Mounting device for a hydraulic thrust control unit and hydraulic thrust control unit

Abstract

A mounting device for a hydraulic thrust reverser control unit and a hydraulic thrust reverser control unit, the mounting device comprising a first frame and a second frame arranged in a rear mounting station of a pylon of an aircraft and spaced apart in a direction of travel of the aircraft, and a support member connected to the first frame and the second frame and extending between the first frame and the second frame in the direction of travel, the support member supporting the hydraulic thrust reverser control unit between the first frame and the second frame from below. The hydraulic thrust reverser control unit is mounted to the rear mounting station of the pylon of the aircraft by the mounting device.

Description

Technical Field

[0001] The present invention relates to a mounting device for a hydraulic thrust reverser control unit and a hydraulic thrust reverser control unit installed using the mounting device. Background Technology

[0002] The thrust reverser system is a core braking system for civil transport aircraft during the landing roll. It drives the thrust reverser cowling within the engine nacelle to slide backward, altering the airflow direction in the nacelle's bypass duct to generate reverse thrust, thus effectively shortening the landing roll distance. Currently, hydraulic thrust reverser systems with hydraulically driven thrust reverser cowlings are the primary thrust reverser technology used in civil aircraft due to their high control precision and stable power output.

[0003] As the core control hub of the aforementioned hydraulic thrust reverser system, the hydraulic thrust reverser control unit integrates core functions such as oil circuit on / off control and motion direction switching. Its integrated design scheme, overall layout and installation structure directly determine the piping layout, weight control and maintenance accessibility of the thrust reverser system. At the same time, it has a direct impact on the overall aerodynamic performance of the aircraft and the design difficulty of the engine. It is a core component of the overall design of the civil aircraft thrust reverser system.

[0004] Currently, the main layout schemes for hydraulic thrust reverser control units on aircraft include split-type and integrated-type layouts. In the split-type layout, the hydraulic thrust reverser control unit is divided into two relatively small independent devices: an isolation control valve and a directional control valve. These are independently located within the engine nacelle to accommodate the limited installation space. However, this split-type layout significantly increases the difficulty of equipment development and manufacturing costs. Furthermore, the dispersed placement of the two devices results in dispersed maintenance points for the thrust reverser system, requiring ground maintenance to cover multiple areas within the nacelle, leading to poor accessibility, increased operational difficulty, and longer maintenance hours. In addition, the increased number of hydraulic sealing points after valve separation increases the risk of hydraulic oil leakage, which is detrimental to the long-term safe and stable operation of the thrust reverser system. In contrast, the integrated layout primarily places the hydraulic thrust reverser control unit as a whole within the aircraft's main landing gear bay, where there is ample installation space. This design eliminates the need for a separate hydraulic thrust reverser control unit, reducing the overall maintenance difficulty. However, when the hydraulic thrust reverser control unit is located in the main landing gear bay, the thrust reverser control lines must run from the main landing gear bay through the center wing, the leading edge of the wing, and the engine mounts to the nacelle, where they connect to the hydraulic actuators that drive the thrust reverser fairing. This results in a longer control line length and a greater increase in line weight per engine. Furthermore, due to the narrow space in the wing, the installation and maintenance of the lines within the wing are more difficult. In addition, the main landing gear bay is a non-airtight compartment, and the aircraft faces severe vibrations, dust, rain, and sudden temperature changes during takeoff and landing. If the hydraulic thrust reverser control unit is exposed to this environment for a long time, its expected service life will be significantly shortened, and the risk of failure will be significantly increased.

[0005] Therefore, there is an urgent need to design an installation device for the hydraulic thrust reverser control unit and a hydraulic thrust reverser control unit installed using the installation device, which can simplify the piping from the hydraulic thrust reverser control unit to the engine nacelle while integrating the structure of the hydraulic thrust reverser control unit. Summary of the Invention

[0006] The present invention was made in view of the above-mentioned problems, and its purpose is to provide an installation device for a hydraulic thrust reverser control unit and a hydraulic thrust reverser control unit installed using the installation device, which can simplify the piping from the hydraulic thrust reverser control unit to the engine nacelle while integrating the structure of the hydraulic thrust reverser control unit.

[0007] To achieve the above objectives, the present invention provides an installation device for a hydraulic thrust reverser control unit, comprising: a first frame and a second frame, the first frame and the second frame being disposed within a rear mounting section of an aircraft pylon and spaced apart in the flight direction of the aircraft; and a support member, the support member being connected to the first frame and the second frame and extending along the flight direction between the first frame and the second frame, the support member supporting the hydraulic thrust reverser control unit from below between the first frame and the second frame.

