DE102007049673A1 - Damaged aircraft recovering method for use during e.g. forced landing, involves lifting construction in such manner that one of supporting elements is insertable into construction, and carrying load received by pieces over elements - Google Patents

Abstract

The method involves lifting a support construction comprising a set of supporting elements (2) stackable on top of each other, by using a lifting element (3) in such a manner that one of the supporting elements is insertable into the construction. The lifting element is lowered, raised and brought in engagement with one of the supporting elements. The lifting, lowering and raising processes are repeated so that connecting pieces are gradually raised. Load received by the pieces is carried over the supporting elements and the lifting element supporting the supporting elements. An independent claim is also included for an aircraft recovery lifter, comprising a basic frame.

Description

The The present invention relates to a method for recovering a damaged one Aircraft, wherein a lifting structure with a floor-mountable Base frame under the wing an aircraft is arranged, and a lifting device on the support surface one for lifting height of the aircraft, with the lifting structure having a connecting piece, the from the lifting structure with a matching, fixed to the wing provided lifting fitting engaged and then with the wing is raised.

Similarly The present invention also relates to an aircraft jack with a base frame and a lifting structure arranged thereon, the below the wing of a damaged aircraft can be arranged to one of the lifting structure worn fitting and one fixed to the wing provided lifting fitting engage with each other and the wing and thereby raise the aircraft to a transportable position.

Appropriate Lifting constructions are already known in principle. They persist z. B. from a hydraulic tripod, d. H. that z. B. three hydraulic cylinders, which are arranged along the edges of an imaginary pyramid and at the point where the three pyramid edges collide with connected to a common connector which can be lifted by the hydraulic cylinders.

in the Fall of emergency landings, unfavorable weather conditions or when technical or human errors occur it happens again and again that aircraft not on a regular Runway be brought to a halt, but over the runway or shoot of a runway and on not designated areas for Keep coming. This may be the suspension or parts of the chassis kink or sink in correspondingly soft ground, so that this Airplane neither independently Still in this situation towed by a tugboat can be. Even on fixed runways it may be too a kinking or shearing of suspension or parts of the chassis come, so that even then, if such a damaged aircraft is on a firm surface, such as B. a runway or taxiway comes to a halt, neither an independent one Moving still a towing with a tug is possible. As far as the ground around the aircraft is sufficiently strong and stable is, in principle, it is possible to lift such an aircraft with a mobile crane and on, for example a broken chassis by a provided with corresponding wheels undercarriage to replace or support the aircraft on it, then with tugs to bring to an aircraft hangar or to a parking space where if necessary further recovery and repair work can be carried out can.

The However, use of a crane is ruled out in case of an uneven or not enough solid Underground. In such soil conditions are the beginning mentioned Aircraft mover used under the wing of the Plane are arranged and positioned so that a connector, which is in the upper part of the corresponding lifting structure, with a special lifting fitting on the underside of the wing in engagement can be brought to the wing and then with the lifting structure So that the airplane can raise altogether until it is in one position in which it is transported away with the help of other facilities can be, such. B. by arranging a wheeled trolley under the wing or under the hull, and towing the aircraft, if the corresponding trolley does not have its own drive unit.

However, the conventional lifters have the disadvantage that they necessarily have to have a relatively large height, as to arrange appropriate transport vehicles or transport structures below the wing or below the fuselage, the wing, for example, raised to a height of 4 to 5 meters above ground or even further must become. In addition, also a base frame must be provided, which has a sufficiently large support surface to sink when receiving the load of the aircraft or a part of the aircraft in soft ground. Also this base frame already has a certain height. In addition, it may happen that the ground in the area of the damaged aircraft is uneven and the fuselage of the aircraft, for example, in a trough or gutter, so that the wings on either side of this trough either partially resting directly on the ground, but at least relatively close to the ground run. Even if the landing gear of the aircraft is kinked or sheared off on one side, the aircraft lowers on one side and rests on one of its wings, wherein in the region of arranged at a certain distance from the fuselage lifting at the bottom of the wing often only relatively little space to Ground is available. In such situations, it is very difficult to arrange the known jack of three arranged in a pyramid shape on a base frame in the desired manner under a wing. Often this costly and tedious ground works are required Lich or a salvage of the entire aircraft must be abandoned completely for economic reasons.

Opposite this State of the art, the present invention, the object of a Procedure for recovering damaged aircraft and a corresponding Aircraft mover with the features mentioned to create, which have a comparatively lower height and yet in capable of supporting the wing and the associated fuselage of the aircraft on a nearly arbitrary size Raise height, as for the recovery of the aircraft may be required.

