Patent Application
20250136267
The disclosure herein relates to a hatch locking device for an aircraft or spacecraft hatch as well as to an aircraft or spacecraft hatch containing such a hatch locking device. The disclosure herein is furthermore concerned with an aircraft or spacecraft containing such an aircraft or spacecraft hatch.
Aircraft doors in a fuselage cell of an aircraft must transfer considerable peripheral loads. The greater the diameter of a fuselage cell the higher are the peripheral loads which arise in the fuselage cell structure. The load transfer between the aircraft door and the fuselage cell structure is commonly provided through a multiple of hooks swivel mounted on a shaft which engage round substantially horizontally fixed shaft sections in the area of the fuselage cell.
High tensile forces act during the flight, in particular, in the case of relatively large aircraft doors or hatches, such as cargo hold hatches, for example. In addition, high load differences, for example in comparison between an unloaded and loaded cargo hold, can occur in the region of the hatch gaps. Therefore, the latch devices are normally designed to withstand high loads resulting in a relative high weight for such latch devices.
According to the disclosure herein, this problem is solved in each case by the subject matter disclosed herein.
According to a first aspect of the disclosure herein, a hatch locking device for an aircraft or spacecraft hatch is provided. The hatch locking device comprises an actuation lever for actuating the hatch locking device, wherein the actuation lever is rotatable about a pivot axis and comprises a protruding section. Moreover, the hatch locking device comprises a latch, which is hinged rotatable about a hinge axis at a hatch frame of the aircraft or spacecraft hatch and configured to be engageable with a corresponding latch counter part of a fuselage frame. Further, the hatch locking device comprises a connector, which mechanically connects the protruding section and the latch such that a rotation of the actuation lever causes a rotation of the latch. In particular, the hatch locking device can be provided for a cargo door.
According to a second aspect of the disclosure herein, an aircraft hatch or an spacecraft hatch comprising a hatch frame and a hatch locking device according to the first aspect of the disclosure herein is provided. The hatch locking device is mounted to the hatch frame, wherein the latch is hinged rotatable at the hatch frame.
According to a third aspect of the disclosure herein, an aircraft or spacecraft comprising an aircraft hatch or an spacecraft hatch according to the second aspect of the disclosure herein is provided.
A fundamental concept of the disclosure herein is to provide a latch mechanism for an aircraft hatch having a reduced weight, reduced costs and reduced complexity. The latch can be engaged with the corresponding latch counter part such that the hatch locking device is positively locked.
A particular advantage in the solution according to an aspect of the disclosure herein is that weight, costs and complexity can be reduced. Furthermore, a reliability of locking an aircraft or spacecraft hatch can be increased. A maintenance of the hatch locking device and sequencing of manufacturing processes can be optimized. In addition, one particular advantage is that the disclosure herein can be applied to an aircraft or spacecraft without the need of changing any configuration of the fuselage of the aircraft or spacecraft. Per hatch locking device one bell crank, one solid connection rod and three bolts and corresponding nuts can be omitted when applying the disclosure herein. Hence, a weight of the aircraft can be reduced by about 5.4 kg or more depending on the number of hatch locking devices provided in the aircraft or spacecraft hatch, for example.
Advantageous embodiments and further developments emerge from the description with reference to the figures.
According to some embodiments of the disclosure herein, the connector comprises an adjustable length for adjusting a distance between the latch and the protruding section of the actuation lever or latching lever, respectively. For example, the distance can be adjusted to compensate tolerances and/or to readjust the hatch locking device during life cycle. In particular, the connector is configured as a connection rod. Furthermore, the hinge axis and the pivot axis can be fixed in relation to each other.
