Complete aircraft engine hanging bracket device

Abstract

The invention relates to an aero-engine complete machine hanging bracket device. The aero-engine complete machine hanging bracket device comprises a T-shaped supporting frame which comprises a base, a supporting column and a top beam, and the top beam is arranged on the base through the supporting column; the two complete machine weight testing modules are respectively arranged at the end part of the top beam, are symmetrically distributed along the supporting column, and are used for measuring the complete machine weight of the aero-engine hung on the complete machine weight testing modules; the plurality of hoisting modules are used for hoisting the aero-engine through a plurality of hoisting points; and the control unit is connected with the complete machine weight testing module and the hoisting modules, and is used for acquiring the complete machine weight information of the aero-engine acquired by the complete machine weight testing module and cooperatively controlling the plurality of hoisting modules to move to release or retract the corresponding hoisting points. The invention provides an aero-engine complete machine hanging bracket device which can improve the aero-engine maintenance efficiency, shorten the maintenance period and reduce the occupational disease risk of maintenance personnel.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine maintenance, and in particular to an aircraft engine complete machine hanger device. Background Art

[0002] In the field of aircraft engines, in order to ensure that the aircraft engines are continuously in an airworthy state, maintenance work should be carried out regularly or irregularly. During maintenance, the aircraft engine needs to be suspended and supported. Generally, there are two support methods:

[0003] 1. The aircraft engine can be suspended by connecting one end of multiple suspension points to the aircraft engine installation point and one end to the overhead crane;

[0004] 2. Connect the aircraft engine installation points through multiple support columns to achieve suspended support for the entire aircraft engine.

[0005] Among them: Method 1, according to maintenance needs, the aircraft engine can be moved up and down to facilitate maintenance personnel to approach the engine and carry out maintenance work, but this solution requires the configuration of a crane and related crane support facilities, which is very expensive; Method 2, the aircraft engine cannot be moved up and down and due to the obstruction of the support column, some areas of the engine are inconvenient for maintenance personnel and maintenance tools and equipment to approach to carry out maintenance work, resulting in relatively low engine maintenance efficiency and a long maintenance cycle. In addition, in order to carry out maintenance work, maintenance personnel need to maintain a special working posture for a long time, increasing the risk of occupational diseases. Summary of the invention

[0006] In view of the above problems in the prior art, the present invention proposes an aircraft engine complete machine hanger device, which can improve the maintenance efficiency of the aircraft engine, shorten the maintenance cycle and reduce the occupational disease risks of maintenance personnel.

[0007] Specifically, the present invention proposes an aircraft engine complete machine hanger device, comprising:

[0008] The T-shaped support frame comprises a base, a support column and a top beam, wherein the top beam is arranged on the base through the support column;

[0009] Two whole-machine weight test modules are respectively arranged at the ends of the top beam and symmetrically distributed along the support column, and the whole-machine weight test modules are used to measure the whole-machine weight of the aircraft engine hung thereon;

[0010] A plurality of hoisting modules, for hoisting the aircraft engine through a plurality of hoisting points, wherein the hoisting modules are arranged at the bottom of the whole machine weight test module, and the hoisting modules are used to lower or retract the hoisting points connected to the aircraft engine;

[0011] A control unit is arranged on the support column, and the control unit is connected to the whole machine weight testing module and the lifting module, and is used to obtain the whole machine weight information of the aircraft engine obtained by the whole machine weight testing module, and coordinately control the actions of multiple lifting modules to lower or retract corresponding lifting points.

[0012] According to one embodiment of the present invention, the hoisting module includes a hoisting point weight test module and a stepper motor, the stepper motor is connected to the whole machine weight test module through the hoisting point weight test module, the hoisting point weight test module is used to measure the tension on the hoisting point corresponding to the hoisting module, and the stepper motor is used to lower or retract the hoisting point corresponding to the hoisting module;

[0013] The whole-machine weight testing module obtains the whole-machine weight of the aircraft engine suspended thereon through the hanging point tension obtained by all the hanging point weight testing modules connected thereto.

[0014] According to one embodiment of the present invention, the control unit is connected to the suspension point weight test module and the stepper motor;

[0015] The control unit calculates the symmetry and center position change of the aircraft engine and records the corresponding data based on the whole-machine weight of the aircraft engine obtained by the whole-machine weight testing module and the corresponding suspension point tension obtained by each suspension point weight testing module;

[0016] The control unit cooperatively controls the plurality of stepper motors to raise or lower the aircraft engine.

[0017] According to an embodiment of the present invention, the hoisting module further includes an anti-falling protection device, and the hoisting point corresponding to the hoisting module is connected to the stepping motor through the anti-falling protection device.

[0018] According to one embodiment of the present invention, the suspension point is made of steel cable or carbon fiber, one end of the suspension point is connected to the aircraft engine, and the other end is connected to the stepper motor through the anti-fall protection device.

