CN1087702C - Mechanism for arming, disarming and activating airplane emergency slide evacuation systems - Google Patents
Mechanism for arming, disarming and activating airplane emergency slide evacuation systems Download PDFInfo
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- CN1087702C CN1087702C CN96111537A CN96111537A CN1087702C CN 1087702 C CN1087702 C CN 1087702C CN 96111537 A CN96111537 A CN 96111537A CN 96111537 A CN96111537 A CN 96111537A CN 1087702 C CN1087702 C CN 1087702C
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Abstract
The present invention relates to a mechanism (10) of an emergency escaping device of an airplane for preparation, relief and triggering. The device is provided with a sliding board, one end of which is connected to a cross rod (16); the mechanism comprises floor connectors (18), wherein each floor connector comprises a base (32) provided with a notch (40) and a claw (42); the claw corresponding to the base can rotate from the locking position for preventing the cross rod from pulling out of the notch to the position allowing the cross rod to pull out of the notch; support connectors (20) which can be arranged on a door are connected with each floor connector when the door is opened and locked; a first crushing plate (58) downwards extends to one side of the notch and approximately faces the notch from the support connectors; a first linkage member (60) and a second linkage member (70) are mutually connected and are rotatablely arranged on the support connectors; a second crushing plate (94) extends out of the second linkage member and approximately faces the first crushing plate.
Description
Relate generally to of the present invention is used to be ready for, remove and trigger the mechanism of sentinel plant, and relates to the mechanism that is used for being ready for, removing and trigger at the people's passenger plane emergency escape device particularly.
Often, seating plane comprises an emergency escape device, has an inflatable slide, uses with cleaning door or passenger door.Generally, slide is connected in the inboard of door, is folding, deflated configuration.Before taking off, the flight personnel are ready for the slide arrangement for evacuation.When device was ready for, the base of slide was anchored in the student's fuselage.In the device that is ready for, open with the joining door of slide and can cause arrangement for evacuation to be triggered.After the triggering, device uses one or more storage tank that holds gas-pressurized to wash landing gate open and spreads out slide and inflation for it.Staff's decontrol be ready for state the time, the base of slide is anchored on the door.Thereby when door was opened, the base of slide moved with door and does not install and can trigger.
This emergency escape device has three significant problems.The first, the staff can open landing gate and not remove this kind device after a normal flight and landing sometimes.This can cause slide to spread out and inflate, and causes the poverty-stricken embarrassment of aircraft company and spends huge.
Secondly, the staff can unconsciously be ready for this kind device occasionally when door is being held.This can cause the base of slide to become not adding anchoring.Do not have drama though do not resemble unconsciously to trigger the slide, but still can cause cost of aircraft company because before aircraft can fly once more staff's anchoring slide again.
The 3rd, the mechanism that is used for triggering urgent slide arrangement for evacuation relies on a mechanical linkage to pierce through a diaphragm of gas-pressurized storage tank to trigger arrangement for evacuation.This mechanical linkage complexity, manufacturing and maintenance spending are big, and if installing and/or safeguard improper, also may be very unreliable.
Once do some effort and solved several these problems.Such as, Japanese Patent the 3rd, 157,297 show a kind of mechanism that is used for being ready for and removing aircraft slide arrangement for evacuation, comprise an interlock system, prevent to be engaged in when door is opened and are ready for.Thereby the staff can not make slide become with Men Wei when door is opened to add anchoring.But, this interlock system is unnecessaryly complicated, and manufacturing and erected cost are very high.
The present invention provides a kind of improved terms of settlement for aforementioned every problem.
The invention provides a kind of mechanism that is used for being ready for, removing and trigger the emergency escape device at aircraft.A kind of employing emergency escape device of the present invention comprises a fire escape and a storage tank, and dress is sealed in the gas-pressurized of a diaphragm back in this jar, and this diaphragm is used to trigger the emergency escape device.Slide comprises a cross bar, is connected in an end of slide.When arrangement for evacuation was ready for, cross bar was fixed on the student's the airframe.If door is opened when arrangement for evacuation is ready for, this device can start to spread out slide and inflation for it.When this device was removed, cross bar was fixed in the bottom surface of door, and the emergency escape device can not be triggered when door is opened.
The present invention includes a pair of floor attaching parts, they are installed on the floor at each side place of door.Each floor attaching parts comprises a breach, is used to put cross bar.One colludes pawl, is included among each floor attaching parts, can be held in position (device is ready for) among the breach to cross bar by one and turn to a cross bar and can withdraw from and block the jail in the position of the lower edge of door (device is removed) from breach.
The present invention also comprises a pair of supporting connecting piece, and they are installed on the aircraft door, is used for engaging with each floor attaching parts when door is closed and lock.Each supporting connecting piece comprises first jaw that stretches downwards.When door was closed and lock, each jaw encased the inside part of each end regions of cross bar.
Each supporting connecting piece also comprises second jaw that stretches downwards, can rotate partly to encase the Outboard Sections in a crossbar end zone.Rotating second jaw is arranged on the handgrip on the door and is achieved to engage cross bar and can remove arrangement for evacuation and to rely on to rotate.Rotating second jaw makes it to enter its position that surrounds cross bar and also can rotate the pawl that colludes of each floor attaching parts and make it to enter one and can make cross bar from position that floor attaching parts breach is let slip when door is shifted to open position.One interlock system strikes up partnership with the linkage of handling second jaw, can guarantee that in rotation on the direction that may discharge cross bar cross bar blocks (and therefore card is firm in landing gate) between the jaw of jail at each supporting connecting piece constantly by preventing second jaw.This interlocking characteristic can prevent that cross bar from owing to operating arrangement for evacuation wrongly accidental release or whereabouts taking place.
