An annular cutting machine for processing the outer shell of a space equipment

Abstract

The present invention belongs to the technical field of cutting machine equipment, and discloses an annular cutting machine for processing the outer shell of aerospace equipment, including a support table and an aerospace outer shell body. At the front and rear ends of the bottom of the inner cavity of the support table, first limiting rods are fixedly connected. On both sides of the outer surface of the first limiting rods, sliders are sleeved. Inside the limiting sleeve, a connecting sleeve is connected by a bearing, and on the inner side of the limiting sleeve, a rubber anti-slip sheet is fixedly connected. Through the cooperation among structures such as the electro-hydraulic rod, the push rod, the limiting sleeve and the rubber anti-slip sheet, the device has the effect of stably fixing the outer shell of the aerospace equipment during cutting. By placing the aerospace outer shell body above the two second limiting rods, the device plays a role in fixing the two sides of the outer surface of the aerospace outer shell body for the first time, thus facilitating the subsequent cutting of the aerospace outer shell body by the operator, and further facilitating the use of the operator.

Description

Technical Field

[0001] The present invention belongs to the technical field of cutting machine equipment, and specifically relates to an annular cutting machine for processing the outer shell of aerospace equipment. Background Technique

[0002] Aerospace parts include various materials used in aircraft and their power plants, accessories, and instruments. They are one of the decisive factors in the development of aerospace engineering technology. Aerospace materials science is a pioneering branch of materials science. The design of aircraft continuously poses new problems to materials science, promoting the development of aerospace materials science forward. The emergence of various new materials also provides new possibilities for the design of aircraft, greatly promoting the development of aerospace technology. Among them, the outer shell of aerospace equipment is cylindrical and protects various internal aerospace parts.

[0003] Currently, when operating personnel cut the outer shell of aerospace equipment, they often need to use cutting equipment. The existing cutting equipment fixes the outer shell of aerospace equipment by using clamping blocks. At the same time, an annular line is drawn on the outer shell of aerospace equipment, and then the operating personnel use a cutting machine to cut the outer shell of aerospace equipment along the annular line. However, since the outer shell of aerospace equipment is fixed by two clamping blocks, when people cut the outer shell of aerospace equipment, the incision is not flat due to the unstable fixation of the clamping blocks on the outer shell of aerospace equipment, resulting in the outer shell of this aerospace equipment not meeting the specified requirements, which is not convenient for the operating personnel to use. Therefore, an annular cutting machine for processing the outer shell of aerospace equipment is proposed to solve the problems raised in the background technique. Summary of the Invention

[0004] To solve the problems raised in the above background technique, the present invention provides an annular cutting machine for processing the outer shell of aerospace equipment. By placing the aerospace shell body above two second limiting rods, at this time, the electric hydraulic rods are operated to reduce the lengths of the two electric hydraulic rods, so that the two sliders drive the vertical frame to move towards each other, and then the vertical frame drives the push rod to move towards the side close to the aerospace shell body. At the same time, due to the limiting effect of the two second limiting rods on the limiting sleeve, when the sleeve rod drives the limiting sleeve and the rubber anti-slip sheet contacts one side of the aerospace shell body, the elastic spring will be compressed. At this time, the device plays a first fixing role on both sides of the outer surface of the aerospace shell body, making this structure have the advantage of stably fixing the outer shell of aerospace equipment during cutting.

[0005] To achieve the above object, the present invention provides the following technical solutions: A ring cutting machine for processing the outer shell of a space equipment, including a support table and the space equipment outer shell body. At the front and rear ends of the bottom of the inner cavity of the support table, there are fixedly connected with first limiting rods. On both sides of the outer surface of the first limiting rods, there are sleeved with sliders. At the front and rear ends of the inner side of the sliders, there are fixedly connected with electric hydraulic rods. At the top of the sliders, there is fixedly connected with a vertical frame. At the top of the inner cavity of the vertical frame, there is movably connected with a push rod. On the outer surface of the push rod, there are sleeved with a sleeve rod and a circular ring plate. On the inner side of the circular ring plate, there is fixedly connected with an elastic spring. At the front and rear ends of the top of the inner cavity of the support table, there is movably connected with a second limiting rod. On the outer surface of the second limiting rod, there is movably connected with a limiting sleeve. Inside the limiting sleeve, there is a bearing connection with a connecting sleeve. On the inner side of the limiting sleeve, there is fixedly connected with a rubber anti-slip sheet.