[0019] According to one embodiment of the present invention, a camera is provided on the support column for photographing the aircraft engine;

[0020] The control unit receives image data of the aircraft engine taken by the camera, and determines whether the aircraft engine has defects based on the image data.

[0021] According to one embodiment of the present invention, the control unit includes a storage module and a comparison module, the storage module is used to obtain or save the electronic data model information of the aircraft engine, and the comparison module is used to compare the image data with the electronic data model information to determine whether the aircraft engine has defects, and the defects include missing parts of the aircraft engine.

[0022] According to one embodiment of the present invention, a touch screen is provided on the support column, the touch screen is connected to the control unit, and the touch screen is used to display the operating status of the aircraft engine hanger device, the operating status including the measurement results of the two whole machine weight test modules, the measurement results of the hanging point weight test module, and the symmetry and center position of the aircraft engine;

[0023] The touch screen can also be used to display a control interface, and the control interface is used to receive control instructions and control the action of the stepper motor based on the control instructions.

[0024] The invention provides an aircraft engine complete machine hanger device, which combines the characteristics of support and overhead crane, and can improve the maintenance efficiency of aircraft engines, shorten the maintenance cycle and reduce the occupational disease risks of maintenance personnel.

[0025] It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as described. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this application. The accompanying drawings illustrate embodiments of the present invention and together with the description serve to explain the principle of the present invention.

[0027] In the attached figure:

[0028] Figure 1 The diagram shows the use status of the aircraft engine complete machine hanger device according to one embodiment of the present invention.

[0029] Figure 2 A schematic side structural diagram of an aircraft engine complete machine hanger device according to an embodiment of the present invention is shown.

[0030] The above drawings include the following reference numerals:

[0031] Machine hanger device 100

[0032] Base 101

[0033] Support column 102

[0034] Top beam 103

[0035] Machine weight test module 104

[0036] Lifting module 105

[0037] Control unit 106

[0038] Hanging point 107

[0039] Lifting point weight test module 108

[0040] Stepper Motor 109

[0041] Fall protection device 110

[0042] Camera 111

[0043] Touch screen 112

[0044] Aircraft Engine 200 DETAILED DESCRIPTION

[0045] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0046] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually merely illustrative and is by no means intended to limit the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0047] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0048] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so that once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0049] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0050] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" may include both "above" and "below". The device may also be positioned in other different ways, rotated 90 degrees or in other orientations, and the spatially relative descriptions used herein are interpreted accordingly.

[0051] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0052] Figure 1 The diagram shows the use status of the aircraft engine complete machine hanger device according to one embodiment of the present invention. Figure 2 The side structural diagram of an aircraft engine complete machine hanger device according to an embodiment of the present invention is shown. As shown in the figure, an aircraft engine complete machine hanger device 100 mainly includes a T-shaped support frame, two complete machine weight test modules 104, a plurality of hoisting modules 105 and a control unit 106.

[0053] The T-shaped support frame includes a base 101, a support column 102 and a top beam 103. The base 101 can be fixed to the ground by bolts, and the top beam 103 is set on the base 101 through the support column 102. The top beam 103 is arranged horizontally on the support column 102 to form a T-shaped support frame. The advantage of the T-shaped support frame is that two aircraft engines 200 can be suspended at both ends of the top beam 103 at the same time to carry out maintenance work. When the two aircraft engines 200 are repaired, the load on the left and right of the whole machine hanger device 100 is more balanced, and the overall structure is more stable.

[0054] Furthermore, two whole-machine weight test modules 104 are respectively arranged at both ends of the top beam 103. That is, the two whole-machine weight test modules 104 are symmetrically distributed along the support column 102. The whole-machine weight test module 104 is used to measure the whole-machine weight of the aircraft engine 200 hung thereon.

[0055] Each whole machine weight test module 104 is equipped with a plurality of hoisting modules 105. Each hoisting module 105 hoists the aircraft engine 200 through its own hoisting point 107. The hoisting module 105 is arranged at the bottom of the whole machine weight test module 104, and the hoisting module 105 is used to lower or retract the hoisting point 107 connected to the aircraft engine 200. It should be noted that the suspension requirements of different types of aircraft engines 200 can be met by selecting and using the hoisting point 107. Suspending the aircraft engine 200 unit body through the hoisting point 107 can meet the requirements of decomposing the aircraft engine 200 into units or assembling the units into the aircraft engine 200. In addition, the whole machine hanger device 100 mainly uses the installation points on the upper part of the aircraft engine 200, and the installation points on the lower part of the aircraft engine 200 are vacated, so as to facilitate the installation of the aircraft engine 200 on the aircraft engine 200 transport bracket through the whole machine hanger device 100, or hoisting from the transport bracket to the whole machine hanger device 100.

