Patent Application
20230150652
This application claims priority to European Patent Application No. 21275158.0 filed Nov. 16, 2021, the entire contents of which is incorporated herein by reference.
The present disclosure is concerned with means for mounting or attaching a rotary actuator to a wing assembly of an aircraft.
Modern aircraft include a number of movable surface or panels such as flight control surface of wing tips that are configured to be movable relative to another part of the aircraft e.g. to another, fixed or stationary part of a wing. The movable parts are typically moved relative to the stationary part by means of an actuator. In applications where it is important to minimise weight and size of parts on an aircraft, rotary actuators are used comprising a fixed stator part and a movable rotor part. Rotary geared actuators (RGAs) have been developed in which the input and the output are linked by a series of gears to step down high speed, low torque rotation to provide slower speed, high torque positioning of a movable part. These actuators are typically positioned along the hinge line between a stationary part of the structure e.g. wing, and a relatively rotatable part. The RGA has so called earth members for fixing the actuator to one of the parts and output members for attachment to the other part. Typically, the earth members are attached to the stationary part of the structure and are mounted via flanges and bolts. The output members are then attached to the movable part also by known attachment means such as bolts or the like.
The attachment lugs and mounts required to attach the earth members to the wing structure and to attach the output members to the moveable part (or vice versa) add to the overall size and weight of the actuator assembly and the envelope required to accommodate the assembly. Where space and weight allowance is limited. Such as in aircraft, there is a desire to reduce the size and weight of mounting/attachment components whilst maintaining the required secure attachment.
In addition, attaching an RGA to the structure is generally time and labour intensive and as each lug/fixing mechanism needs to be fastened securely by hand, there is a risk of human error each time.
Furthermore, each attachment point where a lug or the like is fastened to the structure, is subject to loads that cause local stresses particularly during flight and during operation that can loosen or damage the fastening.
There is, therefore, a need for an improved way of securing an RGA to a structure whilst maintaining secure attachment.
According to the present disclosure, there is provided a rotary actuator assembly for moving a first relatively movable part relative to a second relatively movable part, the assembly comprising a rotary actuator having a plurality of circumferential earth members for attachment to one of the first and the second relatively movable parts and a plurality of circumferential output members for attachment to the other of the first and second relatively movable parts, and wherein at least the plurality of circumferential earth members or the plurality of circumferential output members is provided with radially outwardly extending locking features e.g. splines around their circumference configured to be received in a mounting sleeve having complementary splines to engage with the radially extending splines.
In some examples, both the plurality of circumferential earth members and the plurality of circumferential output members are provided with such radially extending splines.
In another aspect, there is provided a mounting assembly comprising a rotary actuator assembly as described above and a mounting sleeve having a plurality of radially inwardly extending circumferential splines positioned along the length of the sleeve so as to engage with the radially outwardly extending splines of the rotary actuator assembly when inserted in the mounting sleeve.
The rotary actuator extends axially along an axis A defined by the shaft 3 and the gears, earth members 12 and rotor 11 are arranged around the axis such that the rotor rotates about the axis. The earth members 12 are annular or circumferential rings mounted around the shaft 3 and several earth members 12 may be positioned around the actuator spaced apart in the axial direction. The number of earth members can be selected according to the use and design requirements of the actuator.
In a conventional arrangement, the actuator is mounted to the first relatively moveable part 1 via earth members 12 on the actuator. The earth members around the body of the actuator are secured to the wing part 1 in any known way by a fixed fastener such as a bolt attached to the earth member by an external housing (not shown). In the example shown, the earth members 12 are formed with radially extending lugs 22 with a hole therethrough. The lugs fit into attachment mounts 23 provided on the relatively movable part 1 which also have holes therethrough. The earth members are secured in positioned by passing a bolt 24 through the holes in the attachment mounts and the lugs. Each earth member may be provided with several lugs (two are shown for each earth member in the example of
Outlet members 110 are mounted around, and rotate with the rotor 11. The outlet members 110 may be provided at locations along the length of the actuator between earth members 12 but, again, the number and spacing of the outlet members will depend on specific design requirements. The outlet members 110 are arranged to be attached to the other of the relatively movable parts 2. As with the earth members 12, typically, the outlet members are provided with lugs 112 with holes therethrough which fit between mounting attachments 114 affixed to the second relatively movable part and one or more bolts 116 is passed through the matched-up holes to secure the outlet members to the relatively movable part. The bolts 116 can be secured by fasteners 116 either at each lug location or a single bolt passes through all lugs and is secured at its ends.
In this way, the earth members, which do not rotate with the actuator rotor, are fixed to one part of, say, the wing, and the relatively rotatable output members, that rotate with the actuator rotor 11, are attached to move the other part of the wing to rotate it relative to the first part.
As mentioned above, and as can be seen from
In the assembly according to this disclosure, an example of which is shown in
The general structure and function of the rotary actuator according to the disclosure is as described above and will not be described again herein. The difference lies in the way the actuator 100 is attached to the relatively moveable parts e.g. the wing parts.
Instead of the earth members having lugs, the earth members 1120 of the disclosure are provided with radially extending locking features e.g. splines 1121 around the circumference of the annular ring forming the earth member, the splines extending radially outwards. The splines 1121 are configured to engage with complementary splines (not shown) extending inwardly from a socket or sleeve (not shown) formed on the first relatively movable part e.g. the fixed wing part. Instead of splines, the locking features may take other forms that engage to provide the desired locking between the earth members and the receiving sleeve.
Similarly, the output members 1140 may be provided with similar splines 1141 around their circumference with will engage with complementary splines formed in a sleeve part provided on the other relatively movable part e.g. a movable wing panel.
In the example shown, all of the earth members 1120 and the output members 1140 are provided with splines. In other examples, though, it may be that only some of the earth members and/or output members are provided with splines. For example, only the earth members might have a spline fitting with one wing part, while the output members have a conventional lug/mount fitting, or vice versa.
A sleeve for receiving the actuator will be defined by sleeve parts formed on or attached to the adjacent edges of the relatively movable parts i.e. the resulting sleeve formed by the sleeve parts will define the hinge between the two parts and will have inwardly extending splines. The actuator can then be pushed into the sleeve for assembly such that the splines on the earth members 1120 will engage with splines of the sleeve part attached to a fixed structure part and the splines on the output members will engage with splines on the other part of the sleeve that is affixed to the other part.
Once inserted in the sleeve, the actuator can be locked axially in position by any suitable means e.g. bolts, locking rings, caps etc.
Attaching the actuator to the relatively movable parts in this way allows the actuator to be easily mounted but ensures a secure attachment and reliable rotation operation. The fastening components have reduced size and weight compared to known mounting assemblies and spread the stress locations around the rings rather than providing single stress points at the lugs.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 21275158.0 | Nov 2021 | WO | international |
