Locking device for a service access point on an external structure of an aircraft, service access point, aircraft, and method for manufacturing a locking device for a service access point on an external structure of an aircraft.

Abstract

The present invention provides a locking device for a service access point on an external structure of an aircraft. Furthermore, the invention provides a service access point with such a locking device, as well as an aircraft with such a service access point. The present invention also provides a method for manufacturing a locking device for a service access point on an external structure of an aircraft.

Description

[0001] The present invention relates to a locking device for a service access point on an external structure of an aircraft, and to a service access point with such a locking device. Furthermore, the present invention relates to an aircraft with such a service access point, and to a method for manufacturing a locking device for a service access point on an external structure of an aircraft.

[0002] Current access panels are installed in locations where systems, including those located beneath the aircraft skin, require maintenance and repair access throughout the aircraft's lifespan. These access panels typically feature a specially designed door and a dedicated landing zone on the structure to which the door is attached. This zone adheres to stringent tolerances and incorporates additional materials to ensure specific requirements, such as the aerodynamic surface finish of the component. These measures are necessary because the gap around the access door and the resulting edges would negatively impact the aircraft's performance, particularly in terms of aerodynamics. The implementation of current access panels increases the manufacturing, maintenance, and repair costs of the overall product, as well as the overall weight of the aircraft structure.However, gaps and spaces remain on the access panel, particularly in the area of ​​a locking device that can be used to lock or unlock the access panel.

[0003] Both stealth aircraft and regular military aircraft feature such access panels, for example, to allow ground personnel access to maintenance systems. Depending on the frequency of opening, these access panels require latches or locks that can be accessed from the outside of the aircraft with a tool. The locks are designed to impair the aircraft's stealth capabilities as little as possible; that is, the aircraft's surface should be disturbed by irregularities as little as possible.

[0004] Known access panel locking mechanisms still offer potential for improvement in tolerances, particularly regarding gaps and clearances. For example, CN 110017065 A describes a locking mechanism for the hatch cover of an unmanned aerial vehicle (UAV). This hatch cover locking mechanism is designed to facilitate the recovery of a stealth parachute from the UAV and ensures that the UAV can reliably and stably open its parachute and airbag cabins during landing, with the hatch cover locking mechanism located within an equipment cabin. Furthermore, CN 109930935 A describes a vehicle cabin door composite opening and closing device.The combined opening and closing device comprises a vehicle body and a cabin door, the cabin door covering the opening in the vehicle body; one end of the cabin door is connected to the vehicle body by a lifting and rotating mechanism, and the other end is connected to the vehicle body by a rotary shaft mechanism. Furthermore, DE 10 2018 109 995 A1 describes a fastening system for securing components in a vehicle cabin. DE 94 01 456 U1 describes a closure, in particular for storage compartment covers or panels in motor vehicles. WO 2021 / 197 616 A1 describes a latch for a door with an adjustable cam. Furthermore, US 2010 / 0 243 809 A1 describes a device for closing and sealing an opening in a structure such as an external access opening in an aircraft fairing.

[0005] The object of the present invention is to provide a simple service access for maintenance work on an aircraft, while meeting high tolerance requirements.

[0006] According to the invention, this problem is solved by the subject matter of independent claims 1 (device claim) and 11 (method claim) as well as by the subject matter of dependent claims 9 and 10.

[0007] According to a first aspect of the invention, a locking device for a service access point on an external structure of an aircraft is provided. The locking device comprises a base structure for fixed mounting in an opening of a service access point on an external structure. The base structure has a through-opening extending along a longitudinal axis. Furthermore, the locking device includes a cover element that is slidably mounted in the through-opening and relative to the base structure along the longitudinal axis. The cover element is pre-tensioned by a spring assembly and held in a closed position by a stop element in conjunction with the spring assembly. The locking device also includes an actuating shaft extending along the longitudinal axis.Furthermore, the actuating shaft has a handling end for rotary manipulation using a tool and a transmission end for transmitting torque to a lever unit coupled to the transmission end. The handling end is enclosed by the cover. The handling end and the cover are flush with their respective outer surfaces.

[0008] According to a second aspect of the invention, a service access point for an aircraft is provided. The service access point comprises a non-destructively removable section of an aircraft's external structure, wherein the section has an opening. Furthermore, the service access point includes a locking device according to the first aspect of the invention, wherein the base structure is fixedly attached in the opening.

[0009] According to a third aspect of the invention, an aircraft is provided with a service access point according to the second aspect of the invention.