[0056] The control unit 106 is disposed on the support column 102. The control unit 106 is connected to the two whole-machine weight test modules 104 and the hoisting module 105, and is used to obtain the whole-machine weight information of the aircraft engine 200 obtained by the whole-machine weight test module 104, and coordinately control the actions of the multiple hoisting modules 105 to lower or retract the corresponding lifting points 107, so that the aircraft engine 200 can be lifted or lowered.

[0057] Preferably, each hoisting module 105 includes a hoisting point weight test module 108 and a stepper motor 109. The stepper motor 109 is connected to the whole machine weight test module 104 through the hoisting point weight test module 108. The hoisting point weight test module 108 is used to measure the tension on the hoisting point 107 corresponding to the hoisting module 105, and the stepper motor 109 is used to lower or retract the hoisting point 107 corresponding to the hoisting module 105. It is easy to understand that the whole machine weight test module 104 obtains the whole machine weight of the aircraft engine 200 suspended thereon through the tension of the hoisting point 107 obtained by all the hoisting point weight test modules 108 connected thereto.

[0058] Preferably, the control unit 106 is connected to the lifting point weight test module 108 and the stepper motor 109. Based on the whole machine weight of the aircraft engine 200 obtained by the whole machine weight test module 104 and the tension of the corresponding lifting point 107 obtained by each lifting point weight test module 108, the control unit 106 calculates the symmetry and center position change of the aircraft engine 200 hoisted by the whole machine weight test module 104 and records the corresponding data. Specifically, the whole machine weight of the aircraft engine is measured and displayed in real time to ensure that the weight and weight change of the aircraft engine 200 are within the allowable range during the entire maintenance cycle. In addition, when a certain component is installed or removed during the maintenance process, the center of gravity of the aircraft engine 200 will change, so real-time monitoring and recording are crucial to improving the quality of maintenance work. The control unit 106 is also used to coordinately control multiple stepper motors 109 to rotate forward or reverse to lift or lower the aircraft engine 200.

[0059] Preferably, the hoisting module 105 further includes an anti-fall protection device 110. The hoisting point 107 corresponding to the hoisting module 105 penetrates the anti-fall protection device 110 and is connected to the stepper motor 109. By arranging the anti-fall protection device 110 for each hoisting point 107, the safety performance is improved to prevent the aircraft engine 200 from falling.

[0060] Preferably, the suspension point 107 is made of high-strength materials such as steel cables or carbon fibers. One end of the suspension point 107 is connected to the aircraft engine 200 , and the other end is connected to the stepper motor 109 through the anti-fall protection device 110 .

[0061] Preferably, a camera 111 is provided on the support column 102. The camera 111 is used to photograph the hoisted aircraft engine 200. The control unit 106 receives the image data of the aircraft engine 200 photographed by the camera 111, and determines whether the aircraft engine 200 has defects based on the image data. More preferably, the control unit 106 includes a storage module and a comparison module. The storage module is used to obtain or save the electronic data model information of the aircraft engine 200, and the comparison module is used to compare the image data with the electronic data model information to determine whether the aircraft engine 200 has defects. The defect includes missing parts of the aircraft engine 200. In this way, the maintenance efficiency can be further improved, and the occurrence of omissions in the installation of parts can be prevented.

[0062] Preferably, a touch screen 112 is provided on the support column 102. The touch screen 112 is connected to the control unit 106, and the touch screen 112 is used to display the overall operating status of the aircraft engine 200 hanger device. The operating status includes the measurement results of the two whole-machine weight test modules 104, the measurement results of each hanging point weight test module 108, and the symmetry and center position of the hoisted aircraft engine 200. In this embodiment, two touch screens 112 are provided on the support column 102 to respectively display the operating status of the aircraft engines 200 on both sides of the whole-machine hanger device 100. As an example and not a limitation, more touch screens can also be provided according to actual needs for easy operation.

[0063] Furthermore, the touch screen 112 can also be used to display a control interface. The control interface is used to receive control instructions and control the stepper motor 109 based on the control instructions. The touch screen 112 can also be configured with a keyboard and a mouse, and / or by setting a menu, etc., to facilitate viewing relevant information of the whole machine hanger device 100, or selecting and executing corresponding control commands.