[0008] According to the mounting device of the hydraulic thrust reverser control unit of the present invention, the hydraulic thrust reverser control unit can be installed in the space within the rear mounting section of the aircraft sling, thereby enabling integrated configuration of the hydraulic thrust reverser control unit. Furthermore, since the distance between the sling and the engine nacelle is relatively short, the pipeline distance from the hydraulic thrust reverser control unit to the engine nacelle can be shortened, simplifying the pipeline laying operation.

[0009] Furthermore, the mounting device for the hydraulic thrust reverser control unit of the present invention preferably includes a mounting base that is connected to the support member from above and supports the hydraulic thrust reverser control unit from below, wherein the dimension of the mounting base in the spanwise direction of the aircraft decreases from front to rear in the heading direction.

[0010] Therefore, the hydraulic thrust reverser control unit can be installed via the mounting base, which improves the compatibility with hydraulic thrust reverser control units of different specifications. Furthermore, the mounting base is designed according to the shape of the suspended installation section, making it easy to install into the suspended installation section.

[0011] Furthermore, in the mounting device for the hydraulic thrust control unit of the present invention, it is preferable that the mounting base has a drain port extending through in the vertical direction.

[0012] This prevents the accumulation of hydraulic oil from leaking from the hydraulic thrust reverser control unit and avoids contamination of the hydraulic thrust reverser control unit.

[0013] Furthermore, in the mounting device of the hydraulic thrust reverser control unit of the present invention, it is preferable that the first frame and the second frame are disposed on the front side of the heading in the rear mounting section, and the portions of the first frame and the second frame located above the support are arranged parallel to each other.

[0014] This allows for a further reduction in the piping distance from the hydraulic thrust reverser control unit to the engine nacelle, and enables installation in the relatively large space of the hoisted mounting section.

[0015] Furthermore, in the mounting device of the hydraulic thrust reverser control unit of the present invention, it is preferable that the outer peripheries of the first frame and the second frame are sealed to the skin of the rear mounting section.

[0016] This prevents dust, water droplets, and other contaminants in the air from polluting the hydraulic thrust control unit.

[0017] Furthermore, the present invention also provides a hydraulic thrust reverser control unit, which is installed on the aft mounting section of an aircraft pylon via the aforementioned hydraulic thrust reverser control unit mounting device. The hydraulic thrust reverser control unit includes a unit body, and multiple hydraulic interfaces and multiple electrical interfaces are provided on multiple surfaces of the unit body. Among the multiple electrical interfaces or the multiple hydraulic interfaces, the interfaces with lower maintenance requirements are provided on the surface of the unit body located on the forward side of the multiple surfaces, while the interfaces with higher maintenance requirements are provided on the surface of the unit body located on the surface other than the forward side of the multiple surfaces.

[0018] According to the hydraulic thrust reverser control unit of the present invention, the interface with lower maintenance requirements is located on the front side of the rear-mounted section, which is more difficult to access, while the interface with higher maintenance requirements is located on other directional sides. This allows for easy maintenance of the interface with higher maintenance requirements when the hydraulic thrust reverser control unit is installed on the rear-mounted section of the aircraft.

[0019] Furthermore, in the hydraulic thrust control unit of the present invention, it is preferable that the hydraulic interface and the electrical interface are located on different surfaces of the unit body.

[0020] Therefore, in cases such as hydraulic oil leakage from the hydraulic interface, it can prevent the hydraulic oil from coming into contact with the electrical interface, thereby preventing adverse situations such as the hydraulic oil being ignited by an electric spark, and improving safety.

[0021] Furthermore, the hydraulic thrust reverser control unit of the present invention preferably includes an operating handle that is rotatable about the spanwise direction of the aircraft, and when viewed along the heading, the operating handle is located on one side of the spanwise direction relative to the diagonal strut connecting the front mounting section and the rear mounting section in the sling.

[0022] This allows for smooth operation of the control handle.

[0023] Furthermore, the hydraulic thrust control unit of the present invention preferably includes a liquid collection box that opens upward and is connected to the support member from below.

[0024] Therefore, in the event of hydraulic oil leakage from the hydraulic interface, the leaked hydraulic oil can be collected to prevent the hydraulic oil from contaminating the hydraulic thrust control unit.

[0025] Furthermore, in the installation device of the hydraulic thrust control unit of the present invention, it is preferred that the liquid collection box is also connected to the first frame and the second frame, and the liquid collection box is sealed to the support member, the first frame, and the second frame.