According to some further embodiments of the disclosure herein, one end of the connector and the latch form a first contact point, wherein another end of the connector and the protruding section form a second contact point, and wherein a center of the second contact point is arranged on an opposite side of an imaginary connection line between the pivot axis and a center of the first contact point in a locked position in relation to the second contact point in an unlocked position. Thus, a torque applying on the latch in the locked position cannot open the hatch locking device since the torque causes a rotation of the actuation lever against an unlocking direction. In other words, the connector and the actuation lever provide an overcentered condition when the second contact point is in the above described arrangement in the locked position.
Furthermore, the actuation lever can be blocked by a mechanical stop in the locked position to avoid a rotation of the actuation lever, for example. The mechanical stop can be fixed to the hatch frame. In particular, the mechanical stop can be positioned and configured to come into contact with the protruding section in the locked position. For example, the pivot axis of the actuation lever is substantially parallel to the hinge axis of the latch.
According to some further embodiments of the disclosure herein, the hatch locking device further comprises a locking member or locking cam, respectively, for securing the latch in a locked position, wherein the locking member is rotatable about a locking shaft axis, which is substantially parallel to the hinge axis. Hence, the latch is secured by the locking member in the locked position independently of the actuation lever. That means, when the locking member secures the latch, the latch cannot be opened by the actuation lever. For example, the locking member is configured as an eccentric body or locking cam, respectively, which is rotatable about the locking shaft axis such that the eccentric body blocks a correspondingly shaped hump of the latch. Furthermore, the locking shaft axis can be fixed in relation to the hinge axis and the pivot axis.
According to some further embodiments of the disclosure herein, the protruding section and the locking member each comprise a protrusion, which are arranged and configured to face each other when the latch is secured by the locking member, wherein a distance between the facing protrusions is shorter than a perpendicular distance between the center of the second contact point and the imaginary connection line in the locked position. Thus, a rotation of the actuation lever towards the unlocked position is blocked by the protrusions, when the locking member secures the latch. When the locking member does not secure the latch, the protrusions do not face each other since the locking member is rotated about the locking shaft axis compared to the secured condition. The protrusions could also be described as additional locking cams.
According to some further embodiments of the disclosure herein, the distance between the facing protrusions is in the range of about 0.5 mm to 2.0 mm, in particular the distance between the facing protrusions is about 1 mm. A value of an overcentering of the connector and of the actuation lever is larger than the distance between the facing protrusions.
According to some further embodiments of the disclosure herein, the perpendicular distance between the center of the second contact point and the imaginary connection line in the locked position is in the range of about 1.5 mm to 4.0 mm. In particular, the perpendicular distance between the center of the second contact point and the imaginary connection line in the locked position is about 2.5 mm. Thereby, the perpendicular distance between the center of the second contact point and the imaginary connection line is always larger than the distance between the facing protrusions in the locked position.
According to some further embodiments of the disclosure herein, the latch is configured as a latching hook.
According to some further embodiments of the disclosure herein, the at least one hatch locking device comprises four to twelve hatch locking devices. For example, the at least one hatch locking device comprises six, eight or ten hatch locking devices. The four to twelve hatch locking devices can be arranged at a horizontal side of the aircraft or spacecraft hatch, wherein the horizontal side extends perpendicular to the orientation of the fuselage frame, meaning parallel to a longitudinal axis of the fuselage. In an aircraft hatch with six hatch locking devices, for example, a weight of the aircraft hatch can be reduced by about 2.7 kg.
According to some further embodiments of the disclosure herein, the aircraft or spacecraft hatch further comprises a rotatable locking shaft, which is mechanically coupled to the locking member and extends along the locking shaft axis. The locking shaft is configured to rotate the locking member. For example, the locking member is torsionally rigidly coupled to the locking shaft. Moreover, the locking shaft can be operated manually or by a drive unit.
According to some further embodiments of the disclosure herein, the aircraft or spacecraft hatch further comprises an actuation shaft or latching shaft, respectively, which is mechanically coupled to the actuation lever and extends along the pivot axis. The actuation shaft is configured to rotate the actuation lever. For example, the actuation lever is torsionally rigidly coupled to the actuation shaft. Moreover, the actuation shaft can be actuated manually or by a drive unit.
