Equipment mounting structure for airplane

Abstract

The utility model discloses an equipment installation structure for an airplane. The equipment installation structure comprises at least two installation supports, a guide rail and at least one accessory, wherein the guide rail extends in the direction parallel to the course of the airplane and is fixed on the installation supports, and the accessory is used for installing equipment, pipelines or cables. Every two adjacent mounting supports are fixed to different bulkheads arranged on the aircraft in the direction perpendicular to the heading direction of the aircraft, the plane defined by the mounting supports is perpendicular to the heading direction of the aircraft, and a plurality of mounting holes used for mounting accessories are formed in the mounting supports and / or the guide rails. According to the utility model, a plurality of parts of the same airborne system are integrally mounted, so that the layout lengths of pipelines, cables and the like are effectively shortened, the weight of an airplane is effectively reduced, the internal space of the airplane can be effectively utilized, and the mounting and maintenance space is enlarged, thereby improving the manufacturability and the maintainability of the airplane and improving the mounting and maintenance efficiency.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft assembly and manufacturing, and specifically to an equipment installation structure for aircraft. Background Technology

[0002] Airborne system installation structures are crucial components in civil aircraft equipment installation, playing a vital role in supporting equipment, ensuring proper layout, and mitigating vibrations. Currently, components used for equipment installation on aircraft typically include equipment racks, brackets, and support frames. However, these commonly used installation components usually only support a single type of equipment and often require connection to aircraft bulkheads or stringers. Installation structures have the following drawbacks: First, due to the positional limitations of bulkheads and stringers, equipment must be arranged along them, resulting in excessively long piping and cables, increasing aircraft weight. Second, for some complex airborne systems involving numerous devices, more holes need to be drilled in the aircraft bulkheads and stringers, reducing the strength of some structural components or increasing aircraft weight. Third, with equipment arranged along fuselage stringers or bulkheads, access methods for maintenance personnel are typically limited, usually only accessible from the front, and some fasteners near the fuselage side are difficult to disassemble.

[0003] As aircraft become more integrated, the layout of various airborne systems or subsystems tends to be more centralized. Therefore, it is necessary to consider designing an installation structure that can centrally install multiple devices in a certain area in order to reduce the length of aircraft pipes and cables, reduce aircraft weight, and improve aircraft manufacturability and maintainability. Utility Model Content

[0004] The purpose of this invention is to at least partially avoid or solve the above-mentioned technical problems.

[0005] Specifically, this utility model proposes an equipment mounting structure for an aircraft, the equipment mounting structure comprising:

[0006] At least two mounting brackets, wherein two adjacent mounting brackets are fixed to different bulkheads of the aircraft in a direction perpendicular to the aircraft's heading, wherein the plane defined by the mounting brackets is perpendicular to the aircraft's heading;

[0007] A guide rail, fixed to the mounting bracket and extending in a direction parallel to the aircraft's heading; and

[0008] At least one accessory for installing equipment, piping, or cables.

[0009] The mounting bracket and / or guide rail have multiple mounting holes for mounting the at least one accessory.

[0010] According to some embodiments, the mounting bracket includes: a crossbeam extending in a direction perpendicular to the aircraft's heading and fixed at one end to the bulkhead; and a column, one end of which is connected to the other end of the crossbeam and disposed perpendicular to the extension direction of the crossbeam, the other end of which is fixed to the bulkhead at the end of the crossbeam connected thereto. The crossbeam and the column are respectively fixed to the bulkhead by fasteners such as bolts and nuts. The crossbeam and the column bear the main loads of the equipment mounting structure and the equipment thereon; the crossbeam transmits horizontal loads to the aircraft structure, and the column transmits vertical loads to the aircraft structure.

[0011] According to some embodiments, the equipment mounting structure further includes a tie rod, one end of which is fixed to the guide rail or crossbeam, and the other end of which is fixed to the stringer or bulkhead. The tie rod is used to bear the load in the aircraft's flight direction and transmit the overall load of the equipment mounting structure to the aircraft's heading. Preferably, the tie rod is a tubular component, and the other end of which is fixed to the stringer, because the aircraft's heading force is parallel to the stringer, the tie rod can withstand the maximum force in this case.

[0012] According to some embodiments, both ends of the tie rod are provided with a first joint, and the parts of the stringer or partition and the guide rail or crossbeam that connect to the tie rod are provided with corresponding connecting seats. The connecting seats are configured to be detachably connected to the first joints. Specifically, the connecting seats are provided with second joints that match the first joints. The first and second joints are designed with corresponding through holes. The first and second joints are fixedly connected by fasteners passing through the through holes, thereby realizing the fixed connection between the two ends of the tie rod and the stringer or partition, guide rail or crossbeam.

