A connection assembly

Abstract

The present invention relates to a fuselage (2) located on an aircraft, at least one housing (3) located as a cavity on the fuselage (2), at least one piece of equipment (4) that performs a function specified by the manufacturer, at least one pin (5) extending outwardly through the equipment (4) and at least partially inserted in the housing (3), allowing the equipment (4) to be removably attached to the fuselage (2), at least one fixing part (6) positioned in the housing (3) and allowing the equipment (4) to be mounted on the fuselage (2)

Description

[0001] A CONNECTION ASSEMBLY

[0002] This invention relates to fastening devices for mounting engines that provide thrust to aircraft.

[0003] The engine fuselage connection used in jet aircraft is usually made from three points. One point carries the thrust and maneuvering forces, another point carries the traction force and another point carries the forces caused by the rotation of the engine. When the engine is attached to the airframe via additional pieces, it causes stress accumulation and / or stress concentration in the aforementioned area, which shortens the life of the structural parts and fasteners and causes them to wear.

[0004] In the Spanish patent document numbered ES2895276T3, which is included in the state of the art, the engine mounting method in modular airplanes is mentioned. In the document, it is mentioned that the engine is fixed to the frame structure in the aircraft by means of a pin. It is mentioned that the bracket in the document acts as a clamp by applying force to the engine connection pin. In addition, the document mentions the weight that is fixed to the frame structure and provides damping of the force on the engine.

[0005] The present invention provides an engine mounting assembly that provides effective stress distribution in the engine-aircraft connection.

[0006] Another object of the present invention is to eliminate the notch effect at the point where the load is transferred by the engine, thereby extending the life of the part and shortening the assembly & damage detection time.

[0007] The connection assembly defined in the first claim and the claims dependent on this claim, which is realized to achieve the purpose of the invention, comprises a fuselage on the aircraft, preferably having a frame structure. There is a housing on the fuselage in the form of an opening or a cavity. The housing is formed by the machining process during the manufacturing of the fuselage. There is equipment, which is the payload that is fixed to the fuselage and performs the function specified by the manufacturer. On the equipment there is a pin which is a shaft. The surfaces specified by the manufacturer are placed in the housing, allowing the equipment to be mounted on the fuselage. The fixing part is placed in the housing and the equipment is mounted on the fuselage. The inventive connection assembly comprises a housing which is form-fitting with the fixing part. The housing has a larger volume than the fixing part, in which the fixing part is able to rotate in a single-point pivoting center. If the fuselage is a frame structure, the housing has at least partially the same volume as the fixing part and the fixing part can pivot with a singlepoint center of rotation. The fixing part rotates in the housing with a single-point support with the center of rotation at the point specified by the manufacturer. When the equipment is mounted on the fuselage, the area of the pin specified by the manufacturer remains in the housing. By placing the pin in the housing in the fuselage, it is ensured that the equipment is mounted in the fuselage without protruding out of the fuselage. The fixing part provides easier and faster alignment of the pin.

[0008] In one embodiment of the invention, the connection assembly comprises a mounting surface which forms a surface of the housing within the housing. The mounting surface forms the surface of the housing which is opposed to the direction of rotation when the fixing part is rotated in a single-point support while the equipment is attached to the housing. Extending outward from the fuselage in such a way that it is almost completely inside the housing is the lug, which is hollow and hollow inside and which allows the fixing part to be supported on it. On the fixing part, there is a hollow hole with a hollow form on the surface determined by the manufacturer, which is formed by machining during the manufacturing phase, and it is intertwined with the lug, allowing the fixing part to make a rotational movement in the housing with a single point movement. The lug and the hole are form-matched with each other and are almost completely counterbalanced by the user when the equipment is mounted to the fuselage. The fastener passes through the reciprocating hole and lug and ensures that the fastener is supported in the housing.

[0009] In one embodiment of the invention, the connection assembly comprises a fastener mounted in a hole and a lug which are opposed by the user when the equipment is mounted to the housing, and the fastener is moved in the housing from the center of rotation so that the lug is the center of rotation. The fixing part is preferably a clamp, and by means of a concave structure in the center of the fixing part, the pin is almost completely surrounded and the pin is at least partially secured in the housing.