[0010] According to a fourth aspect of the invention, a method for manufacturing a locking device for service access on an external structure of an aircraft, in particular for manufacturing a locking device according to the first aspect of the invention, is provided. The method comprises the following steps: - Attaching a base structure in an opening of a service access on an external structure, wherein the base structure has a through-opening extending along a longitudinal axis. - Insertion of a spring assembly into the base structure, wherein the spring assembly is pre-tensioned and held in position by the placement of a cover assembly. The cover assembly is mounted in the through-opening and is slidably mounted relative to the base structure along its longitudinal axis. - Connecting a lifting device to the covering device so that the covering device is held in a closed position by the spring device in conjunction with the lifting device. - Insertion of an actuating shaft extending along the longitudinal axis. The actuating shaft has a handling end for rotary handling using a tool and a transmission end for transmitting torque to a lever unit coupled to the transmission end, the handling end being bounded by the cover. The handling end and the cover are flush with their respective outer surfaces.

[0011] One of the underlying ideas of the present invention is to improve high tolerance requirements by providing easily manufactured and adjustable components of the locking device, in order to keep requirements for steps and gaps within the smallest possible limits. The longitudinal axis corresponds to a surface normal of the outside of the service access. In the closed position, the outside of the handling end area, the outside of the cover device, and optionally the outside of the base structure lie essentially in one plane. This plane preferably corresponds to a plane of an outside of the service access or the outer structure. That is, the cover device, which is slidably mounted along the longitudinal axis, can also be used to arrange the outside of the cover device and the outside of the base structure flush.For the purposes of this application, the term "plane" also includes curvatures that are insignificant in relation to the surface area. The spring mechanism can be supported by the base structure.

[0012] Due to manufacturing and / or assembly tolerances, the flush-mounted arrangement may exhibit slight steps at the transitions between adjacent components. An advantage of the present invention is that there are few or no steps between the cover device and the handling end area. The cover device according to the invention, in combination with the actuating shaft according to the invention, allows such a step to be precisely adjusted and thus minimized. This increases the precision in the manufacture of the locking device.

[0013] Another advantage of the present invention is that it can be used for applications with stealth technology, since the stealth properties of the aircraft can be improved by mechanical means.

[0014] Advantageous embodiments and further developments result from the dependent claims relating back to the independent claims and from the description with reference to the figures.

[0015] According to one embodiment of the invention, the cover device is axially displaceable along its longitudinal axis relative to the actuating shaft by a compressive force, so that the cover device is in a manipulation position in which the handling end area is freely accessible. The handling end area can, for example, have a slotted profile, a star profile, or a polygonal profile, in particular an external square profile, an external hexagonal profile, or an external octagonal profile. Thus, the actuating shaft can be manipulated using common tools.

[0016] Furthermore, the handling end section can have one of the aforementioned profiles for a predetermined distance along the longitudinal axis and then transition into a cylindrical shape after this predetermined distance. This cylindrical shape has a smaller diameter than the envelope of the handling end section. In this way, the actuating shaft can be rotated relative to the cover in the manipulation position, with the profiled handling end section blocking the cover so that it cannot be pushed into the closed position. This provides a safety function, ensuring that the cover can only be moved into the closed position when the service access is fully locked, i.e., when the actuating shaft is fully rotated. Additionally, the cover can be rotatable relative to the base structure in the manipulation position.

[0017] According to a further embodiment of the invention, the cover device is round, in particular circular, in cross-section with respect to its longitudinal axis. This allows for a reduction of any gap, especially a radial gap, between the cover device and the base structure by turning the required diameter of the cover device or lid to the exact installation dimensions using a lathe. Furthermore, this reduces the tolerances in the chain from the locking device to the service access point. The cover device can be deliberately designed to be very simple, making reworking of the original, oversized lid during assembly very easy. This means that the cover device, as a simple and cost-effective component, can be easily reworked with minimal effort.Furthermore, the actuating shaft and the roundly shaped cover device can be arranged coaxially.

[0018] According to a further embodiment of the invention, the locking device also comprises a housing that is arranged on an inner side of the service access and rotatably mounts the actuating shaft. The housing can enclose the base structure, the cover device, and the stop element, at least partially, on the inner side of the service access or the outer structure.

[0019] According to a further embodiment of the invention, the spring assembly is designed as a compression spring, in particular as a conical compression spring. The compression spring or conical compression spring can be arranged coaxially with the cover assembly. That is, the compression spring or conical compression spring can radially surround the cover assembly or be radially surrounded by the cover assembly. The conical compression spring can be compressed to save a very small footprint.

[0020] Optionally, the cover device can be mounted in the base structure by means of a sliding bushing.

[0021] According to a further embodiment of the invention, the stop is screwed to the cover device by means of a threaded connection, the locking position being adjustable along the longitudinal axis via the threaded connection. In this way, the position of the cover device can be adjusted along the longitudinal axis to ensure that the outer surface of the locking device is as stepless as possible in relation to the service access. This means that a step can be adjusted during assembly by screwing the stop in or out. Advantageously, no tools are required for this. The threaded connection can have a very small thread pitch to allow for very precise adjustment.

