A multi-degree of freedom adjustment mechanism for a space engine

Abstract

The utility model discloses a kind of multi-degree-of-freedom adjusting mechanism for space engine belongs to large equipment transfer technical field.The multi-degree-of-freedom adjusting mechanism includes support platform, support frame, first bracket, second bracket and drive assembly;Support frame is slidably arranged on support platform along first direction;The both ends of second bracket are provided with support, each support is provided with movable block, each movable block is slidably arranged on corresponding support;Drive assembly includes first driving part, second driving part, third driving part, fourth driving part, fifth driving part and sixth driving part, the fixed end of fourth driving part and the fixed end of fifth driving part are rotatably arranged at the both ends of first bracket.The multi-degree-of-freedom adjusting mechanism for space engine provided in the utility model embodiment can automatically complete multi-degree-of-freedom adjustment of space engine by multiple driving parts, and the whole adjustment process is efficient and reliable.

Description

Technical Field

[0001] This utility model belongs to the field of large equipment transfer technology, specifically relating to a multi-degree-of-freedom adjustment mechanism for aerospace engines. Background Technology

[0002] With the continuous development of modern industrial technology, it is necessary to continuously improve work efficiency, increase work accuracy, enhance personnel safety, and reduce labor intensity during equipment transportation.

[0003] Currently, the installation and maintenance of large equipment (such as aircraft engines) still require manual handling and on-site installation. Tools are often used for repeated horizontal and vertical fine-tuning to ensure six degrees of freedom adjustment in the X, Y, and Z axes, as well as pitch, roll, and yaw angles, thereby achieving precise docking of the large equipment with the docking carrier. However, this manual operation not only poses a safety risk but is also inefficient, severely hindering the development of modern industrial technology. Utility Model Content

[0004] In view of the above-mentioned defects or improvement needs of the existing technology, this utility model provides a multi-degree-of-freedom adjustment mechanism for aerospace engines. Its purpose is to automatically complete the multi-degree-of-freedom adjustment of aerospace engines through multiple driving components. The entire adjustment process is highly efficient and reliable, and does not require repeated manual operation with the aid of tools, thus promoting the development of modern industrial technology.

[0005] To achieve the above objectives, this utility model provides a multi-degree-of-freedom adjustment mechanism for aerospace engines, the multi-degree-of-freedom adjustment mechanism including a support platform, a support frame, a first bracket, a second bracket, and a drive assembly; The support frame is slidably arranged on the support platform along a first direction; The first bracket and the second bracket are parallel and spaced apart along the second direction, and both extend along the second direction. The first bracket is slidably arranged on the support frame along the second direction. Each end of the second bracket is provided with a support, and each support is provided with a movable block. Each movable block is slidably arranged on the corresponding support. The sliding directions of the two movable blocks are symmetrically arranged along the center of the second bracket and form an angle with the second direction, so that each movable block moves toward or away from the center direction of the second bracket. The drive assembly includes a first drive member, a second drive member, a third drive member, a fourth drive member, a fifth drive member, and a sixth drive member. The support platform and the support frame are connected by the first drive member, the support frame and the first bracket are connected by the second drive member, and the fixed end of the support frame and the sixth drive member are connected by the third drive member. The fixed ends of the fourth and fifth drive members are rotatably arranged at both ends of the first bracket, and the rotation axes of the fixed ends of the fourth and fifth drive members are both arranged along a second direction. The fixed end of the sixth drive member is slidably arranged on the support frame along the second direction. The output end of the sixth drive member is connected by a drive to the center of the second bracket to drive the second bracket to move along a third direction. Pins are movably inserted into the output ends of the fourth and fifth drive members and the two movable blocks. The output ends of the fourth and fifth drive members are used to drive the corresponding pins to move along a third direction. Each pin is used to be inserted into the positioning hole corresponding to the aerospace engine.

[0006] Optionally, the support frame includes two straight beams and multiple connecting beams. The two straight beams extend along a first direction and are fixedly connected by the multiple connecting beams. Each straight beam has a slide rail arranged along the first direction at both ends, and the support platform slides in cooperation with each slide rail.

[0007] Optionally, the multiple connecting beams are arranged in a star-shaped pattern.

[0008] Optionally, each of the straight beams and each of the connecting beams are channel steel.

