Aero-engine test bed

Abstract

The utility model discloses an aero-engine test bed, and belongs to the technical field of motion attitude analog simulation equipment. A center hinge bottom plate and an oil cylinder bottom plate on the lower end face of the motion platform device are fixedly connected with an equipment foundation through embedded foundation bolts, the rear end face of the plate turnover device is fixedly connected with a bearing platform foundation through embedded parts, and the motion platform device is not fixedly connected with the plate turnover device. The lower end face of a shock absorber in the vibration isolation device and the upper end face of an upper platform in the motion platform device are connected and fixed through bolts, the upper end face of the shock absorber and the lower end face of the aero-engine are connected and fixed through bolts, and the bearing platform foundation and the equipment foundation are connected into a whole. The aero-engine inclination testing device has the advantages of being large in structural bearing capacity, simple in structure, firm, stable, stable in movement, high in movement precision, safe, reliable and the like, inclination tests of different states can be carried out on an aero-engine, and the aero-engine inclination testing device is special equipment for aero-engine attitude analog simulation.

Description

Technical Field

[0001] The utility model relates to an aero-engine test bench, which belongs to the technical field of motion posture simulation equipment and is a special equipment for aero-engine simulation test, which can realize the tilt test of the aero-engine by the motion platform and reduce the resonance phenomenon between the two. Background Art

[0002] During the development of aircraft engines, various attitude tilt tests are required. During the test, resonance between the two needs to be avoided. How to solve this problem in a reasonable way is of great significance to improving the safety and reliability of engine tests. Application No. 202223532220.8 is an attitude-adjustable aircraft engine test bench with small load, complex structure, and small rotation angle. The test types for aircraft engines are relatively single, and the installation space is limited and difficult to install. The vibration generated by the aircraft engine at high speed does not affect the vibration of the test bench, and no safety protection device is designed. This is an important technical problem that needs to be solved when testing aircraft engines. Summary of the invention

[0003] In order to overcome the shortcomings of various existing engine testing technologies, the utility model provides an aircraft engine test bench, which is a special equipment for aircraft engine simulation testing. The aircraft engine test bench can perform a tilt test on the aircraft engine and reduce the resonance phenomenon caused by the engine on the motion platform during the tilt test, thereby avoiding damage to the aircraft engine and the tilt test platform and improving the success rate of the test.

[0004] An aircraft engine test bench, the center hinge bottom plate of the lower end surface of the motion platform device, the cylinder bottom plate and the equipment foundation are connected and fixed by pre-buried anchor bolts, the rear end surface of the flap device is connected and fixed to the base foundation by pre-buried parts, there is no fixed connection between the motion platform device and the flap device, the lower end surface of the vibration absorber in the vibration isolation device, the lower end surface of the vibration isolation device and the upper end surface of the upper platform in the motion platform device are connected and fixed by bolts, the upper end surface of the vibration absorber is connected and fixed to the lower end surface of the aircraft engine by bolts, the base foundation and the equipment foundation are connected as a whole, the base foundation and the positioning tool are connected to the top surface of the equipment foundation, the vibration absorber The upper end is fixed to the lower end of the aircraft engine by bolts, the center hinge bottom plate, the lower platform and the bottom plate of the lower hinge seat of the cylinder are fixed by anchor bolts, positioning fixtures and secondary pouring of the equipment foundation, the bottom plate of the lower hinge seat of the cylinder is fixed to the lower end of the lower hinge seat of the cylinder by bolts, the lower ends of the active cylinder and the auxiliary cylinder are fixed to the upper end of the lower hinge seat of the cylinder by bolts, the upper ends of the active cylinder and the auxiliary cylinder are fixed to the lower end of the upper hinge seat of the cylinder by bolts, the upper end of the upper hinge seat of the cylinder is fixed to the lower end of the upper platform by bolts, the lower end of the anti-torsion arm is fixed to the upper end of the lower platform by bolts, the upper end of the anti-torsion arm is fixed to the lower end of the anti-torsion arm hinge seat by bolts The upper end of the anti-torsion arm hinge seat is fixed with the lower end of the upper platform by bolts, the supporting foundation is fixed with the upper end of the lower platform and the lower end of the center hinge bottom plate by positioning casting through tooling, the lower end of the center hinge is fixed with the upper end of the center hinge bottom plate by bolts, the upper end of the center hinge is fixed with the lower end of the upper platform by bolts, the bottom plate of the lower hinge seat of the flap cylinder of the flap device is fixed with the foundation by casting, the lower end of the lower hinge seat of the flap cylinder is fixed with the upper end of the bottom plate of the lower hinge seat of the flap cylinder by bolts, the upper end of the lower hinge seat of the flap cylinder is fixed with the lower end of the flap cylinder by bolts, the upper end of the flap cylinder is fixed with the upper end of the flap cylinder The lower end of the hinge seat is fixed by bolts, the upper end of the hinge seat on the flap cylinder is fixed to the lower end of the flap by bolts, there are 4 sets of flaps between the base foundation and the motion platform, the upper end of the upper platform of the vibration isolation device is fixed to the lower end of the shock absorber by bolts, the upper end of the shock absorber is fixed to the lower end of the aircraft engine by bolts, the lower end of the vibration isolation device is fixed to the upper end of the upper platform by bolts, one side of the vibration isolation bar of the vibration isolation device is fixed in contact with the side of the aircraft engine, the motion platform of the servo hydraulic device has 2 active cylinders and 2 auxiliary cylinders, the 2 active cylinders are installed on one side of the Y-axis, and the 2 auxiliary cylinders are installed on the other side of the Y-axis.