[0006] In the above technical solution, preferably, on the outer surface of the sleeve rod, on the side close to the circular ring plate, there are fixedly connected with brackets at equal angles in a ring shape. On the side of the brackets away from the circular ring plate, there is fixedly connected with a sleeve. Inside the cavity of the sleeve, there is movably connected with a round rod. On the outer surface of the sleeve, on the side away from the circular ring plate, there is fixedly connected with a connecting frame. On the outer surface of the push rod, there are hinged with connecting rods at equal angles in a ring shape.

[0007] In the above technical solution, preferably, on the inner side of the push rod, there is fixedly connected with a cross-shaped block. On one side of the bottom of the outer surface of the support table, there is fixedly connected with a first motor. At the output shaft end of the first motor, there is fixedly connected with a threaded rod. In the middle of the outer surface of the threaded rod, there is a threaded connection with a matching block. At the front and rear ends of the inner cavity of the matching block, there are fixedly connected with electric telescopic rods. At the top of the electric telescopic rods, there is fixedly connected with a cutting machine. At the top of the outer side of the vertical frame, there is fixedly connected with a second motor.

[0008] In the above technical solution, preferably, the number of the sliders is two. At the front and rear ends of the inner cavities of the two sliders, they are respectively movably connected with both sides of the outer surfaces of the front and rear first limiting rods. The electric hydraulic rods are located inside the sliders. The inner ends of the electric hydraulic rods are fixedly connected with the support table. The front and rear ends of the bottom of the space equipment outer shell body are in contact with the upper surfaces of the front and rear second limiting rods.

[0009] In the above technical solution, preferably, the sleeve rod and the circular ring plate are respectively movably connected with the inner side and the outer side of the outer surface of the push rod. The inner side of the elastic spring is fixedly connected with the outer side of the sleeve rod. The elastic spring is movably sleeved on the outer surface of the push rod. The side of the circular ring plate opposite to the push rod is in contact with the push rod.

[0010] In the above technical solution, preferably, the inner cavities at the front and rear ends of the bottom of the limit sleeve are respectively movably connected to the outer surfaces of the front and rear limit sleeves, the inner cavity of the connecting sleeve is fixedly connected to the inner side of the outer surface of the sleeve rod, the limit sleeve and the rubber anti-slip sheet are equal in diameter to the aerospace shell body, and the rubber anti-slip sheet is made of rubber.

[0011] In the above technical solution, preferably, the top of the round rod is semi-circular and made of rubber, and the round rod is located in the inner cavity of the aerospace shell body and matches the inner cavity of the aerospace shell body.

[0012] In the above technical solution, preferably, the outer surface of the inner end of the connecting rod is hinged to the inner cavity of the inner end of the round rod.

[0013] In the above technical solution, preferably, the inner cavity in the middle of the connecting frame is cross-shaped, the outer surface of the cross block is adaptively clamped with the inner cavity in the middle of the connecting frame, and the two sides of the outer surface of the threaded rod are respectively movably connected to the two sides of the bottom of the inner cavity of the support table.

[0014] In the above technical solution, preferably, the output shaft end of the second motor is fixedly connected to the outer side of the push rod.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0016] 1. Through the cooperation between structures such as the electro-hydraulic rod, the push rod, the limit sleeve, and the rubber anti-slip sheet, the device has the effect of stably fixing the aerospace equipment shell during cutting. By placing the aerospace shell body above the two second limit rods, when the electro-hydraulic rod is operated at this time, the lengths of the two electro-hydraulic rods are reduced, so that the two sliders drive the vertical frame to move towards each other, and then the vertical frame drives the push rod to move towards the side close to the aerospace shell body. At the same time, due to the limiting effect of the two second limit rods on the limit sleeve, when the sleeve rod drives the limit sleeve and the rubber anti-slip sheet contacts one side of the aerospace shell body, the elastic spring will be compressed. At this time, the device plays a first fixing role on both sides of the outer surface of the aerospace shell body, which facilitates the subsequent cutting of the aerospace shell body by the operator, and thus facilitates the use of the operator.