• – die Hebekonstruktion aus aufeinander stapelbaren Stützelementen und mindestens einem Hebeelement besteht, wobei
• – i) ein oder mehrere Stützelemente in der Weise durch das Hebeelement angehoben werden, daß ein weiteres Stützelement in die Konstruktion einfügbar ist, und
• – ii) das Hebeelement abgesenkt und erneut mit mindestens einem der Stützelemente in Eingriff gebracht und angehoben wird, und
• – die Schritte (i) und (ii) gegebenenfalls mehrfach wiederholt werden, so daß
• – das von einem oberen Stützelement getragene Anschlußstück schrittweise angehoben wird, wobei
• – die von dem Anschlußstück aufgenommene Last abwechselnd allein über die aufeinandergestapelten Stützelemente bzw. über die Stützelemente und das diese tragende Hebeelement abgetragen wird.

With regard to the method mentioned, this object is achieved in that

• - The lifting construction consists of stackable support elements and at least one lifting element, wherein
• - i) one or more support elements are raised in such a way by the lifting element, that a further support element can be inserted into the construction, and
• - ii) lowered the lifting element and again brought into engagement with at least one of the support elements and raised, and
• If necessary, steps (i) and (ii) are repeated several times so that
• - The carried by an upper support member fitting is gradually raised, wherein
• - The picked up by the fitting load is alternately removed alone on the stacked support elements or on the support elements and the lifting element carrying this.

at this method and the corresponding device, hereinafter still explained in detail will, must Place under the wing only for the arrangement of the base frame and at least the fitting or one carrying the fitting supporting element suffice. The fitting or the support element, which carries the connector is then raised by a corresponding lifting element so far that another support element inserted into the construction can be. The lifting device is then lowered again and again engaged with at least one of the support members and raised. If necessary, these steps are repeated several times, which means that there also from an upper support element worn fitting step by step is raised, wherein the load received by the connector alternately either alone over the stacked support elements or over the support elements and that this lifting lifting element is removed.

In other words, while the lifting element is being lowered, the load alone is removed via the stack of superimposed supporting elements on the base frame and from there to the ground. Then the lowered lifting element relies on a correspondingly lower position of the support structure again, and raises the support structure with the fitting so far that another support element can be inserted into the structure and then the lifting element is lowered again and the load of the now again added to another support element supplemented stack of support elements. In contrast to the prior art, it is therefore sufficient if the lifting element lifts the support structure so far that only one further support element can be inserted into the construction. However, the lifting element does not have to be designed to reach the entire required height of the wing in a single stroke. This means that the lifting element can be configured correspondingly small and compact. The height of the individual support element can be chosen arbitrarily in principle. Conveniently, the height of the support elements is matched to the maximum stroke of the lifting element, ie the individual support elements are in any case in the vertical direction smaller than the maximum stroke or stroke of the lifting element. Otherwise, the height of the support elements is suitably chosen so that the overall construction has a certain minimum height in an initially under a wing to be arranged state, which is definitely much lower than that of conventional aircraft jacks. For example, the base frame could have a height between 20 and 80 cm and the single support member could also have a height between 20 and 80 cm. For example only, it is assumed that the base frame and support members each have a height of 50 cm. In one such example, the minimum overall height is 1 m, which is significantly less than the height of prior art aircraft jacks. The lifting element can, for. B. be arranged within the base frame and a stroke of z. B. 60 to 80 cm. Conveniently, of course, a plurality of lifting elements are provided at a distance from each other on or in the base frame in order to lift the support elements. By alternately lifting, inserting support elements and lowering the stack of support elements is then built, wherein the support surface is raised and, for example, ten stacked support elements can cause a maximum lifting height for the wing to 4.50 m. Of course, the stack can be supplemented by other support elements, if such a stroke should not be sufficient. One achieves any lifting heights without the lifting element or the lifting elements must have a correspondingly large stroke, which is generally would adversely affect the overall height of the entire device, which also multiply telescoping hydraulic cylinder can alleviate the problem somewhat, but do not change the basic problem, if the required lifting height is many times greater than the initially available under the wing space , ie z. B. is 6 to 10 times this initially available space.

Regarding the aircraft host lift itself is the basis of the invention Task solved by that the Lifting structure stackable support elements and at least one lifting element which one for that is designed to lift at least a given support element so far, the existence another support element in the supporting structure added can be lowered, the lifting element is lowered without receiving the load, while the load of the wing is received by the stacked support elements, and again with a support element engageable to the support elements for adding a another support element raise again.

refinements the method according to the invention and corresponding, embodiments of Device include u. a. two different variants.

According to one first variant are two groups of stackable support elements provided, which expediently be arranged nested. At least one of Groups of support elements is liftable by the lifting element or by a plurality of lifting elements and occurs with a connecting piece or a connecting piece having guide frame engaged to lift this. This lifting takes place so far, below the wing enough space for the Insertion of another support element into the second group of support elements is available. Subsequently becomes the second group of support elements lowered, with the fitting or the frame, which carries the fitting, now on the corresponding higher first group of support elements is deposited and the load over this is removed. Subsequently is the lowered first stack to another support element increased and the lifting element now raises this spiked first set of support elements again to repeat the process just described. Conveniently, consist of the support elements rectangular frame with support posts at the corners and it's an outer frame group and an inner frame group, the outer frame group includes the inner frame group. It can at least the support elements the outer group one in plan view U-shaped Have frames that make it possible from the open side of the U of the stacked outer support member additional inner support elements insert, and additional external support elements around the stack of inner support elements add around.