[0005] The servo oil cylinder and the auxiliary oil cylinder are respectively connected to the hydraulic mechanical lock, and the active oil cylinder is connected to the servo valve block.

[0006] The aircraft engine test bench is a device that can perform tilt tests on aircraft engines. It is developed to avoid the resonance and destruction between the excitation frequency generated by the high-pressure rotor of the aircraft engine and the tilt test platform when it rotates at high speed, so that the tilt test can be carried out smoothly. When the aircraft engine is tested in horizontal, pitch, roll or compound angle attitude, the engine's high-pressure rotor speed will change differently, and its performance will also be affected accordingly, so tilt testing is an indispensable and important link.

[0007] The utility model has the characteristics of large structural load-bearing capacity, simple structure, firmness and stability, stable movement, high movement accuracy, safety and reliability, etc. It can perform tilt tests on aircraft engines in different states and is a special equipment for simulating and emulating the attitude of aircraft engines.

[0008] The aircraft engine test bench of the utility model can be widely used in military and civilian fields. The utility model has significant technical features and can perform tilt, vibration, lubrication and other tests and experiments in different states for different types of aircraft engines. The utility model can effectively reduce the harmful vibrations caused by the aircraft engine to the motion platform when rotating at high speed, ensure the safety of the aircraft engine and the motion platform, and ensure the smooth progress of the test. At the same time, it can also ensure the stability of the motion platform during static load and dynamic load movement, and improve the test efficiency of the aircraft engine to meet the test requirements of the experiment. The utility model provides strong technical support for the development of the aviation field. The utility model is designed with installation protection, which has a protective effect whether it is during the test installation or the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] When considered in conjunction with the accompanying drawings, the present invention can be more completely and better understood and many of the accompanying advantages can be easily known by referring to the detailed description below. However, the drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention, as shown in the figure:

[0010] Figure 1 It is a top view structural schematic diagram of the utility model.

[0011] Figure 2 It is a main structural schematic diagram of the utility model.

[0012] Figure 3 It is a right-side structural schematic diagram of the utility model.

[0013] Figure 4 It is a structural schematic diagram of the vibration isolation device of the utility model.

[0014] Figure 5It is a schematic diagram of the structure of the shock absorber of the utility model.

[0015] Figure 6 It is a schematic diagram of the upper platform structure of the utility model.

[0016] Figure 7 It is a schematic diagram of the central hinge structure of the utility model.

[0017] Figure 8 It is a schematic diagram of the structure of the anti-twist arm hinge seat of the utility model.

[0018] Fig. 9 The utility model is a schematic diagram of the structure of the upper hinge seat of the oil cylinder.

[0019] Fig.10 It is a schematic diagram of the anti-twist arm structure of the utility model.

[0020] Fig.11 It is a schematic diagram of the lower platform structure of the utility model.

[0021] Fig.12 It is a schematic diagram of the structure of the lower hinge seat of the oil cylinder of the utility model.