The handgrip of being ready for and removing the emergency escape device is turned to device is ready for the position and makes second jaw turn to a position, it can partly not surround an end regions of cross bar on this position, and cross bar colluding among the groove that pawl is held in the floor attaching parts by each floor attaching parts.If door is opened, device also is ready for simultaneously, and fire escape will spread out automatically.
Current most preferred embodiment of the present invention comprises a kind of configuration that is used for triggering reliably the emergency escape device.This triggers configuration and comprises an electric exploder, is installed on to push hard storage tank to its open position to landing gate.One battery or other power supplys are connected in electric exploder via two series connected switches.Be in when being ready for the position first switch closure being ready for handgrip with decontrol.Along with the inner door handle is shifted to its open position, second switch closure.Thereby if door is opened, device is ready for simultaneously, and electric current just flows to electric exploder; This causes with regard to piercing through a diaphragm being washed open by one first storage tank, and is inflated to slide by one second storage tank subsequently.
The present invention also provides a flag, is used for showing intuitively that the emergency escape device is ready for.Flag is stretched out from the pawl that colludes of floor attaching parts, and colluding pawl when latched position turns to non-locked position, moves to a second place from a primary importance.When colluding pawl and be in latched position (cross bar is by each attaching parts card jail, floor), the distinct painted areas of flag (or other marks) can be seen at an easy rate.
Aforementioned aspects of the present invention and many attendant advantages after being understood preferably, can be easier to understand in the following detailed description made from reference to combining with each accompanying drawing.
In the accompanying drawing:
Fig. 1 shows a kind of transparent view of being ready for and removing the most preferred embodiment of mechanism, makes and be connected in the landing gate and the floor of aircraft according to the present invention;
Fig. 2 shows the enlarged perspective of this mechanism's one end, is the part is olation;
Fig. 3 shows an end of being ready for and removing mechanism that is shown in Fig. 1, and landing gate is drawn to such an extent that be in and close and latched position, draws to such an extent that be in disarm state and be ready for and remove mechanism;
Fig. 4 shows the mechanism among Fig. 3, and landing gate is drawn to such an extent that close and non-locking, and mechanism draws to such an extent that be in disarm state;
Fig. 5 shows the mechanism that is shown in Fig. 3, and landing gate is closed and locked, and mechanism is activated to be ready for urgent slide arrangement for evacuation;
Fig. 6 shows the mechanism that is shown in Fig. 3, and landing gate is drawn to such an extent that close and non-locking, draws to such an extent that be in the state of being ready for and be ready for and remove mechanism; And
Fig. 7 schematically shows a kind of electric system, is used to handle a kind of emergency escape device of being ready for and removing mechanism that employing is shown in Fig. 1.
Fig. 1 shows a preferred embodiment of mechanism 10 according to the invention, is contained on the cleaning door or passenger door 14 of aircraft.Mechanism 10 can be ready for and remove a kind of urgent slide arrangement for evacuation, and this device can be launched, and is used for withdrawing from aircraft rapidly via landing gate 14.This arrangement for evacuation (not drawing among Fig. 1) comprises an inflatable slide, overlays one after the venting and is fastened among the container of landing gate 14 inner surfaces.The base of slide stretches out from the lower end of container.When mechanism 10 was ready for this device, the base of slide was anchored in the airframe 12 below the landing gate 14.After this device is ready for, open landing gate 14 and can trigger this device, make slide inflate and spread out.
In Fig. 1, a cross bar 16 that is positioned at landing gate 14 footing places is fixed in the end of slide.Mechanism 10 makes cross bar 16 be connected in airframe below the landing gate 14 to be ready for this device.Thereby when arrangement for evacuation triggers slide, the base of slide will and spread out and will be anchored in fuselage below the landing gate along with the slide inflation.In order to remove this device, mechanism 10 makes cross bar 16 be connected in landing gate.Therefore, when landing gate 14 was opened, slide was movable with landing gate.
When landing gate 14 was closed and locked, landing gate 14 made each supporting connecting piece 20 and floor attaching parts 18 centerings along vertical direction, and makes each supporting connecting piece connect each floor attaching parts.Specifically, the door 14 of Fig. 1 is such one type cleaning door or passenger doors, promptly can upwards move with respect to airframe when door is separated door bolt or unblanked.Afterwards, door is outwards swung to open the airport of entry again.When closing, door 14 inwardly slides earlier, moves down to latch or to pin this door with respect to fuselage 12 subsequently.Thereby, close landing gate 14 and just make each supporting connecting piece 20 relative floor attaching parts 18 centering along vertical direction.Secondly, locking landing gate 14 can make each supporting connecting piece 20 move down (with door) so that engage each floor attaching parts 18.The staff can turn to a handgrip 21 on landing gate 14 inboards second place and pin and open landing gate 14 from a primary importance.
As shown in Figure 1, a Torque tube 22 extends between two supporting connecting pieces 20.Remove the stage at arrangement for evacuation, Torque tube 22 is rotated in one direction so that each supporting connecting piece 20 discharges cross bar 16.Be ready for the stage at arrangement for evacuation, Torque tube 22 is rotated with grasping cross bar 16 on another direction.A handgrip 24 that is contained in landing gate 14 inboards is handled between first and second two positions, so that rotate Torque tube 22 on the both direction of needs.Article one, push-and-pull wirerope 26 is connected in Torque tube 22 to handgrip 24 at landing gate 14 footing places, is used for moment of torsion is sent to Torque tube from handgrip.The type of push-and-pull wirerope is, has a firmer epitheca, makes the push-and-pull wirerope to transmit axial force between handgrip 24 and Torque tube 16.When handgrip 24 was twisted and rotates Torque tube 22, the wirerope that is contained in the epitheca the inside slidably stretched up and down.In addition, other structures also can be used for moment of torsion is sent to Torque tube from handgrip 24, such as the expensive not high illustration of conduct, a kind of link rod commonly used or pulley gear.