According to one another variant is provided that only a single group of Stackable support elements is used, which are lifted by the lifting element in the manner that under the respective raised support elements another support element insertable is. Subsequently the lifting element or the lifting elements are lowered and the previously raised group of support elements is thereby on the added one support element discontinued. By further lowering the lifting elements with the previously raised groups of support elements except Intervention brought and with the new, supplemented group of support elements at a lower position, typically at the newly added support element, engaged to raise the entire construction again and another support element add to be able to.

Both Variants cause a gradual lifting of the wing, a Complete the stack of support elements in the extended state of the lifting element, a retraction or Lowering the lifting element while the load from the stack of support elements is received, and a renewed lifting of a stack of support elements the lifting element in order to insert another support element again.

On this way is despite the low lift of the lifting elements and a correspondingly small size, the lifting height in principle unlimited and only by the number of available support elements limited.

The support elements can, As already mentioned, have substantially rectangular frame members with corner posts, where appropriate, if a measure of 2.50 m in at least one (horizontal) direction of the corresponding Frame elements not exceeded So that the entire device can be moved quickly even with the help of trucks over public roads and just about transported larger distances can be. The height the support elements is significantly lower and amounts to for example, between 20 and 80 cm. Such rectangular frame with Corner posts can be stacked in a simple and stable manner.

The Lifting element or the lifting elements are preferably hydraulic or Pneumatic cylinder, of which preferably several are provided. It is understood that alternatively also cables or Winches could be provided.

there it is useful if according to another embodiment the upper ends of each of the support elements or the tops of the support elements with the lower ends or lower sides of the respectively arranged above support elements form-fitting can be brought into engagement.

in the Case of the rectangular frame with corner posts are preferably the corner posts so designed. that she with each above and underlying corner post form-locking engagement. For example can the corner posts have a projection on their lower end face, while they at the upper end a similarly shaped recess have, wherein the projection fits into the respectively underneath Recess engages.

According to one embodiment, in which only one group of support elements is provided, the are each formed identically, it is provided that the support elements in a side view at least in its lower section one Extension, with the bottom of this lower extension or the extended section for engaging each a lifting element is designed. In this way, the bottom remains a support element, after being lifted by the lifting elements, at the bottom free for Pushing and placing on the inserted support element, because the intervention areas for the lifting elements are only in the area of these extensions. It is understood that this Extensions to a support frame both outward how to be inward, depending on whether the lifting elements within the frame profile or outside of the frame profile are arranged. Appropriately, are the relevant extensions in the case of as a rectangular frame with posts trained support elements at the posts of the same. In particular, the posts can be seen in a side view trapezoidal or pyramid-shaped be so that the Bottom of an upper support element in any direction further unloads than the one with the bottom of the upper support element to be engaged top of the underlying post a support element and thus an attack possibility for a Lifting element offers.

Farther it is appropriate if according to a embodiment the invention, the respective lower sides of the extension of the support elements or post a hinged connection with the obe ren ends of Form lifting elements. For example, the subpages could be in the range the respective extensions be semi-cylindrical recesses, in which the trained as a cylinder heads of hydraulic piston or Hydraulic cylinders engage, with the relevant cylinder axes preferably parallel to the longitudinal edges a corresponding rectangular frame, from which the support element consists.

A Such articulated connection has the advantage that the lifting elements outside the line of flight of the one above the other stacked posts can be arranged, taking them under a run at a certain angle to the vertical and this angle while the lifting of a support element changed d. H. especially reduced. This angle change is made by the articulated connection in a simple way allows being also the opposite End of a corresponding hydraulic cylinder accordingly a shaft or a bolt should be mounted to pivot.

Especially in the case of pivotally mounted lifting elements, it is expedient if an additional one support frame is provided during the a one-sided dodging or tilting of a lifting process prevented by the lifting elements raised support element. there it is sufficient if the support frame still to such a height is sufficient, in which he the lowest support element, which by the Lifting elements is raised so far that another support element under it fits, supported. Likewise, the support frame but also directly the hydraulic piston or its upper ends against secure a lateral evasion.

One such additional support frame is preferably arranged so that it allows the insertion of a new, lowest support element not hindered after the previously lowest support element on a corresponding Raised height has been.

The definitely required fitting for connection with a under the wing arranged and in the wing integrated lift fitting must open the uppermost support element to be ordered. Appropriately sees For this purpose, a guide frame in front, which on the top support element seated, with the fitting in turn on the guide frame preferably is arranged freely movable in any horizontal direction and only through the outer boundary of the support frame or the guide frame placed thereon is limited.

