Cabin door locking device, aircraft cabin door or spacecraft cabin door and aircraft or spacecraft

Abstract

The present invention provides a door locking device for an aircraft door or spacecraft door, in particular for a cargo door, an aircraft door or spacecraft door, and an aircraft door or spacecraft, the door locking device comprising: an actuation lever for actuating the door locking device, the actuating rod can rotate around a pivot axis and comprises a protruding part section; a latch element rotatably hinged at the door frame of the aircraft door or spacecraft door about a hinge axis and configured to be engageable with a corresponding latch mating portion of the fuselage frame such that the door locking device locks in a form-fitting manner; and a connecting element mechanically connecting the protruding section and the latch element such that rotation of the actuation lever causes rotation of the latch element. Furthermore, an aircraft door or spacecraft door comprises such a door locking device, and an aircraft comprising such an aircraft door or spacecraft door.

Description

Technical Field

[0001] The present invention relates to a door locking device for an aircraft door or a spacecraft door, and an aircraft door or a spacecraft door comprising such a door locking device. The present invention also relates to an aircraft or a spacecraft comprising such an aircraft door or a spacecraft door. Background Art

[0002] An aircraft door in a fuselage cell of an aircraft has to transfer considerable rim loads. The larger the diameter of the fuselage cell, the higher the rim loads that occur in the fuselage cell structure. The load transfer between the aircraft door and the fuselage cell structure is usually provided by a plurality of swivel hooks mounted on an axle, which engage with a circular axle segment that is fixed approximately horizontally in the region of the fuselage cell.

[0003] High tensions act during flight, in particular in the case of relatively large aircraft doors or hatches, such as, for example, cargo hatches. In addition, high load differences, such as between an empty cargo hatch and a loaded cargo hatch, may occur in the region of the hatch gap. Therefore, latching devices are usually designed to withstand high loads, resulting in a relatively high weight for such latching devices. Summary of the invention

[0004] According to the invention, this problem is solved in each case by the subject-matter of the main aspects.

[0005] According to a first aspect of the present invention, a door locking device for an aircraft door or a spacecraft door is provided. The door locking device comprises an actuating rod for actuating the door locking device, wherein the actuating rod is rotatable about a pivot axis and comprises a protruding section. In addition, the door locking device comprises a latch element, which is rotatably hinged at a door frame of the aircraft door or the spacecraft door about a hinge axis and is configured to be able to engage with a corresponding latch mating part of a fuselage frame. In addition, the door locking device comprises a connecting element, which mechanically connects the protruding section and the latch element, so that the rotation of the actuating rod causes the rotation of the latch element. In particular, the door locking device can be provided for a cargo door.

[0006] According to a second aspect of the present invention, there is provided an aircraft door or a spacecraft door comprising a door frame and a door locking device according to the first aspect of the present invention. The door locking device is mounted to the door frame, wherein the latch element is rotatably hinged at the door frame.

[0007] According to a third aspect of the present invention, there is provided an aircraft or spacecraft comprising an aircraft or spacecraft door according to the second aspect of the present invention.

[0008] The basic idea of ​​the invention is to provide a latch mechanism for an aircraft door which has reduced weight, reduced cost and reduced complexity. A latch element can engage with a corresponding latch counterpart so that the door locking device is locked in a form-fitting manner.

[0009] A particular advantage of the solution according to aspects of the present invention is that weight, cost and complexity can be reduced. In addition, the reliability of locking an aircraft door or a spacecraft door can be improved. The order of the maintenance and manufacturing process of the door locking device can be optimized. In addition, a particular advantage is that the present invention can be applied to an aircraft or a spacecraft without changing any configuration of the fuselage of the aircraft or the spacecraft. When applying the present invention, each door locking device can omit a bell crank, a solid connecting rod and three bolts and corresponding nuts. Therefore, the weight of the aircraft can be reduced by about 5.4 kg or more, for example, depending on the number of door locking devices provided in the aircraft door or the spacecraft door.

