Joint assembly for empennage actuator

Abstract

The utility model relates to a joint assembly for an empennage actuator. In a first example of the joint assembly, the joint assembly includes: an articulated universal joint including a primary force transfer pin for pivotally connecting a primary force transfer path tab of a rear fuselage structure; a motor gear assembly pivotally connected to the articulated universal joint and drivingly connected to the ball screw; the ball screw is connected to the actuator main nut and a main control connector of the empennage in a driving mode, the main control connector is connected to a safety rod of a hinged universal joint, the safety rod is arranged in a hollow space of the ball screw, a standby force transmission pin shaft is arranged on the safety rod, and the connector assembly further comprises a standby connector connecting rod. The standby force transmission path lug is arranged between the standby force transmission path lug and the standby force transmission pin shaft, the first end of the standby force transmission path lug is pivotally connected to the standby force transmission pin shaft, the second end of the standby force transmission path lug extends by a preset length from one end to the standby force transmission path lug in the first direction, and the standby force transmission path lug is fixed.

Description

TECHNICAL FIELD

[0001] The utility model relates to a joint assembly for tail actuator, especially relates to a hinged joint assembly for horizontal stabilizer trim actuator with main and standby force transmission path design. BACKGROUND

[0002] The horizontal stabilizer of the aircraft tail usually adopts single ball screw type electromechanical actuator drive. In order to prevent its structural failure, the actuator usually adopts the design of main and standby double force transmission paths, and the main and standby force transmission paths are connected to the aircraft body structure through corresponding supports respectively. The hinged joint of the actuator is connected to the aircraft body structure, and the control joint is connected to the horizontal stabilizer surface structure.

[0003] Under normal working conditions, the main force transmission path bears, and the remaining gap is used to realize the follow-up of the standby force transmission path and not to bear. Once the main force transmission path is damaged, the standby force transmission path and its support bear, serving as a failure protection design, to meet the design requirements of safety margin.

[0004] The main force transmission path of the horizontal stabilizer trim actuator of the aircraft tail mainly connects the main nut of the actuator and the main control joint of the horizontal stabilizer from the motor gear transmission assembly 12 through the ball screw 13, and connects the main force transmission path lug 2 of the structure through the hinged universal joint 11. Since the control joint and the tail are not reflected in the drawings, they are not directly related to the patent.

[0005] The standby force transmission path of the horizontal stabilizer trim actuator of the aircraft tail mainly connects the standby control joint of the horizontal stabilizer and the standby nut of the actuator to the non-main force transmission part of the ball screw 13 and the safety rod 14 built in the hollow space of the ball screw 13, and is pivotally connected to the standby force transmission path lug 3 of the structure through the pivot joint of the safety rod 14.

[0006] Among them, the connection of the joint assembly of the actuator and the main force transmission path lug 2 of the structure is pivotally connected through the main force transmission pin shaft 112 in the hinged universal joint 11. The connection of the joint assembly and the standby force transmission path lug 3 of the structure is realized through the standby force transmission pin shaft 141 on the safety rod 14. And wherein, the connection between the hinged universal joint 11 and the connection lug 121 of the motor gear transmission assembly 12 is realized through the connection pin shaft 111 of the hinged universal joint 11.

[0007] Since the joint assembly needs the main force transmission path lug 2 and the backup force transmission path lug 3 to rotate around the same center axis during normal operation, the main force transmission pin shaft 112 and the backup force transmission pin shaft 141 need to be coaxial, that is, have a common center axis during design. In addition, the backup force transmission path lug 3 and the main force transmission path lug 2 of the structure also need to ensure coaxial when the lug hole is installed. During the on-board installation of the horizontal stabilizer trim actuator of the aircraft tail wing, the backup force transmission pin shaft 141 and the main force transmission pin shaft 112 need to ensure very high coaxiality with the lug hole of the backup force transmission path lug 3 and the main force transmission path lug 2 of the structure.

[0008] The actuator is installed in the tail compartment, which is narrow and dark. After the positioning of the actuator is completed, the installation space of the backup force transmission pin shaft 141 of the articulated universal joint 1 and the backup force transmission path lug 3 of the structure is too narrow, and the tool accessibility is low, which causes the backup force transmission pin shaft 141 and the backup force transmission path lug 3 to be difficult to install.