This takes into account the fact that when lifting the wing of an aircraft from a position in which the wing is significantly inclined relative to the horizontal, the effective movement of the aircraft represents a rolling movement of the aircraft fuselage on the ground, so that under the wing fixedly arranged Lifting fitting against the stationary support frame also must dodge in a horizontal direction. Since the base frame and the individual support elements are not necessarily aligned exactly parallel or perpendicular to the pivot axis of the fuselage, even in a direction parallel to this aircraft pivot axis direction of movement of the fitting useful and appropriate. This limited horizontal freedom of movement of the connector, the wing can be raised free of any horizontal constraining forces and the fuselage aligned accordingly so that both wings assume their normal position relative to the horizontal, which also corresponds to the transport position of the aircraft. It is understood that depending on the terrain and deviations from this ideal alignment may be possible and useful.

In addition, can for a easier to engage the fitting with the lifting fitting the wing underside the connector at least a horizontal axis can be pivoted and it can be be so designed that it at least limited pivotable about a vertical axis.

Conveniently, has the fitting one Carriage with several rollers on top, on a traverse of the guide frame run. additionally For example, the traverse can be crossed to two transverse to the traverse Side members, similar to the portal of a gantry crane, arranged displaceable or rollable in the direction of the longitudinal members be. Alternatively, the fitting also a ball bearing bed which additional Rotations facilitated, and the actual engagement element of the Connector, the For example, is designed as a kind of ball head, in the trained as a ball socket lifting fitting, can on the Trolley of connector gimbal be stored.

Further Advantages, features and applications of the present Invention will become apparent from the following description of a preferred embodiment and the associated Characters. Show it:

1 a perspective view of a schematically illustrated first embodiment,

2 in a side view the functional principle of in 1 illustrated embodiment,

3 a view similar 1 however with an additional support frame,

4 a side view of the embodiment with support frame according to 3

5 a perspective view accordingly 3 , but with another variant of a support frame

6 a base frame for an alternative embodiment of the invention with two nested support frames,

7 the base frame 6 with a principle also suitable for the first embodiment guide frame with connector

8th to 10 a sequence of method steps for the construction of the second embodiment,

11 a schematic plan view of the guide frame with connector, and

12 different views of the same in the 1 to 5 illustrated first embodiment

In 1 can be seen in a perspective view of a first embodiment of the invention with a base frame 1 , Support elements 2 and lifting elements 3 , The lifting elements 3 consist essentially of hydraulic cylinders 4 and hydraulic pistons 5 , Two hydraulic pistons each 5 are at their upper engagement end via a continuous cylinder rod 12 connected to each other, which at the same time forms part of an engaging joint with the posts 7 the support elements 2 forms. The same device is schematic and in various planar views also in FIG 12 shown.

The support elements 2 are formed as a rectangular frame, which at their corners in each case a post 7 have two adjacent posts 7 each through two round tubes 8th connected to each other. In a first view, the posts have an edgewise rectangular profile and in a view perpendicular thereto a profile of an obliquely angled trapezoid so that they have extensions 7 ' form at their lower ends, which protrude outwardly beyond the frame profile defined by the top of the corner posts. This is even more apparent in 2 , where for one of the only schematically represented with their outlined support elements 2 the posts 7 with outward extensions 7 ' are shown. The posts 7 also have recesses on their upper side 9 on, in which appropriate at the bottom of the posts 7 provided pins 21 that only in 2 are shown for the uppermost support element, engage, so that the stacked support elements 2 positively engaged with each other. Optionally, stacked support elements could additionally by cotter pins or by respectively adjacent tubes 8th encompassing brackets aneinan to be assured.

The functional principle of this aircraft jack is best recognized in 2 , which are the lower support elements 2 only schematically in an outline representation reproduces. The extensions 7 ' the posts are on their underside with approximately semi-cylindrical recesses 13 educated. In an in 2 Dashed position shown, the cylinder rod 12 , Which 2 on one side adjacent hydraulic piston 5 interconnects, form-fitting in the semi-cylindrical recesses 13 pushed in, as shown in the dashed position of the hydraulic piston in 2 is shown. Then the hydraulic cylinders 4 pressurized, so that the hydraulic piston 5 from the hydraulic cylinders 4 be extended and thereby the lowest support element 2 and all supporting elements stacked on top 2 Lift. The hydraulic cylinders 4 are at their lower end to a corresponding shaft 14 pivotally mounted, so that the included between the hydraulic cylinder and the piston on the one hand and a vertical angle on the other hand can change from the position shown in dashed lines in the position shown in phantom. This will be the pistons 5 far from the cylinders 4 extended, that under the raised in this way, the lowest support element 2 another support elements 2 can be inserted, as shown in 2 perpendicular to the paper plane. Because the support elements 2 even lower protrusions 21 have that in the top recesses 9 an underlying support element engage, are guide grooves 11 (please refer 1 ), in which the Vorspünge or pin 21 intervene when a new support element 2 under a raised or a group of raised support members 2 is inserted. The hydraulic pistons 5 However, before inserting a new support element 2 be extended a little further than in 2 shown so that the downwardly projecting pins 21 the upper support elements do not interfere with the insertion of the new support element.