[0064] The aircraft engine complete machine hanger device provided by the present invention has the following advantages:

[0065] 1. Can support maintenance work of 2 aircraft engines at the same time;

[0066] 2. Maintenance personnel use the control unit to control the stepper motor of each lifting point to rotate forward to lower the lifting point and reverse to retract the lifting point, thereby enabling the entire aircraft engine to move up and down to meet maintenance needs. At the same time, there are no support columns on the side of the aircraft engine to interfere with maintenance work, which can improve maintenance efficiency and shorten maintenance cycles, while reducing the risk of maintenance personnel suffering from occupational diseases;

[0067] 3. It can measure and display the weight of the entire aircraft engine in real time to ensure that the engine weight and weight change are within the allowable range during the entire maintenance cycle;

[0068] 4. Through the selection of hanging points, it can meet the suspension requirements of different types of aircraft engines;

[0069] 5. The aircraft engine unit can be suspended by the suspension point, so that the aircraft engine can be disassembled into units or the units can be assembled into an aircraft engine;

[0070] 6. The weight test module of each lifting point can detect the symmetry and center of gravity position of the aircraft engine, and record the changes in the symmetry and center of gravity position of the engine during the entire maintenance cycle;

[0071] 7. Each hanging point is equipped with an anti-fall protection device to prevent the aircraft engine from falling;

[0072] 8. It is convenient to install the aircraft engine on the aircraft engine transport bracket, or to hoist it from the transport bracket to the device;

[0073] 9. By taking a comprehensive photo of the entire engine and comparing the image with the saved electronic data model information, external defects and / or missing parts of the aircraft engine can be discovered, quickly assisting maintenance personnel in carrying out aircraft engine inspections.

[0074] It will be apparent to those skilled in the art that various modifications and variations may be made to the above exemplary embodiments of the present invention without departing from the spirit and scope of the present invention. Therefore, it is intended that the present invention covers modifications and variations of the present invention that fall within the scope of the appended claims and their equivalent technical solutions.

Claims

1. An aircraft engine complete machine hanger device, comprising: The T-shaped support frame comprises a base, a support column and a top beam, wherein the top beam is arranged on the base through the support column; Two whole-machine weight test modules are respectively arranged at the ends of the top beam and symmetrically distributed along the support column, and the whole-machine weight test modules are used to measure the whole-machine weight of the aircraft engine hung thereon; A plurality of hoisting modules, for hoisting the aircraft engine through a plurality of hoisting points, wherein the hoisting modules are arranged at the bottom of the whole machine weight test module, and the hoisting modules are used to lower or retract the hoisting points connected to the aircraft engine; A control unit is arranged on the support column, and the control unit is connected to the whole machine weight testing module and the lifting module, and is used to obtain the whole machine weight information of the aircraft engine obtained by the whole machine weight testing module, and coordinately control the actions of multiple lifting modules to lower or retract corresponding lifting points.

2. The aircraft engine complete machine hanger device according to claim 1, characterized in that: The hoisting module includes a hoisting point weight test module and a stepper motor, the stepper motor is connected to the whole machine weight test module through the hoisting point weight test module, the hoisting point weight test module is used to measure the tension on the hoisting point corresponding to the hoisting module, and the stepper motor is used to lower or retract the hoisting point corresponding to the hoisting module; The whole-machine weight testing module obtains the whole-machine weight of the aircraft engine suspended thereon through the hanging point tension obtained by all the hanging point weight testing modules connected thereto.

3. The aircraft engine complete machine hanger device according to claim 2, characterized in that: The control unit is connected to the lifting point weight test module and the stepping motor; The control unit calculates the symmetry and center position change of the aircraft engine and records the corresponding data based on the whole-machine weight of the aircraft engine obtained by the whole-machine weight testing module and the corresponding suspension point tension obtained by each suspension point weight testing module; The control unit cooperatively controls the plurality of stepper motors to raise or lower the aircraft engine.

4. The aircraft engine complete machine hanger device according to claim 3, characterized in that: The hoisting module also includes an anti-falling protection device, and the hoisting point corresponding to the hoisting module is connected to the stepping motor through the anti-falling protection device.

5. The aircraft engine complete machine hanger device according to claim 4, characterized in that: The suspension point is made of steel cable or carbon fiber, one end of the suspension point is connected to the aircraft engine, and the other end is connected to the stepping motor through the anti-fall protection device.

6. The aircraft engine complete machine hanger device according to claim 1, characterized in that: A camera is provided on the support column for photographing the aircraft engine; The control unit receives image data of the aircraft engine taken by the camera, and determines whether the aircraft engine has defects based on the image data.

7. The aircraft engine complete machine hanger device according to claim 6, characterized in that: The control unit includes a storage module and a comparison module. The storage module is used to obtain or save the electronic data model information of the aircraft engine. The comparison module is used to compare the image data with the electronic data model information to determine whether the aircraft engine has defects, and the defects include missing parts of the aircraft engine.

8. The aircraft engine complete machine hanger device according to claim 4, characterized in that: A touch screen is provided on the support column, the touch screen is connected to the control unit, and the touch screen is used to display the operating status of the aircraft engine hanger device, the operating status including the measurement results of the two whole machine weight test modules, the measurement results of the hanging point weight test module, and the symmetry and center position of the aircraft engine; The touch screen can also be used to display a control interface, and the control interface is used to receive control instructions and control the action of the stepper motor based on the control instructions.

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