[0022] To prevent unintentional rotation of the lifting device, it can have a recess that engages with a projection on the base structure. Optionally, the projection and recess can be designed and dimensioned so that they do not engage in the manipulation position. This allows the cover to be rotated relative to the base structure via the threaded connection in the manipulation position. Once the optimal locking position is found, the threaded connection can be secured with a locking wire, adhesive, or similar material.

[0023] According to a further embodiment of the invention, the base structure is designed as a bushing. The bushing can, for example, be cylindrical, and in particular rotationally symmetrical. Additionally, the base structure and the cover device and / or the actuating shaft can be arranged coaxially. Furthermore, the bushing can be pressed into the opening, glued, or attached in a similarly material-bonded and / or force-fit manner. For example, the base structure can be mounted flush with the outer surface of the cover device, so that the outer surface of the service access is free of any protrusion.

[0024] The basic structure, the cover device, the actuating shaft and the optional housing can each be manufactured independently of one another, for example from a light metal, in particular aluminum, or from a fiber composite material, in particular carbon fiber reinforced plastic.

[0025] According to a further embodiment of the invention, the transmission end region is coupled to a lever unit. The lever unit can be positively and / or force-fitted to the transmission end region, for example by a screw connection. Furthermore, the lever unit can comprise a linkage that actuates one or more unlocking or locking mechanisms, so that the service access can be unlocked or locked.

[0026] According to a further embodiment of the invention, when inserting the actuating shaft, a housing is installed on the inside of the service access and the actuating shaft is inserted through a feed hole in the cover device. The housing can enclose the base structure, the cover device, and the stop element, at least partially, on the inside of the service access or the outer structure. The feed hole can, in particular, correspond to a cross-section of the handling end area.

[0027] According to a further embodiment of the invention, the actuating shaft is pushed through a sliding bearing bushing of the housing until a first retaining ring, pre-mounted on the actuating shaft, comes into contact with the sliding bearing bushing. An axial position of the actuating shaft can be secured by a second retaining ring, which is mounted on a side of the sliding bearing bushing facing away from the first retaining ring after the actuating shaft has been inserted into the sliding bearing bushing.

[0028] According to a further embodiment of the invention, the method further comprises a step of adjusting the locking position to minimize a step between the cover device and the handling end area or between the cover device and the base structure with respect to the respective outer surface, wherein the locking position is adjusted by means of a threaded connection along the longitudinal axis. In this way, the position of the cover device can be adjusted along the longitudinal axis to provide the outer surface of the locking device with as few steps as possible in relation to the service access. This means that a step can be adjusted during assembly by turning the stop in or out. Advantageously, no tools are required for this. The threaded connection can have a very small thread pitch to allow for very precise adjustment.

[0029] To prevent unintentional rotation of the lifting device, it can have a recess that engages with a projection on the base structure. Optionally, the projection and recess can be designed and dimensioned so that they do not engage in the manipulation position. This allows the cover to be rotated relative to the base structure via the threaded connection in the manipulation position. Depending on the number of projections and recesses, the lifting device can be rotated relative to the cover by, for example, 45°, 90°, 135°, or 180° to allow the projections and recesses to engage.

[0030] Alternatively or additionally, the cover can be rotated relative to the actuating shaft, particularly depending on the polygonal profile of the handling end area, for example by 45° for an external hexagonal profile or by 90° for an external square profile, in order not to block the handling end area equipped with the profile. Once the optimal locking position has been found, the threaded connection can be secured with a locking wire, adhesive, or similar material.

[0031] Optionally, the cover device can be mounted in the base structure by means of a sliding bushing, which is pre-installed in the base structure.

[0032] According to a further embodiment of the invention, the method further comprises a step of coupling the transmission end region with a lever unit. The lever unit can be connected to the transmission end region by a positive locking and / or force-locking connection, for example by a screw connection. In addition, the lever unit can comprise a linkage that actuates one or more unlocking or locking mechanisms, so that the service access can be unlocked or locked.

[0033] For example, the locking device can be unlocked or opened by the following steps. A tool with a square cutout pushes the cover or lid, together with the screwed-on locking washer or stop, from the outside towards the inside of the locking device until the outer surface or lid of the cover is pushed beyond the square-shaped handling end of the actuating shaft or drive shaft. This frees the axis of rotation of the actuating shaft, i.e., rotation of the actuating shaft around its longitudinal axis, and the drive shaft, together with the first and second retaining rings and the lever unit or output lever, can be rotated clockwise or counterclockwise. The lever unit or output lever can be engaged with one or more unlocking or opening mechanisms and locking or opening mechanisms.Locking mechanisms, such as a deflection lever, may be connected. Closing or locking the service access using the locking device can be achieved by reversing the steps described above.

