On-wing hair changing equipment

Abstract

The invention relates to on-wing hair changing equipment. The on-wing hair changing equipment comprises a transverse connection mechanism and a transmission mechanism, one end of the first unit body is connected with one end of the transverse connecting mechanism, and the first unit body comprises a unit body supporting piece, a pedal, a driving mechanism and a lifting mechanism; one end of the second unit body is connected with the other end of the transverse connecting mechanism, the second unit body and the first unit body are completely the same in structure, and the engine bracket is borne by pedals of the first unit body and the second unit body; and the control unit is arranged on the transverse connecting mechanism, the control unit is used for controlling the driving mechanisms of the first unit body and the second unit body to act so as to transfer the civil aero-engine, and the control unit is further used for controlling the lifting mechanisms of the first unit body and the second unit body to act. According to the on-wing hair changing equipment, the working efficiency of on-wing hair changing can be improved, and the safety of personnel and equipment is guaranteed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine replacement operations, and in particular to an on-wing engine replacement device. Background Art

[0002] In the field of aviation engines, in order to ensure the continued airworthiness and safe operation of aircraft, on-wing engine replacement is required when an engine failure occurs or reaches restricted use conditions. Due to the large weight and volume of the engine, the complex external layout, and the small on-wing installation space, the engine replacement cycle is long and the operation is difficult. At present, the conventional on-wing engine replacement process is to use a set of guide tooling (including ratchet wrenches, tension scales, support frames and other components) to tighten or loosen the tooling chain through the ratchet wrench to achieve the lifting and lowering of the engine. According to actual conditions, on-wing engine replacement using guide tooling requires at least 8 people to work together to complete. The efficiency of on-wing engine replacement is low, the reliability is poor, and there are safety hazards.

[0003] In this context, how to provide an intelligent on-wing engine replacement equipment for civil aviation engines based on AGV (Automated Guided Vehicle) is an urgent problem to be solved. Summary of the invention

[0004] In view of the above problems in the prior art, the present invention proposes an on-wing engine replacement device, which can improve the work efficiency of on-wing engine replacement and ensure the safety of personnel and equipment.

[0005] Specifically, the present invention proposes an on-wing engine replacement device, which is applicable to civil aviation engines and includes:

[0006] Transverse connection mechanism;

[0007] A first unit body, one end of which is connected to one end of the transverse connection mechanism, the first unit body comprises a unit body support, a pedal, a driving mechanism, and a lifting mechanism, the driving mechanism is arranged on the unit body support, and is used to drive the first unit body to move; the pedal is connected to the unit body support through the lifting mechanism, the pedal is used to carry the engine bracket, the engine bracket is used to support the civil aviation engine, and the lifting mechanism is used to control the lifting of the pedal;

[0008] A second unit body, one end of which is connected to the other end of the transverse connection mechanism, the second unit body has the same structure as the first unit body, and the engine bracket is supported by the pedals of the first unit body and the second unit body;

[0009] A control unit is arranged on the transverse connection mechanism, and the control unit is used to control the action of the driving mechanism of the first unit body and the second unit body to realize the transportation of the civil aviation engine. The control unit is also used to control the action of the lifting mechanism of the first unit body and the second unit body to realize the six-degree-of-freedom attitude adjustment of the civil aviation engine.

[0010] According to one embodiment of the present invention, the driving mechanism comprises two identical driving assemblies, which are respectively arranged at the ends of the unit body support;

[0011] The driving assembly comprises a power base, a driving steering wheel and a sensor assembly. The driving steering wheel is arranged at the bottom of the power base, and the sensor assembly is arranged on the power base for detecting obstacles.

[0012] According to one embodiment of the present invention, the sensor assembly includes a plurality of force sensors and laser sensors, and the force sensors are arranged at the lower part of the power base to be close to the contact surface of the driving steering wheel.

[0013] According to one embodiment of the present invention, the force sensor includes a front force sensor and a side force sensor. The front force sensor is arranged at the front end of the power base to detect obstacles in the front end direction, and the side force sensors are arranged on both sides of the power base to detect obstacles on the side.