[0026] This prevents the hydraulic oil collected in the collection box from leaking out and contaminating the hydraulic thrust control unit. Attached Figure Description

[0027] Figure 1 This is a perspective view showing the support components and mounting base in the mounting device for the hydraulic thrust reverser control unit.

[0028] Figure 2 This is a perspective view showing the first and second frames in the mounting assembly of the hydraulic thrust reverser control unit.

[0029] Figure 3 This is a bottom view of the mounting base.

[0030] Figure 4 This is a side view of the mounting base.

[0031] Figure 5 This is a 3D view of the mounting base.

[0032] Figure 6 This is a three-dimensional view showing the structure of the liquid collection box.

[0033] Figure 7 This is a perspective view showing the structure of the hydraulic thrust reverser control unit.

[0034] Figure 8 From and Figure 7 A perspective view of the structure of the hydraulic thrust reverser control unit as viewed from the opposite side.

[0035] Figure 9 This is a schematic diagram showing the structure of the suspension without the hydraulic thrust reverser control unit installed.

[0036] Figure 10 This is a schematic diagram showing the structure of the suspension when the hydraulic thrust reverser control unit is installed.

[0037] Figure 11 This is a schematic diagram showing the structure of the rear mounting section with the hydraulic thrust reverser control unit installed, where the diagonal bracing is omitted.

[0038] Figure 12 Is Figure 11 The diagram of the diagonal brace is shown based on this.

[0039] Figure 13 This diagram illustrates the oil circuit connection between the hydraulic thrust reverser control unit and the nacelle thrust reverser actuator in this embodiment, and also shows the structure of the hydraulic thrust reverser control unit in this embodiment.

[0040] Figure 14 It is shown as Figure 13The diagram shows the improved hydraulic thrust reverser control unit based on the structure of the hydraulic thrust reverser control unit and the oil circuit connection between the hydraulic thrust reverser control unit and the nacelle thrust reverser actuator.

[0041] (Symbol Explanation)

[0042] 110 Supporting components; 111 Support mounting part; 112 Frame connection part; 120 Mounting base; 121 Mounting surface; 121a drain port; 121b mounting hole; 122 Support surface; 123 Mounting pins; 130 First Frame; 131 First upper frame; 132 First lower frame; 140 Second Frame; 141 Second upper frame; 142 Second lower frame; 200 hydraulic thrust reverser control unit; 210 Unit Main Body; 211 Hydraulic interface; 212 EWIS interface; 212a is an uncommon EWIS interface; 212b commonly uses the EWIS interface; 220 stent; 230 collection box; 231 Box body; 231a Opening; 232 Flange; 300 (aircraft-mounted) rear installation section; 310 Seals; 400 (aircraft-mounted) front mounting section; 500 diagonal brace. Detailed Implementation

[0043] The hydraulic thrust reverser control unit mounting device (hereinafter referred to as the mounting device) and the hydraulic thrust reverser control unit according to an embodiment of the present invention will now be described with reference to the accompanying drawings.

[0044] The mounting device of this embodiment is used to mount the hydraulic thrust reverser control unit 200 to the aircraft pylon, and more specifically, to mount the hydraulic thrust reverser control unit 200 to the aft mounting section 300 located on the trailing edge of the wing in the aircraft pylon.

[0045] like Figure 1 and Figure 2 As shown, the installation device of this embodiment includes a support 110, a mounting base 120, a first frame 130, and a second frame 140.

[0046] In this embodiment, the mounting device includes two identical support members 110, which are arranged along the span of the aircraft and positioned vertically at the midpoints of the first frame 130 and the second frame 140. Furthermore, the two support members 110 are respectively configured such that their length direction is inclined relative to the aircraft's heading; more specifically, as shown... Figure 1 As shown, the two support members 110 are configured such that the spacing in the spanwise direction gradually decreases from front to back in the heading direction, and preferably, the two support members 110 are configured symmetrically with respect to the heading direction.

[0047] The support member 110 includes a support mounting portion 111 and a frame connection portion 112. The support mounting portion 111 is a flat plate that extends in the heading and span directions. The upper plate surface of the support mounting portion 111 is connected to the mounting base 120 to support the mounting base 120, and the lower plate surface of the support mounting portion 111 is connected to the liquid collection box 230, which will be described later.

