Aircraft tail structure on-aircraft-engine-test-bed installation process

Abstract

The application discloses an installation process of an aircraft tail structure on an aero-engine test bench, which comprises the following steps: realizing the installation process of position alignment, drilling, installation and dismounting and reinstallation of the aircraft tail structure. The aircraft tail structure is taken as a reference, and the drilling work of bolt holes of the aircraft tail structure is completed by taking the combination of the aircraft tail structure installation unit and the reference frame as a reference, so that the accuracy of the new combination formed by the installation and connection of the aircraft tail structure, the aircraft tail structure installation unit and the reference frame is ensured, the installation process of position alignment, drilling, installation and dismounting and reinstallation of the aircraft tail structure is realized, and the problem that the installation error cannot be accurately realized due to the preset installation process hole of the aircraft tail structure in the production is solved.

Description

Technical Field

[0001] This invention relates to a process for installing an aircraft tail structure on an aero-engine test bench, belonging to the field of aero-engine testing and installation technology. Background Technology

[0002] When conducting joint tests of an aero-engine and an aircraft tail structure, the aircraft tail structure needs to be installed on the test bench at the aero-engine location. The aircraft tail structure is usually installed using bolts and nuts for detachable fixing. Current technology involves pre-setting installation process holes in the aircraft tail structure during production, which leads to errors during actual installation and prevents accurate installation.

[0003] To address the aforementioned technical problems, this invention provides a process for installing an aircraft tail structure on an aero-engine test bench.

[0004] The present invention is achieved through the following technical solutions.

[0005] This invention provides a process for installing an aircraft tail structure on an aero-engine test bench, comprising:

[0006] The process of aligning, drilling, installing, disassembling, and reinstalling the tail structure of an aircraft.

[0007] The process includes six steps: assembly of the reference frame, installation of the aircraft tail structure adapter on the platform, installation of the aircraft tail structure pitch force measurement structure on the platform, assembly of the aircraft tail structure and its installation unit, installation of the aero engine on the platform, and installation of the aircraft tail structure on the platform.

[0008] The assembly steps of the reference frame are as follows: weld the upper beam and lower beam of the reference frame, and install the upper beam and lower beam of the reference frame to the left transition plate and the right transition plate respectively with bolts, so as to serve as the installation reference for other components.

[0009] The installation steps for the aircraft tail structure adapter frame are as follows: First, use bolts to initially install the upper beams of the aircraft tail structure adapter frame on both sides of the aero-engine test bench. Then, detachably and securely connect the left and right adapter plates of the reference frame to the upper beams of the aircraft tail structure adapter frame using bolts. Next, detachably and securely connect the lower beams of the aircraft tail structure adapter frame on both sides to the left and right adapter plates of the reference frame using bolts. Finally, securely connect the lower beams of the aircraft tail structure adapter frame to the aero-engine test bench using bolts.

[0010] The installation steps for the aircraft tail structure pitch force measurement structure on the test bench are as follows: According to the model diagram of the aircraft tail structure installation on the aero-engine test bench, connect the aircraft tail structure pitch force measurement structures A and B to the reference frame. Then, the assembly of the aircraft tail structure pitch force measurement structures A and B and the reference frame is detachably and fixedly connected to the upper beam and lower beam of the aircraft tail structure adapter frame by bolts.

[0011] The assembly steps of the aircraft tail structure and its mounting unit are as follows: According to the model diagram of the aircraft tail structure on the aircraft engine test bench, two aircraft tail structure mounting units are detachably and fixedly connected to the left and right adapter plates of the reference frame. Taking the combination of the aircraft tail structure mounting units and the reference frame as the reference, the drilling of bolt holes for the aircraft tail structure is completed. The aircraft tail structure is connected to the aircraft tail structure mounting units with bolts and forms a new combination with the reference frame. At this time, the aircraft tail structure, the aircraft tail structure mounting units and the reference frame are removed from the upper beam and the lower beam of the aircraft tail structure adapter frame.

[0012] The steps for installing the aero-engine on the test rig are as follows: Based on the model diagram of the aero-engine test rig installation structure of the aircraft tail structure, the aero-engine is installed on the test rig, and aero-engine rig mounting seats are installed on two spaced-apart test rigs to support and stabilize the aero-engine.

[0013] The steps for installing the aircraft tail structure on the test bench are as follows: Based on the structural model diagram of the aircraft tail structure installed on the aero-engine test bench, the new assembly formed by the aircraft tail structure, the aircraft tail structure installation unit, and the reference frame in step four is connected to the mechanical interfaces of the aircraft tail structure pitch force measurement unit A and the aircraft tail structure pitch force measurement unit B with the upper beam and lower beam of the aircraft tail structure adapter frame, respectively, using bolts.