[0010] In one embodiment of the invention, the fastening arrangement comprises a first opening, which is formed by hollowing out the housing during manufacturing of the housing, and which is hollow and at least partially opposed to a region of the housing. The pin is located almost entirely within the first opening and is surrounded by the fastening part, the concave structure in the center of the fastening part and the first opening together forms a channel. In the channel formed by the concave geometry in the center of the fixing part and the first opening, the bearing element is inserted and the pin is inserted in the bearing element for easy installation of the pin in the channel. The first opening is at least partially semicircular and, when the equipment is mounted in the fuselage, the fixing part is moved in a single-point bearing, contacting the mounting surface and allowing a channel to be formed in the fuselage. The fixing part is connected to the fuselage by means of a bearing element and acts as a structural element in case of reverse loading. In this way, the thrust load from the equipment is transferred directly to the fuselage and the stress level on the fuselage is reduced to achieve optimum stress levels.

[0011] In one embodiment of the invention, the connection assembly comprises a connection part positioned on the other side of the fuselage opposite to the side on which the equipment is installed. The connecting part reacts in response to the moment applied by the equipment to the fuselage and allows stress distribution on the fuselage by absorbing the moment. The form and mass of the fitting is determined by the manufacturer in accordance with the analysis and transfers to the fuselage the forces exerted by the equipment on the fuselage.

[0012] In one embodiment of the invention, the connection assembly comprises a connector for mounting the connector to the fuselage. The connectors are located between the fitting and the fuselage and are positioned on the surface of the fitting facing the fuselage and on the surface of the fuselage facing the fitting.

[0013] In one embodiment of the invention, the connection assembly comprises a fixing part which is a C-shaped clamp. One end of the C-shaped fixing part is provided with a hole and is threaded into the lug and supported in the housing by means of the fastener. The other end of the fixing part is moved so that the lug is the center of rotation and contacts the mounting surface and is mounted on the mounting surface by means of the fastener. In this way, the bearing element and the pin, which are placed in the channel formed by the fixing part and the first opening, are fixed in the channel. The channel formed by the fixing part and the first opening is formfitting with the bearing element and the pin.

[0014] In one embodiment of the invention, the fastening assembly comprises a fastener which is threaded into the lug and the hole by the user and which enables the fastener to be secured in the housing by the user interlocking the lug and the hole in a form-fitting manner.

[0015] In one embodiment of the invention, the connection assembly comprises a second aperture which is hollow in the connection part. The second aperture is formed by machining when the fitting is manufactured. The second aperture forms a channel in the connection part and is opposed to the channel formed by moving the fixing part from the center of rotation, contacting and mounting it on the mounting surface and opposing it to the first opening, and together they form an integrated and single channel. The second aperture and the channel formed by the fixing part and the first opening are located one after the other and opposite each other, through which the bearing element and pin are passed.

[0016] In one embodiment of the invention, the connection assembly comprises a cover disposed on the attachment part so as to cover the surface of the second opening furthest from the fuselage and to act as a bearing member and pin stop when the equipment is attached to the fuselage. The cover is provided with a protrusion at its end, the protrusion allowing the cover to be moved by the user.

[0017] In one embodiment of the invention, the connection assembly comprises a bushing disposed in a channel formed by a user movement of the fixing part to close the first opening. The bushing contacts the lateral walls of the housing in the channel. A pin is inserted into the bushing by means of a bearing element. The bushing ensures that the bearing element is almost completely fixed in the channel formed by the fixing part and the first opening.

[0018] In one embodiment of the invention, the connection assembly comprises a cylindrical bushing forming a cylindrical portion extending along the length of the bushing. A flange is provided on the cylindrical bushing in geometrical form in accordance with the cylindrical bushing. The flange contacts the housing, absorbing the force exerted by the equipment on the housing and ensuring that the bearing element remains stationary in the groove.