[0048] The frame connection portion 112 is a flat plate that extends in both the yaw and vertical directions. The plate surface is arranged vertically. One end of the support mounting portion 111, extending in the longitudinal direction, is connected to one side of the plate surface at approximately the midpoint of the vertical direction of that side's plate surface. The other side of the plate surface is connected to the skin of the hanging rear mounting section 300. Here, both the support mounting portion 111 and the frame connection portion 112 are, for example, made of metal materials such as aluminum alloy and are connected by welding.

[0049] like Figures 3 to 5 As shown, in this embodiment, the mounting base 120 is generally formed as a hollow box, and its spanwise dimension gradually decreases from front to back in the flight direction, while its vertical dimension gradually increases. In other words, the mounting base 120 is formed into a shape that is wider at the front and narrower at the back, and lower at the front and higher at the back. Furthermore, it is preferable that the spanwise dimension of the mounting base 120 gradually decreases from top to bottom in the vertical direction, that is, it is formed into a shape that is wider at the top and narrower at the bottom.

[0050] Mounting base 120 includes mounting surface 121 and support surface 122. Mounting surface 121 is formed such that its dimension in the span direction gradually decreases from front to back, and mounting surface 121 is configured to extend upward from front to back, that is, the rear end of mounting surface 121 is higher than the front end.

[0051] Furthermore, a drain port 121a is formed at the center of the mounting surface 121, which penetrates the mounting surface 121 vertically, allowing liquid to pass through the drain port 121a and enter the collection box 230. Multiple drain ports (e.g., [missing information]) are formed radially outward from the drain port 121a. Figure 5 The four mounting holes 121b shown are for fasteners to pass through in order to mount the hydraulic thrust control unit 200 to the mounting base 120.

[0052] In this embodiment, the mounting base 120 has two support surfaces 122 arranged opposite each other in the spanwise direction. The upper ends of these two support surfaces 122 are connected to the mounting surface 121 from both sides in the spanwise direction, and the lower ends are connected to the support member 110. The dimension of the support surface 122 in the vertical direction is larger than the dimension of the portion of the frame connection portion 112 located above the support mounting portion 111.

[0053] In addition, such as Figure 3 and Figure 5 As shown, a mounting foot 123 is provided at the lower end of the support surface 122. The mounting foot 123 is formed as a flat plate extending longitudinally at the lower end of the support surface 122. It abuts against the upper plate surface of the support mounting part 111 and is connected to the support mounting part 111, for example, by fasteners.

[0054] Furthermore, the mounting foot 123 can be a separate component and fixed to the lower end of the support surface 122 by a suitable connection method, or it can be formed by bending a portion of the lower end of the support surface 122 90 degrees to one side in the expansion direction. Additionally, in Figure 3 and Figure 5 The image shows the mounting foot 123 extending inward relative to the support surface 122, but the mounting foot 123 can also extend outward relative to the support surface 122.

[0055] The first frame 130 is also made of a metal material such as aluminum alloy, and includes a first upper frame 131 located above the support mounting portion 111 in the support member 110 and a first lower frame 132 located below it. The two ends of the first upper frame 131 and the first lower frame 132 in the spanwise direction are respectively connected to the frame connecting portion 112 of the support member 110. Specifically, the two ends of the lower portion of the first upper frame 131 in the spanwise direction are respectively connected to the portion of the frame connecting portion 112 located above the support mounting portion 111, and the two ends of the upper portion of the first lower frame 132 in the spanwise direction are respectively connected to the portion of the frame connecting portion 112 located below the support mounting portion 111. Furthermore, the upper ends of the first lower frame 132 are connected to the lower plate surface of the support mounting portion 111 of the support member 110 on both sides in the spanwise direction, the lower ends of the first upper frame 131 are connected to the upper plate surface of the support mounting portion 111 on both sides in the spanwise direction, and the upper ends of the first lower frame 132 and the lower ends of the first upper frame 131 are connected to each other in the spanwise central portion. Thus, the support member 110 is installed between the first upper frame 131 and the first lower frame 132. Furthermore, the connection between the first upper frame 131, the first lower frame 132 and the various parts of the support member 110 can be achieved, for example, by welding, but it can also be connected by fasteners, or other connection methods can be appropriately selected according to the material or connection strength requirements.

[0056] The second frame 140 is also made of a metal material such as aluminum alloy, and its structure is similar to that of the first frame 130. It includes a second upper frame 141 located above the support mounting portion 111 in the support member 110 and a second lower frame 142 located below it. The connection method between the second upper frame 141 and the second lower frame 142 in the second frame 140 and the support member 110 is the same as the connection method between the first upper frame 131 and the first lower frame 132 in the first frame 130 and the support member 110, and will not be repeated here.