[0014] The beneficial effects of this invention are as follows: the aircraft tail structure uses the combination of the aircraft tail structure installation unit and the reference frame as a reference to complete the drilling of the bolt holes of the aircraft tail structure, ensuring the accuracy of the aircraft tail structure, the aircraft tail structure installation unit and the reference frame when they are installed and connected to form a new combination. This realizes the installation process of aligning the position of the aircraft tail structure, drilling, installing and disassembling, and reinstalling, and solves the problem that the direct pre-setting of installation process holes during the production of the aircraft tail structure leads to errors in actual installation and cannot be accurately installed. Attached Figure Description

[0015] Figure 1 This is a model diagram of the installation structure of the present invention;

[0016] Figure 2 This is a schematic diagram of the assembly of the reference frame of the present invention;

[0017] Figure 3 yes Figure 1 Schematic diagram of Zone I;

[0018] Figure 4 This is a schematic diagram of the installation of the lower beam of the aircraft tail structure adapter frame of the present invention;

[0019] Figure 5 yes Figure 3 Schematic diagram of Zone II;

[0020] In the diagram: 1-Aircraft engine; 2-Aircraft engine rig mounting base; 3-Test rig; 4-Reference frame; 5-Aircraft tail structure mounting unit; 6-Aircraft tail structure; 7-Left side adapter plate; 8-Upper beam; 9-Right side adapter plate; 10-Lower beam; 11-Aircraft tail structure adapter upper beam; 12-Aircraft tail structure pitch force measurement structure A; 13-Aircraft tail structure adapter lower beam; 14-Aircraft tail structure pitch force measurement unit B; 15-Metal pad; 16-Test rig upper mounting base; 17-Adapter upper beam lower mounting base. Detailed Implementation

[0021] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0022] like Figures 1 to 5 As shown.

[0023] The present application discloses a process for installing an aircraft tail structure on an aero-engine test bench, including:

[0024] Step 1, assembling the reference frame: Based on the structural model diagram of the aircraft tail structure 6 installed on the aero-engine test bench, precisely weld the upper beam 8 and lower beam 10 of the reference frame 4. Install the upper beam 8 and lower beam 10 of the reference frame 4 to the left transition plate 7 and the right transition plate 9 respectively with bolts. During the installation process, strictly control the spatial dimensions of the reference frame, which will serve as the installation reference for other components.

[0025] Step 2, Installation of the Aircraft Tail Structure Adapter Mount: Based on the structural model diagram of the aircraft tail structure 6 installed on the aero-engine test bench, the upper beams 11 of the aircraft tail structure adapter mounts on both sides are initially installed on the aero-engine test bench 3 using bolts. The left and right adapter plates 7 and 9 of the reference frame 4 are detachably fixed to the upper beams 11 of the aircraft tail structure adapter mounts using bolts. The lower beams 13 of the aircraft tail structure adapter mounts on both sides are detachably fixed to the left and right adapter plates 7 and 9 of the reference frame 4 using bolts. The lower beams 13 of the aircraft tail structure adapter mounts are then fixedly connected to the aero-engine test bench 3 using bolts. During installation, metal pads 15 of different thicknesses can be used to avoid deviations in test bench installation dimensions and errors in structural component processing. The reference frame 4 is then disassembled from the upper beams 11 and lower beams 13 of the aircraft tail structure adapter mounts.

[0026] Step 3: Installation of the aircraft tail structure pitch force measurement structure on the test bench: Based on the structural model diagram of the aircraft tail structure 6 installed on the aero-engine test bench, connect the aircraft tail structure pitch force measurement structure A12, the aircraft tail structure pitch force measurement unit B14, and the reference frame 4. Then, detachably fix the assembly consisting of the aircraft tail structure pitch force measurement structure A12, the aircraft tail structure pitch force measurement unit B14, and the reference frame 4 to the upper beam 11 and the lower beam 13 of the aircraft tail structure adapter frame using bolts. Disassemble the reference frame 4 from the aircraft tail structure pitch force measurement structure A12 and the aircraft tail structure pitch force measurement unit B14.

[0027] Step 4: Assemble the aircraft tail structure and its mounting units: Based on the model diagram of the aircraft tail structure 6 on the aero-engine test bench, detachably and securely connect two aircraft tail structure mounting units 5 to the left and right adapter plates 7 and 9 of the reference frame 4. Using the assembly formed by the aircraft tail structure mounting units 5 and the reference frame 4 as a reference, complete the drilling of bolt holes for the aircraft tail structure 6. Connect the aircraft tail structure 6 to the aircraft tail structure mounting units 5 with bolts and form a new assembly with the reference frame 4.