[0009] Similarly, when disassembling the actuator, the fastener for fixing the backup force transmission pin shaft 141 of the articulated universal joint 1 and the backup force transmission path lug 3 of the structure is subject to narrow space, and there is a problem of disassembly difficulty and the fastener is easy to fall off and lost during disassembly. Invention content

[0010] In view of the above problems of the prior art, the inventors provide a joint assembly for a tail wing actuator, which provides a backup joint connecting rod and its connecting fastener, and provides a connection between the backup force transmission pin shaft of the articulated universal joint and the backup force transmission path lug of the structure.

[0011] In a first example of the joint assembly, the joint assembly comprises:

[0012] The hinge joint 11 includes a main force transmission pin shaft 112 for pivotally connecting the main force transmission path tab 2 of the rear fuselage structure, a motor gear transmission assembly 12 pivotally connected to the hinge joint 11 and drivingly connected to a ball screw 13, the ball screw 13 drivingly connected to an actuator main nut and a main control joint of the tail wing connected to the hinge joint 11, and a safety rod 14 built in the hollow space of the ball screw 13, the safety rod 14 including a backup force transmission pin shaft 141 for pivotally connecting the backup force transmission path tab 3 of the rear fuselage structure, wherein the joint assembly 1 further includes: a backup joint connecting rod 15 provided between the backup force transmission path tab 3 and the backup force transmission pin shaft 141, a first end 15a of the backup joint connecting rod 15 pivotally connected to the backup force transmission pin shaft 141, and a second end 15b of the backup joint connecting rod 15 extending from the first end 15a by a predetermined length in a first direction towards the backup force transmission path tab 3 and fixed with the backup force transmission path tab 3.

[0013] According to the above configuration, by adding the backup joint connecting rod 15, the position and installation direction of the fastener can be changed, the installation accessibility of the fastener on the backup force transmission path is improved, and the maintainability of the equipment is improved.

[0014] In the second example of the joint assembly, optionally including the first example, the backup force transmission path tab 3 of the rear fuselage structure is rotated by 90 degrees around the central axis in the first direction, and the second end 15b of the backup joint connecting rod 15 is rotated by 90 degrees around the central axis in the first direction relative to the first end 15a.

[0015] According to the above configuration, the installation convenience of the backup joint connecting rod 15 and the fastener of the backup force transmission path tab 3 on the aircraft can be achieved.

[0016] In the third example of the joint assembly, optionally including one or more of the first example and the second example, the second end 15b of the backup joint connecting rod 15 includes a blind hole sleeve 151, the blind hole sleeve 151 is shaped to fit the backup force transmission path tab 3. And the depth of the blind hole sleeve 151 is sufficient to accommodate a predetermined length of the backup force transmission path tab 3 to allow secure fixation with a fastener penetrating through the blind hole sleeve 151 and the backup force transmission path tab 3.

[0017] According to the above configuration, a fast and secure fixation can be achieved with a fastener penetrating through the blind hole sleeve 151 and the backup force transmission path tab 3.

[0018] In the fourth example of the joint assembly, optionally comprising one or more of the first to third examples, the joint assembly further comprises: the spare pin shaft 141 is replaced by the plug pin 142.

[0019] According to the above-mentioned configuration, the accessibility of the installation path of the plug pin 142 during off-machine installation can be achieved.

[0020] The joint assembly for the tail wing actuator of the present application provides connection between the spare pin shaft of the articulated universal joint and the spare force transmission path tab of the structure by adding a spare joint connecting rod and its connecting fastener.

[0021] In addition, rotating the spare joint connecting rod 15 by 90 degrees along the central axis of the first direction can further improve the installation convenience of the spare joint connecting rod 15 and the spare force transmission path tab 3 fastener during on-machine installation. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to describe the embodiments of the above and other features of the present application, a more particular description of the application briefly described above will be rendered by reference to specific embodiments thereof, which are illustrated in the appended drawings. It is to be understood that these drawings are only schematic and are non-limiting embodiments of the application, as the application can be embodied in various forms. The application will be described with the use of the drawings in which:

[0023] Figure 1 is a perspective view of the joint assembly according to the prior art in the installed state;

[0024] Figure 2 is a perspective view of the articulated universal joint of Figure 1 ;

[0025] Figure 3 is a perspective view of the joint assembly according to the embodiment of the present application in the installed state;

[0026] Figure 4 is a perspective view of the spare joint connecting rod of the joint assembly of Figure 3 , wherein the articulated universal joint of the joint assembly is rotated by a predetermined angle;

[0027] Figure 5 is a perspective view of the spare joint connecting rod of Figure 3 and the safety rod in pivotal connection;

[0028] Figure 6 is a perspective exploded view of the spare joint connecting rod of Figure 3 and the spare force transmission path tab in fixed connection.