[0014] According to one embodiment of the present invention, a first emergency stop switch and a first operation indicator light are provided on the top of the power base, the first emergency stop switch is used to implement emergency operation of the first unit body, and the first operation indicator light is used to indicate the operation status of the first unit body.

[0015] According to one embodiment of the present invention, the lifting mechanism includes two identical lifting assemblies, which are respectively arranged at two ends of the unit body support to respectively connect two ends of the pedal;

[0016] The control unit synchronously controls the lifting components to achieve vertical lifting of the civil aviation engine; the control unit coordinately controls the lifting components to achieve six-degree-of-freedom attitude adjustment of the civil aviation engine.

[0017] According to one embodiment of the present invention, a guide rail and a support are provided on the unit body support;

[0018] The lifting assembly comprises a long support, a short support and a driving motor, wherein the long support and the short support are connected by a rotating shaft, one end of the long support is slidably connected to the guide rail, and the other end is rotatably connected to the end of the pedal; one end of the short support is rotatably connected to the rotating shaft, and the other end is rotatably connected to the support;

[0019] The driving motor is arranged on the short support, and the driving mechanism is used to drive one end of the long support to slide on the guide rail, so as to drive the end of the pedal to be lifted or lowered.

[0020] According to one embodiment of the present invention, the lifting assembly further includes a coupling, a trapezoidal screw, a trapezoidal nut, and a shaft flange, wherein the driving motor is connected to the trapezoidal screw via a coupling, the trapezoidal nut is fixed to the long support via a shaft flange, and the trapezoidal nut is arranged on the trapezoidal screw, and the two are threadedly matched;

[0021] The driving motor is started to drive the trapezoidal screw to rotate through the coupling, so that the trapezoidal nut drives one end of the long support to move on the guide rail.

[0022] According to one embodiment of the present invention, a plurality of adapter connectors are provided on the pedal, the adapter connectors can move along the length direction of the pedal and be fixed, and the pedal is connected to the engine bracket via the adapter connectors.

[0023] According to one embodiment of the present invention, the transverse connection mechanism comprises a mechanism body, universal wheels and guide grooves, a plurality of sets of universal wheels are provided at the bottom of the mechanism body, and guide grooves are provided at both ends of the mechanism body;

[0024] A slide rail assembly is provided on the power base and is interactively connected with the guide groove.

[0025] According to one embodiment of the present invention, the control unit is disposed in the mechanism body, and an accordion cover is provided on the top of the mechanism body to prevent foreign matter from entering the control system.

[0026] According to one embodiment of the present invention, a second emergency stop switch and a second operation indicator light are provided on the mechanism body, the first emergency stop switch is used to implement emergency operation of the on-wing engine replacement equipment, and the second operation indicator light is used to indicate the operating status of the on-wing engine replacement equipment.

[0027] According to an embodiment of the present invention, the on-wing hair replacement device further comprises an operating handle, the operating handle wirelessly communicates with the control unit, and the operating handle controls the movement of the first unit body, the second unit body and the transverse connection mechanism through the control unit.

[0028] The present invention provides an on-wing engine replacement device, which controls a first unit body and a second unit body through a control unit to realize the transportation and six-degree-of-freedom attitude adjustment of a civil aviation engine, thereby improving the work efficiency of on-wing engine replacement and ensuring the safety of personnel and equipment.

[0029] 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 claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The accompanying drawings are included to provide further explanation of the present invention, and are incorporated into 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.

[0031] In the attached figure:

[0032] Figure 1 A schematic structural diagram of an on-wing engine replacement device according to an embodiment of the present invention is shown.

[0033] Figure 2 The figure shows the use status of the on-wing engine replacement device according to one embodiment of the present invention.

[0034] Figure 3 yes Figure 2 Schematic diagram of the structure of the first unit body in .

[0035] Figure 4 yes Figure 3 Schematic diagram of the structure of the drive components.

[0036] Figure 5 yes Figure 3 Schematic diagram of the structure of the lifting component.

[0037] Figure 6 yes Figure 2 Schematic diagram of the structure of the transverse connection mechanism. DETAILED DESCRIPTION

[0038] 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.

[0039] 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 only 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.

[0040] 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.