[0019] In one embodiment of the invention, the fastening arrangement preferably comprises a bushing which surrounds the bearing element and which is disposed in the channel formed by the concave surface of the fastening element and the first opening when the fastening element closes the first opening. One of the bushings is inserted into the channel from the equipment installed side of the housing, while the other bushing is inserted into the channel from the other side of the housing and the bushings are mutually opposed to each other. The bushings are press-fitted into the channel. The flange extending from one of the bushings contacts the fuselage from the equipment-mounted side of the fuselage, closing the channel from the outside, while the flange extending from the other bushing contacts the fuselage from the other side of the fuselage, closing the channel from the outside. In this way, in the channel formed by the fixing part and the first opening, the bearing element provides resistance to the loads transferred from the two opposite sides of the fuselage and is immobilized and fixed. The two bushings are made of different materials in order to reduce the fuselage's exposure to drag. Thus, by renewing the bushings, the flight life of the airframe is extended.

[0020] In one embodiment of the invention, the attachment arrangement comprises equipment, preferably a jet engine, positioned on the aircraft and providing the propulsion necessary for flight of the aircraft.

[0021] In one embodiment of the invention, the connection assembly comprises a fuselage having a frame structure, which is an aircraft fuselage.

[0022] The connection arrangement for achieving the object of the present invention is shown in the accompanying figures;

[0023] Figure 1 - Front view of the equipment and pin.

[0024] Figure 2 - Exploded view of the connection assembly.

[0025] Figure 3 - Perspective view of the equipment, fuselage and connection part.

[0026] Figure 4 - Top view of connection part and fuselage.

[0027] The parts in the figures are numbered one by one and the corresponding numbers are given below.

[0028] 1. Connection assembly

[0029] 2. Fuselage

[0030] 201. Mounting surface

[0031] 3. Housing

[0032] 4. Equipment

[0033] 5. Pin

[0034] 6. Fixing part

[0035] 7. Lug

[0036] 8. Hole

[0037] 9. Fastener

[0038] 10. First opening

[0039] 11. Bearing element

[0040] 12. Connection part

[0041] 1201. Second opening

[0042] 1202. Cover

[0043] 13. Bushing 1301. Cylindrical bushing

[0044] 1302. Flange

[0045] (F) Connector

[0046] A connection assembly (1) comprises a fuselage (2) located on an aircraft, at least one housing (3) located as a cavity on the fuselage (2), at least one piece of equipment (4) that performs a function specified by the manufacturer, at least one pin (5) extending outwardly through the equipment (4) and at least partially inserted in the housing (3), allowing the equipment (4) to be removably attached to the fuselage (2), at least one fixing part (6) positioned in the housing (3) and allowing the equipment (4) to be mounted on the fuselage (2).

[0047] The inventive connection assembly (1) comprises the housing (3) form-fitting with the fixing part (6), into which the fixing part (6) is supported at one point and into which the fixing part (6) is mounted at least at another point, which allows the pin (5) passing at least partially through it to be fixed by means of the fixing part (6), so that the fixing part (6) fixes the equipment (4) in the fuselage (2) almost completely within the fuselage (2). (Figure 1)

[0048] There is a fuselage (2), which is the main frame of the aircraft. There is a housing (3) on the fuselage (2), which is hollowed out during the manufacturing of the fuselage (2). On the fuselage (2), there is equipment (4) that can be positioned through the housing (3). Extending outwardly from the equipment (4) is a pin (5) of the volume and form specified by the manufacturer, the volume specified by the manufacturer being at least partially inserted into the housing (3). A fixing part (6) is positioned in the housing (3) and allows the equipment (4) to be mounted on the fuselage (2).

[0049] The housing (3) is form-fitting with the fixing part (6) and the fixing part (6) can move in the housing (3) in such a way that it is supported at a single point. The fixing part (6) is fixed to the fuselage (2) in the housing (3) at a point different from the point where it is supported. A pin (5) is at least partially positioned in the housing (3) and allows the equipment (4) to be mounted on the fuselage (2).