Referring to Fig. 2, cross bar 16 comprises an intermediate host section 28, and cross-sectional geometry is rectangle basically.The common axis line of one cylinder-shaped end 30 from every end of middle main paragraph 28 along the longitudinal axis that is roughly parallel to main paragraph 28 stretches.
Each floor attaching parts 18 comprises a base 32, is used to be installed on airframe 12.Preferably, base 32 comprises each flange 34 that along continuous straight runs stretches, and is that bolt 36 (or his type of its ground penetrate fastener) is worn and cross base 32 is installed on fuselage 12.Base 32 can be adjusted by each shim liner (not shown) of filling in or take down between base 32 and the airframe 12.In addition, the inboard of base 32 and outer fix, promptly base 32 is adjusted in the plate (not shown) that can adopt some band profiles of tooth that embed between base and the fuselage 12 towards and away from the position on the landing gate direction.Serration on the plate can leave selectively to connect the serration that is formed on base 32 bottom surfaces, to adjust the inboard and the outer fix of base.
With reference to Fig. 4, a nick shaped groove 40 is arranged in the district of each base 32.Each groove 40 is in the face of leaving the one side of landing gate 14 and settling to such an extent that be used to put two cylinder-shaped ends 30 of cross bar 16.One roughly straight smooth section 38, it is downward-sloping to leave landing gate 14, constitutes the lower surface of breach 40.Side towards cross bar 16 intermediate host sections of breach 40 is opened wide, so that the cylinder-shaped end 30 of cross bar can put in breach 40, and its mode as shown in Figure 2.An opposite side of breach 40 by a wallboard 44 that stretches up and down as the termination.One second wallboard 44 stretches along the opposite side of base 32.
Be that a rhombus colludes pawl 42 between two wallboards 44, install to such an extent that be used for rotating around a bearing pin 46.The most close breach 40 collude pawl 42 ends when being rotated its nethermost or non-locked position, two cylinder-shaped ends 30 of cross bar 16 can enter or withdraw from breach 40 (Fig. 3 and 4).Colluding pawl 42 ends when being in its uppermost rotation or latched position, cross bar cylindrical part 30 is advanced by lock and is held in breach 40 the insides (Fig. 5 and 6).The center of gravity place of colluding pawl 42 makes colludes pawl and can stay among the latched position.In addition, a torsion spring (not shown) encases bearing pin 46 and colludes pawl 42 with pushing and be in latched position.Thereby, when the cylindrical part 30 of cross bar 16 is positioned among the breach 40, colludes pawl 42 and can be locked in floor attaching parts 18 to cross bar.
One flag 48 is installed on an end that is opposite to breach 40 that colludes pawl 42.This flag comprises that roughly L shaped 50, one legs of support are loaded on and colludes pawl 42.The another leg protrudes upward.One roughly 52, one legs of plate of V-arrangement be longer than another, be loaded on the horizontal leg of L bracket 50.The long leg of V shaped slab sheet 52 is loaded on the leg that protrudes upward of L bracket 50, and Open Side Down to make the V shaped slab sheet.Support 52 and plate 52 can be connected to each other by any method known in the art, such as using penetration type fastener, welding, soldering, lining cement etc.After this will illustrate in more detail that preferably at least a portion flag 48 is painted a kind of color that is easy to notice, as yellow, orange or red.
The part of the base 32 the most close landing gates 14 of floor attaching parts 18 comprises digitation 54 on the other hand, stretches out towards landing gate 14 oblique tops.After this will illustrate in more detail that when landing gate 14 entered off position, finger 54 can start the interlock system on the supporting connecting piece 20.
See the most clearly in Fig. 2, supporting connecting piece 20 comprises that one can be loaded on the base plate 56 of landing gate 14.Stretch out a jaw 58 downwards from base plate 56.As shown in Figure 5, when landing gate 14 was closed and locked, jaw 58 was between two wallboards 44 of floor attaching parts 18, so that a circular arc inner edge 59 of jaw 58 partly encases the cylinder-shaped end of cross bar 16.
Can find out also that in Fig. 2 the bell crank 60 in one first STATEMENT OF FEDERALLY SPONSORED or trough of belt hole is rotatably installed on base plate 56 planes 57 along the vertical direction stretching, extension.Say that more specifically one is press-fit in or otherwise is engaged in the end that the bearing pin of bell crank 60 or axle 62 are passed the suitable aperture of a size on the base plate 56 and be connected in Torque tube 22.Rotate Torque tube 22, this pipe is arranged essentially parallel to the longitudinal center line of cross bar 16, makes axle 62 rotations again and causes bell crank 60 to rotate.
An end place that is positioned at bell crank 60 one connects armed lever 64, leaves axle 62 on the direction of leaving landing gate 14 and stretches out roughly pointing to.Being positioned at connection armed lever 64 far-ends is slotted eyes 68, has two circular arc end regions.The longitudinal axis of slotted eye 68 substantially coincides with the longitudinal axis that connects armed lever 64.