[0022] Fig.13 The utility model is a schematic diagram of the bottom plate positioning tool structure of the lower hinge seat of the oil cylinder.

[0023] Fig.14 It is a schematic diagram of the flap structure of the utility model.

[0024] Fig.15 The utility model is a schematic diagram of the upper hinge seat structure of the flap oil cylinder.

[0025] Fig.16 The utility model is a schematic diagram of the structure of the lower hinge seat of the flap oil cylinder. DETAILED DESCRIPTION

[0026] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0027] Obviously, many modifications and changes made by those skilled in the art based on the purpose of the present invention belong to the protection scope of the present invention.

[0028] Unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this utility model can be understood according to specific circumstances.

[0029] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein, including technical and scientific terms, have the same meaning as generally understood by those skilled in the art.

[0030] To facilitate the understanding of the embodiments, further explanations will be given below, and each embodiment does not constitute a limitation on the embodiments of the invention.

[0031] Example 1: Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 , Fig.14 , Fig.15 and Fig.16 As shown, an aircraft engine test bench includes a motion platform device 1, a flap device 2, a vibration isolation device 3, an aircraft engine 4, a support base 5, an equipment base 6, a vibration isolation device 10, a shock absorber 11, a servo hydraulic device and a servo control device.

[0032] The center hinge bottom plate 32 and the cylinder bottom plate 30 of the lower end face of the motion platform device 1 are connected and fixed to the equipment foundation 6 by embedded anchor bolts. The rear end face of the flap device 2 is connected and fixed to the base foundation 5 by embedded parts. There is no fixed connection between the motion platform device 1 and the flap device 2. The lower end face of the vibration absorber 11 in the vibration isolation device 3 and the lower end face of the vibration isolation device 10 are connected and fixed to the upper end face of the upper platform 21 in the motion platform device 1 by bolts. The upper end face of the vibration absorber 11 is connected and fixed to the lower end face of the aircraft engine 4 by bolts. The base foundation 5 and the equipment foundation 6 are integrally cast during the foundation casting construction. The base foundation 5 is connected to the top surface of the positioning tooling and the equipment foundation 6. The upper end of the vibration absorber 11 is connected and fixed to the lower end of the aircraft engine 4 by bolts.

[0033] The center hinge bottom plate 32, the lower platform 27 and the bottom plate 30 of the lower hinge seat of the oil cylinder are fixed by secondary casting with anchor bolts, positioning fixtures and equipment foundation 6. The bottom plate 30 of the lower hinge seat of the oil cylinder is fixed to the lower end of the lower hinge seat 29 of the oil cylinder by bolts, the lower ends of the active oil cylinder 28 and the auxiliary oil cylinder 31 are fixed to the upper end of the lower hinge seat 29 of the oil cylinder by bolts, the upper ends of the active oil cylinder 28 and the auxiliary oil cylinder 31 are fixed to the lower end of the upper hinge seat 24 of the oil cylinder by bolts, and the upper end of the upper hinge seat 24 of the oil cylinder is fixed to the lower end of the upper platform 21 by bolts. Fixed, the lower end of the anti-torsion arm 25 is fixed to the upper end of the lower platform 27 by bolt connection, the upper end of the anti-torsion arm 25 is fixed to the lower end of the anti-torsion arm hinge seat 23 by bolt connection, the upper end of the anti-torsion arm hinge seat 23 is fixed to the lower end of the upper platform 21 by bolt connection, the supporting foundation 26 is fixed to the upper end of the lower platform 27 and the lower end of the center hinge base plate 32 by positioning casting through tooling, the lower end of the center hinge 22 is fixed to the upper end of the center hinge base plate 32 by bolt connection, and the upper end of the center hinge 22 is fixed to the lower end of the upper platform 21 by bolt connection.

[0034] The bottom plate 44 of the lower hinge seat of the flap cylinder of the flap device is positioned and fixed to the base foundation 5 by casting, the lower end of the lower hinge seat 43 of the flap cylinder and the upper end of the bottom plate 44 of the flap cylinder are fixed by bolts, the upper end of the lower hinge seat 43 of the flap cylinder and the lower end of the flap cylinder 42 are fixed by bolts, the upper end of the flap cylinder 42 and the lower end of the upper hinge seat 41 of the flap cylinder are fixed by bolts, the upper end of the upper hinge seat 41 of the flap cylinder and the lower end of the flap 40 are fixed by bolts, and there are a total of 4 groups of flaps between the base foundation 5 and the motion platform 1.