After inserting a new support element, the hydraulic cylinders 4 depressurized and the piston 5 is moved back accordingly, so that he at the next following support element 2 in the in 2 Dashed piston position shown passes and with this support element 2 can engage.

Because the hydraulic cylinders and pistons around the shaft 14 are pivotally mounted, it makes sense to one-sided dodging or tilting due to a pivoting of the piston and cylinder around the waves 14 to prevent. In part, this is already done by two compression springs 25 , bias the hydraulic cylinders in the starting position shown in dashed lines. Regardless, according to the 3 to 5 a vertical support frame 26 . 26 ' be provided, which optionally on opposite sides of the round tubes 8th the support elements 2 can be present ( 26 ' in 5 ) or in each case from the outside to the cylinder rods 12 on the opposite sides of the support elements ( 26 in the 3 and 4 ) and thereby ensures that during extension of the hydraulic piston 5 a movement of the cylinder rod 12 or the upper end of the hydraulic piston 5 takes place only in the vertical direction, which excludes one-sided evasion or tilting of the stack of support elements.

This additional support frame 26 . 26 ' need only have a small height, which corresponds approximately to the height of one of the support elements, since it is sufficient if only the lowest support element or the upper ends of the hydraulic piston 5 connecting cylinder rods 12 while the extension are prevented from lateral evasive movement. Optionally, corresponding elements of an outer support frame could be disassembled or foldable and independently press spring force on the cylinder rods or on the round tubes of a support element, so that despite a safe guide still a small amount of movement or small tolerance for movement of the support elements remain ,

Instead of of the support frame could but also a controlled support unit be provided, which is supported on a part of the base frame and on casing or on the cylinder of the hydraulic or pneumatic lifting element attacks. This controlled support unit could in turn be hy draulic or pneumatically actuated and controlled so that this upper piston end or the cylinder rod during extension and retraction of the Piston exclusively is moved vertically. The control of the support unit could for this purpose with the Hydraulic lifting elements be positively coupled.

On the first or top support element 2 can still before the complete lifting a guide frame 15 (please refer 11 ) can be fitted together with a connecting piece, which will be described in the context of the second embodiment, but can also be used in the same way for the first embodiment.

According to the second embodiment is also a base frame 1' provided on which in this variant four hydraulic cylinders 4 vertically aligned and rigid on the base frame 1' are attached. as in 6 is shown. 7 shows in addition to the base frame 1' still the guide frame 15 which has a fitting in the form of egg a trolley 18 and a coupling piece 19 carries as it directly engages with a lifting fitting on the underside of the wing. The longitudinal struts 16 This guide frame have short pins on its underside 21 which are sized to fit into corresponding recesses 9 both at the top of supporting elements 2 the first embodiment, supporting elements 2 ' the second embodiment and also directly on the top of the piston 5 fit in the second embodiment

In this embodiment, two separate groups of support elements 2 ' . 2 '' provided, namely outer support elements 2 ' and inner support elements 2 '' , The stack of inner support elements 2 '' Stands firmly on the frame within the four hydraulic cylinders 4 field spanned. First, so many inner support elements 2 '' Stacked on top of each other as they can easily fit under the wing of the damaged aircraft. Subsequently, the outer support elements are stacked, the outer support elements expediently have items that are on the hydraulic piston 5 the hydraulic lifting elements 3 are placed and expediently also cones 21 at its bottom and recesses 9 at its upper end, with the pistons 5 , with each other and with the cones 21 of the guide frame 15 to be able to intervene positively. These outer support elements are piled up as far as this allows the space below the wing. Finally, the corresponding guide frame 15 together with a fitting on the top support element 2 '' the inner stack of support elements 2 '' be put on.

In order to enable a Nachschieben or additional guiding elements after the outer group of support elements is already stacked on each other and possibly already in engagement with the guide frame, the outer support elements could 2 ' be formed in the top view U-shaped, so that they also subsequently a Nachschieben of inner support elements 2 '' easily allow. In particular, the short U-shaped angled pipe ends could 8th on at least one of the narrow sides of the support elements 2 ' detachable to the post 7 be attached to the support elements. This ensures that you then both outer and inner support elements 2 ' . 2 '' can sit on the respective stack when the other stack is in engagement with the guide frame, in turn, on the trolley 18 and the coupling piece 19 is engaged with the lifting fitting of the wing. The inner support elements 2 '' can each through the U-hole of the outer support elements 2 ' in the stack of outer support elements 2 ' be inserted when the outer stack has been raised sufficiently far by the lifting elements, so that a further support element 2 '' can be placed on the inner stack; and after lowering the lifting elements 3 and the settling of the guide frame 15 on the stack of inner support elements 2 '' may be a U-shaped outer support member 2 be placed on the correspondingly far lowered stack of outer support elements. The lower support elements 2 ' may be closed to a complete rectangle.