The opposite end place that is positioned at bell crank 60 is an interlocking armed lever 66, stretches downwards from axle 62, forms an obtuse angle with the connecting arm bar.The far-end of interlocking armed lever 66 forms a dove tail.
One second STATEMENT OF FEDERALLY SPONSORED 70 is rotatably installed on plane 57 in bell crank and inboard position below 60.Say that more specifically the shaped design of each base plate 56 bottom inside part is, form two substantially parallel lug areas 76 and 78 spaced apart, stretch downwards towards floor.
Stretch upwards is one first armed lever 80 of second STATEMENT OF FEDERALLY SPONSORED 70 between flange 76 and 78.One bearing pin or axle 82 are passed an aperture on first armed lever 80 of two apertures of centering on flange 76 and 78 and second STATEMENT OF FEDERALLY SPONSORED 70, thereby second STATEMENT OF FEDERALLY SPONSORED 70 (i.e. first armed lever 80) can center on a rotational that is roughly parallel to the longitudinal axis of cross bar 16.
First armed lever 80 of second STATEMENT OF FEDERALLY SPONSORED 70 comprises that one has the zone line 81 around axle 82 of essentially rectangular cross-sectional plane.First armed lever 80 leave the finger 84 that an aircraft door end farthest forms a directed downwards.Just like will illustrate in more detail like that, finger 84 presses in the landing gate open stage and colludes pawl 42 pawl 42 can not iced or other foreign matters cling or block in the original place to guarantee to collude.
The end regions of first armed lever, 80 the most close aircraft doors 14, its size fixed and arrange: (1) provides a kind of second interconnect device between first armed lever 80 and base plate 56; (2) rotate and collude pawl 42, so that be disengaged at arrangement for evacuation that cross bar 16 discharges from each floor attaching parts when being opened with aircraft door 14; And jaw 58 mutual actions of (3) and base plate 56 to be surrounding the cylinder-shaped end of cross bar 16, are disengaged and landing gate is is opening and closing between the two positions and cross bar is secured to aircraft door 14 when mobile at arrangement for evacuation so that guarantee.
For second interconnect device of first armed lever 80 with base plate 56 is provided, first armed lever 80 comprises two that protrude upward, substantially parallel, spaced apart lug areas 90 and 92.The end stretch of bell crank 60 that includes slotted eye 68 is between flange 90 and 92.One bearing pin or axle 98 are passed the suitable aperture of size on lug area 90 and 92.What be positioned at slotted eye 68 the insides is a cylindrical roller 96, has a central aisle with holding axle 98.Roller 96 makes lug area 90 and 92 (thereby, first armed lever 80 of second STATEMENT OF FEDERALLY SPONSORED 70) to do shifted laterally along conduit 68 during the sequence of operation of after this being discussed of the present invention.
From Fig. 2 to 5 as can be seen, the lug area 90 of first armed lever 80 leaves flange 90 and puts the regional dip stretching, extension downwards of axle 82 to form a jaw 94.Jaw 94 has hook-shaped on geometric configuration slightly, and configuration design must be used for partly surrounding the cylindrical part 30 of cross bar 16 when the emergency escape device is removed.As shown in Figure 4, and will illustrate in more detail, jaw 94 can surround that part of towards aircraft door 14 of cylindrical part 30, so that (be shown in Fig. 3 and 4) when the emergency escape device is disengaged cross bar 16 is secured to aircraft door 14 with jaw 58 concerted actions of supporting connecting piece 20.
One interlock system indicates with label 100 in Fig. 2 generally, can prevent the manner of execution that the present invention is following, promptly is disengaged and aircraft door 14 discharges cross bar 16 when opening at the emergency escape device.If a kind of like this interlock system just might not turn to the position of being ready for to door knob 24, this just may discharge cross bar 16 and it is fallen downwards from the lower edge of landing gate 14.
In the structure shown in Fig. 2 to 6, interlock system 100 is contained in the lower comer zone of the most close landing gate 14 of base plate 56.One both arms crank 102 is positioned at 57 places, plane near base plate 56, comprises a chimeric armed lever 104 that protrudes upward.One starts armed lever 106 forms an obtuse angle with chimeric armed lever 104, leaves aircraft door 14 points upwards.One bearing pin 110 passes the part between chimeric armed lever 104 of extending in of bell crank 102 and the startup armed lever 106, so that bell crank part 102 can rotate around a pivot center that is parallel to cross bar 16 longitudinal axis.
The upper end that is positioned at chimeric armed lever 104 is a finger 112, and inwardly the slotted eye 68 towards bell crank 60 stretches out.One torsion spring 118 between interlock system bell crank 105 and base plate 56 flat boards 57 encases bearing pin 110, so that pushing bell crank 102 is in position shown in Figure 2.On this position, chimeric armed lever 104 is pushed towards bell crank 60, and the finger of chimeric armed lever 104 can prevent the inhour rotation of bell crank 60.
The end regions that starts armed lever 106 curves, or otherwise make to such an extent that be orthogonal to bell crank 102 and prominent to the outside.Be arranged on the quadrature evagination part that starts armed lever 106 is an adjustable retainer 116 (at Fig. 2 to 6 paintings one bolt).When landing gate 14 was closed, shown in Fig. 3 and 5, retainer 116 pressed the upper surface in a finger-like zone 54 of floor attaching parts 18.In every preferred embodiment of the present invention, constitute the coated a kind of flexible material of bolt cap of retainer 116, this helps the dissipating impact force amount and reduces wear.When retainer 116 pressed floor attaching parts 18, the bell crank 102 of interlock system 100 turned to a position, can make the bell crank 60 that has slotted eye upwards be swung the finger 112 of crossing bell crank 102.Will illustrate in more detail that bell crank 102 rotates by this way, and can close at landing gate and remove the position with mechanism handgrip 24 from device and move when device is ready for the position, discharge cross bars 16 from landing gate 14.