For example, the actuation shaft can be coupled mechanically to a drive system, which comprises at least one of the following: a drive shaft, a drive belt or a worm drive. The drive system can be configured to drive/operate the actuation shaft such that the actuation lever can be rotated. Thus, the drive unit does not need to be arranged next to the hatch locking device. In particular, when the aircraft hatch comprises more than one hatch locking device the drive system can couple each hatch locking device to the drive unit. Therefore, each hatch locking device of the aircraft or spacecraft hatch can be operated at the same time.
According to some further embodiments of the disclosure herein, the aircraft or spacecraft hatch is configured as a cargo door.
According to some further embodiments of the disclosure herein, the aircraft or spacecraft further comprises a fuselage frame with a latch counter part, which is configured to receive the latch. In other words, the latch counter part is configured to engage with the latch in the locked position. For example, the latch counter part can comprise or be configured as an adjustable spool for compensating manufacturing and/or installation tolerances.
The disclosure herein is explained more specifically below on the basis of the example embodiments indicated in the schematic figures, in which:
The accompanying figures are intended to convey a further understanding of the embodiments of the disclosure herein. They illustrate embodiments and are used in conjunction with the description to explain principles and concepts of the disclosure herein. Other embodiments and many of the cited advantages emerge in light of the drawings. The elements of the drawings are not necessarily shown to scale in relation to one another. Direction-indicating terminology such as for example “at the top”, “at the bottom”, “on the left”, “on the right”, “above”, “below”, “horizontally”, “vertically”, “at the front”, “at the rear” and similar statements are merely used for explanatory purposes and do not serve to restrict the generality to specific configurations as shown in the figures.
In the figures of the drawing, elements, features and components that are the same, have the same function and have the same effect are each provided with the same reference signs-unless explained otherwise.
The aircraft 1 comprises a fuselage frame 2 with a latch counter part 3, which is configured to receive a latch of the hatch locking device 100, as it is illustrated in
The aircraft hatch 10 comprises a hatch frame 11 and at least one hatch locking device 100. The at least one hatch locking device 100 can comprise four to twelve hatch locking devices 100. For example, the at least one hatch locking device 100 comprises six, eight or ten hatch locking devices. Optionally, the aircraft hatch 10 is configured as a cargo door.
The at least one hatch locking device 100 is mounted to the hatch frame 11, wherein the latch 103 is hinged rotatable at the hatch frame 11.
The four to twelve hatch locking devices 100 can be arranged at a horizontal side of the aircraft hatch 10, wherein the horizontal side extends perpendicular to the orientation of the fuselage frame 2.
The aircraft hatch 10 is attached by a hinge to the fuselage frame 2. Preferably, the aircraft hatch 10 is attached on an upper side of the aircraft hatch 10 to the fuselage frame 2. More particularly, the aircraft hatch 10 is attached by a multi-part hinge, and swivels outwards during the opening movement.
The hatch locking device 100 comprises an actuation lever or latching lever 101, respectively, for actuating the hatch locking device 100, wherein the actuation lever 101 is rotatable about a pivot axis A101 and comprises a protruding section 102.
Further, the hatch locking device 100 comprises a latch 103, which is hinged rotatable about a hinge axis A103 at a hatch frame 11 of the aircraft or spacecraft hatch 10 and configured to be engageable with a corresponding latch counter part 3 of a fuselage frame such that the hatch locking device 100 is positively locked. Exemplarily, the latch 103 is configured as a latching hook.
Additionally, the hatch locking device 100 comprises a connector 104. As illustrated in
One end of the connection rod 104 and the latching hook 103 form a first contact point 104a, wherein another end of the connection rod 104 and the protruding section 102 form a second contact point 104b, and wherein a center of the second contact point 104b is arranged on an opposite side of an imaginary connection line ICL between the pivot axis A101 and a center of the first contact point 104a in a locked position in relation to the second contact point 104b in an unlocked position. Thus, the connection rod 103 and the actuation lever 101 provide an overcentered condition when the second contact point 104b is in the above described arrangement in the locked position.