[0057] In this embodiment, the first frame 130 and the second frame 140 are arranged along the heading on the suspended aft mounting section 300, positioned near the heading side within the aft mounting section 300. Furthermore, the first upper frame 131 and the second upper frame 141 are configured parallel to each other; "parallel" here means that when viewed along the spanwise direction, the first upper frame 131 and the second upper frame 141 are completely parallel or approximately parallel. Therefore, compared to the case where the first upper frame 131 is inclined relative to the second upper frame 141, a larger space is created between the first upper frame 131 and the second upper frame 141 along the heading, providing ample space for the installation of the hydraulic thrust reverser control unit 200 and increasing the degree of freedom in the installation of the hydraulic thrust reverser control unit 200 within the aft mounting section 300.

[0058] Furthermore, the yaw distance between the first upper frame 131 and the second upper frame 141 is greater than the yaw dimension of the hydraulic thrust reverser control unit 200, and the vertical dimension of the first upper frame 131 and the second upper frame 141 is greater than the sum of the vertical dimensions of the mounting base 120 and the hydraulic thrust reverser control unit 200. This ensures that a space is formed between the first upper frame 131 and the second upper frame 141 to accommodate the installation of the hydraulic thrust reverser control unit 200.

[0059] Furthermore, the first lower frame 132 can be configured to be inclined relative to the second lower frame 142, and the degree of inclination can be specifically adjusted according to the overall force transmission requirements of the skin of the rear mounting section 300. This allows the hydraulic thrust reverser control unit 200 to be installed in the space between the first upper frame 131 and the second upper frame 141, while simultaneously meeting the force transmission support requirements for the skin by adjusting the configuration of the first lower frame 132 and the second lower frame 142. Additionally, it is preferable that the lower ends of the first lower frame 132 and the second lower frame 142 are shaped to have good aerodynamic performance, thereby giving the skin attached to the lower ends of the first lower frame 132 and the second lower frame 142 a shape with good aerodynamic performance.

[0060] Furthermore, in this embodiment, such as Figure 2 As shown, the upper ends of the first frame 130 and the second frame 140 are connected to the seal 310 in the aft mounting section 300 of the aircraft pylon, and can be connected to the skin of the aft mounting section 300 via the seal 310, thereby preventing dust or water droplets in the air from contacting the hydraulic thrust reverser control unit 200 and affecting its function. Furthermore, preferably, the outer peripheries of both the first frame 130 and the second frame 140 are connected to the skin via the seal 310.

[0061] Furthermore, in this embodiment, the first frame 130 and the second frame 140 are additional frames provided in the suspended rear mounting section 300. However, the first frame 130 and the second frame 140 may also be formed by adjusting a part of the original frame structure in the rear mounting section 300 according to the above configuration and shape.

[0062] like Figure 7 and Figure 8 As shown, the hydraulic thrust control unit 200 of this embodiment is an integrated hydraulic thrust control unit 200, which includes a unit body 210, a bracket 220 and a liquid collection box 230.

[0063] The unit body 210 has hydraulic oil flow channels machined inside, and integrates components such as isolation control valve core assembly, directional control valve core assembly, and pressure regulating valve core assembly to realize the on / off, reversal, pressure regulation and safety protection of hydraulic oil.

[0064] The unit body 210 is equipped with a hydraulic interface 211 and an electrical wiring interconnection system interface (referred to as "EWIS interface 212"). The EWIS interface 212 is an interface for inputting and outputting electrical power and electrical signals to the hydraulic thrust reverser control unit 200. It is connected to a power source via a power line to provide power to various components within the unit body 210, or connected to a relevant control system via a signal line to send and receive control signals to control various components within the unit body 210.

[0065] In this embodiment, the EWIS interface 212 includes a commonly used EWIS interface 212b and a rarely used EWIS interface 212a. The commonly used EWIS interface 212b refers to the interface with high maintenance requirements, such as cable disassembly or visual inspection, for example, the interface used for power supply, receiving control commands, outputting status feedback, and performing fault diagnosis. The rarely used EWIS interface 212a refers to the interface with relatively low maintenance requirements, for example, the interface used for calibration and debugging, program writing, etc.

[0066] In this embodiment, such as Figure 7 and Figure 8 As shown, the commonly used EWIS interface 212b is located on the rear side of the unit body 210, that is, in the heading direction, it is located relatively rearward, while the unused EWIS interface 212a is located on the forward side of the unit body 210. Therefore, the commonly used EWIS interface 212b can be accessed from between the first frame 130 and the second frame 140, facilitating maintenance and repair of the commonly used EWIS interface 212b. Furthermore, by placing the unused EWIS interface 212a on the less accessible forward side, the flexibility in configuring the other interfaces on the unit body 210 is increased.