[0034] The above embodiments and further developments can be combined with one another as appropriate. Further possible embodiments, further developments, and implementations of the invention also include combinations of features of the invention described previously or subsequently with respect to the exemplary embodiments, even if not explicitly mentioned. In particular, those skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

[0035] The present invention is explained in more detail below with reference to exemplary embodiments and the accompanying figures. The figures show: Fig. 1 a schematic representation of a locking device for a service access on an external structure of an aircraft according to an embodiment of the invention; Fig. 2 a schematic sectional view of a section of a service access for an aircraft with a locking device for the service access on an external structure of the aircraft according to a further embodiment of the invention; Fig. 3 a schematic perspective view of the basic structure of the locking device Fig. 2; Fig. 4 a schematic perspective view of the cover device of the locking device Fig. 2; Fig. 5 a schematic perspective view of the stop element of the locking device made of Fig. 2; Fig. 6 a schematic side view of an aircraft with a service access according to a further embodiment of the invention; and Fig. 7 a flowchart of a method for manufacturing a locking device for a service access on an external structure of an aircraft according to a further embodiment of the invention.

[0036] In the figures of the drawing, identical, functionally equivalent and similarly acting elements, features and components - unless otherwise stated - are each provided with the same reference symbols.

[0037] Although specific embodiments and further developments are presented and described herein, the person skilled in the art will prefer that a multitude of alternative and / or similar embodiments can replace the specific embodiments presented and described without departing from the scope of the present invention. This application is intended to generally cover all variations or modifications of the specific embodiments described herein.

[0038] The accompanying figures are intended to provide a further understanding of embodiments of the invention and serve, in conjunction with the description, to explain the principles and concepts of the invention. Other embodiments and many of the aforementioned advantages become apparent with regard to the drawings. The drawings are to be understood merely as schematic drawings, and the elements of the drawings are not necessarily shown to scale. Directional terminology such as "above," "below," "left," "right," "over," "below," "horizontal," "vertical," "front," "back," and similar terms are used for explanatory purposes only and are not intended to limit the generality of the invention to specific embodiments as shown in the figures.

[0039] Fig. Figure 1 shows a schematic representation of a locking device 100 for a service access on an external structure of an aircraft according to an embodiment of the invention.

[0040] The locking device 100 comprises, by way of example, a base structure for fixed mounting in an opening of a service access on an external structure, wherein the base structure has a through-opening extending along a longitudinal axis Z. The locking device 100 further comprises a cover device which is slidably mounted in the through-opening and relative to the base structure along the longitudinal axis Z. The cover device is pre-tensioned by a spring device and held in a closed position by a stop element in conjunction with the spring device. The longitudinal axis Z extends out of the plane of the drawing and is at a right angle to the transverse axes X and Y.

[0041] Furthermore, the locking device 100 comprises an actuating shaft extending along the longitudinal axis Z, a handling end region for rotary handling using a tool, and a transmission end region 132 for transmitting torque to a lever unit 140 coupled to the transmission end region 132, the handling end region being bounded by the cover device. The handling end region and the cover device are arranged flush with their respective outer surfaces.

[0042] Furthermore, the locking device 100 can have a housing 150 that is arranged on the inside of the service access and rotatably mounts the actuating shaft. The housing 150 can enclose the base structure, the cover device, and the stop element, at least partially, on the inside of the service access or the outer structure. Optionally, the housing 150 can have bores for being screwed to the outer structure, for example. Alternatively or additionally, the housing 150 can be materially bonded to the base structure or the outer structure.

[0043] In Fig. In addition, section axis AA is shown in 1, whose section view is shown alongside the section view in Fig. 2 corresponds.

[0044] Fig. Figure 2 shows a schematic sectional view of a section of a service access 10 for an aircraft with a locking device 100 for the service access 10 on an external structure 2 of the aircraft according to a further embodiment of the invention.

[0045] The service access 10 comprises a non-destructively removable section of the outer structure 2, the section having an opening 11.

[0046] The service access 10 further comprises the locking device 100, which by way of example includes a base structure 110, a cover device 120, a spring device 122, a stop means 124, an actuating shaft 130, a lever unit 140 and a housing 150.

[0047] The base structure 110 is fixedly attached in the opening 11 of the service access 10. The base structure 110 has a through-opening 112 that extends along a longitudinal axis Z. The longitudinal axis Z corresponds, for example, to a surface normal of the outside of the service access 10.