[0010] Advantageous embodiments and other developments emerge from the description with reference to the drawings.

[0011] According to some embodiments of the invention, the connecting element comprises an adjustable length for adjusting the distance between the latching element and the protruding section of the actuating rod or the latching rod. For example, the distance can be adjusted to compensate for tolerances and / or to readjust the door locking device during the life cycle. In particular, the connecting element is configured as a connecting rod. Furthermore, the articulation axis and the pivot axis can be fixed relative to each other.

[0012] According to some other embodiments of the present invention, one end of the connecting element and the latch element form a first contact point, wherein the other end of the connecting element and the protruding section form a second contact point, and wherein the center of the second contact point in the locked position is arranged on the opposite side of the imaginary connecting line between the pivot axis and the center of the first contact point relative to the second contact point in the unlocked position. Therefore, a torque applied to the latch element in the locked position cannot open the door locking device because the torque causes the actuating rod to rotate against the unlocking direction. In other words, when the second contact point is in the arrangement in the locked position described above, the connecting element and the actuating rod provide an over-center state.

[0013] Furthermore, the actuating lever can be in the locked position, for example, blocked by a mechanical stop to prevent rotation of the actuating lever. The mechanical stop can be fixed to the door frame. In particular, in the locked position, the mechanical stop can be positioned and configured to contact the protruding section. For example, the pivot axis of the actuating lever is substantially parallel to the articulation axis of the latch element.

[0014] According to some other embodiments of the present invention, the door locking device also includes a locking member or a locking cam for fixing the latch element in the locking position, wherein the locking member can rotate around the locking shaft axis, and the locking shaft axis is substantially parallel to the hinge axis. Therefore, the latch element is fixed in the locking position by the locking member independently of the actuating rod. This means that when the locking member fixes the latch element, the latch element cannot be opened by the actuating rod. For example, the locking member is correspondingly configured as an eccentric body or a locking cam that can rotate around the locking shaft axis, so that the eccentric body blocks the correspondingly shaped protrusion of the latch element. In addition, the locking shaft axis can be fixed relative to the hinge axis and the pivot axis.

[0015] According to some other embodiments of the present invention, the protruding section and the locking member each include a protrusion, which is arranged and configured to face each other when the latch element is fixed by the locking member, wherein the distance between the facing protrusions is less than the vertical distance between the center of the second contact point and the imaginary connecting line in the locked position. Therefore, when the locking member fixes the latch element, the rotation of the actuating rod toward the unlocked position is blocked by the protrusion. When the locking member does not fix the latch element, the protrusions do not face each other because the locking member rotates around the locking shaft axis compared to the fixed state. The protrusions can also be described as additional locking cams.

[0016] According to some other embodiments of the invention, 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. The overcenter value of the connecting element and the actuating rod is greater than the distance between the facing protrusions.

[0017] According to some other embodiments of the present invention, in the locked position, the vertical distance between the center of the second contact point and the imaginary connecting line is in the range of about 1.5 mm to 4.0 mm. In particular, in the locked position, the vertical distance between the center of the second contact point and the imaginary connecting line is about 2.5 mm. Thus, in the locked position, the vertical distance between the center of the second contact point and the imaginary connecting line is always greater than the distance between the facing protrusions.

[0018] According to some other embodiments of the present invention, the latching element is configured as a latching hook.

[0019] According to some other embodiments of the present invention, the at least one door locking device comprises four to twelve door locking devices. For example, the at least one door locking device comprises six, eight or ten door locking devices. The four to twelve door locking devices may be arranged at a horizontal side of an aircraft door or a spacecraft door, wherein the horizontal side extends perpendicular to the orientation of the fuselage frame, which means extending parallel to the longitudinal axis of the fuselage. For example, in an aircraft door with six door locking devices, the weight of the aircraft door may be reduced by about 2.7 kg.