[0013] According to some implementations, the first connector is a single-ear connector, and the second connector is a double-ear connector, or vice versa. During installation, the single-ear connector is inserted between the two ears of the double-ear connector, and then the two are fixedly connected by pins, thereby achieving a fixed connection between the two ends of the tie rod and the stringer or frame, guide rail or beam.

[0014] According to some embodiments, the accessory includes a first bracket detachably fixed to the beam or guide rail for mounting equipment, pipes, or cables. The first bracket includes a base plate, two opposing first sidewalls extending from two opposing first edges of the base plate in a direction perpendicular to the extension direction of the base plate, and a second sidewall extending in a direction perpendicular to the extension direction of the base plate and disposed between the two first sidewalls.

[0015] The substrate has mounting holes for mounting equipment, pipes or cables, and the second sidewall has a first fixing hole for fixing the first bracket to the crossbeam or guide rail. The first bracket is fixed to the crossbeam or guide rail by fasteners such as bolts and nuts.

[0016] According to some embodiments, the accessory further includes clamps for installing equipment, pipes, or cables, the clamps being configured to be detachably fixed to the first bracket, beam, or guide rail. It should be noted that the clamps can be directly and detachably fixed to the beam or guide rail, or they can be detachably fixed to the beam or guide rail via the first bracket.

[0017] According to some embodiments, the clamp includes a base, a fixed portion formed on the top of the base with an arc-shaped inner surface, and a movable portion whose two ends are respectively detachably connected to the two ends of the fixed portion. The inner surface of the movable portion is arc-shaped, so that when the movable portion is installed on the fixed portion, the inner surface of the movable portion and the inner surface of the fixed portion together form a ring capable of receiving at least a portion of the fixed equipment, pipeline or cable.

[0018] The base has a slot in the middle, and a second fixing hole is formed on the bottom surface of the slot, allowing the clamp to be fixed to the crossbeam or guide rail using fasteners such as bolts and nuts. The slot in the base saves space and facilitates the installation of fasteners, while also helping to reduce the weight of the aircraft.

[0019] According to some embodiments, the accessory further includes a second bracket detachably fixed to the crossbeam along the aircraft's heading. The second bracket has mounting holes for installing equipment, pipes, or cables. Specifically, the second bracket has a U-shaped cross-section, and third fixing holes are formed on both sides of the second bracket, allowing it to be fixed to the crossbeam using fasteners such as bolts and nuts. It should be noted that, provided the second bracket is fixed to the crossbeam and can accommodate the installation of equipment, pipes, or cables, the cross-section of the second bracket can be any structure other than a U-shape.

[0020] According to some implementation methods, the first bracket, clamp, and second bracket mentioned above are all sheet metal parts, and there can be one or more of them. The number and position of the first bracket, clamp, and second bracket can be adjusted according to the actual situation to meet the installation requirements of different equipment, pipelines, or cables.

[0021] According to some embodiments, the equipment mounting structure further includes a first connecting member disposed at the connection between the crossbeam and the column for fixing the two together. The first connecting member includes a first plate and a second plate connected to one end of the first plate and disposed perpendicular to the extending direction of the first plate. The first plate is detachably mounted on the crossbeam, and the second plate is detachably mounted on the column, or vice versa. The first connecting member improves the robustness of the connection between the crossbeam and the column.

[0022] According to some embodiments, a rib is provided on one side of the first connector, perpendicular to the first plate and the second plate, and connecting the first plate and the second plate. The rib can improve the connection strength between the first plate and the second plate, thereby improving the stability of the first connector.

[0023] According to some implementation methods, the connection between the first plate and the second plate is designed with rounded corners, and the connection between the rib and the first plate and the second plate is designed with rounded corners, which facilitates the processing and production of the first connector and reduces the defect rate.

[0024] According to some embodiments, the equipment mounting bracket further includes a second connector disposed at the connection point of the guide rail, crossbeam, and column for connecting the three together. The second connector includes a base plate, two opposing first sides extending from two opposing third edges of the base plate in a direction perpendicular to the base plate, and a second side extending in a direction perpendicular to the base plate and disposed between the two first sides. The base plate is detachably mounted on the guide rail, the first side near the column is detachably mounted on the column, and the second side is detachably mounted on the crossbeam. The second connector improves the robustness of the connection between the guide rail, crossbeam, and column.

[0025] According to some embodiments, the guide rail also includes a control guide rail for adjusting the overall balance and stability of the frame of the equipment mounting structure. The control guide rail extends in a direction parallel to the flight path of the aircraft and is installed on a part of the crossbeam where no other components or structures are placed.

[0026] According to some embodiments, the guide rail is configured to have weight-reducing holes for reducing the weight of the guide rail. The weight-reducing holes can be circular or any other shape, such as square, rectangular, triangular, etc.