[0048] The cover device 120 is mounted in the through-opening 112 and is displaceable relative to the base structure 110 along the longitudinal axis Z. Optionally, the cover device 120 can be mounted in the base structure 110 by means of a sliding bushing 111, as shown in Fig. Figure 2 is illustrated by way of example. The cover device 120 is pre-tensioned by the spring device 122 and held in a closed position by the stop element 124 in conjunction with the spring device 122. Fig. Figure 2 shows the cover device 120 in the closed position.

[0049] For example, the cover device 120 can be round in cross-section with respect to the longitudinal axis Z. Thus, a gap G, in particular a radial gap G, between the cover device 120 and the base structure 110 can be reduced by turning the required diameter of the cover device 120 or the lid to the exact installation requirements using a lathe.

[0050] The cover device 120 can be deliberately designed to be very simple, so that reworking the original, oversized cover during the assembly stage is very easy. Furthermore, the actuating shaft 130 and the round cover device 120 can be arranged coaxially.

[0051] The spring assembly 122 can, for example, be designed as a conical compression spring, but is not limited to this configuration; it can also be any other type of compression spring. The conical compression spring 122 can be arranged coaxially with the cover assembly 120. That is, the conical compression spring 122 can radially surround the cover assembly 120. The conical compression spring 122 can be compressed to save a very small footprint.

[0052] The actuating shaft 130 extends along the longitudinal axis Z. The actuating shaft 130 has a handling end section 131 for rotary handling using a tool and a transmission end section 132 for transmitting torque to the lever unit 140 coupled to the transmission end section 132. The handling end section 131 is enclosed by the cover 120. The handling end section 131 and the cover 120 are arranged flush with their respective outer surfaces 120a and 131a.

[0053] In the closed position, for example, the outer surface 131a of the handling end area 131, the outer surface 120a of the cover device 120, and the outer surface 110a of the base structure 110 lie essentially in one plane. This plane preferably corresponds to a plane of an outer surface of the service access 10 or of the outer structure 2. That is, the cover device, which is slidably mounted along the longitudinal axis Z, can also be used to arrange the outer surface 120a of the cover device 120 and the outer surface 110a of the base structure 110 flush with each other.

[0054] For example, the cover device 120 can be axially displaceable along the longitudinal axis Z relative to the actuating shaft 130 by a compressive force, so that the cover device 120 is in a manipulation position in which the handling end area 131 is freely accessible. Fig. 2. The cover device 120 can thus be pushed to the left. The handling end area 131 can, for example, have a polygonal profile, in particular an external square profile, an external hexagonal profile or an external octagonal profile, but is not limited to this. Thus, the actuating shaft 130 can be manipulated using common tools.

[0055] Furthermore, the handling end area 131 can have the polygonal profile for a predetermined distance in the direction of the longitudinal axis Z and change or transition into a cylindrical shape after the predetermined distance, as exemplified in Fig. Figure 2 illustrates this. The cylindrical shape can have a smaller diameter than the envelope of the handling end region 131. In this way, the actuating shaft 130 can be rotated relative to the cover device 120 in the manipulation position, with the profiled handling end region 131 blocking the cover device 120 so that it cannot be pushed into the closed position. This provides a safety function to allow the cover device 120 to move into the closed position only when the service access 10 is fully locked, i.e., when the actuating shaft 130 is fully rotated. Furthermore, the cover device 120 can be rotatable relative to the base structure 110 in the manipulation position.

[0056] The housing 150 can be arranged on an inner side of the service access 10 and rotatably mount the actuating shaft 130. The housing 150 can enclose the base structure 110, the cover device 120, and the stop 124, at least partially, on the inner side of the service access 10 or the outer structure 2. Optionally, the actuating shaft 130 can be mounted, for example, in a sliding bearing bushing 152, wherein a first retaining ring 133 pre-mounted on the actuating shaft 130 and a second retaining ring 134 mounted on a side of the sliding bearing bushing 152 facing away from the first retaining ring 133 axially secure the actuating shaft 130.

[0057] The lifting device 124 can be screwed to the cover device 120 by means of a threaded connection 126, the locking position being adjustable along the longitudinal axis Z by means of the threaded connection 126. In this way, the position of the cover device 120 can be adjusted along the longitudinal axis Z, as shown in the illustration of the Fig. 2 also to the right or left, in order to provide the outer side 110a, 120a, 131a of the locking device 100 in relation to the service access 10 as step-free as possible. This means that by turning the stop element 124 inwards or outwards, a step can be adjusted during assembly.

[0058] To secure the lifting device 124 against unintentional twisting, the lifting device 124 can have a recess 125 which can engage with a projection 113 of the base structure 110, as shown in Fig. Figure 2 is shown as an example. Optionally, the projection 113 and the recess 125 can be designed and dimensioned such that they do not interlock in the manipulation position. In this way, the cover device 120 can be rotated relative to the base structure 110 via the threaded connection 126 in the manipulation position.