The guide frame is configured to be either from the inner stack of support members 2 '' as well as the outer stack of guide elements 2 ' can be worn. The guide frame consists essentially of two longitudinal struts, which are dimensioned so that they are the posts of the outer guide elements 2 ' cover and in particular the pins 21 have in the upper recesses 9 the post 7 can engage with the longitudinal struts 16 also has a longitudinal slot 27 have, in the webs 23 at the top of the plates 22 can engage, forming the narrow sides of the spanned by the inner support elements rectangular frame.

The two longitudinal struts 16 are by a crossbeam 17 interconnected, which in turn in the longitudinal direction of the longitudinal struts on this displaceable z. B. on rollers or ball bearings, is arranged. Additional struts, which keep the two longitudinal struts at a constant distance, are not shown here, but could optionally be additionally present. The traverse 17 could also with a guide pin, not shown here in the longitudinal slot 27 engage the longitudinal struts. On the traverse 17 in turn runs essentially in the longitudinal direction of a trolley 18 , which is the actual coupling piece 19 for engaging with the lift fitting on the underside of the wing.

After all supporting elements 2 ' . 2 '' have been stacked as far as it allows the space under the wing and also the guide frame on the top of the support elements 2 ' respectively. 2 '' are seated, the hydraulic pistons 5 extended simultaneously while lifting the out of the outer support elements 2 ' existing stack. Unless the guide frame already on the top of the outer support elements anyway 2 ' In any case, after lifting the outer support element stack, it will become with the uppermost support element 2 ' come into contact (the pins 21 the longitudinal struts 16 in the recesses 9 the post 7 engage) and then through the outer stack of support members 2 ' further raised, taking after Reaching the wing, the coupling piece 19 with the lever fitting 20 is engaged. The hydraulic pistons are then extended further and lift in this way the wing. When the outer stack of support elements 2 ' and the wing have been raised so far, then under the guide frame enough space for the insertion of an inner support member 2 '' is present, becomes another support element 2 '' on the inner stack of support elements 2 '' placed. As already mentioned, the outer support elements for this purpose are either U-shaped and open on one side or they have in the vertical direction enough wide gaps to the insertion of the support elements 2 '' to allow with a correspondingly lower height. If necessary, the stroke of the hydraulic piston is sufficient 5 also from, after the complete extension of the reciprocating piston several additional support elements 2 '' be able to put on the inner stack of support elements.

Subsequently, the hydraulic pistons 5 retracted again, ie the outer stack of support elements 2 ' is lowered accordingly, wherein the guide frame now on the top of the inner support elements 2 '' is discontinued (under positive engagement de bridge 23 in the longitudinal slot 27 ) and the outer stack of support elements 2 ' is lowered so far that under the guide frame another support element 2 ' on the outer stack of support elements 2 ' can be put on. As already mentioned, the outer support elements should 2 ' be designed for this purpose in plan view U-shaped to the side of the inner stack of support elements 2 '' engage around the outer stack to be pushed. Optionally, the support elements 2 ' for this purpose have on the open U-side a releasable strut (for example in the form of a tube 8th ), which after putting the support element 2 ' can be reassembled to the outer support element 2 ' to give greater stability

As already mentioned, if the stroke of the piston 5 or the cylinder 4 sufficient, if necessary, several external support elements 2 ' below the guide frame 15 be placed on the outer stack. However, for practical reasons, the height of the support elements 2 . 2 ' and 2 '' Adjust to the maximum lift of the lifting elements in order to build the stack as quickly and effectively as possible. The stroke of the lifting elements is in turn limited by the desired low height of the base frame including the lifting elements. As already mentioned, in practicable embodiments, the height of the support elements will be between 30 and 80 cm, the lift of the lifting elements 3 must be in the same order of magnitude and in any case must be greater than the lowest support elements are high.

In the manner described above, the support surface can also be gradually raised by the second embodiment, wherein the hydraulic cylinders always raise the outer stack of support members so far that the inner stack of support members to at least one further support member 2 '' can be increased, then the wing over the guide frame 15 on the inner stack is dropped and the lowered outer stack of support elements in turn with one or more other support elements 2 ' is increased.

Conveniently, the stroke of the hydraulic lifting elements is adapted so that it is only slightly larger, z. B. 50% greater than the height of the outer and / or inner support elements 2 ' respectively. 2 '' , It only needs to be ensured that from any initial position out the outer stack can be raised so far that on the inner stack so many inner support elements 2 '' can be placed, as required, after the complete lowering of the hydraulic lifting elements below the guide frame for the insertion of another outer support member 2 ' Place is. In the event that more space under the wing is available in a specific situation, significantly higher support elements can form the initial stack and initially without the aid of the lifting elements 3 be put on top of each other. Only when the fitting comes into contact with or in contact with the support surface, the lifting elements must be used to carry out the lifting process described above.