[0027] According to some embodiments, the number of guide rails is multiple, and the equipment mounting structure also includes a reinforcing beam extending in a direction perpendicular to the aircraft's heading for connecting multiple adjacent guide rails. The reinforcing beam can improve the stability of the connection between the multiple guide rails, thereby improving the overall stability of the equipment mounting structure.

[0028] According to some implementation methods, the connection points between the guide rails, crossbeams, columns, and tie rods are electrically connected, thereby creating electrical conductivity between them. This ensures that the equipment installation structure is an equipotential body and avoids potential differences between the assembled components. Specifically, the guide rails, crossbeams, columns, and tie rods are all made of metal. Electrical conductivity is achieved by removing the adhesive surface or paint from the connection surfaces of the guide rails, crossbeams, columns, and tie rods at the connection points.

[0029] According to some implementation methods, the connection points between the beams, columns, and tie rods and the girder and partition frame are also electrically connected as described above, so that the beams, columns, and tie rods and the girder and partition frame are electrically connected to each other at the connection points.

[0030] The positive effects of this utility model are as follows:

[0031] 1. This utility model comprehensively considers the installation requirements of airborne system equipment, pipelines, and cables, and adopts a more compact layout, placing multiple components of the same airborne system on a single equipment installation structure. For example, it integrates and installs equipment, pipelines, and cables on the aircraft together, effectively shortening the layout length of pipelines and cables and effectively reducing the weight of the aircraft.

[0032] 2. This utility model adopts an integrated installation design, which effectively utilizes the internal space of the aircraft, thereby increasing the installation and maintenance space, thus improving the manufacturability and maintainability of the aircraft, making it easier for manufacturing personnel to install airborne systems, and also making it easier for maintenance personnel to carry out inspection and maintenance work, thereby improving installation and maintenance efficiency.

[0033] 3. This utility model is applicable to equipment, pipelines, and cables that are far from the airframe structure. It is suitable for use in the installation design of inerting systems and can also be used for the installation and layout of some small integrated systems during flight testing and operation. Attached Figure Description

[0034] Figure 1 A schematic diagram of the equipment installation structure according to a preferred embodiment of the present invention is shown.

[0035] Figure 2 A schematic diagram of the device mounting structure according to a preferred embodiment of the present invention is shown from a lower view.

[0036] Figure 3 A schematic diagram of the structure of the mounting bracket, guide rail and tie rod assembly according to a preferred embodiment of the present invention is shown.

[0037] Figure 4 A partial schematic diagram of the tie rod installation according to a preferred embodiment of the present invention is shown;

[0038] Figure 5 A partial schematic diagram of the connection between the tie rod and the stringer according to a preferred embodiment of the present invention is shown.

[0039] Figure 6 A schematic diagram of the structure of the first bracket according to a preferred embodiment of the present invention is shown.

[0040] Figure 7 A schematic diagram of the guide rail, crossbeam, and clamp assembly according to a preferred embodiment of the present invention is shown.

[0041] Figure 8 A schematic diagram of the structure of the first connector located at the connection portion according to a preferred embodiment of the present invention is shown.

[0042] Figure 9 A schematic diagram of the structure of the second connector located at the connection portion according to a preferred embodiment of the present invention is shown.

[0043] The reference numerals in the attached figures are explained as follows:

[0044] 100. Mounting bracket; 110. Crossbeam; 111. First notch; 120. Column; 130. First connector; 131. First plate; 132. Second plate; 133. Rib; 134. Second notch; 140. Second connector; 141. Base plate; 142. First side; 143. Second side; 200. Guide rail; 210. Adjustable guide rail; 220. Weight reduction hole; 300. Mounting hole; 400. Tie rod; 410. First joint; 420. 421. Connecting seat; 422. Fixing plate; 430. Fixing seat; 500. Second connector; 510. First bracket; 520. Base plate; 530. First side wall; 530. Second side wall; 600. Clamp; 610. Base; 611. Groove; 612. Second fixing hole; 620. Fixing part; 630. Movable part; 640. Standard clamp; 700. Second bracket; 800. Reinforcing beam; 910. Long stringer; 920. Partition frame; 930. Equipment; 940. Pipeline. Detailed Implementation

[0045] In the following description, preferred embodiments of the present disclosure will be described in more detail with reference to the accompanying drawings. Although preferred embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be thorough and complete, and will fully convey the scope of the present disclosure to those skilled in the art.

[0046] Unless the context requires otherwise, throughout the specification and claims, the word “comprising” and its variations, such as “including” and “having”, shall be understood to have an open, inclusive meaning, that is, to be interpreted as “including, but not limited to”.

[0047] Throughout this specification, references to "one embodiment" or "some embodiments" indicate that a particular feature, structure, or characteristic described in connection with an embodiment is included in at least one embodiment. Therefore, the appearance of "in one embodiment" or "in some embodiments" in various places throughout the specification does not necessarily refer to the same embodiment. Furthermore, a particular feature, structure, or characteristic may be combined in any way in one or more embodiments.

