and also can be two that are arranged at two ends respectively, can certainly be other quantity.Door-shaped frame 2 is fixedly connected on floor layer 6.Medial surface bottom stereoplasm frame 4 side branch offers chute, portion is then provided with slide-bar to floor layer 6 front end outer side, stereoplasm frame 4 coordinates by means of the slide-bar in the floor layer 6 front end outer side portion of chute and vestibule diaphragm device 1, thus realize stereoplasm frame 4 can carry out upper and lower certain amplitude movement relative to floor layer, thus regulate the height of docking framework; Movement herein can such as realize by means of the hydraulic actuator 15 be arranged near stereoplasm frame.And use energy storage equipment between door-shaped frame 2 and stereoplasm frame 6 and reclaim winding mechanism 8, energy storage equipment can be such as gas spring 7.On each side, multiple actuator is connected with (in order to various fuselage surface curvature can be adapted between stereoplasm frame 4 and flexible frame 5, can accept in scope at cost, the quantity of actuator is preferably The more the better), such as hydraulic actuator 9, consider for simplification, in the present embodiment, the number of hydraulic actuator is herein 5.These 5 actuators are preferably distributed on every side of flexible frame dispersedly, but preferably have 2 tops being separately positioned on every side branch of flexible frame in multiple actuator at least, are beneficial to the laminating of flexible frame and fuselage cover.That is, the flexible frame in the present invention departs from floor layer, and it is supported by stereoplasm frame and actuator completely, 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, but near an actuator of middle (being preferably in stereoplasm frame 3/1 to four/4ths altitude range), such as shown in Figure 1, it is again fixedly connected on stereoplasm frame 4 by means of detouchable 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 is also fine, but connect by means of detachable fixed support, be then conducive to the support of replacing different length to regulate flexible frame relative to the upper-lower height of stereoplasm frame.Flexible frame both sides branch is also respectively arranged with multiple distance measuring sensor 10, and this apomecometer can be such as ultrasonic range finder, infrared ambulator or laser rangefinder, prioritizing selection laser rangefinder in the present embodiment.The installation of apomecometer on flexible frame can adopt well-known conventional means, such as, the form of support can be adopted to be arranged on flexible frame, and this laser rangefinder also can be arranged among the perforate on flexible frame.Apomecometer preferably disperses to be distributed on longitudinal height of flexible frame, and certainly, in order to measure accurately, they should be on same vertical curve.The front end of floor layer telescoping section is also provided with apomecometer 13.Apomecometer quantity on flexible frame can identical from 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, would not cause too much infringement like this, be conducive to the use of apomecometer simultaneously to flexible frame.
The periphery in the space between flexible frame and door-shaped frame is equipped with vestibule diaphragm.Vestibule diaphragm device 1 also comprises the controller (not shown) being arranged on door-shaped frame 2 upper back, for receiving the signal and the operation of hydraulic control actuator 9 and winding mechanism 8 that laser rangefinder obtains, going back controller in addition and also controlling a warning device.Therefore this controller can have following function: when causing connecting bridge to tremble relative to airplane skin due to passenger's boarding, and then the warning passenger that gives the alarm when causing connecting bridge docking framework to depart from fuselage cover larger distance (being such as 10 centimetres) postpones action, and laser rangefinder again starts wind2 release energy storage equipment or primer fluid hydraulic actuator, until can measure distance reenter safe range (sounding all clear).
Introduce the method for operating of the vestibule diaphragm device 1 in the present invention below in detail.
First, before vestibule diaphragm device contacts with fuselage cover, the initial stage is used at connecting bridge, the laser rangefinder opened on vestibule diaphragm device measures the distance of stereoplasm frame distance airframe, connecting bridge vertically aircraft advance and (two apomecometers on the same level line that is arranged on flexible frame can be utilized, if their two distances measured are equal, connecting bridge just vertically aircraft advance is described), and when close to the aircraft certain distance that will dock, this distance is (because aircraft surfaces is arc line shaped, therefore the data of each laser rangefinder measurement are different, distance herein can be any one in the laser rangefinder on flexible frame data of measuring, be preferably the data measured by actuator near centre) when can be arbitrary set point value between 0.5-5 rice, preferably 1 meter, temporary transient stopping connecting bridge is near the motion of aircraft, controller controls each actuator according to the distance value that each laser rangefinder measures and carries out respective stretching with yielding flexibility framework.Note also that in this step check the stadia surveying that is positioned at flexible frame top or bottom to data be whether the excessive data of deformity, that is, if connecting bridge or docking framework are not on same height with the hatch door that will dock in initial debugging, the light that the survey meter being so probably positioned at flexible frame top or bottom sends or signal are in the hatch door scope vacated and enter inside, now also illustrate that docking framework is not in height well alignd with hatch door, the height of docking framework now can be regulated by means of actuator 15, until top or bottom stadia surveying to data enter normal range, certainly to be on the safe side, now still can continue mobile a bit of distance.In addition, operate herein and also can adopt manually-operated mode.After regulating docking framework height, then carry out the deformation process of flexible frame.