Remove and landing gate 14 when not fastened with a bolt or latch at arrangement for evacuation, supporting connecting piece 20 is positioned at floor attaching parts 18 tops, as shown in Figure 4.Thereby finger 54 and torsion spring 118 that retainer 116 no longer presses floor attaching parts 18 promote the interlocking armed lever 66 of the chimeric armed lever 104 of bell crank 102 against trough of belt hole bell crank 60.This just cause the finger 112 of the chimeric armed lever 104 of interlock system bell crank 102 be in trough of belt hole bell crank 60 interlocking armed lever 66 below, be ready for by the chance that prevents slide arrangement for evacuation under the situation that final cross bar 16 is by mistake discharged.
Examine or check in the normal departure from port of aircraft and during arriving and running of the present invention during the emergency escape, will have more fully the present invention and understand.
When aircraft was prepared departure from port, aircraft door 14 was flapped toward off position.As can be seen, this picture is gone out and is closed but do not fasten with a bolt or latch as yet in Fig. 4, and the cylindrical end 30 of cross bar 16 is grasped between two jaws 58 and 94 of each supporting connecting piece 20, so as to cross bar 16 being fastened in the bottom surface of landing gate 14 securely.The finger 112 of bell crank 106 extends under the upper end of bell crank 60, rotate as follows so as to the handgrip 24 (not drawing among Fig. 4) that prevents landing gate 14, promptly may rotate bell crank 60 and discharge cross bar 16 the clamping between jaw 58 and 94.When device was in this situation, the pawl 42 that colludes of floor attaching parts 18 was pushed, and the upper end of consequently colluding pawl extends through the aperture of groove 46.When landing gate 14 had been fastened with a bolt or latch, landing gate moved down, and promoted each base plate 56 against relevant floor attaching parts 18.As shown in Figure 3, latching aircraft door 14 can be seated in each rounded ends 30 of cross bar 16 among the groove of each floor attaching parts 18.On this point of the sequence of operation, cross bar 16 is still firm in the bottom surface of door by the jaw 58 and 94 cards of each base plate 56.It is further noted that aircraft door 14 moves to position below it, that fasten and can cause the circular arc turning 86 of roller 88 and base plate 56 each first armed lever 80 to be pressed in above the upper end of colluding pawl 42 of each floor attaching parts 18 downwards.This rotates with regard to the upper end that causes colluding pawl 42, so that it can not extend through the aperture of base plate 56 grooves 40.In addition, along with landing gate 14 moves down, the finger portion that protrudes upward 54 of contact floor, backing block 116 ends of bell crank 102 attaching parts 18.Be in Fig. 3 fully downwards and during the position that fastenes at door 14, backing block 116 presses the digitation 54 of base plate 56, and bell crank 102 is rotated on the position simultaneously, the finger 112 that can make the upper end of bell crank 60 cross bell crank 102 downwards.
Next step of the sequence of operation is to be ready for the emergency escape device so that take off.In order to be ready for this device, the handgrip 24 of mechanism 10 is rotated one and can causes push-and-pull wirerope 26 to rotate on the position in (with respect to the orientation that is shown in Fig. 2 to 6) along clockwise direction.Especially with reference to Fig. 5, rotate bell crank 60 and can cause corresponding rotation first armed lever 80, so that jaw 94 is rotated and leaves the rounded ends 30 of cross bar 16.In addition, rotate arc corners that first armed lever 80 can drive the roller 88 and first armed lever 80 upwards and leave the end of colluding pawl 42.This can discharge and collude pawl 42, and it turns back to the position that is pushed, and it extends through the aperture of groove 40 in this position, and its degree is enough to prevent that cross bar rounded ends 30 from deviating from from groove 40.
But for to being engaged in the demonstration that the crew who is ready for this device provides a failure-free sense of touch, the top edge of bell crank 60 contacts a stop motion mechnism when bell crank 60 is rotated the position of being ready for.See most clearly in Fig. 2, this stop motion mechnism comprises a flange 120, and the position above bell crank 60 is protruding from base plate 56 Surface Vertical ground.One bolt 116, or similar adjustable stop motion mechanism passes flange 120 and stretches upwards.Be flapped toward when being ready for the position at bell crank 60, the top edge of bell crank is forced to lean the effect of bolt 116 heads a kind of to form " very thorough ", exactly like the operation of various handle assemblies, these handgrips are connected by some solid components, rather than soft a little pushing wirerope 26.
One when the customary arrival of aircraft destination, and the crew removes the position and decontrol by the handgrip 24 of mechanism 10 is turned to.This causes bell crank 60 to be rotated on the aforementioned location that is shown among Fig. 3.When bell crank 60 is flapped toward the releasing position, but the upper surface of bell crank 60 upper ends contacts a stop motion mechnism so that the demonstration of sense of touch to be provided, and promptly handgrip 24 had reached already and removed the position.But the stop motion mechnism that provides sense of touch to show structurally is similar to and is used to show that handgrip 24 is positioned device and is ready for locational aforementioned stop motion mechnism.Specifically, an outstanding flange 122 is stretched out from base plate 56 in a certain position more than bell crank 60 upper ends.One adjustable backing block 116 (being a bolt in drawn device) passes flange 122 and protrudes upward.