[0020] According to some other embodiments of the present invention, the aircraft door or spacecraft door 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 rigidly coupled to the locking shaft in terms of torsion. In addition, the locking shaft can be manually operated or operated by a drive unit.

[0021] According to some other embodiments of the present invention, the aircraft door or spacecraft door further comprises an actuation shaft or a latch shaft, respectively, which is mechanically coupled to the actuation rod and extends along the pivot axis. The actuation shaft is configured to rotate the actuation rod. For example, the actuation rod is rigidly coupled to the actuation shaft in terms of torsion. In addition, the actuation shaft can be manually actuated or actuated by a drive unit.

[0022] For example, the actuating shaft may be mechanically coupled to a drive system comprising at least one of the following: a drive shaft, a drive belt or a worm drive. The drive system may be configured to drive / operate the actuating shaft such that the actuating rod may be rotated. Thus, the drive unit does not need to be arranged adjacent to the door locking device. In particular, when the aircraft door comprises more than one door locking device, the drive system may couple each door locking device to the drive unit. Thus, each door locking device of the aircraft door or spacecraft door may be operated simultaneously.

[0023] According to some other embodiments of the present invention, the aircraft door or the spacecraft door is configured as a cargo door.

[0024] According to some other embodiments of the present invention, the aircraft or spacecraft further comprises a fuselage frame having a latching counterpart configured to receive the latching element. In other words, the latching counterpart is configured to engage with the latching element in the locked position. For example, the latching counterpart may include or be configured as an adjustable spool for compensating for manufacturing tolerances and / or installation tolerances. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The invention is explained in more detail below based on an exemplary embodiment indicated in a schematic diagram, in which:

[0026] Figure 1 A schematic diagram of an aircraft having an aircraft door comprising a door locking device according to an embodiment of the present invention is shown; and

[0027] Figure 2 A schematic diagram showing a hatch door locking device in a locked position according to another embodiment of the present invention is shown. DETAILED DESCRIPTION

[0028] The accompanying drawings are intended to convey a further understanding of embodiments of the present invention. The accompanying drawings illustrate embodiments and are used in conjunction with the specification to explain the principles and concepts of the present invention. Many advantages of other embodiments and cited advantages appear from the accompanying drawings. The elements of the accompanying drawings are not necessarily shown in scale relative to each other. Terms indicating directions such as, for example, "at the top", "at the bottom", "at the left", "at the right", "above", "below", "horizontally", "vertically", "at the front", "at the rear" and similar statements are only for illustrative purposes and are not intended to be generally limited to specific configurations as shown in the figures.

[0029] In the figures of the drawings, elements, features and components that are identical, have the same function and have the same effect are each provided with the same reference numerals, unless otherwise stated.

[0030] Figure 1 A schematic diagram of an aircraft 1 with an aircraft door 10 is shown, which comprises a door locking device 100 .

[0031] The aircraft 1 comprises a fuselage frame 2 having a latching counterpart 3 configured to receive a latching element of a door locking device 100, such as Figure 2 For example, the latch mating part may include or be configured as an adjustable spool for compensating for manufacturing tolerances and / or installation tolerances.

[0032] The aircraft door 10 includes a door frame 11 and at least one door locking device 100. The at least one door locking device 100 may include four to twelve door locking devices 100. For example, the at least one door locking device 100 includes six, eight or ten door locking devices. Optionally, the aircraft door 10 is configured as a cargo door.

[0033] At least one door locking device 100 is mounted to the door frame 11 , wherein a latching element 103 is rotatably hinged at the door frame 11 .

[0034] Four to twelve door locking devices 100 may be arranged at a horizontal side of the aircraft door 10 , wherein the horizontal side extends perpendicularly to the orientation of the fuselage frame 2 .

[0035] The aircraft door 10 is attached to the fuselage frame 2 by means of a hinge. Preferably, the aircraft door 10 is attached to the fuselage frame 2 on the upper side of the aircraft door 10. More specifically, the aircraft door 10 is attached by means of a multi-part hinge and is swiveled outwards during the opening movement.