[0050] In one embodiment of the invention, the connection assembly (1) comprises at least one mounting surface (201) forming the surface of the fuselage (2) in the housing (3) opposite the fixing part (6), at least one lug (7) in the housing (3), extending outwardly from the mounting surface (201), having a hollow form and allowing the fixing part (6) to be rotatably located thereon, The fixing part (6) comprises at least one hole (8) which is located as an opening on the fixing part (6) and which is form compatible with the lug (7), and at least one fastener (9) which enables the fixing part (6) to be mounted to the fuselage (2) in the housing (3) by passing through the lug (7) and the hole (8) located coaxially. In this way, when the equipment (4) is mounted in the fuselage (2), the fixing part (6) is moved by the user so that the pin (5) is at least partially enclosed by the concave surface of the fixing part (6), which is at least partially at its midpoint. (Figure - 2)

[0051] In one embodiment of the invention, the connection assembly (1) comprises a fixing part (6) which is fixed to the lug (7) by means of a fastener (9) through the hole (8) and is moved by the user around the lug (7), thereby allowing the equipment (4) to be mounted on the fuselage (2). In this way, the forces acting on the fuselage (2) of the equipment (4) are effectively distributed.

[0052] In one embodiment of the invention, the connection assembly (1) comprises at least one first opening (10), at least partially perpendicular to the direction in which the fuselage (2) extends along its length, at least one first opening (10) recessed in the fuselage (2) and opposed to the housing (3), at least one bearing element (11) at least partially disposed in the first opening (10) and disposed in the channel formed in the fuselage (2) by being surrounded by the fixing part (6), into which the pin (5) is inserted to secure the equipment (4) to the fuselage (2). The convex surface forming almost completely the central region of the fixing part (6) closes the first opening (10) and together with the bearing element (11) forms a form-fitting channel. (Figure - 2)

[0053] In one embodiment of the invention, the connection assembly (1) comprises at least one connection part (12) on the opposite side of the fuselage (2) from the side on which the equipment (4) is installed and which provides resistance to the moment generated by the equipment (4) on the fuselage (2). The connection part (12) creates a counter bending moment by forming a weight against the bending moment caused by the force of the equipment (4) on the fuselage (2) and has the geometry to meet the force of the equipment (4) on the fuselage (2) at the value determined by the manufacturer. (Figure - 3, Figure - 4)

[0054] In one embodiment of the invention, the connection assembly (1) comprises at least one connector (F) for mounting the connection part (12) to the fuselage (2). The connector (F) is positioned at user-specified locations on the connection part (12) to provide moment control in response to a force acting on the fuselage (2) of the equipment (4).

[0055] In one embodiment of the invention, the connection assembly (1) comprises a fixing part (6), which is a clamp of substantially C-shaped form, one end of which is supported on the hole (8) by means of a fastener (9) to the lug (7), the other end of which is pivoted around the lug (7) and mounted on the mounting surface (201) by means of a connector (F), the first opening (10) being substantially completely closed, allowing a channel to be formed in the fuselage (2). By moving the fixing part (6) so that the pin (5) is mounted in the channel formed by moving the pin (5) with the center of rotation of the lug (7), the pin (5) is easily aligned by the user and provides convenience in assembly / disassembly operations.

[0056] In one embodiment of the invention, the connection assembly (1) comprises a fastener (9) for securing the fixing part (6) to the fuselage (2) in the housing (3) by passing the fixing part (6) through the lug (7) and the hole (8) so that the lug (7) and the hole (8) are form-fitting and intertwined with each other. This allows the movement of the fixing part (6) only to close the first opening (10) and prevents it from moving out of the housing (3).

[0057] In one embodiment of the invention, the connection assembly (1) comprises at least one second opening (1201) in which a bearing element (11) is inserted, which is located one after the other and which is opposite to the channel formed by the fixing part (6) closing the first opening (10), which is hollow in the connection part (12). There is no gap between the formed channel and the second aperture (1201) and when the equipment (4) is mounted to the fuselage (2), the pin (5) is first passed through the channel into the second aperture (1201). The formed channel and the second opening (1201) are form-compatible and opposed to each other (Figure - 2).