Be under the situation of removing the position at device, the crew makes aircraft door 14 take off door bolt, and door 14 promptly is moved upwards up on the described position of Fig. 4.Move on to the position that is shown in Fig. 4 along with aircraft door, bell crank is allowed to rotate (in Fig. 3 and 4, inhour), so that the digitation 112 of bell crank 102 stretches below the upper end of bell crank 60, is ready for the position so as to fixing bell crank 60 in case locking mechanism handgrip 24 moves to device.Once illustrated at Fig. 4 in the past that each rounded ends 30 of cross bar 16 was that the jaw 58 and 94 by supporting connecting piece 20 encases and holds with a firm grip.In addition, along with aircraft door 14 moves up, collude pawl 42 and turn back to the position that is urged, the upper end of colluding pawl on this position extends through the aperture of base plate 56 upper grooves 40.Thereby cross bar 16 is fixed in the bottom surface of door, and door can be opened and not unfolded fire escape.
The running of expanded emergency arrangement for evacuation of the present invention can be understood with reference to Fig. 5 and 6.Particularly, as preceding pointed, Fig. 5 aircraft door that drawn is closed and is fastened and operates the present invention to be ready for the situation of emergency escape device.Under the state of being ready for, each cylinder-shaped end of cross bar 16 is placed among the groove 40 of each floor attaching parts 18.Because the pawl 42 that colludes of each floor attaching parts 18 is pushed to one and colludes pawl upper end and extend through on the position in groove 40 apertures, each rounded ends 30 (thereby cross bar 16) block firm in the floor of aircraft.
As shown in Figure 6, when door 14 was not fastened, door moved up, and cause each supporting bracket 20 to be moved away from each floor attaching parts 18, and back door 14 can be flapped toward the open position, cross bar 16 simultaneously, thereby and the base card jail of fire escape in the bottom of landing gate door opening.Along with the unlatching of landing gate, the emergency escape device is triggered, and for the fire escape inflation, so that stretch out passenger and crew is escaped from downwards rapidly.
The finger 84 of the directed downwards of second link rod 70 is in order on the unlikely unlocked position that is frozen in as shown in Figure 3 in the end of colluding pawl 42 of guaranteeing the most close cross bar 16.More specifically say,, collude pawl 42 possibility clamping stagnations on the position of non-locking, although there is a side pressure strength to make it to return latched position owing to freeze or other reasons.Thereby, when supporting connecting piece 20 is moved away from colluding pawl 42, as shown in Figure 4, collude pawl and perhaps can stay on the unlocked position.This is a kind of trouble when being ready for the slide arrangement for evacuation in mechanism 10 because floor connecting element 18 may not can anchoring cross bar 16 rightly.
Therefore, when being ready for the slide arrangement for evacuation in mechanism 10, finger 84 turns to a following position as illustrated in Figures 5 and 6.Thereby, when door 14 pins as shown in Figure 5, finger 84 press leave cross bar 16 farthest collude pawl 42 ends, force and collude pawl and turn back to latched position.
Withdraw fire escape although can use various devices to combine with expanded emergency with the present invention, every currently preferred embodiment of the present invention is all used a kind of electrical interlocking system, only is in to be ready at mechanism's handgrip 24 just to allow triggering when position and inner door place its open position to 21.This preferred disposition is schematically depicted among Fig. 7.In the configuration of Fig. 7, a battery pack 132 or other power supplys even come from a squib 146, and this pipe is loaded on a storage tank place.When electric current fed to squib 146, explosive was lighted to drive a penetration device that can pierce through a diaphragm in the storage tank 148.The air pressure that is provided by storage tank 148 starts a pneumatic actuator 150 washing landing gate 14 rapidly open, and fire escape is inflated by one second storage tank (not shown).
Adopt the configuration of Fig. 7, mechanism's handgrip 24 be in device be ready for position and inner door when being seated in the open position to 21 fire escape can be unfolded.Particularly, switch 124 mechanically is connected in handgrip 24 (other parts perhaps of the present invention), so that 124 on switch is in when being ready for the position just closed (conduction) at device.Equally, also closure (conduction) just when inboard aircraft door handgrip 21 is seated in its open position only of tandem tap 126.
One test switch 142 and a safety switch 144 are fitted together with battery pack 132.Safety switch 144 be used to cut off lead to squib 146 electric power to prevent unconsciously to trigger squib in the maintenance period.Test switch 142 is in all the time and cut-offs the position, unless be pressed.When the staff presses test switch 144, it is connected to a lamp (not shown) among the common circuit, if trikle charger and/or quick charger provide electric power to battery 134, and if battery charge surpass a predeterminated level, lamp will be light.
Though the preferred embodiments of the present invention have been done diagram and explanation, are appreciated that and can make various changes therein and can not deviate from spirit of the present invention and category.As illustrative limiting examples, push-and-pull wirerope 26 perhaps can replace with a kind of STATEMENT OF FEDERALLY SPONSORED such as straight-bar, and chargeable battery 132 perhaps can be the battery of long non-charging type of a kind of life-span and remove the needs of charger 136 from.Because these and other may be by the change of having done the people who has general proficient in the art, replacement and correction, desired is that the category of the patent of at this point authorizing will only be subjected to the restriction of every qualification in appended every claim.