[0009] Optionally, the first bracket includes a transition section, two connecting sections, and two support sections. The transition section is slidably arranged on the support frame along a second direction. The two ends of the transition section are respectively connected to one end of the two connecting sections. The connecting sections are arranged at an angle. The other ends of the two connecting sections are respectively connected to the corresponding support sections. The two support sections are spaced apart from the transition section in a third direction. The fixed ends of the fourth driving member and the fifth driving member are rotatably arranged on the corresponding support sections.

[0010] Optionally, each of the support segments has two lugs spaced apart along the second direction, and a first rotating shaft is inserted into each of the two corresponding lugs. Each first rotating shaft extends along the second direction, and the fixed end of the fourth driving member or the fixed end of the fifth driving member can be rotatably sleeved on the corresponding first rotating shaft.

[0011] Optionally, both the output end of the fourth driving member and the output end of the fifth driving member are provided with a rotating seat arranged in a rotatable manner. The rotation axis of the rotating seat is arranged along the first direction, and the pin can be movably inserted into the side of each rotating seat away from the corresponding output end.

[0012] Optionally, each of the rotating seats includes a connecting plate and two parallel spaced ear plates. The two sides of the connecting plate are perpendicularly connected to the two ear plates respectively. The output ends of the fourth driving member and the fifth driving member are located between the corresponding two ear plates and are hinged to one end of the two ear plates through a second rotating shaft. The pin is movably inserted into the other end of the two ear plates.

[0013] Optionally, the support platform includes a plurality of spaced-apart seats for connecting a tractor.

[0014] Optionally, the first driving component, the second driving component, the third driving component, the fourth driving component, the fifth driving component, and the sixth driving component are servo cylinders or linear modules.

[0015] The aforementioned improved technical features can be combined with each other as long as they do not conflict with each other.

[0016] In summary, the beneficial effects of the above-described technical solutions conceived by this utility model compared with the prior art include: The multi-degree-of-freedom adjustment mechanism for aerospace engines provided in this embodiment of the invention, when transferring and docking the aerospace engine, firstly, is installed on the output end of a tractor, and the two ends of multiple pins are respectively connected in the multi-degree-of-freedom adjustment mechanism and in the aerospace engine. At this time, the first and second brackets provide reliable support at both ends of the aerospace engine, ensuring the stability of the aerospace engine during subsequent fine-tuning. Then, the tractor transports the aerospace engine to the vicinity of the target position on the corresponding docking carrier, thereby realizing the long-stroke transfer and initial positioning of the aerospace engine.

[0017] Next, for displacement adjustment in the first direction, the first driving component drives the support frame to slide along the first direction, thereby achieving fine-tuning of the aero-engine's displacement in the first direction. For displacement adjustment in the second direction, the second driving component drives the first bracket, and simultaneously the third driving component drives the sixth driving component, causing the first bracket and the sixth driving component to move synchronously in the same direction. This allows both brackets to move synchronously in the same direction, thus causing both ends of the aero-engine to move synchronously along the second direction, thereby achieving fine-tuning of the overall displacement of the aero-engine in the second direction. For displacement adjustment in the third direction, the fourth and fifth driving components drive one end of the aero-engine to move along the third direction, and simultaneously the sixth driving component drives the other end of the aero-engine to move along the third direction, ultimately achieving fine-tuning of the overall displacement of the aero-engine in the third direction. For pitch angle adjustment (i.e., rotation around the second direction), the fourth and fifth driving components do not move; the sixth driving component drives the other end of the aero-engine to rise and fall (the fixed ends of the fourth and fifth driving components drive one end of the aero-engine to rise and fall accordingly during rotation), thereby achieving precise adjustment of the aero-engine's pitch angle. For yaw angle adjustment (i.e., rotation around the first direction), the fourth or fifth drive component on one side drives one end of the aero-engine to rise and fall. Meanwhile, the two movable blocks on the second bracket slide on their corresponding supports (one block rises diagonally, the other descends diagonally), causing the other end of the aero-engine to rise and fall accordingly, thus achieving precise adjustment of the aero-engine's yaw angle. For yaw angle adjustment (i.e., rotation around the third direction), the second drive component drives the first bracket to move forward (e.g., to the right), while simultaneously the third drive component drives the sixth drive component to move in the opposite direction (e.g., to the left). This causes the first and sixth drive components to move synchronously in opposite directions, allowing both brackets to move synchronously in opposite directions. This causes both ends of the aero-engine to rotate around the center, ultimately achieving precise adjustment of the aero-engine's yaw angle. After the aero-engine completes precise adjustment of all six degrees of freedom, fasteners are used to connect the aero-engine to the docking equipment, ultimately achieving precise docking of the aero-engine.

