Demonstrator for determining the forces applied by an aircraft engine on a support and including a three-point V-shackle
The three-point V-shaped shackle with instrumented sensors in the demonstrator addresses the challenge of precise force measurement between an aircraft engine and its support by providing distinct force paths and accurate sensor positioning.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- AIRBUS OPERATIONS (SAS)
- Filing Date
- 2024-12-16
- Publication Date
- 2026-06-19
AI Technical Summary
Existing demonstrators struggle to precisely determine the forces transmitted between an aircraft engine and its support due to the hyperstatic nature of the assembly, making it difficult to separate and measure forces accurately between different connection points.
A demonstrator using a three-point V-shaped shackle with instrumented sensors is employed, featuring distinct force paths and sensors positioned equidistantly to measure forces accurately between different connection points.
Enables precise measurement of forces along separate paths, allowing for more accurate determination of forces transmitted between the engine and support.
Smart Images
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Abstract
Description
Title of the invention: Demonstrator for determining the forces applied by an aircraft engine on a support and comprising a three-point V-shaped shackle
[0001] The present application relates to a demonstrator for determining the forces applied by an aircraft engine on an interface and comprising a three-point V-shackle.
[0002] According to an embodiment visible in figures 1 and 2, an aircraft 10 comprises several propulsion units 12 which are positioned under the wing 14 of the aircraft 10.
[0003] A propulsion assembly 12 includes a motor 16, a nacelle (not shown in [Fig.2]) positioned around the motor 16 and a mast 18 connecting the motor 16 to the rest of the aircraft 10, in particular to the wing 14.
[0004] For the remainder of this description, a longitudinal direction X is parallel to the axis of rotation A16 of the motor 16. A transverse plane is a plane perpendicular to the axis of rotation A16 of the motor 16. A horizontal transverse direction Y is a direction perpendicular to the axis of rotation A16 of the motor 16 and horizontal. A vertical transverse direction Z is a direction perpendicular to the axis of rotation A16 of the motor 16 and vertical. A vertical median plane PMV (visible in [Fig. 3]) is a vertical plane containing the axis of rotation A16 of the motor 16.
[0005] The engine 16 includes a fan 20 which comprises a fan housing 20.1 and a reactor core 22 comprising a front part 22.1 positioned inside the fan 20, a central part 22.2 and a rear part 22.3 including in particular a nozzle.
[0006] The mast 18 includes a primary structure 24, in the form of a box, which is connected to the sail 14 by a sail attachment system 26 and to the motor 16 by a motor attachment system 28.1, 28.2, 28.3. This primary structure 24 includes a front end 24.1, a middle part 24.2 and a rear end 24.3.
[0007] According to a configuration visible in [Fig.2], the engine attachment system comprises a front attachment 28.1 connecting the front end 24.1 of the primary structure 24 and the front and / or central part 22.1, 22.2 of the reactor core 22, a rear attachment 28.2 connecting the rear end 24.3 and / or the middle part 24.2 of the primary structure 24 and the rear part 22.3 of the reactor core 22, as well as two connecting rods 28.3, positioned symmetrically with respect to the vertical median plane PMV of the engine 16, connecting the primary structure 24 and the forward and / or central part 22.1, 22.2 of the reactor core 22.
[0008] Alternatively, the front attachment 28.1 could connect the front end 24.1 of the primary structure 24 and the blower housing 20.1 of the blower 20.
[0009] According to one embodiment, the rear attachment 28.2 is configured to absorb forces in the horizontal and vertical transverse directions Y, Z, as well as a torque around the drive shaft A16. It comprises: a. a transverse beam 30 integral with the primary structure 24, b. at least one first two-point shackle 32, positioned from a first side of the vertical median plane PMV, connected to the transverse beam 30 by a first connecting axis 32.1 and to the motorization 16 by a second connecting axis 32.2, c. at least one second three-point shackle 34, positioned on a second side of the vertical median plane PMV, connected to the motorization 16 by a third connecting axis 34.1 and to the cross beam 30 by fourth and fifth connecting axes 34.2, 34.3.
[0010] The different connecting axes 32.1, 32.2, 34.1, 34.2, 34.3 are substantially parallel to each other and to the longitudinal direction X.
[0011] According to this embodiment, the first two-point shackle 32 is configured to ensure the transfer of forces in an approximately vertical direction. In addition, the second three-point shackle 34 is configured to ensure the transfer of forces in the horizontal and vertical transverse directions Y, Z.
[0012] According to one embodiment, the motor attachment system includes at least one fail-safe type safety link 36, connecting the cross beam 30 and the motor 16.
[0013] The three-point shackle 34 has an approximately triangular contour comprising three holes positioned at the vertices of the triangular shape.
[0014] A demonstrator for determining the forces applied by an aircraft engine on a support (such as a primary structure for example) includes an interface linking the engine and the support, substantially identical to a rear attachment of an aircraft propulsion assembly, which includes a three-point shackle 38 visible in [Fig.4].