Furthermore, the actuation lever 101 can be blocked by a mechanical stop 105 in the locked position to avoid a rotation of the actuation lever 101, for example. The mechanical stop 105 is fixed to the hatch frame 11. In particular, the mechanical stop 105 is positioned and configured to come into contact with the protruding section 102 in the locked position. For example, the pivot axis A101 of the actuation lever 101 is parallel to the hinge axis A103 of the latching hook 103. In case of a rotation against the unlocking direction a force is transmitted into the hatch frame instead of the mechanism of the hatch locking device. In case of a rotation against the unlocking direction a force is transmitted into the hatch frame 11 instead of the mechanism of the hatch locking device 100.
In
The protruding section 102 and the locking member 106 each comprise a protrusion 102a, 106a, which are arranged and configured to face each other when the latching hook 103 is secured by the locking member 106, wherein a distance d1 between the facing protrusions 102a, 106a is shorter than a perpendicular distance d2 between the center of the second contact point 104b and the imaginary connection line ICL in the locked position. Thus, a rotation of the actuation lever 101 towards the unlocked position is blocked by the protrusions 102a, 106a, when the locking member 106 secures the latching hook 103. When the locking member 106 does not secure the latching hook 103, the protrusions 102a, 106a do not face each other since the locking member 106 is rotated about the locking shaft axis A106 compared to the secured condition.
The distance d1 between the facing protrusions 102a, 106a is about 1 mm. The perpendicular distance d2 between the center of the second contact point and the imaginary connection line in the locked position is about 2.5 mm.
The aircraft hatch 10 exemplarily comprises a hatch frame 11, a rotatable locking shaft 12, an actuation shaft/latching shaft 13 and a hatch locking device 100. Optionally, the aircraft hatch 10 may comprise a drive system (not shown). The drive system could be mounted to the hatch frame 11 and drive the actuation lever 101. The drive system could mechanically couple or comprise the actuation shaft 13. The hatch locking device 100 is mounted to the hatch frame 11. For example, the hatch locking device 100 is arranged between two adjacent hatch frames 11.
The locking shaft 12 is mechanically coupled to the locking member 106 and extends along the locking shaft axis A106. The locking shaft 12 is configured to rotate the locking member 106. For example, the locking member 106 is torsionally rigidly coupled to the locking shaft 12. Moreover, the locking shaft 12 can be operated manually or by a drive unit.
The actuation shaft 13 is mechanically coupled to the actuation lever 101 and extends along the pivot axis A101. The actuation shaft 13 is configured to rotate the actuation lever 101. For example, the actuation lever 101 is torsionally rigidly coupled to the actuation shaft 13. Moreover, the actuation shaft 13 can be actuated manually or by a drive unit.
In the detailed description above, various features have been combined in one or more examples in order to improve the rigorousness of the illustration. However, it should be clear in this case that the above description is of merely illustrative but in no way restrictive nature. It serves to cover all alternatives, modifications and equivalents of the various features and example embodiments. Many other examples will be immediately and directly clear to a person skilled in the art on the basis of his knowledge in the art in consideration of the above description.
The example embodiments have been chosen and described in order to be able to present the principles underlying the disclosure herein and their application possibilities in practice in the best possible way. As a result, those skilled in the art can optimally modify and utilize the disclosure herein and its various example embodiments with regard to the intended purpose of use. In the claims and the description, the terms “including” and “having” are used as neutral linguistic concepts for the corresponding terms “comprising”. Furthermore, use of the terms “a”, “an” and “one” shall not in principle exclude the plurality of features and components described in this way.
While at least one example embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the example embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
| Number | Date | Country | Kind |
|---|---|---|---|
| 23206057 | Oct 2023 | EP | regional |