[0017] 2. Through the cooperation among structures such as the bracket, sleeve, connecting frame, and connecting rod, the device has the effect of secondary fixation on the outer shell of the aerospace equipment during cutting. By continuously operating the electro-hydraulic rod, the push rod continues to move towards the side close to the aerospace outer shell body. At the same time, since the rubber anti-slip sheet on the limit sleeve contacts the aerospace outer shell body, when the push rod continues to move towards the side close to the aerospace outer shell body, the fixed sleeve rod causes the elastic spring to be further compressed. At the same time, the push rod drives the bottom of the connecting rod to move towards the side close to the aerospace outer shell body, so that the inner end of the connecting rod pushes the round rod to move outward, and then the rubber arc block at the top of the round rod contacts the inner cavity of the aerospace outer shell body, thus realizing the secondary fixation of the aerospace outer shell body and further improving the fixation effect on the outer shell of the aerospace equipment.

[0018] 3. Through the cooperation among structures such as the mating block, electric telescopic rod, cutting machine, and second motor, the device has the function of circularly cutting the outer shell of the aerospace equipment. By operating the first motor, the threaded rod will rotate, and then the mating block drives the electric telescopic rod and the cutting machine to move, so that the top of the cutting machine is at the bottom of the position where the aerospace outer shell body needs to be cut. At this time, operating the electric telescopic rod makes the cutting machine move upward, thus realizing the cutting of the bottom of the aerospace outer shell body. At the same time, the operator operates the second motor. At this time, the operation of the second motor will make the push rod rotate, and at the same time drive the sleeve rod, bracket, and connecting rod to rotate, and then make the circular ring plate, connecting frame, and aerospace outer shell body rotate, finally realizing the circular cutting of the aerospace outer shell body and facilitating the use of the operator. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is the schematic diagram of the overall structure of the present invention;

[0020] Figure 2 is Figure 1 the enlarged view of part A in

[0021] Figure 3 is the front sectional structure schematic diagram of the present invention;

[0022] Figure 4 is Figure 3 the enlarged view of part B in

[0023] Figure 5 is Figure 4 the enlarged view of part C in

[0024] Figure 6 is the top structure schematic diagram of the present invention;

[0025] Figure 7 is the structure schematic diagram of the slider of the present invention;

[0026] Figure 8 Exploded view of the push rod of the present invention;

[0027] Figure 9 Schematic structural diagram of the electric telescopic rod of the present invention.

[0028] In the figure: 1, support table; 2, first limiting rod; 3, slider; 4, electro-hydraulic rod; 5, vertical frame; 6, aerospace shell body; 7, push rod; 8, sleeve rod; 9, circular ring plate; 10, elastic spring; 11, limiting sleeve; 12, rubber anti-slip sheet; 13, second limiting rod; 14, bracket; 15, sleeve; 16, round rod; 17, connecting frame; 18, connecting rod; 19, cross block; 20, first motor; 21, threaded rod; 22, mating block; 23, electric telescopic rod; 24, cutting machine; 25, second motor; 26, connecting sleeve. Detailed implementation manners

[0029] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0030] As Figures 1 to 9 shown, the present invention provides an annular cutting machine for processing the outer shell of aerospace equipment, including a support table 1 and an aerospace shell body 6. The front and rear ends of the bottom of the inner cavity of the support table 1 are fixedly connected with first limiting rods 2. Both sides of the outer surface of the first limiting rods 2 are sleeved with sliders 3. The front and rear ends of the inner side of the sliders 3 are fixedly connected with electro-hydraulic rods 4. The top of the sliders 3 is fixedly connected with a vertical frame 5. The top of the inner cavity of the vertical frame 5 is movably connected with a push rod 7. The outer surface of the push rod 7 is sleeved with a sleeve rod 8 and a circular ring plate 9. The inner side of the circular ring plate 9 is fixedly connected with an elastic spring 10. The front and rear ends of the top of the inner cavity of the support table 1 are movably connected with second limiting rods 13. The outer surface of the second limiting rods 13 is movably connected with a limiting sleeve 11. The inside of the limiting sleeve 11 is connected with a connecting sleeve 26 by a bearing. The inner side of the limiting sleeve 11 is fixedly connected with a rubber anti-slip sheet 12; by operating the electro-hydraulic rod 4 at this time, the two sliders 3 drive the vertical frame 5 to move towards each other, and then the vertical frame 5 drives the push rod 7 to move towards the side close to the aerospace shell body 6. At the same time, due to the limiting effect of the two second limiting rods 13 on the limiting sleeve 11, when the sleeve rod 8 drives the limiting sleeve 11 and the rubber anti-slip sheet 12 contacts one side of the aerospace shell body 6, the elastic spring 10 will be compressed. At this time, the device plays a role in fixing the two sides of the outer surface of the aerospace shell body 6 for the first time, so as to facilitate the subsequent cutting of the aerospace shell body 6 by the operator, and thus facilitate the use of the operator.