[0035] The upper end of the upper platform 21 of the vibration isolation device is fixed to the lower end of the shock absorber 11 by bolts, the upper end of the shock absorber 11 is fixed to the lower end of the aircraft engine 4 by bolts, the lower end of the vibration isolation device 10 is fixed to the upper end of the upper platform 21 by bolts, and one side of the vibration isolation strip of the vibration isolation device 10 is fixed to the side of the aircraft engine 4, thereby providing a limit protection for the aircraft engine 4.

[0036] The motion platform of the servo hydraulic device has a total of 4 servo cylinders, 2 active cylinders 28 are installed on the same side of the Y-axis, and 2 auxiliary cylinders 31 are installed on the other side of the Y-axis. The upper ends of the piston rods of the 4 cylinders are designed with hydraulic mechanical locks. The 4 cylinders have the same structure and can be switched according to use. The difference between the main and auxiliary cylinders is that the active cylinder 28 is installed with a servo valve block.

[0037] Example 2: Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 , Fig.14 , Fig.15 and Fig.16 As shown, an aircraft engine test bench, the equipment foundation 6 and the pedestal foundation 5 need to be cast first, the lower platform 27 and the bottom plate 30 of the lower hinge seat of the oil cylinder are positioned by anchor bolts and tooling, and then cast and fixed for the second time, and the center hinge bottom plate 32 is positioned and fixed by anchor bolts and tooling when the support foundation 26 is cast for the third time. When casting the equipment foundation 6 and the pedestal foundation 5, it is necessary to reserve a hydraulic pipeline trench and a cable trench to facilitate later construction.

[0038] A motion mode of an aircraft engine test bench. When the motion platform is in a stopped state, the upper platform is horizontal, the flap device is horizontal, and the staff can go to the motion platform through the flap to debug the aircraft engine. When the motion platform is working, the staff evacuates, the flap is flipped up to a vertical state, and acts as a protective guardrail. The motion platform and the flap device are designed with an interlocking device. The motion platform performs pitch, roll and compound motion with the central axis of the central hinge as the motion center, so as to test the aircraft engine.

[0039] Example 3: Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 , Fig.14 , Fig.15 and Fig.16 As shown, an aircraft engine test bench comprises:

[0040] Motion platform device: The bottom plate 30 of the lower hinge seat of the cylinder is fixed to the lower end of the lower hinge seat 29 of the cylinder by bolts, the bottom plate 30 of the lower hinge seat of the cylinder is connected to the positioning tool and the equipment foundation 6 by anchor bolts, and is positioned and fixed by secondary pouring, the lower ends of the active cylinder 28 and the auxiliary cylinder 31 are respectively fixed to the upper end of the lower hinge seat 29 of the cylinder by bolts, the upper ends of the active cylinder 28 and the auxiliary cylinder 31 are respectively fixed to the lower end of the cylinder upper hinge seat 24 by bolts, the upper end of the cylinder upper hinge seat 24 is fixed to the lower end of the upper platform 21 by bolts, and the upper end of the center hinge 22 is fixed to the upper platform 2 The lower end of the anti-torsion arm 25 is fixed by bolts, the upper end of the anti-torsion arm hinge seat 23 is fixed by bolts to the lower end of the upper platform 21, the lower end of the anti-torsion arm 25 is fixed by bolts to the upper end of the lower platform 27, the upper end of the anti-torsion arm 25 is fixed by bolts to the lower end of the anti-torsion arm hinge seat 23, the upper end of the anti-torsion arm hinge seat 23 is fixed by bolts to the lower end of the upper platform 21, the support foundation 26 is fixed by the upper end of the lower platform 27 and the lower end of the center hinge bottom plate 32 through positioning fixtures and equipment foundation 6, and the lower end of the center hinge 22 is fixed by bolts to the upper end of the center hinge bottom plate 32.