[0048] Furthermore, the terms "first," "second," etc., used in the specification and claims are used merely for clarity of description to distinguish various objects, and do not limit the size, quantity, or other order of the objects described. Directional terms indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are used solely for the purpose of describing this application, not to indicate or imply that the objects referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this application.

[0049] This invention proposes an equipment installation structure for an aircraft, wherein the aircraft fuselage structure includes a stringer 910 extending along the aircraft's heading and a bulkhead 920 perpendicular to the aircraft's heading. The equipment installation structure according to this invention can be fixed to the stringer 910 or the bulkhead 920, thereby achieving integrated installation of equipment, pipes, and cables on the aircraft.

[0050] As attached Figure 1 and 2 As shown, the equipment mounting structure according to this utility model includes at least two mounting brackets 100, a guide rail 200, and at least one accessory. Two adjacent mounting brackets 100 are fixed to different bulkheads 920 of the aircraft, arranged in a direction perpendicular to the aircraft's heading, and the plane defined by the mounting brackets 100 is perpendicular to the aircraft's heading. The guide rail 200 extends in a direction parallel to the aircraft's heading and is fixed to the mounting bracket 100. At least one accessory is used for mounting equipment, pipes, or cables, and a plurality of mounting holes 300 for mounting the accessory are formed in the mounting brackets 100 and / or the guide rail 200.

[0051] In one implementation, see Appendix Figure 1 and 2 The mounting bracket 100 includes a crossbeam 110 and a column 120. The crossbeam 110 extends in a direction perpendicular to the aircraft's heading and is fixed at one end to a bulkhead 920. The column 120 is positioned perpendicular to the extension direction of the crossbeam 110, with one end connected to the other end of the crossbeam 110. The other end of the column 120 is fixed to the bulkhead 920, where the end of the crossbeam 110 is connected. The crossbeam 110 and the column 120 are fixed to the bulkhead 920, for example, by fasteners. The guide rail 200 can also be fixed to the crossbeam 110, for example, by fasteners. The crossbeam 110 and the column 120 will bear the main loads of the equipment mounting structure and the equipment mounted on it. The crossbeam 110 is mainly used to transfer horizontal loads to the aircraft structure, while the column 120 is mainly used to transfer vertical loads to the aircraft structure.

[0052] In one implementation, as shown in the appendix Figure 3 As shown, the equipment mounting structure also includes a tie rod 400. One end of the tie rod 400 is fixed to the guide rail 200 or the crossbeam 110, and the other end is fixed to the stringer 910 or the bulkhead 920. The tie rod 400 is mainly used to bear the loads of the equipment mounting structure and the equipment installed on it along the aircraft's flight direction, and to transfer the loads along the aircraft's flight direction to the aircraft structure.

[0053] In one embodiment, the tie rod 400 is formed as a tubular component, with one end fixed to the guide rail 200. This facilitates shortening the length of the tie rod 400, thereby saving material. The other end of the tie rod 400 can be fixed to the stringer 910. Since the tie rod is mainly used to bear the loads of the equipment mounting structure and the equipment mounted on it along the aircraft's flight direction, and the extension direction of the stringer 910 is parallel to the aircraft's flight direction, the tie rod 400 can withstand the maximum load in this case.

[0054] Further details are attached. Figure 4 and 5As shown, each end of the tie rod 400 is provided with a first connector 410, and the parts of the stringer 910 or partition 920, guide rail 200 or crossbeam 110 that connect to the tie rod 400 are provided with corresponding connecting seats 420. The connecting seats 420 are configured to be detachably connected to the first connectors 410. Specifically, the connecting seats 420 are provided with second connectors 430 that cooperate with the first connectors 410. Both the first connectors 410 and the second connectors 430 are designed with corresponding through holes, so that the first connectors 410 and the second connectors 430 can be fixedly connected by passing fasteners through the through holes, thereby realizing the fixed connection between the two ends of the tie rod 400 and the stringer 910 or partition 920, guide rail 200 or crossbeam 110 respectively.

[0055] In one embodiment, the connector 420 is an integral structure, see attached drawing. Figure 4 The connecting seat 420 located on the guide rail 200 includes a fixing plate 421 and a second connector 430 formed above the fixing plate 421. The fixing plate 421 can be fixed to the guide rail 200 by, for example, fasteners. See Appendix Figure 5 The connecting seat 420 located on the stringer 910 includes a fixed seat 422 and a second connector 430 formed below the fixed seat 422. The fixed seat 422 has a groove formed in the middle and is fixed to the stringer 910, for example, by fasteners. The design of forming a groove in the fixed seat 422 saves space and facilitates the installation of fasteners, and also helps to reduce the weight of the aircraft.