[0036] Figure 2 A schematic diagram of a door locking device 100 in a locked position is shown. In the illustrated locked position, the door locking device 100 is integrated in an aircraft door 10 and locked to the fuselage frame. The door locking device 100 is configured for a cargo door.

[0037] The door locking device 100 accordingly comprises an actuating lever or latching lever 101 for actuating the door locking device 100 , wherein the actuating lever 101 is rotatable about a pivot axis A101 and comprises a protruding section 102 .

[0038] Furthermore, the door locking device 100 comprises a latching element 103, which is rotatably hinged about a hinge axis A103 at a door frame 11 of an aircraft door or a spacecraft door 10 and is configured to be able to engage with a corresponding latching counterpart 3 of a fuselage frame, so that the door locking device 100 is locked in a form-fitting manner. Exemplarily, the latching element 103 is configured as a latching hook.

[0039] In addition, the door locking device 100 comprises a connecting element 104. Figure 2 , the connecting element 104 is configured as a connecting rod. The connecting rod 104 mechanically connects the protruding section 102 and the latch hook 103, so that a rotation of the actuating rod 101 causes a rotation of the latch hook 103. The connecting rod 104 comprises an adjustable length for adjusting the distance between the latch hook 103 and the protruding section 102 of the actuating rod 101. For example, the distance can be adjusted to compensate for tolerances and / or to readjust the hatch door locking device 100 during the life cycle. In addition, the articulation axis A103 and the pivot axis A101 are fixed relative to each other.

[0040] One end of the connecting rod 104 and the latch hook 103 form a first contact point 104a, wherein the other end of the connecting rod 104 and the protruding section 102 form a second contact point 104b, and wherein, relative to the second contact point 104b in the unlocked position, the center of the second contact point 104b in the locked position is arranged on the opposite side of the imaginary connecting line ICL between the pivot axis A101 and the center of the first contact point 104a. Therefore, when the second contact point 104b is in the arrangement in the locked position described above, the connecting rod 104 and the actuating rod 101 provide an over-center state.

[0041] Furthermore, the actuating rod 101 can be in the locked position by being blocked by, for example, a mechanical stop 105 to prevent rotation of the actuating rod 101. The mechanical stop 105 is fixed to the door frame 11. In particular, in the locked position, the mechanical stop 105 is positioned and configured to be in contact with the protruding section 102. For example, the pivot axis A101 of the actuating rod 101 is parallel to the hinge axis A103 of the latch hook 103. In the case of a rotation against the unlocking direction, the force is transmitted to the door frame instead of the mechanism of the door locking device. In the case of a rotation against the unlocking direction, the force is transmitted to the door frame 11 instead of the mechanism of the door locking device 100.

[0042] exist Figure 2 , the hatch locking device 100 further comprises a locking member / locking cam 106 for fixing the latch hook 103 in the locking position, wherein the locking member 106 is rotatable about a locking shaft axis A106, which is substantially parallel to the articulation axis A103. Thus, the latch hook 103 is fixed in the locking position by the locking member 106 independently of the actuation rod 101. This means that when the locking member 106 fixes the latch hook 103, the latch hook 103 cannot be opened by the actuation rod 101. For example, the locking member 106 is configured as an eccentric body, which is rotatable about the locking shaft axis A106, so that the eccentric body blocks a correspondingly shaped protuberance of the latch hook 103. Furthermore, the locking shaft axis A106 can be fixed relative to the articulation axis A103 and the pivot axis A101.

[0043] The protruding section 102 and the locking member 106 each include protrusions 102a, 106a, which are arranged and configured to face each other when the latch hook 103 is fixed by the locking member 106, wherein a distance d1 between the facing protrusions 102a, 106a is smaller than a perpendicular distance d2 between the center of the second contact point 104b and the imaginary connecting line ICL in the locked position. Therefore, when the locking member 106 fixes the latch hook 103, the rotation of the actuating rod 101 toward the unlocked position is blocked by the protrusions 102a, 106a. When the locking member 106 does not fix the latch hook 103, the protrusions 102a, 106a do not face each other because the locking member 106 rotates around the locking shaft axis A106 compared to the fixed state.