[0041] Flipping device: The bottom plate 44 of the lower hinge seat of the flap cylinder and the pedestal foundation 5 are positioned and fixed by casting, the lower end of the lower hinge seat 43 of the flap cylinder and the upper end of the bottom plate 44 of the flap cylinder are fixed by bolts, the upper end of the lower hinge seat 43 of the flap cylinder and the lower end of the flap cylinder 42 are fixed by bolts, the upper end of the flap cylinder 42 and the lower end of the upper hinge seat 41 of the flap cylinder are fixed by bolts, the upper end of the upper hinge seat 41 of the flap cylinder and the lower end of the flap 40 are fixed by bolts, and there are a total of 4 groups of flaps between the pedestal foundation 5 and the motion platform 1.

[0042] Vibration isolation device: The upper end of the upper platform 21 is fixed to the lower end of the shock absorber 11 by bolts, the upper end of the shock absorber 11 is fixed to the lower end of the aircraft engine 4 by bolts, the lower end of the vibration isolation device 10 is fixed to the upper end of the upper platform 21 by bolts, and one side of the vibration isolation bar of the vibration isolation device 10 is fixed to the side of the aircraft engine 4, which plays a role of limiting protection for the aircraft engine 4.

[0043] Servo hydraulic device: The motion platform has a total of 4 servo cylinders, 2 active cylinders 28 are installed on the same side of the Y-axis, and 2 auxiliary cylinders 31 are installed on the other side of the Y-axis. The upper ends of the piston rods of the 4 cylinders are designed with hydraulic mechanical locks. The 4 cylinders have the same structure and can be switched according to use. The difference between the main and auxiliary cylinders is that the active cylinder 28 is installed with a servo valve block.

[0044] Example 4: Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 , Fig.14 , Fig.15 and Fig.16 As shown, an aircraft engine test bench is composed of a motion platform device, a flap device, a vibration isolation device, a servo hydraulic device and a servo control device. The motion platform device is a device that carries the aircraft engine for tilting test movement; the flap device is used to ensure that when the motion platform is stopped, the flap carries the staff to debug the aircraft engine horizontally, and the flap is vertical, and the motion platform performs tilting movement, and the flap device plays a protective role; the vibration isolation device is a device connected between the aircraft engine and the motion platform, so that the two have a vibration isolation effect to avoid resonance; the servo hydraulic device is the power source and actuating actuator of the motion platform sub-device, providing stable power and safety guarantee for the test bench; the servo control device mainly realizes on-site power, control power supply, safety circuit control and local debugging, etc. At the same time, the measurement and control device drives the motion platform to realize posture exercises with different degrees of freedom and realize the motion reproduction of the relevant motion spectrum. The servo control device adopts existing technology products.

[0045] The lower platform, center hinge bottom plate and cylinder lower hinge seat bottom plate at the bottom of the motion platform are fixed to the equipment foundation by pre-embedded method, and then fastened to the rest of the motion platform components by high-strength bolts. The motion platform foundation is designed with a cap foundation. The plane of the cap foundation is at the same height as the platform surface on the motion platform. A flap device is installed in the gap between the platform and the cap foundation on the motion platform. The flap device can be in a horizontal or vertical state. Guardrails are installed around the plane of the cap foundation. A step ladder is designed at one end of the cap foundation for the convenience of staff to board. The vibration isolation device is installed between the platform surface and the aircraft engine on the operating platform.

[0046] The servo hydraulic device has 4 servo cylinders, 2 of which are active cylinders on the same side of the Y axis, and the other 2 are auxiliary cylinders on the other side of the Y axis. The active cylinder is the power output to drive the motion platform to move, and the auxiliary cylinder plays an auxiliary damping role. The 4 cylinders have the same structure and can be switched according to use. The servo cylinders and auxiliary cylinders are connected to hydraulic mechanical locks respectively.

[0047] The oil cylinder of the flap device and the servo oil cylinder of the motion platform use the same oil source and can be controlled separately. The main function of the servo control device is to realize the power, control power supply, safety circuit control and local debugging on site. At the same time, the measurement and control device drives the motion platform to realize the posture movement of different degrees of freedom and realize the motion reproduction of the relevant motion spectrum. While testing and transmitting the motion parameters, it is also responsible for the fault detection and safety protection of the safety device.