[0015] According to one arrangement, the three-point shackle 38 comprises a first through-hole 38.1 configured to house a first connecting shaft A38.1 linking the three-point shackle 38 and the drive unit 16, as well as second and third holes 38.2, 38.3 configured to house second and third connecting shafts A38.2, A38.3 linking the three-point shackle 38 and the support. This three-point shackle 38 allows the transfer of forces oriented along the horizontal transverse directions and vertical Y and Z from the first connection axis A38.1 to the second and third connection axes A38.2, A38.3.
[0016] This three-point shackle 38 is instrumented and includes sensors, such as strain gauges for example, to determine the forces (or stresses) transmitted from the first connecting axis A38.1 to the second and third connecting axes A38.2, A38.3.
[0017] Since this assembly is hyperstatic, it is difficult to determine precisely and separately the forces transmitted between the first connecting axis A38.1 and the second connecting axis A38.2 and, on the other hand, those transmitted between the first connecting axis A38.1 and the third connecting axis A38.3.
[0018] The present invention aims to remedy all or part of the drawbacks of the prior art.
[0019] To this end, the invention relates to a demonstrator, enabling the simulation of forces transmitted between an aircraft engine and a support, comprising an attachment system which connects the engine and the support and includes at least one three-point shackle connected to the engine by a first connecting axis and to the crossbeam by second and third connecting axes, the three-point shackle having first, second and third through holes configured to house respectively the first, second and third connecting axes.
[0020] According to the invention, the three-point shackle has a V-shape and comprises a first arm extending between first and second ends, the first and second through holes being positioned respectively near the first and second ends of the first arm, and a second arm extending between first and second ends, the first and third through holes being positioned near the first and second ends of the second arm. In addition, the three-point shackle comprises at least first and second sensors positioned respectively at the first and second arms and configured to determine forces and / or stresses.
[0021] Providing a three-point V-shaped shackle allows for the generation of dissociated first and second force paths and for obtaining more precise force measurements on the one hand between the first and second through holes and, on the other hand, between the first and third through holes.
[0022] According to another feature, the second branch comprises a first segment common with the first branch and a second segment extending from the first segment to the second end, the first branch having a thickness greater than the second segment of the second branch.
[0023] According to another feature, the second branch comprises first and second faces substantially centered between first and second faces of the first branch.
[0024] According to another feature, the first or second sensor is positioned approximately equidistant from the first and second or third through orifices.
[0025] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:
[0026] [Fig-1] is a perspective view of an aircraft,
[0027] [Fig.2] is a schematic representation of an aircraft propulsion system (without a gondola) illustrating a method of realization of the earlier art,
[0028] [Fig.3] is a perspective view of a rear attachment of a propulsion assembly illustrating a method of realizing earlier art,
[0029] [Fig.4] is a perspective view of a three-point shackle from a demonstrator determining the forces between a motor and a support illustrating a prior art embodiment
[0030] [Fig.5] is a perspective view of a force determination demonstrator between a motor and a support illustrating an embodiment of the invention,
[0031] [Fig.6] is a perspective view of a three-point shackle of the demonstrator visible in [Fig. 5],
[0032] [Fig.7] is a schematic representation of the three-point shackle, visible on the [Fig.6], showing the different paths of effort as a function of the forces applied at the level of a first axis of connection.
[0033] According to an embodiment visible on 5, a demonstrator 40 allowing the simulation of forces transmitted between an aircraft engine 42 and a support 44, such as a primary structure of an aircraft mast for example, includes an attachment system 46, connecting the engine 42 and the support 44, configured to ensure a transfer of forces between the engine 42 and the support 44 along horizontal and vertical transverse directions Y, Z located in a plane perpendicular to a longitudinal direction X (parallel to the axis of the engine 42).
[0034] This fastening system 46 comprises: a. a transverse beam 48 attached to the support 44, b. at least one first two-point shackle 50, positioned on a first side of the vertical median plane PMV, connected to the transverse beam 48 by a first connecting axis 50.1 and to the motor 42 by a second connecting axis 50.2, c. at least one second three-point shackle 52, positioned on a second side of the vertical median plane PMV, connected to the motorization 42 by a first connecting axis 52.1 and to the cross beam 48 by second and third connecting axes 52.2, 52.3.
[0035] The different connecting axes 50.1, 50.2, 52.1, 52.2, 52.3 are substantially parallel to each other and to the longitudinal direction X.
[0036] With the exception of the three-point shackle 52, the other elements of the demonstrator may be identical to those of a prior art demonstrator.
[0037] The second three-point shackle 52 is configured to ensure a transfer of forces along the horizontal and vertical transverse directions Y, Z between the motor 42 and the support 44.
[0038] This three-point shackle 52 includes first, second and third through holes 54.1, 54.2, 54.3 configured to house respectively the first, second and third connecting axes 52.1, 52.2, 52.3. These through holes 54.1, 54.2, 54.3 are located at each of the vertices of a triangle.