[0041] 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 application. Meanwhile, 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 actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the 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, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0042] 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.

[0043] 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.

[0044] Figure 1 A schematic structural diagram of an on-wing engine replacement device according to an embodiment of the present invention is shown. Figure 2The figure shows the use state of an on-wing engine replacement device according to an embodiment of the present invention. As shown in the figure, the present invention provides an on-wing engine replacement device 100 suitable for civil aircraft engines. The on-wing engine replacement device 100 mainly includes a transverse connection mechanism 101, a first module 102, a second module 103 and a control unit 104.

[0045] One end of the first unit body 102 is connected to one end of the horizontal connection mechanism 101 . Figure 3 yes Figure 2 Schematic diagram of the structure of the first unit body in FIG. As shown in the figure, the first unit body 102 includes a unit body support 105, a pedal 106, a driving mechanism and a lifting mechanism. The driving mechanism is arranged on the unit body support 105, and is used to drive the first unit body 102 to move. The pedal 106 is connected to the unit body support 105 through the lifting mechanism, and the pedal 106 is used to carry the engine bracket 200. The engine bracket 200 is used to support a civil aviation engine. The lifting mechanism is used to control the lifting of the pedal 106.

[0046] One end of the second unit body 103 is connected to the other end of the lateral connection mechanism 101. The second unit body 103 has the same structure as the first unit body 102, and the two are basically arranged in parallel along the length direction. The engine bracket 200 is supported by the pedals 106 of the first unit body 102 and the second unit body 103.

[0047] The control unit 104 is disposed on the lateral connection mechanism 101. The control unit 104 is used to control the driving mechanism of the first unit body 102 and the second unit body 103 to achieve the transportation of the civil aircraft engine. The control unit 104 is also used to control the lifting mechanism of the first unit body 102 and the second unit body 103 to achieve the six-degree-of-freedom attitude adjustment of the civil aircraft engine.

[0048] Figure 4 yes Figure 3 Schematic diagram of the structure of the drive components in. Figure 3 As shown, the driving mechanism includes two identical driving assemblies 107 which are respectively fixed at the ends of the unit body support 105 by bolts.

[0049] Each driving assembly 107 includes a power base 109, a driving steering wheel 110 and a sensor assembly. The driving steering wheel 110 is arranged at the bottom of the power base 109, and the driving steering wheel 110 is the power source of the driving assembly 107. The driving steering wheel 110 is provided with an active motor and a steering motor at the same time, and has a vertical steering function without a turning radius. It should be noted that during the adaptation process of the engine bracket 200, the driving steering wheels 110 of the first unit body 102 and the second unit body 103 are independently motion controlled. During the engine transportation process, the control unit 104 can realize the coordinated motion control of the driving steering wheels 110 of the first unit body 102 and the second unit body 103. Further, the sensor assembly is arranged on the power base 109 to detect obstacles, realize the protection function of stopping immediately when an obstacle is touched, and prevent the equipment from being damaged by collision.

[0050] Preferably, the sensor assembly includes a plurality of force sensors and a laser sensor 111. The force sensor is disposed at the lower portion of the power base 109 to be close to the contact surface (usually the ground) of the driving steering wheel 110. The force sensor is mainly used to prevent the wing-mounted engine replacement device 100 from touching ground obstacles during movement. The laser sensor 111 is used to monitor space obstacles in real time. More preferably, the force sensor includes a front force sensor 112 and a side force sensor 113. The front force sensor 112 is disposed at the front end of the power base 109 to detect obstacles in the front direction, and the side force sensor 113 is disposed on both sides of the power base 109 to detect side obstacles. By way of example and not limitation, the side force sensors 113 may also be disposed on both sides of the unit body support 105 to sense side obstacles and avoid collisions.

[0051] Preferably, a first emergency stop switch 114 and a first operation indicator light 115 are provided on the top of the power base 109. The first emergency stop switch 114 is used to implement emergency operation of the first module 102. The first operation indicator light 115 is used to indicate the operation status of the first module 102. For example, the first operation indicator light 115 is a flashing yellow light, indicating that the first module 102 is in operation, which has a safety warning function.