[0031] As shown Figure 2 and 4 shown in FIG. 8, on one side of the outer surface of the sleeve rod 8 near the circular ring plate 9, brackets 14 are fixedly connected annularly and equiangularly. On the side of the bracket 14 away from the circular ring plate 9, a sleeve 15 is fixedly connected. A round rod 16 is movably connected in the inner cavity of the sleeve 15. On the side of the outer surface of the sleeve 15 away from the circular ring plate 9, a connecting frame 17 is fixedly connected. Connecting rods 18 are annularly and equiangularly hinged to the outer surface of the push rod 7; by continuously operating the electro-hydraulic rod 4, the push rod 7 continues to move towards the side close to the aerospace shell body 6. At the same time, since the rubber anti-slip piece 12 on the limit sleeve 11 contacts the aerospace shell body 6, when the push rod 7 continues to move towards the side close to the aerospace shell body 6 at this time, the fixed sleeve rod 8 causes the elastic spring 10 to be further compressed. At the same time, the push rod 7 drives the bottom of the connecting rod 18 to move towards the side close to the aerospace shell body 6, so that the inner end of the connecting rod 18 pushes the round rod 16 to move outwards, so that the rubber arc block at the top of the round rod 16 contacts the inner cavity of the aerospace shell body 6, thereby realizing the secondary fixation of the aerospace shell body 6.

[0032] As shown Figure 3 and 5 shown in FIG. 9, a cross block 19 is fixedly connected to the inner side of the push rod 7. A first motor 20 is fixedly connected to one side of the bottom of the outer surface of the support table 1. The output shaft end of the first motor 20 is fixedly connected with a threaded rod 21. A mating block 22 is threadedly connected to the middle of the outer surface of the threaded rod 21. Electric telescopic rods 23 are fixedly connected to the front and rear ends of the inner cavity of the mating block 22. A cutting machine 24 is fixedly connected to the top of the electric telescopic rod 23. A second motor 25 is fixedly connected to the top of the outer side of the vertical frame 5; by operating the first motor 20, the threaded rod 21 will rotate, and then the mating block 22 drives the electric telescopic rod 23 and the cutting machine 24 to move, so that the top of the cutting machine 24 is at the bottom of the place where the aerospace shell body 6 needs to be cut. At this time, the electric telescopic rod 23 is operated to make the cutting machine 24 move upwards, thereby realizing the cutting of the bottom of the aerospace shell body 6. At the same time, the operator operates the second motor 25. At this time, the operation of the second motor 25 will cause the push rod 7 to rotate, and at the same time drive the sleeve rod 8, the bracket 14 and the connecting rod 18 to rotate, so that the circular ring plate 9, the connecting frame 17 and the aerospace shell body 6 rotate, thereby realizing the circular cutting of the aerospace shell body 6.

[0033] As shown Figure 1 and 3As shown in Figures 6, there are two sliders 3. The front and rear ends of the inner cavities of the two sliders 3 are respectively movably connected to both sides of the outer surfaces of the front and rear first limiting rods 2. The electric hydraulic rod 4 is located inside the slider 3. The inner end of the electric hydraulic rod 4 is fixedly connected to the support table 1. The front and rear ends of the bottom of the aerospace shell body 6 are in contact with the upper surfaces of the front and rear second limiting rods 13. Through the operation of the electric hydraulic rod 4 and the limiting effect of the first limiting rod 2, the two sliders 3 move towards each other, facilitating the subsequent fixing of the aerospace shell body 6 by the device. At the same time, the design of the two second limiting rods 13 plays a role in supporting the aerospace shell body 6 at the initial stage.

[0034] As Figure 2 , 4 As shown in Figures 7 and 8, the sleeve rod 8 and the circular ring plate 9 are respectively movably connected to the inner side and the outer side of the outer surface of the push rod 7. The inner side of the elastic spring 10 is fixedly connected to the outer side of the sleeve rod 8. The elastic spring 10 is movably sleeved on the outer surface of the push rod 7. The circular ring plate 9 is in contact with the opposite side of the push rod 7. The inner cavities at the front and rear ends of the bottom of the limiting sleeve 11 are respectively movably connected to the outer surfaces of the front and rear limiting sleeves 11. The inner cavity of the connecting sleeve 26 is fixedly connected to the inner side of the outer surface of the sleeve rod 8. The limiting sleeve 11 and the rubber anti-slip sheet 12 have the same diameter as the aerospace shell body 6. The rubber anti-slip sheet 12 is made of rubber. Through the design of the elastic spring 10, when the push rod 7 drives the aerospace shell body 6 to rotate, the circular ring plate 9 rotates synchronously with the elastic spring 10, the push rod 7 and the sleeve rod 8, thereby preventing damage. At the same time, the elastic force of the elastic spring 10 will push the sleeve rod 8, causing the limiting sleeve 11 and the rubber anti-slip sheet 12 to move towards the side close to the aerospace shell body 6, so that the rubber anti-slip sheet 12 contacts the aerospace shell body 6, achieving the effect of first fixing both sides of the aerospace shell body 6.