[0056] In one embodiment, the first connector 410 is a single-ear connector and the second connector 430 is a double-ear connector, or vice versa. During installation, the construction personnel insert the single-ear connector between the two ears of the double-ear connector and then fix the two together with fasteners such as pins, thereby achieving a fixed connection between the two ends of the tie rod 400 and the stringer 910 or the partition 920, the guide rail 200 or the crossbeam 110, respectively.

[0057] In one embodiment, the accessory includes a first bracket 500 for mounting equipment, conduits, or cables, see Appendix Figure 2 The first bracket 500 is detachably fixed to the crossbeam 110 or the guide rail 200. Additionally, as shown in the attached... Figure 6As shown, the first bracket 500 includes a base plate 510, two first sidewalls 520, and a second sidewall 530. The two first sidewalls 520 extend from two opposing first edges of the base plate 510 in a direction perpendicular to the extension direction of the base plate 510. The second sidewall 530 extends in a direction perpendicular to the extension direction of the base plate 510 and is disposed between the two first sidewalls 520. The base plate 510 has mounting holes for mounting equipment, pipes, or cables, and the second sidewall 530 also has first fixing holes for fixing the first bracket 500 to the crossbeam 110 or the guide rail 200. Thus, the first bracket 500 can be fixed to the crossbeam 110 or the guide rail 200 by fasteners.

[0058] In one implementation, as shown in the appendix Figure 7 As shown, the accessories also include clamps 600 for installing equipment, pipes, or cables. The clamps 600 are detachably fixed to the first bracket 500, the crossbeam 110, or the guide rail 200. It should be noted that the clamps 600 can be directly and detachably fixed to the crossbeam 110 or the guide rail 200, or they can be detachably fixed to the crossbeam 110 or the guide rail 200 via the first bracket 500.

[0059] In one implementation, see Appendix Figure 7 The clamp 600 includes a base 610, a fixing part 620, and a movable part 630. The fixing part 620 is disposed on the top of the base 610, and its inner surface is formed into a curved arc. The inner surface of the movable part 630 is also formed into a curved arc, and the two ends of the curved part 630 are detachably connected to the two ends of the fixing part 620, respectively. Thus, when the movable part 630 is installed on the fixing part 620, the inner surface of the movable part 630 and the inner surface of the fixing part 620 together can form a ring capable of receiving and fixing at least a portion of equipment, pipes, or cables. Preferably, the two ends of the movable part 630 are fixedly connected to the two ends of the fixing part 620 by fasteners such as bolts and nuts.

[0060] For further details, please see the appendix. Figure 7 A slot 611 is formed in the middle of the base 610, and a second fixing hole 612 is formed on the bottom surface of the slot 611, so that the clamp 600 can be fixed to the crossbeam 110 or the guide rail 200, for example, by fasteners. The design of forming a slot 611 in the base 610 can save space and facilitate the installation of fasteners, and also help to reduce the weight of the aircraft.

[0061] In one implementation, see Appendix Figure 7The clamp 600 is a standard clamp 640 and only includes a fixing part 620 with an inner curved surface. The two ends of the fixing part 620 can be fixed to the first bracket 500, the crossbeam 110 or the guide rail 200, respectively, for example by fasteners. The standard clamp 640 is suitable for fixing tubular or cylindrical equipment 930, pipelines 940 and cables, etc.

[0062] In one implementation, see Appendix Figure 3 and 7 The accessory also includes a second bracket 700, which is detachably fixed to the crossbeam 110 along the aircraft's heading and primarily serves to support equipment. The second bracket 700 has mounting holes 300 for installing equipment, pipes, or cables. Specifically, the second bracket 700 has a U-shaped cross-section, and third fixing holes are formed on both sides of the second bracket 700, thereby allowing the second bracket 700 to be fixed to the crossbeam 110, for example, by fasteners.

[0063] It should be noted that, provided that the second bracket 700 is fixed on the crossbeam 110 and can be used to install equipment, pipes or cables, the cross section of the second bracket 700 can be any other suitable structure other than the "U" shaped structure.

[0064] As described above, the first bracket 500 and the second bracket 700 are both sheet metal parts, while the clamp 600 can be made of metal, rubber, or plastic. The number of the first bracket 500, clamp 600, and second bracket 700 can be one or more in combination, and their quantity and position can be adjusted according to actual needs to meet the installation requirements of different equipment, pipelines, or cables. It should be noted that some equipment, when installed on the equipment mounting structure according to this utility model using the first bracket 500, typically needs to be used in combination with the clamp 600.