Claims (13)
1, a kind of mechanism that is used for being ready at aircraft/removing and trigger the emergency escape device, this device comprises a fire escape, it has a cross bar that is connected in slide one end, device is disengaged when cross bar is connected in a landing gate, and when cross bar is connected in student's airframe, be ready for, Men Kecong one closes with latched position and shifts to a unlatching and a unlocked position, and this mechanism comprises:
(a) a floor attaching parts can be installed on student's airframe, and the floor attaching parts comprises:
(i) base, formation one is used to put the breach of cross bar; And
(ii) one collude pawl, be installed on base, collude pawl and can prevent that from one the latched position that cross bar is deviate from from breach from turning to a unlocked position of allowing that cross bar is deviate from from breach with respect to base among cross bar is positioned at breach the time;
(b) supporting connecting piece can be installed on aircraft door and be engaged in the floor attaching parts when door is closed and lock, and this supporting connecting piece comprises first jaw that stretches out downwards, and this jaw is positioned at a side of breach, and faces breach when door is closed and lock;
(c) one first STATEMENT OF FEDERALLY SPONSORED, be rotatably installed on supporting connecting piece along a pivot center that is roughly parallel to the cross bar longitudinal axis, this first STATEMENT OF FEDERALLY SPONSORED comprises that one connects armed lever, has an end that stretches away from pivot center, wherein a slotted eye is formed at this end that connects armed lever, connecting armed lever can turn to a second place from a primary importance, and can forward primary importance to from the second place; And
(d) one second STATEMENT OF FEDERALLY SPONSORED is rotatably installed on supporting connecting piece along a pivot center that is roughly parallel to the cross bar longitudinal axis, and this second STATEMENT OF FEDERALLY SPONSORED comprises:
(i) a crooked armed lever has an ancon and an end, and this end comprises a bearing pin, from the end along crossing out and be received among the slotted eye of first link rod; And
(ii) one second jaw, roughly face first jaw, whereby, when door is closed and lock, the connection armed lever of first STATEMENT OF FEDERALLY SPONSORED turns to the second place from primary importance can be caused ancon to press colluding pawl and make colluding pawl and turning to unlocked position, and cause second jaw to rotate towards first jaw, when cross bar is among the breach of floor attaching parts, cross bar is held between first and second jaws, thereby removes the emergency escape device; And turning to primary importance from the second place, the connection armed lever of first STATEMENT OF FEDERALLY SPONSORED can cause ancon from colluding pawl and moving away and make and collude pawl and turn to latched position, and cause second jaw, thereby when cross bar is among the breach of floor attaching parts, cross bar is discharged and is ready for the emergency escape device between two jaws from the first jaw turn-off.
2, according to the described mechanism of claim 1, wherein the emergency escape device comprises a storage tank, hold the gas-pressurized that is sealed in a diaphragm back, and landing gate comprises a door knob, be movable to an open position to open landing gate, and be movable to an off position to close landing gate, this mechanism also comprises:
(a) mechanism's handgrip is connected in first link rod, in order to rotate first link rod;
(b) one first switch has the position of cut-offfing and a make position, is connected in mechanism's handgrip, when the emergency escape device is ready for, and first switch closure, and when the emergency escape device was removed, first switch cut-off;
(c) second switch has the position of cut-offfing and a make position, is connected in door knob, when door knob is in the open position, and the second switch closure, and when door knob was in the closed position, second switch cut-off;
(d) power supply; And
(e) electric exploder, being installed on storage tank also can be triggered to pierce through the diaphragm in the storage tank by electric power, this electric exploder, first and second switches, and power supply all is together in series on electric each other, wherein power supply is powered to electric exploder when first and second switch closures, thereby triggers electric exploder and pierce through diaphragm in the storage tank to trigger the emergency escape device.
3, according to the described mechanism of claim 1, also comprise a flag, stretch out from colluding pawl, this flag is shifted to a second place from a primary importance when latched position turns to unlocked position colluding pawl, as a telltale directly perceived, show whether the emergency escape device is ready for, and whether the emergency escape device is removed.
4, according to the described mechanism of claim 1, comprise that also one removes retainer, be connected in supporting connecting piece, remove retainer and connect rotating of armed lever and sense of touch ground with restriction and show that the emergency escape device removes but collide this at the connection armed lever of STATEMENT OF FEDERALLY SPONSORED first link rod when primary importance turns to the second place.
5, according to the described mechanism of claim 4, wherein first STATEMENT OF FEDERALLY SPONSORED comprises an interlocking armed lever, extends in and removes below the retainer, and this interlocking armed lever upwards rotates when primary importance turns to the second place and collision releasing backing block at armed lever.
6, according to the described mechanism of claim 4, also comprise and be ready for retainer, be connected in supporting connecting piece, but wherein first gangbar is ready for retainer in the collision when the second place turns to primary importance of the connection armed lever of first gangbar and is connected upwards rotating of armed lever and sense of touch ground with restriction and show that the emergency escape device is ready for.
7, according to the described mechanism of claim 6, wherein be ready for retainer and above the connection armed lever of first STATEMENT OF FEDERALLY SPONSORED, be connected in supporting connecting piece, be ready for retainer and connect armed lever connecting armed lever collision when the second place turns to primary importance.
8, according to the described mechanism of claim 1, also comprise and be ready for retainer, be connected in supporting connecting piece, but wherein first STATEMENT OF FEDERALLY SPONSORED is ready for retainer in the collision when the second place turns to primary importance of the connection armed lever of first STATEMENT OF FEDERALLY SPONSORED and is connected upwards rotating of armed lever and sense of touch ground with restriction and show that the emergency escape device is ready for.
9, according to the described mechanism of claim 8, wherein be ready for retainer and above the connection armed lever of first STATEMENT OF FEDERALLY SPONSORED, be connected in supporting connecting piece, be ready for retainer and connect armed lever connecting armed lever collision when the second place turns to primary importance.
10, according to the described mechanism of claim 1, also comprise a roller,, be used among slotted eye, rolling coaxially round bearing pin.