With reference to accompanying drawing 2, it schematically simulates the mode of texturing of the flexible frame of the vestibule diaphragm device in the present invention.First utilizing the distance of the distance fuselage measured by the apomecometer on flexible frame, generating the fuselage cover surface radian that will dock via controller simulation, as marked shown in 101; Then to this arc curve of docking framework translation until attachment point intersection location on this camber line and flexible frame, this attachment point i.e. point of connection of that actuator not pivotable and flexible frame.
Therefore the flexible frame after can learning distortion according to the length (because its extensibility is poor, ignoring spread length herein) of flexible frame branch should as marked as shown in 102.And then after distortion, elongation or the retracted length of (stereoplasm frame 106 of simulation keeps motionless) associated actuator just can calculate.Subsequently controller according to aforementioned calculated amount activate hydraulic actuator of the present invention can realize the flexible frame after being out of shape can have with will in conjunction with the identical radian of fuselage cover.Flexible frame, the actuator of initial position and the actuator after stretching in mark 103,104,105 difference representative simulation in this figure.In this process, that actuator not pivotable keeps not stretching.In addition, in order to the distortion of flexible frame more accurately can be guaranteed, the present invention can also arrange auxiliary actuator (not shown) between actuator (not comprising that actuator not pivotable) and stereoplasm frame, because the deflection angle of simulation actuator 104 in frame deformation process can calculate according to the method described above, auxiliary actuator therefore can be used according to calculated angle to deflect the actuator between flexible frame and stereoplasm frame.Described computation process can be completed by controller, and relevant mathematic calculation is all the common practise in affiliated field.
In this process, framework both sides can independently operate, that is the distortion of flexible frame both sides can be different when needed, and this is for being very favorable during the corner that the appearance of hatch door periphery is larger, and therefore the present invention has very outstanding alerting ability in docking operation.And the actuator in the present invention just completed actuating before docking, therefore overload can not be there is due to the fault of self or because of control system error.
After this, namely continue to control connecting bridge to advance, and (distance measured by apomecometer compares with anticipated value) slow down connecting bridge speed of advance when moving closer to airframe, (according to comparing of laser rangefinder measuring distance and anticipated value, this value is relevant to apomecometer installation site) namely brakes connecting bridge until when flexible frame fits in fuselage cover.Afterwards, the apomecometer 13 of flaggy front end, stronghold telescoping section, controls actuator 12 and extends floor segment 11, until this floor segment and fuselage are fitted.
Then controller controls winding mechanism release energy storage equipment, make it that docking framework is closely pressed on fuselage cover, because the flexible frame in the present invention is by actuator-operated distortion, therefore the energy storage equipment in the present invention, without the need to applying larger thrust in the prior art, therefore also just reduces the risk that vestibule diaphragm device damages fuselage cover.
In passenger's boarding process, because the weight extruding of external conditions or passenger causes vestibule diaphragm device relative to fuselage cover generation deflection or disengaging, because laser rangefinder can measure the change of distance, if therefore the distance of flexible frame and fuselage cover reaches a predetermined threshold (being such as 10 centimetres), controller can control warning device accordingly and give the alarm, and laser rangefinder again starts wind2 release energy storage equipment or primer fluid hydraulic actuator, until can measure distance reenter safe range.
Because the engagement frame in the present invention was just provided with the surperficial radian of fuselage cover before laminating fuselage cover, therefore, it is possible to improve sealing property, reduce the hurtful risk of fuselage skin simultaneously.Also there is alarm in addition and again revise the advantage of laminating degree.What below do not elaborate is all the common practise in affiliated field.