[0035] As Figure 2 , 4 As shown in Figures 7 and 8: The top of the round rod 16 is semi-circular and made of rubber. The round rod 16 is located inside the aerospace shell body 6 and is matched with the inner cavity of the aerospace shell body 6. The outer surface of the inner end of the connecting rod 18 is hinged to the inner cavity of the inner end of the round rod 16. By further moving the push rod 7 towards the side close to the aerospace shell body 6, the sleeve rod 8 is fixed, causing the elastic spring 10 to be further compressed. At the same time, the push rod 7 drives the bottom of the connecting rod 18 to move towards the side close to the aerospace shell body 6, so that the inner end of the connecting rod 18 pushes the round rod 16 to move outwards, causing the rubber arc block at the top of the round rod 16 to contact the inner cavity of the aerospace shell body 6, thereby realizing the secondary fixing of the aerospace shell body 6.

[0036] As Figure 3 , 4As shown in Figures 7 and 8, the inner cavity in the middle of the connecting frame 17 is cross-shaped. The outer surface of the cross-shaped block 19 is adaptively clamped with the inner cavity in the middle of the connecting frame 17. The two sides of the outer surface of the threaded rod 21 are respectively movably connected to the two sides of the bottom of the inner cavity of the support platform 1. The output shaft end of the second motor 25 is fixedly connected to the outer side of the push rod 7. Through the design of the cooperation between the cross-shaped inner cavity in the middle of the connecting frame 17 and the outer surface of the cross-shaped block 19, when the round rod 16 squeezes and fixes the inner cavity of the aerospace shell body 6, at this time, the cross-shaped block 19 is located in the inner cavity of the connecting frame 17. Thus, when the second motor 25 operates, the second motor 25 rotates, which will drive the connecting frame 17, the sleeve 15 and the support 14 to rotate, and further make the sleeve rod 8 drive the limit sleeve 11, the rubber anti-slip sheet 12 and the aerospace shell body 6 to rotate synchronously, so as to facilitate the operator to cut the aerospace shell body 6, thus facilitating the use of the operator.

[0037] The working principle and usage process of the present invention:

[0038] First, the operator places the aerospace shell body 6 above the two second limit rods 13. At this time, the electric hydraulic rods 4 are operated to reduce the lengths of the two electric hydraulic rods 4, so that the two sliders 3 drive the vertical frame 5 to move towards each other, and further the vertical frame 5 drives the push rod 7 to move towards the side close to the aerospace shell body 6. At the same time, due to the limiting effect of the two second limit rods 13 on the limit sleeve 11, when the sleeve rod 8 drives the limit sleeve 11 and the rubber anti-slip sheet 12 contacts one side of the aerospace shell body 6, the elastic spring 10 will be compressed. At this time, the device plays a role in fixing the two sides of the outer surface of the aerospace shell body 6 for the first time;

[0039] Subsequently, the operator continues to operate the electric hydraulic rod 4 to make the push rod 7 continue to move towards the side close to the aerospace shell body 6. At the same time, since the rubber anti-slip sheet 12 on the limit sleeve 11 contacts the aerospace shell body 6, when the push rod 7 continues to move towards the side close to the aerospace shell body 6, the fixed sleeve rod 8 makes the elastic spring 10 be further compressed. At the same time, the push rod 7 drives the bottom of the connecting rod 18 to move towards the side close to the aerospace shell body 6, so that the inner end of the connecting rod 18 close to the inside pushes the round rod 16 to move outwards, so that the rubber arc block at the top of the round rod 16 contacts the inner cavity of the aerospace shell body 6, thus realizing the secondary fixation of the aerospace shell body 6, so as to facilitate the operator to cut the aerospace shell body 6 subsequently;