[0018] In other words, the multi-degree-of-freedom adjustment mechanism for aerospace engines provided by this utility model embodiment can automatically complete the multi-degree-of-freedom adjustment of aerospace engines through multiple driving components. The entire adjustment process is highly efficient and reliable, and does not require repeated manual operation with the aid of tools, thus promoting the development of modern industrial technology. Attached Figure Description

[0019] Figure 1 This is a first view of a multi-degree-of-freedom adjustment mechanism for an aerospace engine provided in an embodiment of this utility model; Figure 2This is a second view of a multi-degree-of-freedom adjustment mechanism for an aerospace engine provided in an embodiment of this utility model; Figure 3 This is a schematic diagram of the structure of the second bracket provided in this embodiment of the utility model; Figure 4 This is a schematic diagram of the structure of the first bracket provided in this embodiment of the utility model; Figure 5 This is a schematic diagram of the rotating seat provided in an embodiment of the present invention.

[0020] In all the accompanying drawings, the same reference numerals denote the same technical features, specifically: 1. Support platform; 2. Support frame; 21. Straight beam; 211. Slide rail; 22. Connecting beam; 3. First bracket; 31. Transfer section; 32. Connecting section; 33. Support section; 34. Seat ear; 4. Second bracket; 41. Support; 411. Waist-shaped hole; 42. Movable block; 51. First driving component; 52. Second driving component; 53. Third driving component; 54. Fourth driving component; 55. Fifth driving component; 56. Sixth driving component; 6. Pin; 7. Rotating seat; 71. Connecting plate; 72. Ear plate. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only for explaining the present utility model and are not intended to limit the present utility model. Furthermore, the technical features involved in the various embodiments of the present utility model described below can be combined with each other as long as they do not conflict with each other.

[0022] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0024] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0025] In this utility model, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0026] Example: Figure 1 This is a first view of a multi-degree-of-freedom adjustment mechanism for an aerospace engine provided in an embodiment of this utility model. Figure 2 This is a second view of a multi-degree-of-freedom adjustment mechanism for aerospace engines provided in an embodiment of this utility model, combined with... Figure 1 and Figure 2 As shown, the multi-degree-of-freedom adjustment mechanism includes a support platform 1, a support frame 2, a first bracket 3, a second bracket 4, and a drive assembly.

[0027] The support frame 2 is slidably arranged on the support platform 1 along the first direction (X-axis direction).

[0028] The first bracket 3 and the second bracket 4 are parallel and spaced apart along the second direction (Y-axis direction), and both extend along the second direction. The first bracket 3 is slidably arranged on the support frame 2 along the second direction.

[0029] Figure 3 This is a schematic diagram of the structure of the second bracket provided in an embodiment of the present invention, as shown below. Figure 3 As shown, both ends of the second bracket 4 are provided with supports 41, and each support 41 is provided with a movable block 42. Each movable block 42 is slidably arranged on the corresponding support 41. The sliding direction of the two movable blocks 42 is symmetrically arranged along the center of the second bracket 4 and forms an angle with the second direction, so that each movable block 42 moves toward or away from the center of the second bracket 4.

[0030] The drive assembly includes a first drive member 51, a second drive member 52, a third drive member 53, a fourth drive member 54, a fifth drive member 55, and a sixth drive member 56. The support platform 1 and the support frame 2 are connected via the first drive member 51. The support frame 2 and the first bracket 3 are connected via the second drive member 52. The fixed ends of the support frame 2 and the sixth drive member 56 are connected via the third drive member 53. The fixed ends of the fourth drive member 54 and the fifth drive member 55 are rotatably arranged at both ends of the first bracket 3, and the rotation axis of the fixed end of the fourth drive member 54 is connected to the fixed end of the fifth drive member 55. The rotation shafts of the ends are all arranged along the second direction. The fixed end of the sixth drive member 56 is slidably arranged on the support frame 2 along the second direction. The output end of the sixth drive member 56 is connected to the center of the second bracket 4 to drive the second bracket 4 to move along the third direction (Z-axis direction). The output ends of the fourth drive member 54, the fifth drive member 55, and the two movable blocks 42 are all movably fitted with pins 6. The output ends of the fourth drive member 54 and the fifth drive member 55 are used to drive the corresponding pins 6 to move along the third direction. Each pin 6 is used to be inserted into the corresponding positioning hole of the aerospace engine.