[0029] The drawings are drawn to scale generally, however the dimensions in the drawings are merely illustrative and need not be strictly drawn to scale, but are intended to clarify the description. In other embodiments, other relative dimensions can be used.

[0030] In this and in the following, identical features appearing in different drawings are denoted by identical or similar reference numerals.

[0031] List of reference numerals:

[0032] 1 joint assembly

[0033] 11 knuckle joint

[0034] 111 connecting pin shaft

[0035] 112 main force transmission pin shaft

[0036] 12 motor gear transmission assembly

[0037] 121 connecting tab

[0038] 13 ball screw

[0039] 14 safety lever

[0040] 141 backup force transmission pin shaft

[0041] 142 insertion pin

[0042] 15 backup joint link

[0043] 15a first end

[0044] 15b second end

[0045] 151 blind hole sleeve

[0046] 2 main force transmission path tab

[0047] 3 backup force transmission path tab DETAILED DESCRIPTION

[0048] Firstly, the present utility model mainly relates to any manufacturing field related to joint assembly with backup force transmission path tab joint. The present utility model relates to a hinged joint assembly for a horizontal stabilizer trim actuator with main and backup force transmission path design.

[0049] The term "fixed" used herein is intended to describe a component connected to another component and capable of maintaining a position relative to each other, thus forces, torques, etc. can be transmitted from one component to another.

[0050] The "shape adaptation" in the context of the present application is intended to describe that the shape of at least a portion of one component can cooperate with the shape of at least a portion of another component, and the "shape adaptation" does not require complete shape correspondence, and can be partial shape correspondence, for example, one component is convex and can be received in a curved recess of another component, or a key of one component can be partially received in a slot of another component, as long as there is a force transmission path, no matter how many, within the scope of the present application.

[0051] Directional terms used herein, such as "top", "bottom", "upper", "lower", "inner", "inwardly", "outer", and "outwardly", are used to assist in describing the present application according to the orientation of the embodiments shown in the drawings. Unless otherwise specified, such as "horizontal direction", "gravity direction", etc., the directional terms are not absolute up, down, horizontal, vertical, etc., and should not be interpreted as limiting the present application to any particular direction.

[0052] The terms "comprise", "have", "contain" and variations thereof used herein are intended as open-ended transitional phrases, terms or words that require the presence of the specified component / steps, and also allow the presence of other components / steps.

[0053] In the present application, unless explicitly stated to the contrary, the terms "first", "second", etc. are not intended to represent any order, position, number or difference in importance, but are merely used as labels for distinguishing different positions, components, and are used to distinguish one element, component, region and / or position from another element, component, region and / or position.

[0054] In the present application, a plurality of different embodiments will be provided for the sealing assembly having the above structure, and the specific structure of each embodiment will be described in detail below with reference to the drawings.

[0055] First, refer to Figures 1 to 6 , a schematic description of the present application is provided. Among them, Figure 1 shows a perspective view of the joint assembly of the prior art in the installed state; Figure 2 shows a perspective view of the articulated universal joint of Figure 1 ; Figure 3 shows a perspective view of the joint assembly of the embodiment of the present application in the installed state; Figure 4 shows a perspective view of the spare joint link of the joint assembly of Figure 3 , wherein the articulated universal joint of the joint assembly rotates by a predetermined angle; Figure 5 shows a perspective exploded view of the spare joint link and the safety rod for pivotally connecting the spare joint link of Figure 3 ; Figure 6 shows a perspective view of the spare joint link and the safety rod for pivotally connecting the spare joint link of Figure 3A perspective exploded view of a spare joint connecting rod and a spare force transmission path ear piece.

[0056] A coordinate system is provided in the drawings for reference, the z-axis can be a vertical axis, the x-axis can be a transverse axis, and the y-axis can be a longitudinal axis. When referring to the direction, the positive direction can refer to the direction of the arrow of the y-axis, the x-axis and the z-axis, and the negative direction can refer to the opposite direction of the arrow of the y-axis, the x-axis and the z-axis.