[0044] The distance d1 between the facing protrusions 102a, 106a is about 1 mm. In the locked position, the vertical distance d2 between the center of the second contact point and the imaginary connecting line is about 2.5 mm.

[0045] The aircraft door 10 exemplarily includes a door frame 11, a rotatable locking shaft 12, an actuating shaft / latch shaft 13, and a door locking device 100. Optionally, the aircraft door 10 may include a drive system (not shown). The drive system may be mounted to the door frame 11 and drive the actuating rod 101. The drive system may be mechanically coupled or include the actuating shaft 13. The door locking device 100 is mounted to the door frame 11. For example, the door locking device 100 is arranged between two adjacent door frames 11.

[0046] The locking shaft 12 is mechanically coupled to the locking member 106 and extends along a 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. Furthermore, the locking shaft 12 may be manually operated or operated by a drive unit.

[0047] The actuation shaft 13 is mechanically coupled to the actuation lever 101 and extends along a 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. Furthermore, the actuation shaft 13 may be actuated manually or by a drive unit.

[0048] In the above detailed description, various features have been combined in one or more examples to improve the rigor of the illustration. However, it should be clear in this case that the above description is merely illustrative and not restrictive. It is intended to cover all alternatives, modifications and equivalents of the various features and exemplary embodiments. Considering the above description, many other examples will be immediately and directly clear to those skilled in the art based on their knowledge in the art.

[0049] The exemplary embodiments have been selected and described in order to be able to present the basic principles of the invention and their application possibilities in practice in the best possible way. Therefore, a person skilled in the art can best modify and utilize the invention and its various exemplary embodiments with respect to the intended purpose of use. In the claims and the description, the terms "comprising" and "having" are used as neutral language concepts corresponding to the term "including". In addition, the use of the terms "a", "an" and "an" should not in principle exclude multiple features and components described in this way.

[0050] Although at least one exemplary embodiment of the present invention is disclosed herein, it should be understood that modifications, replacements, and alternatives may be obvious to those of ordinary skill in the art and may be made without departing from the scope of the present disclosure. The present disclosure is intended to cover any adaptation or variation of the exemplary embodiments. In addition, in the present disclosure, the terms "including" or "including" do not exclude other elements or steps, the terms "one" or "an" do not exclude plural numbers, and the term "or" means one or both. In addition, unless otherwise implied by the disclosure or context, the features or steps already described may also be used in combination with other features or steps, and may be used in any order. The present disclosure is hereby incorporated by reference into the complete disclosure of any patent or application to which it claims interest or priority.

[0051] Reference numerals list

[0052] 1 Aircraft or spacecraft

[0053] 2 Body frame

[0054] 3 Latch mating part

[0055] 10 Aircraft hatch or spacecraft hatch

[0056] 11 Door frame

[0057] 12 Locking shaft

[0058] 13 Actuating shaft

[0059] 100 Door locking device

[0060] 101 Actuating rod

[0061] 102 Protruding section

[0062] 102a: protrusion of the protruding section

[0063] 103 Latch element

[0064] 104 Connecting elements

[0065] 104a First contact point

[0066] 104b Second contact point

[0067] 105 Mechanical stopper

[0068] 106 Locking member

[0069] 106a: Protrusion of locking member

[0070] A101 Pivot axis

[0071] A103 articulated axis

[0072] A106 locking shaft axis

[0073] ICL imaginary connection line

[0074] d1 Distance between facing protrusions

[0075] d2 The vertical distance between the center of the second contact point and the imaginary connecting line