[0052] Figure 5 yes Figure 3 Preferably, in combination with Figure 3As shown, the lifting mechanism includes two identical lifting assemblies 108, which are respectively arranged at the two ends of the unit body support 105 to respectively connect the two ends of the pedal 106. The control unit 104 synchronously controls the lifting assembly 108 to synchronously lift or lower the pedals 106 of the first unit body 102 and the second unit body 103 to achieve vertical lifting of the civil aircraft engine. The control unit 104 coordinates and controls the lifting assembly 108 to lift and / or lower one end or multiple ends of the first unit body 102 and the second unit body 103, and adjusts the posture of the first unit body 102 and / or the second unit body 103 to achieve six-degree-of-freedom attitude adjustment of the civil aircraft engine.

[0053] Preferably, guide rails 116 and supports 117 are fixedly provided on the unit support 105 by bolts. In this embodiment, two parallel guide rails 116 and two supports 117 are provided at one end of the unit support 105. The lifting assembly 108 includes two long pillars 118, two short pillars 119 and a driving motor 120. The long pillars 118 and the short pillars 119 are rotatably connected through a rotating shaft 122. Pulleys 121 are provided at the bottom ends of the two long pillars 118, and the two long pillars 118 are respectively slidably matched with the two guide rails 116 through the pulleys 121, so that the long pillars 118 can slide freely along the guide rails 116. The other end of the long pillar 118 is rotatably connected with the end of the pedal 106. One end of the short pillar 119 is connected with the rotating shaft 122 provided on the long pillar 118. The other ends of the two short pillars 119 are respectively rotatably connected with the two supports 117 through pins.

[0054] The driving motor 120 is arranged on the short support 119. The driving motor 120 is used to drive the bottom end of the long support 118 to slide on the guide rail 116, so as to drive the end of the pedal 106 to achieve lifting. It is easy to understand that the bottom end of the long support 118 of the lifting mechanism is connected to the guide rail 116 with a single degree of freedom, and the bottom end of the short support 119 is hingedly connected to the support 117. By sliding the bottom end of the long support 118 forward and backward on the guide rail 116, the angle between the long support 118 and the short support 119 is changed, so as to adjust the horizontal height of the top end of the long support 118, thereby driving the lifting of the end of the pedal 106. In fact, a connecting rod 123 is provided at the end of the pedal 106, and the top end of the long support 118 is rotatably connected to the connecting rod 123 through a ball bearing 139. The pedal 106 and the unit body support 105 form a parallelogram mechanism through the lifting mechanism, which is conducive to realizing the on-wing engine replacement attitude adjustment of the civil aviation engine, and has sufficient degree of freedom margin.

[0055] Preferably, the lifting assembly 108 also includes a coupling 124, a trapezoidal screw 125, a trapezoidal nut 126 and a shaft flange 127. The driving motor 120 is connected to the trapezoidal screw 125 through the coupling 124, and the trapezoidal nut 126 is fixed to the long support 118 through the shaft flange 127. The trapezoidal nut 126 is arranged on the trapezoidal screw 125, and the two are threadedly matched. The driving motor 120 is started, and the trapezoidal screw 125 is driven to rotate through the coupling 124, so that the trapezoidal nut 126 drives the bottom end of the long support 118 to move on the guide rail 116. In other words, the rotational motion output by the driving motor 120 is converted into the linear motion of the trapezoidal nut 126, which drives the bottom end of the long support 118 to move on the guide rail 116 to adjust the height of the end of the pedal 106. It is easy to understand that the control unit 104 adjusts the posture of the pedal 106 through the lifting components 108 at both ends of the control unit 104 support member 105, and adjusts the posture of the pedal 106 of the first unit body 102 and the second unit body 103, thereby adjusting the on-wing engine replacement posture of the civil aviation engine.

[0056] Preferably, a limit switch 128 is provided on the guide rail 116 to prevent the lifting assembly 108 from having a travel risk.