[0057] Embodiment 1

[0058] In an embodiment of the utility model, the joint assembly 1 for the tail actuator generally includes a hinged universal joint 11, a motor gear transmission assembly 12, a ball screw 13, a safety rod 14 and a spare joint connecting rod 15.

[0059] The hinged universal joint 11 includes a main force transmission pin shaft 112, which is used for the pivotal connection of the main force transmission path ear piece 2 of the horizontal stabilizer of the rear fuselage structure.

[0060] The motor gear transmission assembly 12 is pivotally connected to the hinged universal joint 11 and drivingly connected to the ball screw 13.

[0061] The ball screw 13 is drivingly connected to the actuator main nut and the main control joint of the horizontal stabilizer of the tail.

[0062] The safety rod 14 is built in the hollow space of the ball screw 13, and the safety rod 14 includes a spare force transmission pin shaft 141, which is used for the pivotal connection of the spare force transmission path ear piece 3 of the horizontal stabilizer of the rear fuselage structure. The main force transmission pin shaft 112 and the spare force transmission pin shaft 141 are coaxial.

[0063] The spare joint connecting rod 15 is arranged between the spare force transmission path ear piece 3 and the spare force transmission pin shaft 141, the first end 15a of the spare joint connecting rod 15 is pivotally connected to the spare force transmission pin shaft 141, the second end 15b of the spare joint connecting rod 15 extends a predetermined length from the first end 15a along the positive direction of the z-axis and towards the spare force transmission path ear piece 3, and the second end 15b is fixed for the spare force transmission path ear piece 3.

[0064] By splitting the installation and disassembly of the complex horizontal stabilizer trim actuator spare hinge joint into two steps, step 1 realizes the connection of the spare joint connecting rod 15 and the horizontal stabilizer trim actuator spare hinge joint on the plane, and step 2 realizes the connection of the spare joint connecting rod 15 and the aircraft structure joint on the plane, the position and installation direction of the fastener can be changed, the installation accessibility of the fastener on the spare force transmission path is improved, and the maintainability of the equipment is improved.

[0065] It should be understood that the connector assembly 1 used herein is only one example, and this utility model is not limited thereto.

[0066] Example 2

[0067] In Embodiment 1, the spare connector rod 15 of the connector assembly 1 serves only as an extension of the spare force transmission path lug 3. However, the connector assembly 1 of this invention is not limited to this; the spare connector rod 15 can also provide a larger tool installation workspace.

[0068] In this embodiment 2, as Figure 3 As shown, in order to increase the accessibility of fastener installation, the spare force transmission path lug 3 of the horizontal stabilizer of the rear fuselage structure can be rotated 90 degrees about its central axis along the z-axis, and correspondingly, the second end 15b of the spare connector rod 15 can be rotated 90 degrees relative to the first end 15a about its central axis along the z-axis.

[0069] Therefore, before the actuator is installed onto the connector assembly 1, during the pre-installation process of the connector assembly 1, the angle of the hinged universal joint 11 can be adjusted to provide installation space for the spare connector link 15.

[0070] Better, such as Figure 4 , Figure 5 As shown, the spare force transmission pin 141 can be replaced by a pin 142, which enables the accessibility of the installation path of the pin 142 when it is installed off-machine.

[0071] Similarly, the mounting path for the pin 142 can be obtained by rotating the hinged universal joint 11 around the connecting pin 111. The pin 142 can be secured by multiple bolts, washers, and a fuse. The position of the mounting bolt holes for the pin 142 is changed relative to the spare force transmission pin 141, and the mounting path for the mounting bolts can also be obtained simultaneously after the hinged universal joint 11 is rotated around the connecting pin 111.

[0072] The connection between the spare connector rod 15 and the safety rod 14 will be described in detail below.

[0073] First, the ball bearing can be inserted into the lug hole of the spare connector rod 15. The bearing hole of the ball bearing should be kept coaxial with the lug hole of the spare connector rod 15. Furthermore, a bushing is placed inside the two lug holes of the safety rod 14, with the bushing base facing inwards, and the bushing hole coaxial with the lug hole of the safety rod 14.

[0074] Subsequently, the lugs of the spare connector rod 15 are inserted between the two bushings located in the lug holes on both sides of the safety rod 14. Furthermore, the position of the spare connector rod 15 is adjusted so that the bearing hole of the ball bearing is coaxial with the lug hole of the safety rod 14.