[0067] Hydraulic interface 211 is a connection port for inputting and outputting hydraulic oil to the hydraulic thrust reverser control unit 200. It connects to the aircraft's hydraulic system and thrust reverser actuator via hydraulic oil lines to form a hydraulic circuit. In this embodiment, as... Figure 7 As shown, four hydraulic ports 211 are disposed on the spanwise side of the unit body 210, and one hydraulic port 211 is disposed on the aftward side of the unit body 210. However, the arrangement of the hydraulic ports 211 is not limited to... Figure 7 As shown, it is sufficient to set the unit body 210 on a surface different from the surface set by the EWIS interface 212.

[0068] Therefore, the hydraulic interface 211 and the EWIS interface 212 are located on different surfaces on the unit body 210. Even if hydraulic oil leaks at the hydraulic interface 211, the leaked hydraulic oil will not come into contact with the cable connected to the EWIS interface 212, preventing the leaked hydraulic oil from burning due to electric sparks and causing safety hazards.

[0069] like Figure 6 As shown, the liquid collection box 230 includes a box body 231 with an upward opening 231a and a flange 232 extending outward from the box body 231. The flanges 232 extending to both sides abut against the lower plate surface of the support mounting portion 111 from below and are connected to the support mounting portion 111, for example, by fasteners, thereby mounting the liquid collection box 230 to the support member 110 from below.

[0070] When viewed vertically, the opening 231a of the housing 231 is configured to have a portion that does not overlap with the mounting base 120 in the flight direction. More specifically, the opening 231a of the housing 231 has portions located in front of and behind the mounting base 120 in the flight direction. Furthermore, when viewed vertically, the opening 231a of the housing 231 at least partially overlaps with the drain port 121a on the mounting base 120, and preferably the drain port 121a is located within the opening 231a. Thus, in the event of hydraulic oil leakage from the unit body 210 or the hydraulic interface 211, the leaked and dripping hydraulic oil can be effectively recovered by the collection box 230, preventing hydraulic oil from adhering to other structures and causing contamination.

[0071] Furthermore, preferably, the flanges 232 on both sides of the liquid collection box 230 are connected to the first frame 130 and the second frame 140, and the connections between the flanges 232 and the first frame 130, the second frame 140, and the support member 110 are sealed with sealant. Therefore, even if the hydraulic oil collected inside the box 231 leaks out due to aircraft turbulence, the leaked hydraulic oil will not leak out from the gaps at the connections and cause contamination.

[0072] Furthermore, although not shown, the hydraulic thrust reverser control unit 200 also includes a restraint handle, which is equivalent to the operating handle in this embodiment. It is connected to various valve core assemblies within the unit body 210 via a linkage or other mechanism, and is rotatable about its spanwise direction. This rotation drives the various valve core assemblies, switching the hydraulic circuit within the unit body 210 between on and off states. In this embodiment, the restraint handle is positioned above the unit body 210 and rearward in the yaw direction. Furthermore, the restraint handle is located on one side of the spanwise direction relative to the diagonal brace 500 connecting the rear mounting section 300 frame to the front mounting section 400. Therefore, even if the hydraulic thrust reverser control unit 200 is installed inside the pylon, the rotation of the restraint handle is not affected by the diagonal brace 500.

[0073] The following describes an example of the hydraulic thrust reverser control unit 200 mounting device and the method of mounting the hydraulic thrust reverser control unit 200 by suspension.

[0074] When installing the hydraulic thrust reverser control unit 200 mounting device onto the suspended rear mounting section 300, firstly, the upper ends of the first upper frame 131 and the second upper frame 141 are fixed to the main crossbeam of the rear mounting section 300 frame. Then, the two support members 110 are connected to the first upper frame 131 and the second upper frame 141 from below, respectively. Specifically, the frame connecting portion 112 of the support member 110 is connected to the first upper frame 131 and the second upper frame 141 from both sides of the span, and at the same time, the support mounting portion 111 is connected to the first upper frame 131 and the second upper frame 141 from below.

[0075] Next, the first lower frame 132 and the second lower frame 142 are installed from below to the first upper frame 131 and the second upper frame 141 respectively, and the first lower frame 132 and the second lower frame 142 are connected to the frame connection part 112 and the support mounting part 111 of the support member 110 respectively.