[0059] The transmission end section 132 can be coupled to the lever unit 140. The lever unit 140 can be positively and / or force-fitted to the transmission end section 132, for example by a screw connection. Furthermore, the lever unit 140 can include a linkage (not shown) that actuates one or more unlocking or locking mechanisms, so that the service access 10 can be unlocked or locked.

[0060] Fig. Figure 3 shows a schematic perspective view of the base structure 110 of the locking device 100. Fig. 2.

[0061] The base structure 110 can, for example, be designed as a bushing. The bushing 110 can, for example, be cylindrical. Additionally, the base structure 110, the cover device 120, and the actuating shaft 130 can be arranged coaxially. Furthermore, the bushing 110 can be pressed, glued, or similarly bonded and / or force-fitted into the opening 11. For example, the base structure 110 can be flush with the outer surface 120a of the cover device 120, so that the outer surface of the service access 10 is without a protrusion. The base structure 110 can also have a through-opening 112.

[0062] For example, the base structure 110 can have a plurality, in particular an even number, of projections 113. The plurality of projections 113 can comprise two, three, four, five, six, or eight projections 113. The projections 113 themselves can each be identical in design. Regardless of the number of projections 113, the projections 113 can be evenly distributed around a circumference of the base structure 110. Fig. 3 The basic structure includes, for example, four projections 113, which are evenly distributed around the circumference.

[0063] Fig. Figure 4 shows a schematic perspective view of the cover device 120 of the locking device 100. Fig. 2.

[0064] The cover device 120 can, for example, be circular in cross-section with respect to the longitudinal axis Z. The cover device 120 can be deliberately designed to be very simple, so that reworking the original, oversized cover during the assembly stage is very easy. This means that the cover device 120, as a simple and cost-effective component, can be easily reworked with minimal effort. Furthermore, the actuating shaft 130 and the circular cover device 120 can be arranged coaxially.

[0065] For example, the cover device 120 can have a mushroom-shaped outer contour. Alternatively or additionally, the cover device 120 can have a feed hole 128. The feed hole 128 can, for example, be arranged coaxially with a rotation axis of the cover device 120. The shape of the feed hole 128 can correspond to the outer contour of the handling end area 131.

[0066] Furthermore, the cover device 120 can have a thread for the threaded connection 126 on a cylindrical surface.

[0067] Fig. Figure 5 shows a schematic perspective view of the stop 124 of the locking device 100. Fig. 2.

[0068] The lifting device 124 can have a plurality, in particular an even number, of recesses 125. The plurality of recesses 125 is specifically designed to engage with the plurality of projections 113 of the base structure 110. Optionally, the projections 113 and the recesses 125 can each be designed and dimensioned such that they do not engage with each other in the manipulation position. In this way, the cover device 120 can be rotated relative to the base structure 110 via the threaded connection 126 in the manipulation position.

[0069] The multitude of recesses 125 can comprise two, three, four, five, six, or eight recesses 125. The recesses 125 themselves can each be identical in design. Regardless of the number of recesses 125, the recesses 125 can be evenly distributed around the circumference of the lifting device 124. Fig. 5 The lifting device 124 includes, for example, four recesses 125 which are evenly distributed around the circumference.

[0070] Furthermore, the lifting device 124 can have a thread for the threaded connection 126 on an inner cylindrical surface.

[0071] Fig. Figure 6 shows a schematic side view of an aircraft 1 with a service access 10 according to a further embodiment of the invention.

[0072] The external structure 2 can be designed as a wing, fuselage, nacelle, vertical stabilizer or the like.

[0073] Fig. Figure 7 shows a flowchart of a method V for manufacturing a locking device 100 for a service access 10 on an external structure 2 of an aircraft 1 according to a further embodiment of the invention.

[0074] The procedure V includes, for example, a step V1 attaching a base structure 110, a step V2 inserting a spring device 122 into the base structure 110, a step V3 connecting a stop device 124, a step V4 inserting an actuating shaft 130, an optional step V5 adjusting the locking position and an optional step V6 coupling the transmission end area 132 with a lever unit 140.

[0075] In step V1, a base structure 110 is attached to the outer structure 2 in an opening 11 of the service access 10, wherein the base structure 110 has a through opening 112 extending along a longitudinal axis Z.

[0076] In step V2, a spring assembly 122 is inserted into the base structure 110, whereby the spring assembly 122 is pre-tensioned and held in position by the placement of a cover assembly 120. The cover assembly 120 is mounted in the through-opening 112 and is displaceable relative to the base structure 110 along the longitudinal axis Z. Optionally, the cover assembly 120 can be mounted in the base structure 110 by means of a sliding bushing 111, which is pre-installed in the base structure.