[0058] In one embodiment of the invention, the connection assembly (1) comprises at least one cover (1202) positioned on the connection part (12) so as to close the second opening (1201), enclosing the bearing element (11) by closing the second opening (1201) and allowing the pin (5) to be aligned with the fuselage (2). This allows the pin (5) to move within the channel formed by the fixing part (6) and the first opening (10) and the second opening (1201) over a distance specified by the manufacturer, and to align the pin (5) to the fuselage (2).

[0059] In one embodiment of the invention, the connection assembly (1) comprises at least one bushing (13) which is located almost entirely within the channel formed by the fixing part (6) closing the first opening (10), which surrounds the bearing element (11) and allows the bearing element (11) to be positioned within the channel. The outer surfaces of the bushing (13) contact the fuselage (2) within the formed channel and surround the bearing element (11). In this way, it is ensured that after the assembly of the equipment (4) to the fuselage (2), the bearing element (11) remains almost completely stationary in the channel. In one embodiment of the invention, the connection assembly (1) comprises at least one cylindrical bushing (13) forming a longitudinal portion of the bushing (13), at least one cylindrical bushing (1301) and at least one flange (1302) extending outwardly from the cylindrical bushing (1301) in conformity in form with the cylindrical bushing (1301), contacting the fuselage (2) and allowing the bearing element (11) to remain substantially completely fixed in the first opening (10). This prevents movement of the bearing element (11) and the pin (5) within the channel in response to the force exerted by the equipment (4) on the fuselage (2).

[0060] In one embodiment of the invention, the connection assembly (1) comprises two cylindrical bushings (1301), which are arranged opposite to each other in a channel formed almost entirely by the fixing part (6) closing the first opening (10), are fixed to each other by an interference fit and surround the bearing element (11), It comprises two flanges (1302), one located on the side of the fuselage (2) on which the equipment (4) is mounted, and the other located on the opposite side of the fuselage (2) to the side on which the equipment (4) is mounted, which are opposed to each other and thus allow the bearing element (11) to remain substantially completely stationary within the formed channel. One of the flanges (1302) is located on the side on which the equipment (4) is attached to the fuselage (2), and the other flange (1302) is located on the opposite side of the fuselage (2) and is located in the second opening (1201) in the connecting part (12). One of the flanges (1302) counteract forces transmitted from the equipment (4) towards the fuselage (2), while the other counteracts forces transmitted in the opposite direction, thus almost completely preventing movement of the bearing element (11) in both directions within the formed channel and the second opening (1201).

[0061] In one embodiment of the invention, the connection assembly (1) comprises equipment (4) which is an engine positioned on the aircraft and which generates the thrust necessary for flight of the aircraft.

[0062] In one embodiment of the invention, the connection assembly (1) comprises a fuselage (2) which is the fuselage of the aircraft and has a frame structure. The fuselage (2) and the connection part (12) are preferably made of titanium. This ensures long lifetime and high strength.

Claims

CLAIMS1. A connection assembly (1), comprising a fuselage (2) located on an aircraft, at least one housing (3) located as a cavity on the fuselage (2), at least one piece of equipment (4) that performs a function specified by the manufacturer, at least one pin (5) extending outwardly through the equipment (4) and at least partially inserted in the housing (3), allowing the equipment (4) to be removably attached to the fuselage (2), at least one fixing part (6) positioned in the housing (3) and allowing the equipment (4) to be mounted on the fuselage (2), characterized by the housing (3) form-fitting with the fixing part (6), into which the fixing part (6) is supported at one point and into which the fixing part (6) is mounted at least at another point, which allows the pin (5) passing at least partially through it to be fixed by means of the fixing part (6), so that the fixing part (6) fixes the equipment (4) in the fuselage (2) almost completely within the fuselage (2).