[0076] Then, the mounting base 120 is installed from above to the support mounting part 111 using fasteners, the unit body 210 is installed to the mounting base 120, and the liquid collection box 230 is installed from below to the support mounting part 111, thereby installing the hydraulic thrust control unit 200 into the hanger.

[0077] At this time, the hydraulic interface 211 on the main body 210 is connected to the hydraulic actuator in the engine nacelle via a hydraulic oil pipeline. The hydraulic oil pipeline is laid in a way that, for example, it runs from the rear mounting section 300 through the front mounting section 400 inside the suspension and into the engine nacelle, thereby shortening the pipeline path for hydraulic oil delivery and reducing the pipeline weight.

[0078] Furthermore, since the distance between the installation location of the hydraulic thrust reverser control unit 200 and the engine nacelle is shortened, the oil circuit connection between the hydraulic thrust reverser control unit 200 and the thrust reverser actuator in the nacelle can be optimized.

[0079] Specifically, in Figure 13 The hydraulic thrust reverser control unit 200 and the nacelle thrust reverser actuator of this embodiment are shown in the oil circuit connection method. Figure 14 The diagram illustrates the hydraulic thrust reverser control unit, which serves as the improved basis for the hydraulic thrust reverser control unit 200, and the hydraulic circuit connection between this hydraulic thrust reverser control unit and the nacelle thrust reverser actuator. It should be noted that... Figure 14The hydraulic thrust reverser control unit shown is also a hydraulic thrust reverser control unit that can be installed in the aft mounting section of the aircraft. However, for ease of explanation, the following description will use the example of a hydraulic thrust reverser control unit located in a position relatively far from the engine nacelle, such as the main flight deck. Figure 14 As shown, between the hydraulic thrust reverser control unit, which forms the basis of the improvement, and the nacelle thrust reverser actuator, oil circuits are provided in the hydraulic thrust reverser control unit, more specifically, between the directional control valve and the third lock and the hydraulic actuator. Hydraulic oil from the directional control valve is simultaneously delivered to the third lock and the hydraulic actuator. This is because the distance between the hydraulic thrust reverser control unit and the thrust reverser actuator is relatively large, requiring direct delivery of hydraulic oil to the thrust reverser actuator to ensure the oil pressure used for performing the thrust reverser operation and the third lock unlocking action.

[0080] And such Figure 13 As shown, in this embodiment, the oil circuit (supply circuit) from the directional control valve to the third lock is eliminated between the hydraulic thrust reverser control unit 200 and the nacelle thrust reverser actuator. Instead, an oil circuit is added between the hydraulic actuator and the third lock. This allows the hydraulic oil supplied to the hydraulic actuator to also be supplied to the third lock to unlock it. Since the distance between the hydraulic thrust reverser control unit 200 and the hydraulic actuator and the third lock is shorter, it is easier to ensure the oil pressure supplied to the hydraulic actuator, thereby improving the reliability and stability of the oil supply to the third lock via the hydraulic actuator. Furthermore, since the length of the eliminated oil supply circuit between the directional control valve and the third lock is typically much greater than the length of the added oil circuit between the hydraulic actuator and the third lock, the overall weight of the piping is reduced.

[0081] Furthermore, since the oil supply line from the directional control valve to the third lock has been eliminated, for example, it is possible to eliminate... Figure 14 The hydraulic interface is obtained by the double-dotted line border. Figure 13 The structure of the thrust reverser control unit can be further simplified, and the space occupied by the thrust reverser control unit can be reduced, making it more suitable for installation in smaller installation spaces such as the rear mounting section of the aircraft pylon.

[0082] (Main effects of this implementation method)

[0083] According to the mounting device and hydraulic thrust reverser control unit 200 of this embodiment, by installing the integrated hydraulic thrust reverser control unit 200 in the aft mounting section of the aircraft pylon via the hydraulic thrust reverser control unit 200 mounting device, the space in the aft mounting section can be utilized to install the integrated hydraulic thrust reverser control unit 200. This avoids the increased maintenance difficulty caused by the separate design of the hydraulic thrust reverser control unit 200, while shortening the distance of the hydraulic oil pipeline from the hydraulic thrust reverser control unit 200 to the engine nacelle, reducing the weight increase caused by excessively long hydraulic oil pipelines, and lowering the difficulty of pipeline laying and maintenance. In addition, the airtightness inside the pylon is relatively good, reducing the adverse effects of dust, moisture, etc. in the air on the hydraulic thrust reverser control unit 200.