[0077] In step V3, a lifting device 124 is connected to the cover device 120, so that the cover device 120 is held in a closed position by the spring device 122 in conjunction with the lifting device 124.

[0078] In the Insertion step V4, an actuating shaft 130 is inserted, extending along the longitudinal axis Z, having a handling end section 131 for rotary handling using a tool and a transmission end section 132 for transmitting torque to a lever unit 140 coupled to the transmission end section 132. For example, the actuating shaft 130 can be pushed through a sliding bearing bushing 152 of the housing 150 until a first retaining ring 133, pre-mounted on the actuating shaft 130, comes into contact with the sliding bearing bushing 152. An axial position of the actuating shaft 130 can be secured by a second retaining ring 134, which is mounted on a side of the sliding bearing bushing 152 facing away from the first retaining ring 133 after the actuating shaft 130 has been inserted into the sliding bearing bushing 152. The handling end area 131 is enclosed by the covering device 120.The handling end area 131 and the covering device 120 are arranged flush with their respective outer surfaces 120a, 131a.

[0079] Furthermore, when inserting the actuating shaft V4, a housing 150 can be installed on an inner side of the service access 10, and the actuating shaft 130 can be inserted through a feed hole 128 of the cover device 120. The housing 150 can enclose the base structure 110, the cover device 120, and the stop 124, at least partially, on the inner side of the service access 10 or the outer structure. The feed hole 128 can, in particular, correspond to a cross-section of the handling end area 131.

[0080] In the optional Adjustment step V5, the locking position can be adjusted to minimize a step between the cover device 120 and the handling end area 131, or between the cover device 120 and the base structure 110, with respect to the respective outer surface 110a, 120a, 131a. The locking position is adjusted by a threaded connection 126 along the longitudinal axis Z. This allows the position of the cover device 120 to be adjusted along the longitudinal axis Z to provide the outer surface of the locking device with as few steps as possible in relation to the service access 10. This means that a step can be adjusted during assembly by turning the stop element 124 in or out.

[0081] To secure the lifting device 124 against unintentional rotation, the lifting device can have a recess that can engage with a projection of the base structure. Optionally, the projection and the recess can be designed and dimensioned such that they do not engage in the manipulation position. In this way, the cover device can be rotated relative to the base structure via the threaded connection in the manipulation position. Depending on the number of projections 113 and recesses 125, the lifting device 124 can be rotated relative to the cover device 120 by, for example, 45°, 90°, 135°, or 180° to allow the projections 113 and recesses 125 to engage.

[0082] Alternatively or additionally, the cover device 120 can be rotated relative to the actuating shaft 130, particularly depending on the polygonal profile of the handling end area 131, for example by 45° for an external hexagonal profile or by 90° for an external square profile, in order not to block the handling end area 131 equipped with the profile. Once the optimal locking position has been found, the threaded connection 126 can be secured by a locking wire, adhesive, or similar material.

[0083] In the optional coupling step V6, the transmission end section 132 can be coupled to a lever unit 140. The lever unit 140 can be connected to the transmission end section 132 positively and / or non-positively, for example by means of a screw connection. Furthermore, the lever unit 140 can include a linkage that actuates one or more unlocking or locking mechanisms, so that the service access can be unlocked or locked.

[0084] After applying steps V1 to V6, the locking device 100 can be, for example, as shown in Fig. 2 is shown and described.

[0085] In the preceding detailed description, various features have been summarized in one or more examples to improve the clarity of the presentation. However, it should be clear that the above description is merely illustrative and in no way limiting. It serves to cover all alternatives, modifications, and equivalents of the various features and embodiments. Many other examples will be immediately and directly clear to the person skilled in the art based on their technical knowledge, given the above description.

[0086] The exemplary embodiments were selected and described to best illustrate the principles underlying the invention and its practical applications. This enables those skilled in the art to optimally modify and utilize the invention and its various embodiments with regard to the intended purpose. In the claims and the description, the terms "including" and "comprising" are used as neutral language terms for the corresponding terms "comprehensive." Furthermore, the use of the terms "a," "a," and "an" is not intended to fundamentally exclude multiple features and components described in this way.