[0031] The multi-degree-of-freedom adjustment mechanism for aerospace engines provided in this embodiment of the invention, when transferring and docking the aerospace engine, firstly, is installed on the output end of a tractor, and the two ends of multiple pins 6 are respectively connected in the multi-degree-of-freedom adjustment mechanism and in the aerospace engine. At this time, the first bracket 3 and the second bracket 4 provide reliable support at both ends of the aerospace engine, ensuring the stability of the aerospace engine during subsequent fine-tuning. Then, the aerospace engine is transferred to the vicinity of the target position on the corresponding docking carrier by the tractor, thereby realizing the long-stroke transfer and initial positioning of the aerospace engine.

[0032] Next, for displacement adjustment in the first direction, the first drive member 51 drives the support frame 2 to slide along the first direction, thereby achieving fine adjustment of the displacement of the aero-engine in the first direction. For displacement adjustment in the second direction, the second drive member 52 drives the first bracket 3, and simultaneously the third drive member 53 drives the sixth drive member 56, so that the first bracket 3 and the sixth drive member 56 move synchronously in the same direction. This allows the two brackets to move synchronously in the same direction, thereby causing both ends of the aero-engine to move synchronously along the second direction, thus achieving fine adjustment of the overall displacement of the aero-engine in the second direction. For displacement adjustment in the third direction, the fourth drive member 54 and the fifth drive member 55 drive one end of the aero-engine to move along the third direction, and simultaneously the sixth drive member 56 drives the other end of the aero-engine to move along the third direction, thus finally achieving fine adjustment of the overall displacement of the aero-engine in the third direction. For pitch angle adjustment (i.e., rotation around the second direction), the fourth drive component 54 and the fifth drive component 55 do not move. The sixth drive component 56 drives the other end of the aero-engine to rise and fall (the fixed ends of the fourth drive component 54 and the fifth drive component 55 drive one end of the aero-engine to rise and fall accordingly during rotation), thereby achieving precise adjustment of the aero-engine pitch angle. For yaw angle adjustment (i.e., rotation around the first direction), one side of the fourth drive component 54 or the fifth drive component 55 drives one side of the aero-engine to rise and fall, while the two movable blocks 42 on the second bracket 4 slide on the corresponding supports 41 (one movable block 42 rises obliquely, and the other movable block 42 falls obliquely), causing the other two sides of the aero-engine to rise and fall accordingly, thereby ultimately achieving precise adjustment of the aero-engine yaw angle. For yaw angle adjustment (i.e., rotation around a third direction), the second drive component 52 drives the first bracket 3 to move forward (e.g., to the right), while simultaneously the third drive component 53 drives the sixth drive component 56 to move in the opposite direction (e.g., to the left). This causes the first bracket 3 and the sixth drive component 56 to move synchronously in opposite directions, thus enabling the two brackets to move synchronously in opposite directions. This allows the two ends of the aero-engine to rotate around the center, ultimately achieving precise adjustment of the aero-engine's yaw angle. After the aero-engine completes the precise adjustment of six degrees of freedom, the aero-engine and docking equipment are connected using fasteners, thus achieving precise docking of the aero-engine.

[0033] In other words, the multi-degree-of-freedom adjustment mechanism for aerospace engines provided by this utility model embodiment can automatically complete the multi-degree-of-freedom adjustment of aerospace engines through multiple driving components. The entire adjustment process is highly efficient and reliable, and does not require repeated manual operation with the aid of tools, thus promoting the development of modern industrial technology.

[0034] In addition, the overall structure of this multi-degree-of-freedom adjustment mechanism is compact, and multiple driving components can be reused when performing multi-degree-of-freedom adjustments, which greatly reduces the space occupied.