[0065] Furthermore, as mentioned above, the crossbeam 110, column 120, and guide rail 200 are all sheet metal parts. The cross-sections of the crossbeam 110 and column 120 are not limited to L-shapes; they can be any other suitable shape. However, the preferred cross-section is L-shaped, which not only saves material but also provides good load-bearing capacity and helps reduce aircraft weight. The cross-section of the guide rail 200 is not limited to L-shapes, rectangles, or I-shapes; it can be any other suitable shape. Moreover, multiple guide rails 200 with different cross-sectional shapes can be combined according to actual needs.

[0066] In one implementation, see Appendix Figure 3 The equipment installation structure also includes a first connector 130, located at the connection between the crossbeam 110 and the column 120, for fixing the two together. Additionally, as shown in the attached... Figure 8As shown, the first connector 130 includes a first plate 131 and a second plate 132 that extends perpendicularly to the first plate 131 and is connected to one end of the first plate 131. The first plate 131 is detachably mounted on the crossbeam 110, and the second plate 132 is detachably mounted on the column 120, or vice versa. This first connector 130 thus improves the robustness of the connection between the crossbeam 110 and the column 120.

[0067] In one implementation, see Appendix Figure 8 One plate of the L-shaped beam 110 has a first notch 111 at its connection with the column 120. Another plate of the L-shaped beam 110 is attached to one plate of the L-shaped column 120. At this point, a first plate 131 is placed on the same side as the other plate of the beam 110 and the plate of the column 120, and a second plate 132 is attached to the other plate of the column 120. The points where the first plate 131, the other plate of the beam 110, and the plate of the column 120 are attached are fixedly connected, for example, by fasteners. Simultaneously, the points where the second plate 132 is attached to the other plate of the column 120 are fixedly connected, for example, by fasteners. Furthermore, a second notch 134 is also formed on the first plate 131. In addition to fixing the first plate 131, the other plate of the crossbeam 110, and the plate of the column 120 together with fasteners, the first plate 131 and the other plate of the crossbeam 110 are also fixed together with fasteners, and the part of the first plate 131 facing the plate of the column 120 is also fixed together with fasteners, thereby improving the stability of the connection between the first connector 130 and the crossbeam 110 and the column 120.

[0068] In one implementation, see Appendix Figure 8 A rib 133 is provided on one side of the first connector 130, which is perpendicular to the first plate 131 and the second plate 132 and connects the first plate 131 and the second plate 132. The rib 133 can improve the connection strength between the first plate 131 and the second plate 132, thereby improving the stability of the first connector 130.

[0069] Furthermore, the connection between the first plate 131 and the second plate 132 is designed with rounded corners, and the connection between the rib 133 and the first plate 131 and the second plate 132 is also designed with rounded corners. This facilitates the processing and production of the first connector 130 and helps to reduce the defect rate.

[0070] It should be noted that the crossbeam 110 and the column 120 can be fixedly connected by the first connector 130 as described above. Depending on the actual situation or requirements, the crossbeam 110 and the column 120 can also be designed as an integral structure.

[0071] In one implementation, see Appendix Figure 2 The equipment mounting bracket 100 also includes a second connector 140, located at the connection point of the guide rail 200, crossbeam 110, and column 120, for connecting the three together. Additionally, as shown in the attached... Figure 9 As shown, the second connector 140 includes a base plate 141, two first side portions 142, and a second side portion 143. The two first side portions 142 extend from two opposing third edges of the base plate 141 in a direction perpendicular to the base plate 141, and the second side portion 143 extends in a direction perpendicular to the base plate 141 and is disposed between the two first side portions 142. The base plate 141 is detachably mounted on the guide rail 200, the first side portion 142 near the column 120 is detachably mounted on the column 120, and the second side portion 143 is detachably mounted on the crossbeam 110. Thus, the second connector 140 improves the robustness of the connection between the guide rail 200, the crossbeam 110, and the column 120.

[0072] In one implementation, see Appendix Figure 9 The guide rail 200 is placed above one plate of the L-shaped beam 110, while one plate of the L-shaped column 120 is positioned outside the other plate of the L-shaped beam 110, with the two plates fitting together. The base plate 141 is then placed below the guide rail 200 and secured to it, for example, with fasteners. Simultaneously, one of its first side portions 142 fits against the other plate of the L-shaped column 120 and is secured to it, for example, with fasteners, while the second side portion 143 fits against the other plate of the L-shaped beam 110 and is secured to it, for example, with fasteners. Preferably, the base plate 141, guide rail 200, and one plate of the L-shaped beam 110 are secured to each other at the points where they fit together, thereby improving the stability of the connection between the second connector 140 and the guide rail 200, beam 110, and column 120.

[0073] Furthermore, the side of the first side 142 away from the second side 143 is designed with a chamfered structure, which can save materials and also help reduce the weight of the aircraft.