[0075] Again, the pin 142 is inserted in the coaxial direction to fix the relative position relationship between the backup joint link 15 and the safety bar 14. Then, two sets of bolts and washers are used to fasten the pin 142 and the lug of the safety bar 14. Finally, a cotter pin can be used to fix the bolts and nuts, preventing the bolts from rotating loose, and completing double insurance.

[0076] The fixing mode of the second end 15b and the backup force transmission path lug 3 is not limited, as long as it can be fixed to each other.

[0077] Preferably, as shown in Figure 4 The second end 15b of the backup joint link 15 can include a blind hole sleeve 151. The blind hole sleeve 151 is shaped to fit the backup force transmission path lug 3, so that it can be fixed by using a through fastener that penetrates the blind hole sleeve 151 and the backup force transmission path lug 3.

[0078] The depth of the blind hole sleeve 151 is sufficient to accommodate a predetermined length of the backup force transmission path lug 3, as shown in Figure 6 to allow it to be fixed by using a through fastener that penetrates the blind hole sleeve 151 and the backup force transmission path lug 3.

[0079] The connection between the backup joint link 15 and the backup force transmission path lug 3 will be described in detail below.

[0080] First, two nylon washers are attached to the fastener hole periphery of the blind hole sleeve 151 of the backup joint link 15 as support. In addition, two bushings are placed at the fastener hole, with the bushing base facing inward.

[0081] Subsequently, the backup joint link 15 is connected to the backup force transmission path lug 3 of the aircraft structure by adjusting the position of the actuator. In addition, the position of the backup joint link 15 is adjusted so that the fastener hole of the backup joint link 15 is coaxial with the fastener hole on the structural backup force transmission path lug 3.

[0082] Again, the bolts and 2 washers are installed in the coaxial direction and the nuts are tightened to fix the relative position relationship between the backup joint link 15 and the backup force transmission path lug 3. Finally, a cotter pin can be used to fix the bolts and nuts, preventing the bolts from rotating loose, and completing double insurance.

[0083] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme of the present application is described clearly and completely in combination with the specific embodiments and drawings of the present application.

[0084] It should be understood that the steps shown above in connection with the specific embodiments are illustrative in nature and that the skilled person can add or delete corresponding steps and can adjust the order of execution of one or some of the steps or replace one or more of the steps with analogous steps.

[0085] While various embodiments have been described above, it should be understood that they have been described in the context of, and are for the purpose of, a portion of embodiments of the application, and that they can be implemented in other specific forms without departing from the spirit and essential characteristics of the subject matter disclosed. It is to be understood that the subject matter that is disclosed is not limited in its application to the details set forth in the description contained and / or the examples cited, and that the subject matter is capable of other embodiments and of being practiced or carried out in various ways.

Claims

1. A connector assembly for a tail fin actuator, the connector assembly (1) comprising: The hinged universal joint (11) includes a main force transmission pin (112), which is used to pivotally connect the main force transmission path lug (2) of the rear fuselage structure. A motor gear drive assembly (12) is pivotally connected to the hinged universal joint (11) and drivably connected to the ball screw (13); A ball screw (13) is driven to be connected to the actuator main nut and the main control joint of the tail fin, the main control joint being connected to the articulated universal joint (11). The safety bar (14) is built into the hollow space of the ball screw (13). The safety bar (14) includes a spare force transmission pin (141), which is used to pivotally connect to the spare force transmission path lug (3) of the rear fuselage structure. The connector assembly (1) is characterized in that it further includes: A spare connector rod (15) is disposed between the spare force transmission path lug (3) and the spare force transmission pin (141). The first end (15a) of the spare connector rod (15) is pivotally connected to the spare force transmission pin (141). The second end (15b) of the spare connector rod (15) extends a predetermined length from the first end (15a) toward the spare force transmission path lug (3) in a first direction, and the second end (15b) is used to fix the spare force transmission path lug (3).

2. The connector assembly according to claim 1, characterized in that, The spare force transmission path lug (3) of the rear fuselage structure rotates 90 degrees around the central axis along the first direction, and The second end (15b) of the spare connector rod (15) is rotated 90 degrees relative to the first end (15a) about the central axis along the first direction.

3. The connector assembly according to claim 1, characterized in that, The second end (15b) of the spare connector rod (15) includes a blind hole sleeve (151) whose shape matches the spare force transmission path lug (3).

4. The connector assembly according to claim 1, characterized in that, The spare force transmission pin (141) is replaced by a pin (142).

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