[0057] Preferably, reference Figure 1 and Figure 3 , a plurality of adapter connectors 129 are provided on the pedal 106. The adapter connector 129 can move along the length direction of the pedal 106 and be fixed, and the pedal 106 is connected to the engine bracket 200 through the adapter connector 129. In this example, two adapter connectors 129 are provided on the pedal 106 close to the engine bracket 200, and the adapter connector 129 is fixed with the lifting hole on the engine bracket 200 to transmit power for civil aviation engine transportation and on-wing replacement. The position of the adapter connector 129 on the pedal 106 is adjustable to adapt to different models of engine brackets 200, thereby improving the versatility of on-wing replacement.

[0058] Figure 6 yes Figure 2 Schematic diagram of the structure of the transverse connection mechanism in. As shown in the figure, the transverse connection mechanism 101 includes a mechanism body 130, universal wheels 131 and guide grooves 132. A plurality of sets of universal wheels 131 are provided at the bottom of the mechanism body 130. In the present embodiment, three sets of universal wheels 131 are provided at the bottom of the mechanism body 130, and the three sets of universal wheels 131 are basically located at the three vertices of an equilateral triangle, so as to avoid the risk of the transverse connection mechanism 101 tipping over and can operate independently. Furthermore, guide grooves 132 are provided at both ends of the mechanism body 130. A slide rail assembly 133 is provided on the power base 109 of the first unit body 102, and the slide rail assembly 133 is interactively connected with the guide groove 132. In the present embodiment, four sets of guide grooves 132 are provided at one end of the mechanism body 130, and guide bearings are installed on the guide grooves 132. Combined with Figure 3 As shown, the slide rail assembly 133 on the power base 109 is provided with four slide rails corresponding to the four sets of guide grooves 132 , and is used to realize the assembly or disassembly of the transverse connection mechanism 101 and the first unit body 102 and the second unit body 103 .

[0059] Preferably, the control unit 104 is arranged in the mechanism body 130. An accordion cover 134 is provided on the top of the mechanism body 130 to prevent foreign matter from entering the control unit 104. The control unit 104 provides power and related signal processing for the on-wing engine replacement device 100. The power supply can supply power to the driving mechanism and the lifting mechanism of the first unit body 102 and the second unit body 103. The power supply can be an external power supply or a built-in battery to meet the engine replacement operation under different working conditions. The control unit 104 can collect the operation data in the on-wing engine replacement work and transmit it to an external device. The operation data includes data such as the transportation of civil aviation engines, on-wing engine replacement positioning, attitude adjustment, safety warning, and obstacle recognition and avoidance. The control unit 104 is used to realize intelligent control and human-computer interaction in the on-wing engine replacement process.

[0060] Preferably, a second emergency stop switch 135 and a second operation indicator light 136 are provided on the mechanism body 130. The second emergency stop switch 135 is used to implement emergency operation of the on-wing transaxle device 100, and the second operation indicator light 136 is used to indicate the operation status of the on-wing transaxle device 100.

[0061] Preferably, a sensor 137 is provided on the side of the transverse connection mechanism 101 for monitoring obstacles around the transverse connection mechanism 101. The sensor 137 may be a laser sensor 111. It should be noted that the sensor components of the first unit body 102 and the second unit body 103, and the sensor 307 of the transverse connection mechanism 101 constitute a safety protection system of the on-wing engine replacement device 100, which can realize safety warning, obstacle identification and avoidance of civil aviation engines during transportation and engine replacement.

[0062] Preferably, the on-wing engine replacement device 100 also has an operating handle 138. The operating handle 138 communicates wirelessly with the control unit 104. The operating handle 138 controls the first unit body 102, the second unit body 103 and the transverse connection mechanism 101 through the control unit. The operating handle 138 is designed on the left side of the transverse connection mechanism 101 and adopts a convenient hanging design for easy access by operators. The operating handle 138 has a touch screen, which can display the operating status of the on-wing engine replacement device 100. The staff can realize the ground transfer and on-wing engine replacement of the civil aircraft engine by operating the handle.