[0074] In one implementation, see Appendix Figure 3 and 7 The guide rail 200 also includes a control guide rail 210 for adjusting the overall balance and stability of the frame of the equipment installation structure. The control guide rail 210 extends in a direction parallel to the aircraft's heading and is installed on a part of the crossbeam 110 where no other components or structures are placed. The control guide rail 210 is a sheet metal part, and its cross-section is not limited to L-shaped, rectangular, or I-shaped, but can be any other suitable shape.

[0075] In one implementation, see Appendix Figure 3 and 7 The guide rail 200 is provided with weight-reducing holes 220 to reduce the weight of the guide rail 200. The design of the weight-reducing holes 220 is beneficial to reducing the weight of the aircraft. The weight-reducing holes 220 can be circular or any other suitable shape, such as square, rectangular, triangular, etc.

[0076] It should be understood that the weight reduction hole 220 is constructed on a part of the guide rail 200 where no other components or structures are placed, or the weight reduction hole 220 is constructed on the control guide rail 210. This facilitates the reduction of the weight of the equipment installation structure according to this utility model, and thus helps to reduce the weight of the aircraft.

[0077] In one implementation, see Appendix Figure 2 and 7 The number of guide rails 200 can be designed to be multiple. The equipment installation structure also includes a reinforcing beam 800 extending in a direction perpendicular to the aircraft heading to connect multiple adjacent guide rails 200. The reinforcing beam 800 can improve the stability of the connection between multiple guide rails 200, thereby improving the overall stability of the equipment installation structure.

[0078] It is understandable that the length of the guide rail 200 can be adjusted according to actual needs. Multiple guide rails 200 can have different lengths. Longer guide rails can be supported and fixed by two adjacent crossbeams 110, while shorter guide rails can be supported and fixed by one adjacent crossbeam 110 and one reinforcing beam 800. Longer and shorter guide rails can also be supported and fixed by other appropriate structures, and longer guide rails can also be constructed by combining multiple shorter guide rails; there are no specific limitations on this.

[0079] In one embodiment, the guide rail 200, crossbeam 110, column 120, and tie rod 400 are all made of metal, and the connection points between them undergo electrical bonding treatment. This ensures electrical conductivity between the connection points, guaranteeing that the equipment installation structure is an equipotential body and preventing potential differences between the assembled components. Specifically, electrical conductivity is achieved by removing the adhesive or paint from the connection surfaces of the guide rail 200, crossbeam 110, column 120, and tie rod 400 at their connection points.

[0080] Furthermore, the connection points between the beams 110, columns 120, and tie rods 400 and the girder 910 and partition 920 are also electrically connected as described above, thereby enabling electrical conductivity between the beams 110, columns 120, and tie rods 400 and the girder 910 and partition 920 at their connection points.

[0081] It should be noted that the detachable installation or detachable fixing in this application can be achieved using fasteners or any other suitable structure. Furthermore, the fasteners can be bolts and nuts, or other suitable components such as pins.

[0082] According to the installation method of the equipment installation structure of this utility model, the crossbeam 110 and column 120 are first assembled and fixed on the aircraft bulkhead 920. Then, the guide rail 200 and / or tie rod 400 are installed. Finally, the quantity and position of the first bracket 500, clamp 600, and second bracket 700 are selected according to the actual situation to meet the integrated installation requirements of different equipment, pipelines, or cables. It should be noted that the installation sequence of the crossbeam 110, column 120, guide rail 200, tie rod 400, etc., as described above is not specifically limited and can be adjusted appropriately according to the actual situation.

[0083] The equipment installation structure of this utility model enables the integrated installation of multiple components of the same airborne system. For example, it integrates aircraft equipment, pipes, and cables, effectively shortening the layout length of pipes and cables and reducing aircraft weight. It also effectively utilizes the aircraft's internal space, increasing installation and maintenance space, thereby improving the aircraft's manufacturability and maintainability. This facilitates the installation of airborne systems by manufacturing personnel and the inspection and maintenance work by maintenance personnel, improving installation and maintenance efficiency. The equipment installation structure of this utility model is suitable for equipment, pipes, and cables located far from the airframe structure. It is suitable for use in inerted system installation designs and can also be used for the installation and layout of some small integrated systems during flight testing and operation phases.

[0084] It should be noted that the features or combinations of features described above according to the present utility model, as well as the features and combinations of features mentioned and / or shown only in the accompanying drawings, can be used not only in the corresponding combinations, but also in other combinations or individually, without departing from the scope of the present utility model.

[0085] This utility model has been described through the above embodiments. However, it should be understood that the above embodiments are for illustrative purposes only and are not intended to limit this utility model to the scope of the described embodiments. Those skilled in the art should understand that many more changes and modifications can be made based on the teachings of this utility model, and all such changes and modifications fall within the protection scope of this utility model.