In a further variant (not shown) of the second embodiment are for the inner and outer stacks of support elements 2 ' . 2 '' each own lifting elements 3 provided, wherein the lifting elements for the inner and the outer stack independently and z. B. can be operated alternately. Thus, while one stack is lowered to set up another support element, the other stack is raised, so that possibly equal to two support elements can be placed on the lowered stack and vice versa. Instead of putting on two support elements, higher support elements could be used in this variant, the height of which can be greater than the maximum stroke of the individual lifting elements. With this variant, therefore, the entire lifting process could be accelerated.

The the coupling piece 19 carrying trolleys 18 is on the traverse 17 arranged movably in the longitudinal direction and the traverse 17 is in turn on the longitudinal struts 16 movable angeord net, preferably on rollers or corresponding ball bearings, so that thereby any horizontal movements of the lifting sling can be collected, which this could occur due to the determined by the support of the fuselage or the other aircraft parts pivot axis during lifting of the support surface.

In addition, the invention provides that after sufficient lifting of the wing and thus possibly also of the aircraft fuselage, whereby two corresponding devices could attack on opposite sides of the fuselage on both wings, the aircraft with the help of tugs or the like is transported away. It is understood that this either the base frame 1 . 1' must be equipped with appropriate wheels or a chassis or that the base frame and the support elements are replaced by a further frame construction, which allow the underrunning of the wing by means of a corresponding tractor. For this purpose, for example, a corresponding portal frame could be set up outside the base frame 1 . 1' is supported and in the upper support elements has cross members, for example, under the traverse 17 or under the longitudinal struts 16 pushed or can be connected to these firmly. Optionally, also the trolley 18 have lateral arms which can be placed on corresponding cross members of a portal frame. For this purpose, for example, the outer stack of support elements 2 ' One last May will be raised until appropriate outriggers or parts of the guide frame 15 are arranged above the trusses of the portal frame, which are then positioned according to the boom, whereupon the hydraulic cylinders are retracted again and thus either guide frame 15 or its traverse 17 or just the trolley 18 rests with its arms on the portal frame. Then the two stacks of support elements 2 ' . 2 '' be dismantled and transported away and also the base frame 1 . 1' can be transported away or as far as possible, disassembled and dismantled.

The portal frame is accordingly designed sufficiently large so that a suitable for aircraft transport tractor vehicle can be driven under the portal and thus under the wing, receives the carriage or trolley with corresponding hydraulic lifting devices, whereupon the portal frame is dismantled and then with the help of Tractor vehicle, which may for example also have a chassis of caterpillars, is transported away, it being understood that a similar vehicle can be used, for example, under the opposite wing or attack other tractors on nose gear or other suitable points of the fuselage to the aircraft as a whole and to tow it in cooperation with a tug under the wing. Alternatively, the basic frame could be 1 . 1' itself be equipped with a chassis and optionally also a drive device, but the chassis relative to the base frame liftable you should be lowered to lower during the lifting process, the load only on the base frame on the ground.

For purposes the original one Revelation is noted that all features as they are from the present description, the drawings and the claims for a To open up a specialist, even if they are described concretely only in connection with certain other characteristics were, both individually and in any compilations can be combined with other features or feature groups disclosed herein are, unless expressly so was excluded or technical conditions such combinations impossible or make pointless. On the comprehensive, explicit representation of all conceivable combinations of features is here only for brevity and omitted for the readability of the description.

1'

base frame

1

base frame

2, 2 ', 2' '

support elements

3

lifting members

4

hydraulic cylinders

5

hydraulic pistons

6

baseplate

7

post

8th

round tubes

9

recesses

10

..

11

guide

12

cylinder rod

13

semi-cylindrical recess

14

wave

15

guide frame

16

long vines

17

traverse

18

trolley

19

coupling

20

lifting fog

21

spigot

22

plate

23

web

24

...

25

compression springs

26

support frame

27

longitudinal slot

Claims (18)