[0039] Each of the first, second, and third connecting axes 52.1, 52.2, 52.3 forms with the three-point shackle 52 a joint comprising at least one pivot axis. In one configuration, each of the joints comprises a ball bearing interposed between the first, second, or third connecting axis 52.1, 52.2, 52.3 and the three-point shackle 52.
[0040] According to a particular feature of the invention, the three-point shackle 52 has a V-shape and comprises a first arm 56 extending between first and second ends 56.1, 56.2, the first and second through-holes 54.1, 54.2 being respectively positioned near the first and second ends 56.1, 56.2, and a second arm 58 extending between first and second ends 58.1, 58.2, the first and third through-holes 54.1, 54.3 being positioned near the first and second ends 58.1, 58.2, the first ends 56.1, 58.1 of the first and second arms 56, 58 coinciding and forming a common area of the first and second arms 56, 58. The first through-hole 54.1 is located at the level of the common area of the first and second branches 56, 58.
[0041] The second branch 58 includes a first segment Tl common with the first branch 56 and a second segment T2 which extends from the first segment Tl to the second end 58.2.
[0042] In operation, as illustrated in [Fig.7], the three-point shackle 52 defines a first force path 60.1 between the first and second through holes 54.1, 54.2 at the level of the first arm 56 as well as a second force path 60.2 between the first and third through orifices 54.1, 54.3 at the level of the second branch 58.
[0043] Each branch 56, 58 has a first face F56, F58 located approximately perpendicular to the longitudinal direction X and a second face F56', F58' substantially parallel to the first face F56, F58.
[0044] According to one configuration, the first branch 56 has a thickness greater than the second section T2 of the second branch 58. The first and second faces F58, F58' of the second branch 58 are substantially centered between the first and second faces F56, F56' of the first branch 56.
[0045] The three-point shackle 52 is instrumented and includes at least first and second sensors 62.1, 62.2, such as strain gauges for example, positioned respectively at the first and second arms 56, 58 and the first and second force paths 60.1, 60.2 and configured to determine forces and / or stresses transmitted from the first connecting axis 52.1 to the second and third connecting axes 52.2, 52.3. Thus, the first arm 56 includes at least one first sensor 62.1 and the second arm 58 includes at least one second sensor 62.2.
[0046] According to one arrangement, the first sensor 62.1 is positioned approximately equidistant from the first and second through orifices 54.1, 54.2. The second sensor 62.2 is positioned approximately equidistant from the first and third through orifices 54.1, 54.3.
[0047] Providing a three-point shackle 52 in V allows the first and second paths of forces 60.1, 60.2 to be separated and the forces to be measured precisely on the one hand from the first through orifice 54.1 to the second through orifice 54.2 and, on the other hand, from the first through orifice 54.1 to the third through orifice 54.3.
[0048] As illustrated in [Fig.7], when the forces are oriented substantially parallel to the transverse and vertical direction Z as illustrated in parts (A) and (B), the forces essentially pass through the first branch 56, which defines the first force path 60.1, and are measured by the first sensor 62.1. When the forces are oriented substantially parallel to the transverse and horizontal direction Y as illustrated in parts (C) and (D), the forces essentially pass through the second branch 58, which defines the second force path 60.2, and are measured by the second sensor 62.2.
Claims
Demands
1. Demonstrator (40) for simulating forces transmitted between an aircraft engine (42) and a support (44), comprising an attachment system (46) which connects the engine (42) and the support (44) and includes at least one three-point shackle (52) connected to the engine (42) by a first connecting axis (52.1) and to the crossbeam (48) by second and third connecting axes (52.2, 52.3), the three-point shackle (52) having first, second and third through holes (54.1, 54.2, 54.3) configured to house the first, second and third connecting axes (52.1, 52.2, 52.3) respectively; characterized in that the three-point shackle (52) has a V-shape and includes a first arm (56) extending between first and second ends (56.1, 56.2), the first and second through holes (54.1, 54.2) being respectively positioned near the first and second ends (56.1, 56.2) of the first arm (56), and a second arm (58) extending between first and second ends (58.1, 58.2), the first and third through holes (54.1, 54.3) being positioned near the first and second ends (58.1, 58.2) of the second arm (58), the three-point shackle (52) comprising at least first and second sensors (62.1, 62.2) positioned respectively at the first and second arms (56, 58) and configured to determine forces and / or stresses.
2. Demonstrator according to the preceding claim, characterized in that the second branch (58) comprises a first section (T1) common with the first branch (56) and a second section (T2) extending from the first section (T1) to the second end (58.2), the first branch (56) having a thickness greater than the second section (T2) of the second branch (58).
3. Demonstrator according to the preceding claim, characterized in that the second branch (58) comprises first and second faces (F58, F58') substantially centered between first and second faces (F56, F56') of the first branch (56).
4. Demonstrator according to any one of the preceding claims, characterized in that the first or second sensor (62.1, 62.2) is positioned approximately equidistant from the first and second or third through holes (54.1, 54.2, 54.3).