Claims

1. A door locking device (100), the door locking device (100) being used for an aircraft door or a spacecraft door (10), in particular for a cargo door, the door locking device (100) comprising: an actuating rod (101) for actuating the door locking device (100), wherein the actuating rod (101) is rotatable about a pivot axis (A101) and comprises a protruding section (102); a latch element (103) which is rotatably hinged about a hinge axis (A103) at a door frame (11) of the aircraft or spacecraft door (10) and is configured to be engageable with a corresponding latch counterpart (3) of a fuselage frame (2); and A connecting element (104) mechanically connects the protruding section (102) and the latching element (103) such that rotation of the actuating rod (101) causes rotation of the latching element (103).

2. The door locking device (100) according to claim 1, wherein: The connecting element (104) comprises an adjustable length for adjusting the distance between the latching element (103) and the protruding section (102) of the actuating rod (101).

3. The door locking device (100) according to claim 1 or 2, wherein: One end of the connecting element (104) and the latch element (103) form a first contact point (104a), wherein the other end of the connecting element (104) and the protruding section (102) form a second contact point (104b), and wherein, relative to the second contact point (104b) in the unlocked position, the center of the second contact point (104b) in the locked position is arranged on the opposite side of an imaginary connecting line (ICL) between the pivot axis (A101) and the center of the first contact point (104a).

4. The hatch locking device (100) according to one of the preceding claims, further comprising a locking member (106) for fixing the latch element (103) in the locked position, wherein The locking member (106) is rotatable about a locking shaft axis (A106), which is substantially parallel to the hinge axis (A103).

5. The door locking device (100) according to claim 4, wherein: The protruding section (102) and the locking member (106) each include protrusions (102a, 106a), which are arranged and configured to face each other when the latch element (103) is fixed by the locking member (106), wherein a distance (d1) between the facing protrusions (102a, 106a) is smaller than a perpendicular distance (d2) between the center of the second contact point (104b) and the imaginary connecting line (ICL) in the locked position.

6. The door locking device (100) according to claim 5, wherein: The distance (d1) between the facing protrusions (102a, 106a) is in the range of about 0.5 mm to 2.0 mm, in particular the distance (d1) between the facing protrusions is about 1 mm.

7. The hatch door locking device (100) according to claim 5 or 6, wherein: In the locked position, the vertical distance (d2) between the center of the second contact point (104b) and the imaginary connecting line (ICL) is in the range of about 1.5 mm to 4.0 mm, in particular, in the locked position, the vertical distance (d2) between the center of the second contact point and the imaginary connecting line is about 2.5 mm.

8. The hatch door locking device (100) according to one of the preceding claims, wherein: The latching element (103) is designed as a latching hook.

9. An aircraft door or a spacecraft door (10), comprising: Door frame (11); as well as At least one door locking device (100) according to one of the preceding claims, which is mounted to the door frame (11), wherein the latching element (103) is hinged at the door frame (11) in a rotatable manner.

10. The aircraft door or spacecraft door (10) according to claim 9, wherein: The at least one door locking device (100) comprises four to twelve door locking devices (100).

11. An aircraft door or spacecraft door (10) according to claim 9 or 10, further comprising a rotatable locking shaft (12), the rotatable locking shaft (12) being mechanically connected to the locking member (106) and extending along the locking shaft axis (A106).

12. An aircraft or spacecraft door (10) according to one of claims 9 to 11, further comprising an actuation shaft (13) which is mechanically coupled to the actuation rod (101) and extends along the pivot axis (A101).

13. An aircraft or spacecraft (1) having an aircraft or spacecraft door (10) according to one of claims 9 to 12.

14. An aircraft or spacecraft (1) according to claim 13, wherein: The aircraft door or spacecraft door (10) is configured as a cargo door.

15. The aircraft or spacecraft (1) according to claim 14, further comprising a fuselage frame (2), the fuselage frame (2) having a latch counterpart (3), the latch counterpart (3) being configured to receive the latch element (103).

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