[0028] Step 5, Installing the aircraft engine on the test rig: Based on the model diagram of the aircraft tail structure 6 on the aircraft engine test rig, install the aircraft engine 1 on the test rig 3. Install the aircraft engine test rig mounting base 2 on the two symmetrically spaced test rigs 3 to support and stabilize the aircraft engine 1, so that the thrust of the aircraft engine 1 during the test is transmitted to the test rig 3 through the aircraft engine test rig mounting base 2.

[0029] Step Six: Installation of the aircraft tail structure on the test bench: Based on the structural model diagram of the aircraft tail structure 6 installed on the aero-engine test bench, the new assembly formed by the aircraft tail structure 6, the aircraft tail structure installation unit 5, and the reference frame 4 in Step Four is connected to the mechanical interfaces of the aircraft tail structure pitch force measurement unit A12 and the aircraft tail structure pitch force measurement unit B14 with the upper beam 11 and the lower beam 13 of the aircraft tail structure adapter frame using bolts.

[0030] Since the aircraft tail structure 6 is based on the assembly consisting of the aircraft tail structure mounting unit 5 and the reference frame 4, the drilling of the bolt holes of the aircraft tail structure 6 is completed. This ensures the accuracy of the aircraft tail structure 6, the aircraft tail structure mounting unit 5 and the reference frame 4 when they are installed and connected to form a new assembly. This realizes the installation process of aligning the aircraft tail structure 6, drilling, installing, disassembling and reinstalling it. This solves the problem that the aircraft tail structure is directly pre-set with installation process holes during production, which leads to errors in actual installation and makes it impossible to install accurately.

Claims

1. A process for installing an aircraft tail structure on an aero-engine test bench, characterized in that, The process includes six steps: assembly of the reference frame, installation of the aircraft tail structure adapter on the platform, installation of the aircraft tail structure pitch force measurement structure on the platform, assembly of the aircraft tail structure and its installation unit, installation of the aero engine on the platform, and installation of the aircraft tail structure on the platform. The assembly steps of the reference frame are as follows: weld the upper beam (8) and lower beam (10) of the reference frame (4), and install the upper beam (8) and lower beam (10) of the reference frame (4) to the left transition plate (7) and the right transition plate (9) respectively with bolts, so as to serve as the installation reference for other components; The steps for installing the aircraft tail structure adapter on the test bench are as follows: First, use bolts to symmetrically install the upper beams (11) of the aircraft tail structure adapter on both sides on the aero-engine test bench (3). Then, use bolts to detachably and fix the left and right adapter plates (7) and the right adapter plates (9) of the reference frame (4) to the upper beams (11) of the aircraft tail structure adapter. Use bolts to detachably and fix the lower beams (13) of the symmetrical aircraft tail structure adapter on both sides to the left and right adapter plates (7) and the right adapter plates (9) of the reference frame (4). Finally, use bolts to fix the lower beams (13) of the aircraft tail structure adapter to the aero-engine test bench (3). The installation steps of the aircraft tail structure pitch force measurement structure on the test bench are as follows: According to the model diagram of the aircraft tail structure (6) installed on the aero-engine test bench, connect the aircraft tail structure pitch force measurement structure A (12), the aircraft tail structure pitch force measurement unit B (14) and the reference frame (4). Then, the combination of the aircraft tail structure pitch force measurement structure A (12), the aircraft tail structure pitch force measurement unit B (14) and the reference frame (4) is detachably fixed to the aircraft tail structure adapter frame upper beam (11) and the aircraft tail structure adapter frame lower beam (13) by bolts. The assembly steps of the aircraft tail structure and its installation unit are as follows: According to the model diagram of the aircraft tail structure (6) on the aircraft engine test bench, two aircraft tail structure installation units (5) are detachably and fixedly connected to the left adapter plate (7) and right adapter plate (9) of the reference frame (4). Taking the combination of the aircraft tail structure installation unit (5) and the reference frame (4) as the reference, the drilling work of the bolt holes of the aircraft tail structure (6) is completed. The aircraft tail structure (6) is connected to the aircraft tail structure installation unit (5) by bolts and forms a new combination with the reference frame (4). The steps for installing the aircraft engine on the test bench are as follows: According to the model diagram of the aircraft tail structure (6) on the aircraft engine test bench, the aircraft engine (1) is installed on the test bench (3), and the aircraft engine test bench mounting base (2) is installed on the two symmetrically distributed test benches (3) to support and stabilize the aircraft engine (1). The steps for installing the aircraft tail structure on the test bench are as follows: Based on the structural model diagram of the aircraft tail structure (6) installed on the aircraft engine test bench, the new assembly formed by the aircraft tail structure (6), the aircraft tail structure installation unit (5) and the reference frame (4) in step four is connected to the mechanical interfaces of the aircraft tail structure pitch force measurement unit A (12) and the aircraft tail structure pitch force measurement unit B (14) with the upper beam (11) and the lower beam (13) of the aircraft tail structure adapter frame by bolts.

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