[0035] For example, the first driving component 51, the second driving component 52, the third driving component 53, the fourth driving component 54, the fifth driving component 55, and the sixth driving component 56 are servo cylinders or linear modules, which have high precision and are easy to automate. In addition, each support 41 is provided with an inclined oblong hole 411, and each movable block 42 is fitted with a guide pin. Each guide pin is slidably inserted into the corresponding oblong hole 411, thereby guiding and limiting the movable block 42 during the sliding process.

[0036] See Figure 1 and Figure 2 The support frame 2 includes two straight beams 21 and multiple connecting beams 22. Both straight beams 21 extend along a first direction and are fixedly connected by the multiple connecting beams 22. Each straight beam 21 has a slide rail 211 arranged along the first direction at both ends, and the support platform 1 slides in cooperation with each slide rail 211. The straight beams 21 support the slide rails 211, the multiple slide rails 211 ensure the reliability of the sliding of the support frame 2, and the connecting beams 22 connect the two straight beams 21.

[0037] For example, there are two first driving members 51, and the support platform 1 and each straight beam 21 are connected by a first driving member 51.

[0038] Furthermore, the multiple connecting beams 22 are arranged in a star-shaped pattern, which provides stability and high connection strength.

[0039] In addition, all straight beams 21 and all connecting beams 22 are made of channel steel, which provides high structural strength.

[0040] In this embodiment, the support platform 1 includes multiple spaced-apart seats for connecting to a tractor. Specifically, there are four seats located at the four right angles of the support frame 2, and these four seats can be used to connect to the scissor lift mechanism on the tractor.

[0041] Figure 4 This is a structural schematic diagram of the first bracket provided in an embodiment of the present utility model, as shown below. Figure 4 As shown, the first bracket 3 includes a transition section 31, two connecting sections 32 and two support sections 33. The transition section 31 is slidably arranged on the support frame 2 along the second direction. The two ends of the transition section 31 are respectively connected to one end of the two connecting sections 32. The connecting sections 32 are arranged at an angle. The other ends of the two connecting sections 32 are respectively connected to the corresponding support sections 33. The two support sections 33 are spaced apart from the transition section 31 in the third direction. The fixed end of the fourth driving member 54 and the fixed end of the fifth driving member 55 are rotatably arranged on the corresponding support sections 33.

[0042] In the above embodiment, the transition section 31 plays a sliding role, while the connecting section 32 plays a role in raising the support section 33, reducing the volume of the support section 33, and avoiding interference between the fourth drive member 54 and the fifth drive member 55 and the support frame 2 during installation.

[0043] For example, the end of the connecting segment 32 facing the transition segment 31 has a larger diameter to ensure connection strength.

[0044] Furthermore, each support section 33 has two lugs 34 spaced apart along the second direction. Each of the two corresponding lugs 34 is fitted with a first rotating shaft. Each first rotating shaft extends along the second direction. The fixed end of the fourth driving member 54 or the fixed end of the fifth driving member 55 can be rotatably sleeved on the corresponding first rotating shaft, thereby realizing the rotational installation of the fourth driving member 54 and the fifth driving member 55 on the first bracket 3 through the lugs 34 and the first rotating shaft.

[0045] Figure 5 This is a schematic diagram of the structure of the rotating seat provided in this embodiment of the utility model, combined with... Figure 4 and Figure 5 As shown, a rotating seat 7 is provided on the output end of the fourth driving member 54 and the output end of the fifth driving member 55. The rotation axis of the rotating seat 7 is arranged along the first direction, and a pin 6 can be movably inserted on the side of each rotating seat 7 away from the corresponding output end.

[0046] It is easy to understand that when connecting the multi-degree-of-freedom adjustment mechanism and the space engine via pin 6, the space engine is often hoisted above the multi-degree-of-freedom adjustment mechanism, and then pin 6 is inserted into the space engine after its own lifting and lowering. However, pin 6, located at the front, is prone to interfering with the space engine during the lifting process. The position of pin 6 can be adjusted by rotating seat 7. After pin 6 is raised and lowered into place, it can be rotated back to its original position and inserted into the space engine.

[0047] Specifically, each rotating seat 7 includes a connecting plate 71 and two parallel spaced ear plates 72. The two sides of the connecting plate 71 are perpendicularly connected to the two ear plates 72 respectively (i.e., the whole is H-shaped). The output ends of the fourth driving member 54 and the fifth driving member 55 are located between the corresponding two ear plates 72 and are hinged to one end of the two ear plates 72 through the second rotating shaft. The pin 6 is movably inserted into the other end of the two ear plates 72, thereby achieving reliable rotational support for the pin 6.