[0048] The motion platform device is a device that carries the aircraft engine for tilting test movements; the flap device is used to ensure that when the motion platform is stopped, the flap can horizontally carry the staff to debug the aircraft engine, and secondly, when the motion platform is tilting, the flap plays a protective role vertically; the vibration isolation device is a device connected between the aircraft engine and the motion platform, which has a vibration isolation effect between the two to avoid resonance; the servo hydraulic device is the power source and actuating actuator of the motion platform sub-device, providing stable power and safety for the test bench; the servo control device is mainly used to realize on-site power, control power supply, safety circuit control and local debugging, etc. At the same time, the servo control device drives the motion platform to realize posture exercises with different degrees of freedom and realize the motion reproduction of the relevant motion spectrum.

[0049] As described above, the embodiments of the present invention are described in detail, but it is obvious to those skilled in the art that there are many variations as long as they do not deviate from the inventive point and effect of the present invention. Therefore, all such variations are also included in the protection scope of the present invention.

Claims

1. An aero engine test bench, characterized in that: The center hinge bottom plate and the cylinder bottom plate of the lower end face of the motion platform device are connected and fixed to the equipment foundation through embedded anchor bolts. The rear end face of the flap device is connected and fixed to the base foundation through embedded parts. There is no fixed connection between the motion platform device and the flap device. The lower end face of the vibration absorber in the vibration isolation device, the lower end face of the vibration isolation device and the upper end face of the upper platform in the motion platform device are connected and fixed through bolts. The upper end face of the vibration absorber is connected and fixed to the lower end face of the aircraft engine through bolts. The base foundation is connected to the equipment foundation as a whole. The base foundation is connected to the top surface of the positioning tooling and the equipment foundation. The upper end of the vibration absorber is connected and fixed to the lower end of the aircraft engine through bolts. The center hinge bottom plate, the lower platform and the bottom plate of the lower hinge seat of the cylinder are positioned and fixed by anchor bolts, positioning tooling and secondary pouring of the equipment foundation. The bottom plate of the lower hinge seat of the cylinder is fixed to the lower end of the lower hinge seat of the cylinder by bolts, the lower ends of the active cylinder and the auxiliary cylinder are fixed to the upper end of the lower hinge seat of the cylinder by bolts, the upper ends of the active cylinder and the auxiliary cylinder are fixed to the lower end of the upper hinge seat of the cylinder by bolts, the upper end of the upper hinge seat of the cylinder is fixed to the lower end of the upper platform by bolts, the lower end of the anti-torsion arm is fixed to the upper end of the lower platform by bolts, the upper end of the anti-torsion arm is fixed to the lower end of the anti-torsion arm hinge seat by bolts, the upper end of the anti-torsion arm hinge seat is fixed to the lower end of the upper platform by bolts, the supporting foundation is fixed to the upper end of the lower platform and the lower end of the center hinge bottom plate by positioning casting and fixing through tooling, the lower end of the center hinge is fixed to the upper end of the center hinge bottom plate by bolts, the upper end of the center hinge is fixed to the lower end of the upper platform by bolts, The bottom plate of the lower hinge seat of the flap cylinder of the flap device is fixed to the foundation of the platform by casting. The lower end of the lower hinge seat of the flap cylinder is fixed to the upper end of the bottom plate of the lower hinge seat of the flap cylinder by bolts. The upper end of the lower hinge seat of the flap cylinder is fixed to the lower end of the flap cylinder by bolts. The upper end of the flap cylinder is fixed to the lower end of the upper hinge seat of the flap cylinder by bolts. The upper end of the upper hinge seat of the flap cylinder is fixed to the lower end of the flap by bolts. There are 4 sets of flaps between the foundation of the platform and the motion platform. The upper end of the upper platform of the vibration isolation device is fixed to the lower end of the shock absorber by bolts, the upper end of the shock absorber is fixed to the lower end of the aircraft engine by bolts, the lower end of the vibration isolation device is fixed to the upper end of the upper platform by bolts, one side of the vibration isolation bar of the vibration isolation device is fixed in contact with the side of the aircraft engine, and the motion platform of the servo hydraulic device has 2 active cylinders and 2 auxiliary cylinders, the 2 active cylinders are installed on one side of the Y-axis, and the 2 auxiliary cylinders are installed on the other side of the Y-axis.

2. An aero-engine test bench according to claim 1, characterized in that: The servo oil cylinder and the auxiliary oil cylinder are respectively connected to the hydraulic mechanical lock.

3. The aircraft engine test bench according to claim 1, characterized in that: The active cylinder is connected to the servo valve block.

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