[0063] The following is a description of the actual operation process of the on-wing engine replacement device in conjunction with all the accompanying drawings. The specific steps include:

[0064] a) Install the civil aircraft engine on the engine bracket and secure it with bolts;

[0065] b) Move the on-wing engine replacement device to the front end of the engine bracket by operating the handle, and try to ensure that the center line of the on-wing engine replacement device coincides with the center line of the engine bracket;

[0066] c) Separating the first unit body and the second unit body of the on-wing engine replacement device to the same displacement on both sides by operating the handle, driving the on-wing engine replacement device to a certain position, and ensuring that the adapter connector is aligned with the lifting hole of the engine bracket;

[0067] d) The first unit body and the second unit body of the drive wing replacement equipment converge to the same displacement, ensuring that the adapter connector is reliably and firmly connected to the engine bracket;

[0068] e) Drive the on-wing engine replacement equipment to transfer the engine to the appropriate position just below the aircraft wing pylon;

[0069] f) Calibrate the parameters of the non-contact displacement sensors of the first unit body and the second unit body respectively, wherein the non-contact displacement sensors should be calibrated with the corresponding limit blocks on the aircraft wing suspension;

[0070] g) Pre-adjust the position of the civil aviation engine in terms of α, β, and γ angle rotations by visual observation through the touch screen interface of the operating handle, and after the angles are adjusted in place, perform translation adjustments in the X, Y, and Z directions;

[0071] h) When the adjusted engine attitude value and the theoretical attitude value are within the tolerance range, the on-wing engine replacement equipment feedback attitude adjustment is completed;

[0072] i) After the on-wing engine replacement operation is completed, the four sets of lifting mechanisms on the first and second modules of the on-wing engine replacement equipment fall back to the lowest point;

[0073] j) Use the operating handle to transfer the on-wing engine replacement equipment away from the on-wing engine replacement station to complete the entire operation.

[0074] It should be noted that during the posture adjustment process, the control unit monitors the values ​​of the torque of each axis and the three-dimensional force sensor in real time and feeds back to the control unit. When a sudden change occurs in a certain direction of force and torque, the control unit adjusts according to a predetermined algorithm to keep the force on the first unit body and the second unit body balanced.

[0075] The present invention provides an on-wing engine replacement device, which has the following functions:

[0076] a) Realize six-degree-of-freedom attitude adjustment during on-wing engine replacement of civil aviation engines;

[0077] b) Realize the free transportation of civil aviation engines on the ground;

[0078] c) Realize obstacle recognition and avoidance during ground transportation of civil aviation engines;

[0079] d) Provide safety warning during the on-wing engine replacement process to prevent collision;

[0080] e) Realize the collection and data transmission of aircraft engine on-wing replacement information;

[0081] f) Realize artificial intelligence control of the entire on-wing engine replacement process.

[0082] The present invention provides an on-wing engine replacement device, the main features of which are as follows:

[0083] a) Replace the conventional guide tooling method to avoid collision with obstacles during the replacement process;

[0084] b) Adopting lifting mechanism to replace manual lifting operation to improve the accuracy and work efficiency of on-wing engine replacement;

[0085] c) Four sets of lifting mechanisms to increase the flexibility of the engine replacement equipment and realize the six-degree-of-freedom attitude adjustment of civil aviation engines;

[0086] d) Arrange multiple sets of sensors to realize obstacle recognition, alarm and avoidance during the transportation of civil aviation engines;

[0087] e) Design adaptable connectors to accommodate engine brackets of different specifications.

[0088] 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 on-wing engine replacement device, applicable to civil aviation engines, comprising: Transverse connection mechanism; A first unit body, one end of which is connected to one end of the transverse connection mechanism, the first unit body comprises a unit body support, a pedal, a driving mechanism, and a lifting mechanism, the driving mechanism is arranged on the unit body support, and is used to drive the first unit body to move; the pedal is connected to the unit body support through the lifting mechanism, the pedal is used to carry the engine bracket, the engine bracket is used to support the civil aviation engine, and the lifting mechanism is used to control the lifting of the pedal; A second unit body, one end of which is connected to the other end of the transverse connection mechanism, the second unit body has the same structure as the first unit body, and the engine bracket is supported by the pedals of the first unit body and the second unit body; A control unit is arranged on the transverse connection mechanism, and the control unit is used to control the action of the driving mechanism of the first unit body and the second unit body to realize the transportation of the civil aviation engine. The control unit is also used to control the action of the lifting mechanism of the first unit body and the second unit body to realize the six-degree-of-freedom attitude adjustment of the civil aviation engine.