[0087] For example, the present invention is not limited to the application of aerodynamic external structures, but can also be applied to conventional external structures and access flaps prepared therein. Reference symbol list 1 aircraft 2. External structure 10 Service Access 11 Opening 100 aircraft 110 Basic structure 110a Outside of the base structure 111 Sliding bushing 112 Passage opening 113 lead 120 Cover device 120a Outside of the cover device 122 Spring assembly 124 Lifting equipment 125 recess 126 Threaded connection 128 Feed hole 130 Actuating shaft 131 Handling end area 131a Outer surface of the handling end area 132 Transmission end range 133 first retaining ring 134 second retaining ring 140 lever unit 150 cases 152 Plain bearing bushing G G gap between cover device and base structure X, Y transverse axis Z Longitudinal axis V Procedure V1 Attach V2 Insert V3 Connect Insert V4 V5 Customize V6 coupling

Claims

[1] Locking device (100) for a service access (10) on an external structure (2) of an aircraft (1), comprising the locking device (100): a base structure (110) for fixed installation in an opening (11) of a service access (10) on an outer structure (2), wherein the base structure (110) has a through opening (112) extending along a longitudinal axis (Z); a cover device (120) which is slidably mounted in the through-opening (112) and relative to the base structure (110) along the longitudinal axis (Z), wherein the cover device (120) is pre-tensioned by a spring device (122) and is held in a closed position by a stop means (124) in conjunction with the spring device (122); and an actuating shaft (130) extending along the longitudinal axis (Z), comprising a handling end region (131) for rotary handling using a tool and a transmission end region (132) for transmitting a torque to a lever unit (140) coupled to the transmission end region (132), wherein the handling end region (131) is bounded by the cover device (120), and wherein the handling end region (131) and the cover device (120) are arranged flush with respect to a respective outer surface (120a, 131a). [2] Locking device (100) according to claim 1, wherein the cover device (120) is axially displaceable along the longitudinal axis (Z) relative to the actuating shaft (130) by a pressure force, so that the cover device (120) is in a manipulation position in which the handling end area (131) is freely accessible. [3] Locking device (100) according to claim 1 or 2, wherein the cover device (120) is round in cross-section with respect to the longitudinal axis (Z). [4] Locking device (100) according to one of the preceding claims, further comprising a housing (150) which is arranged on an inside of the service access (10) and rotatably supports the actuating shaft (130). [5] Locking device (100) according to one of the preceding claims, wherein the spring device (122) is designed as a compression spring. [6] Locking device (100) according to one of the preceding claims, wherein the stop means (124) is screwed to the cover device (120) by means of a threaded connection (126), wherein the locking position can be adjusted along the longitudinal axis (Z) by means of the threaded connection (126). [7] Locking device (100) according to one of the preceding claims, wherein the base structure (110) is designed as a bushing. [8] Locking device (100) according to one of the preceding claims, wherein the transmission end area (132) is coupled to a lever unit (140). [9] Service access (10) for an aircraft (1) having service access (10): a non-destructively removable section of an external structure (2) of an aircraft (1), wherein the section has an opening (11); and a locking device (100) according to one of the preceding claims, wherein the base structure (110) is fixedly attached in the opening (11). [10] Aircraft (1) with a service access (10) according to claim 9. [11] Method (V) for manufacturing a locking device for a service access on an external structure (2) of an aircraft (1), the method (V) comprising: Attaching (V1) a base structure (110) in an opening (11) of a service access (10) to an outer structure (2), wherein the base structure (110) has a through opening (112) extending along a longitudinal axis (Z); Insertion (V2) of a spring device (122) into the base structure (110), wherein the spring device (122) is pre-tensioned and held in position by placing a cover device (120) on it, wherein the cover device (120) is mounted in the through-opening (112) and is displaceable relative to the base structure (110) along the longitudinal axis (Z); Connecting (V3) a lifting device (124) to the covering device (120), so that the cover device (120) is held in a closed position by the spring device (122) in conjunction with the stop device (124); and Insertion (V4) of an actuating shaft (130) extending along the longitudinal axis (Z), comprising a handling end region (131) for rotary handling using a tool and a transmission end region (132) for transmitting a torque to a lever unit (140) coupled to the transmission end region (132), wherein the handling end area (131) is bounded by the covering device (120), and wherein the handling end area (131) and the covering device (120) are arranged flush with respect to a respective outer surface (120a, 131a). [12] Method (V) according to claim 11, wherein when inserting (V4) the actuating shaft a housing (150) is installed on an inside of the service access (10) and the actuating shaft (130) is inserted through a feed hole (128) of the cover device (120). [13] Method (V) according to claim 11 or 12, wherein the actuating shaft (130) is pushed through a sliding bearing bushing (152) of the housing (150) until a first retaining ring (133) pre-mounted on the actuating shaft (130) comes into contact with the sliding bearing bushing (152). [14] Method (V) according to any one of claims 11 to 13, further comprising adjusting (V5) the closure position to minimize a step between the cover device 120 and the handling end area 131 or between the cover device 120 and the base structure 110 with respect to the respective outer side (110a, 120a, 131a), wherein the closure position is adjusted by a threaded connection (126) along the longitudinal axis (Z). [15] Method (V) according to any one of claims 11 to 14, further comprising coupling (V6) the transmission end area (132) with a lever unit (140).

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