2. A connection assembly (1) according to claim 1 , characterized by at least one mounting surface (201) forming the surface of the fuselage (2) opposite the fixing part (6) in the housing (3), at least one lug (7) located in the housing (3), extending outwards from the mounting surface (201), having a hollow form and allowing the fixing part (6) to be rotatably positioned thereon, at least one hole (8) located as an opening on the fixing part (6) and form-fitting with the lug (7), at least one fastener (9) for mounting the fixing part (6) to the fuselage (2) in the housing (3) by passing it through the coaxially located lug (7) and the hole (8).

3. A connection assembly (1) according to claim 2, characterized by the fixing part (6) being fixed to the lug (7) by means of a fastener (9) through the hole (8) and moved by the user around the lug (7), thus allowing the equipment (4) to be mounted on the fuselage (2).

4. A connection assembly (1) according to any one of the preceding claims, characterized by at least one first aperture (10), at least partially perpendicular to the direction in which the fuselage (2) extends along the length of the fuselage (2), hollowly located in the fuselage (2) and opposed to the housing (3), at least one bearing element (11) at least partially located in the first opening (10) and at least partially located in the channel formed in the fuselage (2) surrounded by the fixing part (6), into which the pin (5) is inserted to fix the equipment (4) to the fuselage (2).

5. A connection assembly (1) according to any one of the preceding claims, characterized by provided with at least one connecting part (12) on the side opposite to the side on whichthe equipment (4) is installed on the fuselage (2) and which provides resistance against the moment generated by the equipment (4) on the fuselage (2).

6. A connection assembly (1) according to claim 5, characterized by at least one connector (F) for mounting the connection part (12) to the fuselage (2).

7. A connection assembly (1) according to claim 4 to claim 6, characterized by the fixing part(6) which is a clamp of substantially C-shaped form, one end of which is supported on the hole (8) to the lug (7) by means of a fastener (9), the other end of which is pivoted around the lug (7) and mounted on the mounting surface (201) by means of a connector (F), covering the first opening (10) substantially completely and allowing a channel to be formed in the fuselage (2).

8. A connection assembly (1) according to any one of claims 2 to 7, characterized by the lug(7) and the hole (8) being form-fitting and intertwined with each other, and by the fastener (9), which is passed through the lug (7) and hole (8) by intertwining, allowing the fixing part (6) to be fixed to the fuselage (2) in the housing (3).

9. A connection assembly (1) according to any one of claims 5 to 8, characterized by at least one second aperture (1201), in which the bearing element (11) is inserted, located as a recess in the connection part (12), opposite to and successively located with the channel formed by the fixing part (6) by closing the first opening (10).

10. A connection assembly (1) according to claim 9, characterized by at least one cover (1202) is positioned on the connection part (12) so as to close the second opening (1201), enclosing the bearing element (11) by closing the second opening (1201) and allowing the pin (5) to be aligned with the fuselage (2).

11. A connection assembly (1) according to claim 4 to claim 10, characterized by at least one bushing (13) located almost entirely within the channel formed by the fixing part (6) closing the first opening (10), surrounding the bearing element (11) and allowing the bearing element (11) to be positioned within the channel.

12. A connecting assembly (1) according to claim 11 , characterized by at least one cylindrical bushing (13) forming the longitudinal portion of the bushing (13), at least one flange (1302) extending outwardly from the cylindrical bushing (1301) in conformity in form with thecylindrical bushing (1301), contacting the fuselage (2) and allowing the bearing element (11) to remain substantially completely fixed in the first opening (10).

13. A connection assembly (1) according to claim 12, characterized by two cylindrical bushes (1301), which are located opposite each other in the channel formed almost completely by the fixing part (6) closing the first opening (10), fixed to each other with an interference fit and surround the bearing element (11), two flanges (1302), one on the equipment (4) mounting side of the fuselage (2), the other on the side opposite to the equipment (4) mounting side of the fuselage (2) and facing each other, thus allowing the bearing element (11) to remain almost completely fixed in the formed channel.

14. A connection assembly (1) according to any one of the preceding claims, characterized by the equipment (4) being an engine positioned on the aircraft and providing the propulsion necessary for the flight of the aircraft.

15. A connection assembly (1) according to any one of the preceding claims, characterized by the fuselage (2) being the fuselage of the aircraft and has a frame structure.

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