[0048] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A multi-degree-of-freedom adjustment mechanism for aerospace engines, characterized in that, The multi-degree-of-freedom adjustment mechanism includes a support platform, a support frame, a first bracket, a second bracket, and a drive assembly; The support frame is slidably arranged on the support platform along a first direction; The first bracket and the second bracket are parallel and spaced apart along the second direction, and both extend along the second direction. The first bracket is slidably arranged on the support frame along the second direction. Each end of the second bracket is provided with a support, and each support is provided with a movable block. Each movable block is slidably arranged on the corresponding support. The sliding directions of the two movable blocks are symmetrically arranged along the center of the second bracket and form an angle with the second direction, so that each movable block moves toward or away from the center direction of the second bracket. The drive assembly includes a first drive member, a second drive member, a third drive member, a fourth drive member, a fifth drive member, and a sixth drive member. The support platform and the support frame are connected by the first drive member, the support frame and the first bracket are connected by the second drive member, and the fixed end of the support frame and the sixth drive member are connected by the third drive member. The fixed ends of the fourth and fifth drive members are rotatably arranged at both ends of the first bracket, and the rotation axes of the fixed ends of the fourth and fifth drive members are both arranged along a second direction. The fixed end of the sixth drive member is slidably arranged on the support frame along the second direction. The output end of the sixth drive member is connected by a drive to the center of the second bracket to drive the second bracket to move along a third direction. Pins are movably inserted into the output ends of the fourth and fifth drive members and the two movable blocks. The output ends of the fourth and fifth drive members are used to drive the corresponding pins to move along a third direction. Each pin is used to be inserted into the positioning hole corresponding to the aerospace engine.

2. The multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 1, characterized in that, The support frame includes two straight beams and multiple connecting beams. The two straight beams extend along a first direction and are fixedly connected by the multiple connecting beams. Each straight beam has a slide rail arranged along the first direction at both ends, and the support platform slides in cooperation with each slide rail.

3. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 2, characterized in that, The multiple connecting beams are arranged in a star-shaped pattern.

4. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 2, characterized in that, All of the straight beams and all of the connecting beams are channel steel.

5. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 1, characterized in that, The first bracket includes a transition section, two connecting sections, and two support sections. The transition section is slidably arranged on the support frame along a second direction. The two ends of the transition section are respectively connected to one end of the two connecting sections. The connecting sections are arranged at an angle. The other ends of the two connecting sections are respectively connected to the corresponding support sections. The two support sections are spaced apart from the transition section in a third direction. The fixed ends of the fourth driving member and the fifth driving member are rotatably arranged on the corresponding support sections.

6. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 5, characterized in that, Each of the support sections has two lugs spaced apart along the second direction. A first rotating shaft is inserted into each of the two corresponding lugs. Each first rotating shaft extends along the second direction. The fixed end of the fourth driving member or the fixed end of the fifth driving member can be rotatably sleeved on the corresponding first rotating shaft.

7. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 1, characterized in that, Both the output end of the fourth driving member and the output end of the fifth driving member are provided with rotating seats arranged in a rotatable manner. The rotation axis of the rotating seats is arranged along the first direction, and the pin can be movably inserted into the side of each rotating seat away from the corresponding output end.

8. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to claim 7, characterized in that, Each of the rotating seats includes a connecting plate and two parallel spaced ear plates. The two sides of the connecting plate are perpendicularly connected to the two ear plates respectively. The output ends of the fourth driving member and the fifth driving member are located between the corresponding two ear plates and are hinged to one end of the two ear plates through a second rotating shaft. The pin is movably inserted into the other end of the two ear plates.

9. A multi-degree-of-freedom adjustment mechanism for aerospace engines according to any one of claims 1 to 8, characterized in that, The support platform includes multiple spaced seats for connecting to a tractor.

10. A multi-degree-of-freedom adjustment mechanism for an aerospace engine according to any one of claims 1 to 8, characterized in that, The first driving component, the second driving component, the third driving component, the fourth driving component, the fifth driving component, and the sixth driving component are servo cylinders or linear modules.

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