Those skilled in the art can make replacement or modification according to content disclosed by the invention and the art technology grasped to content of the present invention; but these replacements or modification should not be considered as disengaging the present invention design, and these replacements or modification are all in the interest field of application claims protection.
Claims (1)
1. the method for deploying of a vestibule diaphragm device, described vestibule diaphragm device comprises door-shaped frame (2), docking framework (3) and Telescopic floor board (6), it is characterized in that Telescopic floor board (6) comprises the telescoping section (11) being positioned at front end, it is flexible that this telescoping section utilizes the first actuator (12) to realize, described docking framework (3) comprises stereoplasm frame (4) and flexible frame (5), the height of flexible frame is greater than the height of stereoplasm frame, jack (8) and energy storage equipment (7) is connected with between door-shaped frame (2) and stereoplasm frame (4), slide-bar on the chute that stereoplasm frame (4) utilizes self to offer and floor (6) outside portion matches and merges by means of the 3rd actuator (15) thus realize stereoplasm frame and can move up and down a segment distance relative to floor, flexible frame (5) is not directly connected in floor layer, be connected with multiple second actuator (9) between stereoplasm frame (4) and flexible frame (5), one in multiple second actuator is non-pivotally fixedly connected to stereoplasm frame again by means of shelf support (14), flexible frame both sides branch and telescoping section (11) front end are also respectively arranged with laser rangefinder, it is characterized in that the method comprises the steps: to open the distance that described laser rangefinder measures flexible frame distance airframe, before vestibule diaphragm device vertically aircraft and then when close to the aircraft certain distance that will dock, temporarily stop vestibule diaphragm device near the motion of aircraft, whether detection or artificial observation docking framework are on suitable height relative to hatch door, if not then needing to utilize the 3rd actuator up-down adjustment docking framework one segment distance, the Distance geometry actuator that on flexible frame, multiple laser rangefinder measurement obtains is utilized to control flexible frame distortion: the distance value that controller receives measured by apomecometer generates the fuselage cover arc curve that will dock, generate based on this curve and there is flexible frame position data after the distortion of aforementioned radian, determine each second actuator stroke further, and activate described second actuator accordingly, thus the flexible frame after being out of shape is made to have identical surface curvature with the fuselage cover that will dock, continue to control vestibule diaphragm device to advance, when flexible frame laser rangefinder measuring distance reaches predetermined value, braking connecting bridge, according to the apomecometer in Telescopic floor board section, control the first actuator and make Telescopic floor board section stretch laminating fuselage cover, controller controls winding mechanism release energy storage equipment, makes it that docking framework is closely pressed on fuselage cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310067040.3A CN103253378B (en) | 2013-03-01 | 2013-03-01 | Frame and airplane jointing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310067040.3A CN103253378B (en) | 2013-03-01 | 2013-03-01 | Frame and airplane jointing method |
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| Publication Number | Publication Date |
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| CN103253378A CN103253378A (en) | 2013-08-21 |
| CN103253378B true CN103253378B (en) | 2015-02-25 |
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| CN201310067040.3A Active CN103253378B (en) | 2013-03-01 | 2013-03-01 | Frame and airplane jointing method |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3301028B1 (en) * | 2016-09-28 | 2019-09-04 | Hübner GmbH & Co. KG | Coupling module as interface between a passenger bridge or passenger staircase and the fuselage of a plane |
| CN108438248B (en) * | 2018-05-15 | 2019-04-30 | 中国国际海运集装箱(集团)股份有限公司 | Connecting bridge assists the system and method that picks |
| CN114384090B (en) * | 2021-12-30 | 2023-12-22 | 中国飞机强度研究所 | Device and method for detecting damage of fuselage barrel section in strength test |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5257431A (en) * | 1990-08-15 | 1993-11-02 | Bridgetech, Inc. | Airplane loading bridge |
| SE515352C2 (en) * | 1999-11-09 | 2001-07-16 | Fmt Int Trade Ab | Coupling device for a passenger bridge |
| CN201026994Y (en) * | 2007-02-15 | 2008-02-27 | 天津工程机械研究院 | Contraposition, contact joint controlling system of mobile passenger bridge and airplane |
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