Claims

1. An equipment mounting structure for an aircraft, characterized in that, The equipment installation structure includes: At least two mounting brackets, wherein two adjacent mounting brackets are fixed to different bulkheads of the aircraft in a direction perpendicular to the aircraft's heading, wherein the plane defined by the mounting brackets is perpendicular to the aircraft's heading; A guide rail, fixed to the mounting bracket and extending in a direction parallel to the aircraft's heading; and At least one accessory for installing equipment, piping, or cables. The mounting bracket and / or guide rail have multiple mounting holes for mounting the at least one accessory.

2. The equipment mounting structure for an aircraft according to claim 1, characterized in that, The mounting bracket includes: a crossbeam extending in a direction perpendicular to the aircraft's heading and fixed at one end to the frame; and a column connected at one end to the other end of the crossbeam and disposed perpendicular to the extension direction of the crossbeam, the other end of the column being fixed to the frame on which the crossbeam is connected.

3. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The equipment mounting structure also includes a tie rod, one end of which is fixed to the guide rail or crossbeam, and the other end of which is fixed to the aircraft's stringer or bulkhead.

4. The equipment mounting structure for an aircraft according to claim 3, characterized in that, Both ends of the tie rod are provided with a first joint, and the long stringer or partition and the guide rail or crossbeam are provided with corresponding connecting seats at the parts that connect with the tie rod. The connecting seats are configured to be detachably connected to the first joint.

5. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The accessory includes a first bracket for mounting equipment, pipes or cables that is detachably fixed to the crossbeam or guide rail. The first bracket includes a base plate, two opposing first sidewalls extending from two opposing first edges of the base plate in a direction perpendicular to the extension direction of the base plate, and a second sidewall extending in a direction perpendicular to the extension direction of the base plate and disposed between the two first sidewalls. The substrate has mounting holes for mounting equipment, pipes or cables, and the second sidewall has a first fixing hole for fixing the first bracket to the crossbeam or guide rail.

6. The equipment mounting structure for an aircraft according to claim 5, characterized in that, The accessories also include clamps for installing equipment, pipes or cables, which are configured to be detachably fixed to the first bracket, beam or rail.

7. The equipment mounting structure for an aircraft according to claim 6, characterized in that, The clamp includes a base, a fixed part formed on the top of the base with an arc-shaped inner surface, and a movable part whose two ends are detachably connected to the two ends of the fixed part, the movable part having an arc-shaped inner surface, such that when the movable part is installed on the fixed part, the inner surface of the movable part and the inner surface of the fixed part together form a ring capable of receiving at least a portion of the fixed equipment, pipe or cable. The base has a slot in the middle and a second fixing hole on the bottom surface of the slot, so that the clamp can be fixed to the crossbeam or guide rail by fasteners.

8. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The accessory also includes a second bracket detachably fixed to the crossbeam along the flight path of the aircraft, the second bracket having mounting holes for installing equipment, pipes or cables.

9. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The equipment installation structure further includes a first connecting member disposed at the connection between the crossbeam and the column for fixing the two together. The first connecting member includes a first plate and a second plate connected to one end of the first plate and disposed perpendicular to the extension direction of the first plate. The first plate is detachably mounted on the crossbeam, and the second plate is detachably mounted on the column, or vice versa.

10. The equipment mounting structure for an aircraft according to claim 9, characterized in that, One side of the first connector is provided with a rib that is perpendicular to the first plate and the second plate and connects the first plate and the second plate.

11. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The equipment installation structure further includes a second connector disposed at the connection point of the guide rail, the crossbeam and the column, for connecting the three together. The second connector includes a base plate, two opposing first sides extending from two opposing second edges of the base plate in a direction perpendicular to the base plate, and a second side extending in a direction perpendicular to the base plate and disposed between the two first sides. The base plate is detachably mounted on the guide rail, the first side near the column is detachably mounted on the column, and the second side is detachably mounted on the crossbeam.

12. The equipment mounting structure for an aircraft according to claim 2, characterized in that, The guide rail also includes a control guide rail for adjusting the overall balance and stability of the frame of the equipment installation structure. The control guide rail extends along a direction parallel to the flight path of the aircraft and is installed on the crossbeam.

13. The equipment mounting structure for an aircraft according to claim 1, characterized in that, The guide rail is configured to have weight-reducing holes for reducing the weight of the guide rail.

14. The equipment mounting structure for an aircraft according to claim 1, characterized in that, The number of guide rails is multiple, and the equipment mounting structure also includes a reinforcing beam extending in a direction perpendicular to the aircraft's heading to connect multiple adjacent guide rails.

15. The equipment mounting structure for an aircraft according to claim 3, characterized in that, The connection points between the guide rails, crossbeams, columns, and tie rods are electrically connected, thereby enabling electrical conductivity between the guide rails, crossbeams, columns, and tie rods at the connection points.

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