[0084] In addition, by adopting a front-wide and rear-narrow structure for the installation device, the space within the rear installation section can be fully utilized for installation, thereby improving the installation adaptability of the installation device.

[0085] Furthermore, on the main body of the unit, the EWIS interface, which requires higher maintenance, is located on an easily accessible side, while the EWIS interface, which requires relatively less maintenance, is located on a less accessible side. Based on the EWIS interface placement, the hydraulic interface is located on a different side than the EWIS interface. This reduces the impact of hydraulic oil leakage from the hydraulic interface on the EWIS cable and lowers the risk of leaked hydraulic oil igniting.

[0086] The present invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited to the above embodiments.

[0087] For example, in the above embodiment, the case of using two support members to support the mounting base for mounting the HCU was described as an example, but the form of the support members is not limited to this. The support member can also be a single flat plate with dimensions larger than the mounting base in both spanwise and yaw directions, and is disposed between the first upper frame and the first lower frame, and the second upper frame and the first lower frame. This support member can be connected to the mounting base by fasteners to support the mounting base, and can also be connected to the liquid collection box by fasteners to install the liquid collection box below the unit body. In this case, an opening can be provided on the flat plate of the support member to allow leaked hydraulic oil to flow into the liquid collection box.

[0088] Furthermore, in the above embodiment, the case in which the first frame includes a separate first upper frame and a first lower frame and the second frame includes a separate second upper frame and a second lower frame was described as an example. However, the first frame and the second frame can also be an integral frame. In this case, in order to form a space for installing the HCU between the upper parts of the first frame and the second frame, the upper parts of the first frame and the second frame are arranged in parallel, and the lower part can be processed into a shape suitable for supporting the skin or a shape with good aerodynamic performance by bending or other processing.

[0089] It should be understood that within the scope of this invention, the various parts of the embodiments can be freely combined, or the various parts of the embodiments can be appropriately modified or omitted.

Claims

1. An installation device for a hydraulic thrust reverser control unit, characterized in that, include: A first frame and a second frame are disposed within the rear mounting section of the aircraft's sling and are spaced apart in the aircraft's heading. as well as A support member, which is connected to the first frame and the second frame, and extends along the heading between the first frame and the second frame. The support member supports the hydraulic thrust control unit from below between the first frame and the second frame.

2. The mounting device for the hydraulic thrust reverser control unit according to claim 1, characterized in that, It also includes a mounting base that connects to the support member from above and supports the hydraulic thrust reverser control unit from below. The size of the mounting base in the spanwise direction of the aircraft decreases from front to back in the heading direction.

3. The mounting device for the hydraulic thrust reverser control unit according to claim 2, characterized in that, The mounting base has a drain port that extends vertically through it.

4. The mounting device for the hydraulic thrust reverser control unit according to any one of claims 1 to 3, characterized in that, The first frame and the second frame are disposed in the rear mounting section on the forward side of the heading. The portions of the first frame and the second frame located above the support are arranged parallel to each other.

5. The mounting device for the hydraulic thrust reverser control unit according to any one of claims 1 to 3, characterized in that, The outer peripheries of the first frame and the second frame are sealed to the skin of the rear mounting section.

6. A hydraulic thrust reverser control unit, mounted on the aft mounting section of an aircraft pylon via the mounting device of any one of claims 1 to 5, characterized in that, The hydraulic thrust reverser control unit includes a unit body, on which multiple hydraulic interfaces and multiple electrical interfaces are provided on multiple surfaces. Of the plurality of electrical interfaces or the plurality of hydraulic interfaces, the interfaces with lower maintenance requirements are located on the face of the unit body located on the forward side of the plurality of surfaces, while the interfaces with higher maintenance requirements are located on the face of the unit body located on the surface other than the forward side of the plurality of surfaces.

7. The hydraulic thrust reverser control unit according to claim 6, characterized in that, The hydraulic interface and the electrical interface are located on different surfaces of the unit body.

8. The hydraulic thrust reverser control unit according to claim 6 or 7, characterized in that, It also includes an operating handle that is rotatable about the span of the aircraft. When viewed along the heading, the operating handle is located on one side of the span direction relative to the diagonal brace connecting the front and rear mounting sections in the suspension.

9. The hydraulic thrust reverser control unit according to claim 6 or 7, characterized in that, It also includes a liquid collection box, which opens upward and is connected to the support member from below.

10. The hydraulic thrust reverser control unit according to claim 9, characterized in that, The liquid collection box is also connected to the first frame and the second frame. The liquid collection box is sealed to the support member, the first frame, and the second frame.

Images