2. The on-wing engine replacement device according to claim 1, characterized in that: The driving mechanism comprises two identical driving assemblies, which are respectively arranged at the ends of the unit body support; The driving assembly comprises a power base, a driving steering wheel and a sensor assembly. The driving steering wheel is arranged at the bottom of the power base, and the sensor assembly is arranged on the power base for detecting obstacles.

3. The on-wing engine replacement device according to claim 2, characterized in that: The sensor assembly includes a plurality of force sensors and a laser sensor, wherein the force sensors are arranged at the lower part of the power base so as to be close to the contact surface of the driving steering wheel.

4. The on-wing engine replacement device according to claim 3, characterized in that: The force sensor includes a front force sensor and a side force sensor. The front force sensor is arranged at the front end of the power base to detect obstacles in the front end direction. The side force sensors are arranged on both sides of the power base to detect obstacles on the sides.

5. The on-wing engine replacement device according to claim 3, characterized in that: A first emergency stop switch and a first operating indicator light are provided on the top of the power base. The first emergency stop switch is used to implement emergency operation on the first unit body, and the first operating indicator light is used to indicate the operating state of the first unit body.

6. The on-wing engine replacement device according to claim 1, characterized in that: The lifting mechanism includes two identical lifting assemblies, which are respectively arranged at two ends of the unit body support to respectively connect two ends of the pedal; The control unit synchronously controls the lifting components to achieve vertical lifting of the civil aviation engine; the control unit coordinately controls the lifting components to achieve six-degree-of-freedom attitude adjustment of the civil aviation engine.

7. The on-wing engine replacement device according to claim 6, characterized in that: A guide rail and a support are provided on the unit body support; The lifting assembly comprises a long support, a short support and a driving motor, wherein the long support and the short support are connected by a rotating shaft, one end of the long support is slidably connected to the guide rail, and the other end is rotatably connected to the end of the pedal; one end of the short support is rotatably connected to the rotating shaft, and the other end is rotatably connected to the support; The driving motor is arranged on the short support, and the driving mechanism is used to drive one end of the long support to slide on the guide rail, so as to drive the end of the pedal to be lifted or lowered.

8. The on-wing engine replacement device according to claim 7, characterized in that: The lifting assembly further includes a coupling, a trapezoidal screw, a trapezoidal nut, and a shaft flange. The driving motor is connected to the trapezoidal screw through the coupling. The trapezoidal nut is fixed to the long support through the shaft flange. The trapezoidal nut is arranged on the trapezoidal screw, and the two are threadedly matched. The driving motor is started to drive the trapezoidal screw to rotate through the coupling, so that the trapezoidal nut drives one end of the long support to move on the guide rail.

9. The on-wing engine replacement device according to claim 1, characterized in that: A plurality of adapter connectors are arranged on the pedal, and the adapter connectors can move along the length direction of the pedal and be fixed, and the pedal is connected to the engine bracket through the adapter connectors.

10. The on-wing engine replacement device according to claim 2, characterized in that: The transverse connection mechanism comprises a mechanism body, universal wheels and guide grooves, a plurality of sets of universal wheels are arranged at the bottom of the mechanism body, and guide grooves are arranged at both ends of the mechanism body; A slide rail assembly is provided on the power base and is interactively connected with the guide groove.

11. The on-wing hair replacement device according to claim 10, characterized in that: The control unit is arranged in the mechanism body, and an accordion cover is arranged on the top of the mechanism body to prevent foreign matter from entering the control system.

12. The on-wing hair replacement device according to claim 10, characterized in that: A second emergency stop switch and a second operating indicator light are provided on the mechanism body. The first emergency stop switch is used to implement emergency operation of the on-wing engine replacement device, and the second operating indicator light is used to indicate the operating status of the on-wing engine replacement device.

13. The on-wing engine replacement device according to claim 10, characterized in that: The on-wing hair replacement device further includes an operating handle, which is in wireless communication with the control unit, and which controls the actions of the first unit body, the second unit body and the transverse connection mechanism through the control unit.

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