11, according to the described mechanism of claim 1, also comprise an interlocking STATEMENT OF FEDERALLY SPONSORED, be connected in supporting connecting piece, this interlocking STATEMENT OF FEDERALLY SPONSORED can turn to a non-locked position from a latched position, chimeric first STATEMENT OF FEDERALLY SPONSORED on last position and prevent that first STATEMENT OF FEDERALLY SPONSORED from turning to primary importance from the second place, and on one position, back, throw off first STATEMENT OF FEDERALLY SPONSORED, and this interlocking STATEMENT OF FEDERALLY SPONSORED comprises a torsion spring, pushing interlocking STATEMENT OF FEDERALLY SPONSORED is stayed on the latched position.
12, according to the described mechanism of claim 11, the STATEMENT OF FEDERALLY SPONSORED of wherein interlocking forms a both arms crank, has first and second armed levers, and the protruding top between first and second armed lever, and wherein this protruding top is rotatably installed on supporting connecting piece.
13, according to the described mechanism of claim 1, wherein the floor attaching parts is closed first armed lever that contacts the interlocking STATEMENT OF FEDERALLY SPONSORED when locking at door, withstands first armed lever and causes interlocking chimeric and turn to non-locked position so as to applying a thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96111537A CN1087702C (en) | 1996-08-22 | 1996-08-22 | Mechanism for arming, disarming and activating airplane emergency slide evacuation systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96111537A CN1087702C (en) | 1996-08-22 | 1996-08-22 | Mechanism for arming, disarming and activating airplane emergency slide evacuation systems |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1174797A CN1174797A (en) | 1998-03-04 |
| CN1087702C true CN1087702C (en) | 2002-07-17 |
Family
ID=5121149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN96111537A Expired - Lifetime CN1087702C (en) | 1996-08-22 | 1996-08-22 | Mechanism for arming, disarming and activating airplane emergency slide evacuation systems |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1087702C (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101218150B (en) * | 2005-07-15 | 2010-05-19 | 空中客车德国有限公司 | Emergency opening device for an overhead locker with a lowerable shell |
| CN107813946A (en) * | 2017-11-08 | 2018-03-20 | 成都富凯飞机工程服务有限公司 | A kind of aircraft escape slide is anti-to misplace system for prompting and method |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3006995B1 (en) * | 2013-06-14 | 2017-03-17 | Latecoere | AIRPORT DOOR TOBOGGAN ARMING / DISARMING METHOD AND MECHANISM FOR IMPLEMENTING THE SAME |
| US10118708B2 (en) * | 2015-10-19 | 2018-11-06 | Goodrich Corporation | Evacuation slide with beam structure comprising four-point cross section |
| US9945488B2 (en) * | 2015-11-10 | 2018-04-17 | Goodrich Corporation | Mechanically-activated inflation valve actuation apparatus |
| CN105383680B (en) * | 2015-11-24 | 2017-12-29 | 中国商用飞机有限责任公司 | The emergent slide armed trigger mechanism of aircraft door |
| EP3708483B1 (en) * | 2019-03-14 | 2021-09-15 | SFS Intec Holding AG | Holding device for wall modules |
| CN113978737A (en) * | 2021-11-10 | 2022-01-28 | 中航沈飞民用飞机有限责任公司 | Escape slide control mechanism for landing door of civil passenger plane |
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| US3852854A (en) * | 1973-04-05 | 1974-12-10 | Lockheed Aircraft Corp | Girt bar latching system |
| US4125235A (en) * | 1977-04-04 | 1978-11-14 | The Boeing Company | Apparatus for opening an aircraft door and for arming and disarming an escape slide deploying mechanism |
| EP0192503A1 (en) * | 1985-01-24 | 1986-08-27 | AEROSPATIALE Société Nationale Industrielle | Mechanism for the automatic actuation of a rescue device at the time an exit door is opened |
| EP0507359A1 (en) * | 1991-03-08 | 1992-10-07 | The Boeing Company | Mechanism for releasing stored gas from a pressure vessel |
| US5400985A (en) * | 1993-02-22 | 1995-03-28 | The Boeing Company | Airplane escape slide system and rotational girt bar therefor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3852854A (en) * | 1973-04-05 | 1974-12-10 | Lockheed Aircraft Corp | Girt bar latching system |
| US4125235A (en) * | 1977-04-04 | 1978-11-14 | The Boeing Company | Apparatus for opening an aircraft door and for arming and disarming an escape slide deploying mechanism |
| EP0192503A1 (en) * | 1985-01-24 | 1986-08-27 | AEROSPATIALE Société Nationale Industrielle | Mechanism for the automatic actuation of a rescue device at the time an exit door is opened |
| EP0507359A1 (en) * | 1991-03-08 | 1992-10-07 | The Boeing Company | Mechanism for releasing stored gas from a pressure vessel |
| US5400985A (en) * | 1993-02-22 | 1995-03-28 | The Boeing Company | Airplane escape slide system and rotational girt bar therefor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101218150B (en) * | 2005-07-15 | 2010-05-19 | 空中客车德国有限公司 | Emergency opening device for an overhead locker with a lowerable shell |
| CN107813946A (en) * | 2017-11-08 | 2018-03-20 | 成都富凯飞机工程服务有限公司 | A kind of aircraft escape slide is anti-to misplace system for prompting and method |
| CN107813946B (en) * | 2017-11-08 | 2020-11-20 | 成都富凯飞机工程服务有限公司 | System and method for reminding mistaken release prevention of emergency slide of airplane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1174797A (en) | 1998-03-04 |
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