A method for recovering a damaged aircraft, wherein a lifting structure with a bottom-mounted base frame ( 1 . 1' ) is arranged under the wing of the aircraft, and a lifting device raises the wing to a height required for the removal of the aircraft, the lifting structure comprising a connecting piece ( 18 . 19 ), which is brought by the lifting structure with a suitable lifting fitting on the support surface in engagement and then further raised with the support surface, characterized in that - the lifting structure of stackable support elements ( 2 . 2 ' . 2 '' ) and at least one lifting element ( 3 ), wherein - i) one or more support elements ( 2 . 2 ' . 2 '' ) in the manner by the lifting element ( 3 ), that another support element ( 2 . 2 ' . 2 '' ) is insertable into the construction, and - ii) the lifting element ( 3 ) and lowered again with at least one of the support elements ( 2 . 2 ' . 2 '' ) and raised, and - steps (i) and (ii) are optionally repeated several times, so that - that of an upper support element ( 2 . 2 ' . 2 '' ) worn fitting ( 18 . 19 ) is gradually increased, wherein - the load taken up by the connecting piece alternately solely over the stacked support elements ( 2 . 2 ' . 2 '' ) or via the support elements ( 2 . 2 ' . 2 '' ) and this lifting lifting element ( 3 ) is removed. A method according to claim 1, characterized in that two nested groups of stackable support elements ( 2 ' . 2 '' ) are provided, of which at least one first is gradually raised to the second group another support element ( 2 '' ) is added, whereupon the lifting element ( 3 ) with the first raised group of support elements ( 2 ' ), the load in the meantime eroded over the increased second group and the first group by another support element ( 2 ' ) and raised again. Method according to claim 1, characterized in that the lifting element ( 3 ) and the support elements ( 2 . 2 ' . 2 '' ) are designed so that after lifting at least one given support element, another support element can be inserted into the support structure, whereupon the lifting element of the raised support member releasably and with a arranged below the raised support member support element is engageable. Method according to one of claims 1 to 3, characterized that the stacked support elements while a lifting operation secured against lateral displacement or tilting become Aircraft mover with a base frame ( 1 . 1' ) and a lifting structure arranged thereon, which can be arranged below a wing of a damaged aircraft to a connecting piece ( 18 . 19 ) and a fixedly provided on the wing lifting fitting to engage and lift the wing and thus the aircraft in a transportable position, characterized in that the lifting structure stackable support elements ( 2 . 2 ' . 2 '' ) and at least one lifting element ( 3 ) which is designed to support at least one given supporting element ( 2 . 2 ' . 2 '' ) so far that a further support element ( 2 . 2 ' . 2 '' ) can be inserted into the support structure, wherein the lifting element ( 3 ) is lowered without receiving the load, while the load of the support surface is taken up by the stacked support elements, and again with a support member is engageable to raise the support elements for the addition of another support element again. Aircraft elevator according to claim 5, characterized in that a plurality of hydraulic or pneumatic cylinders ( 4 ) are provided. Aircraft elevator according to one of claims 5 or 6, characterized in that the support elements ( 2 . 2 ' . 2 '' ) the shape of rectangular frame with corner posts ( 7 ) to have Aircraft lift of any one of claims 5 to 7, characterized in that the upper ends of each of the support elements with the lower ends of each arranged above support elements form fit in Intervention can be brought. Aircraft jack according to one of claims 5 to 8, characterized in that two of its independent groups of stackable support elements ( 2 ' . 2 '' ) are provided, of which at least one first group by the at least one lifting element ( 3 ) can be raised in order, after corresponding lifting of the first group, the second group by a further support element ( 2 '' ) and after lowering the first group and receiving the load by the second group and the first group to another support element ( 2 ' ) and raise again to replenish the second group. Aircraft jack according to claim 9, characterized in that the first group and the second group of supporting elements ( 2 ' . 2 '' ) are arranged nested. Aircraft elevator according to one of claims 5 to 8, characterized in that only one group of supporting elements ( 2 ) is provided, wherein the support elements ( 2 ) and the lifting element ( 3 ) are configured such that under a raised by the lifting element supporting element ( 2 ) Space for the insertion of another support element ( 2 ), wherein the lifting element ( 3 ) after the insertion of the further support element ( 2 ) of the raised support element ( 2 ) releasably and with the below the raised support element ( 2 ) arranged supporting element ( 2 ) is engageable. Aircraft mountains lift according to claim 11, characterized in that the support elements in a side view at least in the lower section an extension ( 7 ' ), the underside of the lower extension ( 7 ' ) for engaging with lifting elements ( 3 ) is designed. Aircraft mover according to claim 12, characterized in that the respective lower sides of the extensions form a hinged connection ( 12 . 13 ) with the upper ends of the lifting elements. Aircraft mover according to one of claims 11 to 13, characterized in that an additional support frame is provided during the the lifting of a support element a lateral deflection or tilting of the lifting element and the with it raised support elements prevented. Aircraft mover according to claim 1, characterized that the support frame the support elements up to a height against lateral displacement or tilting secures, at least the insertion of a new support element allowed under the lowest raised support element. Aircraft jack according to claim 1, characterized in that on the uppermost support element a connecting piece ( 18 . 19 ) is provided for connection to a under the wing and fixedly arranged with this lifting fitting. Aircraft jack according to claim 1, characterized in that the connecting piece ( 18 . 19 ) on a guide frame ( 15 ), which is seated on the uppermost support member, is arranged freely movable in the horizontal direction. Aircraft mover according to claim 1, characterized that this Connector at least a horizontal axis is pivotally mounted.