[0040] After the position of the aerospace shell body 6 is fixed, when the operator operates the first motor 20 at this time, the threaded rod 21 will rotate, and then the matching block 22 will drive the electric telescopic rod 23 and the cutting machine 24 to move, so that the top of the cutting machine 24 is at the bottom of the place where the aerospace shell body 6 needs to be cut. At this time, operate the electric telescopic rod 23 to make the cutting machine 24 move upward, so as to realize the cutting of the bottom of the aerospace shell body 6. At the same time, the operator operates the second motor 25. At this time, the operation of the second motor 25 will make the push rod 7 rotate, and at the same time drive the sleeve rod 8, the bracket 14 and the connecting rod 18 to rotate, and then make the ring plate 9, the connecting frame 17 and the aerospace shell body 6 rotate, so as to realize the annular cutting operation of the aerospace shell body 6.

[0041] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusively, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.

[0042] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An annular cutting machine for processing the shell of a space equipment, comprising a support table (1) and a space shell body (6), characterized in that: At the front and rear ends of the bottom of the inner cavity of the support table (1), a first limiting rod (2) is fixedly connected. On both sides of the outer surface of the first limiting rod (2), sliding blocks (3) are sleeved. At the front and rear ends of the inner side of the sliding block (3), an electric hydraulic rod (4) is fixedly connected. At the top of the sliding block (3), a vertical frame (5) is fixedly connected. At the top of the inner cavity of the vertical frame (5), a push rod (7) is movably connected. On the outer surface of the push rod (7), a sleeve rod (8) and a circular ring plate (9) are sleeved. On the inner side of the circular ring plate (9), an elastic spring (10) is fixedly connected. At the front and rear ends of the top of the inner cavity of the support table (1), a second limiting rod (13) is movably connected. On the outer surface of the second limiting rod (13), a limiting sleeve (11) is movably connected. Inside the limiting sleeve (11), a connecting sleeve (26) is connected by a bearing. On the inner side of the limiting sleeve (11), a rubber anti-slip sheet (12) is fixedly connected; The sleeve rod (8) and the circular ring plate (9) are respectively movably connected to the inner side and the outer side of the outer surface of the push rod (7). The inner side of the elastic spring (10) is fixedly connected to the outer side of the sleeve rod (8). The elastic spring (10) is movably sleeved on the outer surface of the push rod (7). The side of the circular ring plate (9) opposite to the push rod (7) is in contact; The inner cavities at the front and rear ends of the bottom of the limiting sleeve (11) are respectively movably connected to the outer surfaces of the front and rear two limiting sleeves (11). The inner cavity of the connecting sleeve (26) is fixedly connected to the inner side of the outer surface of the sleeve rod (8); The number of the sliding blocks (3) is two. The front and rear ends of the inner cavities of the two sliding blocks (3) are respectively movably connected to both sides of the outer surfaces of the front and rear two first limiting rods (2). The electric hydraulic rod (4) is located inside the sliding block (3). The inner end of the electric hydraulic rod (4) is fixedly connected to the support table (1). The front and rear ends of the bottom of the aerospace shell body (6) are in contact with the upper surfaces of the front and rear two second limiting rods (13).

2. The annular cutting machine for processing the outer shell of a space equipment according to claim 1, characterized in that: On the outer surface of the sleeve rod (8) near the circular ring plate (9), brackets (14) are fixedly connected at equal angles in a ring shape. On the side of the bracket (14) away from the circular ring plate (9), a sleeve (15) is fixedly connected. Inside the sleeve (15), a round rod (16) is movably connected. On the outer surface of the sleeve (15) away from the circular ring plate (9), a connecting frame (17) is fixedly connected. On the outer surface of the push rod (7), connecting rods (18) are hinged at equal angles in a ring shape; The outer surface of the inner end of the connecting rod (18) is hinged to the inner cavity of the inner end of the round rod (16).

3. The annular cutting machine for processing the outer shell of a space equipment according to claim 2, wherein: On the inner side of the push rod (7), a cross-shaped block (19) is fixedly connected. On one side of the bottom of the outer surface of the support platform (1), a first motor (20) is fixedly connected. The output shaft end of the first motor (20) is fixedly connected with a threaded rod (21). The middle part of the outer surface of the threaded rod (21) is threadedly connected with a mating block (22). At the front and rear ends of the inner cavity of the mating block (22), an electric telescopic rod (23) is fixedly connected. The top of the electric telescopic rod (23) is fixedly connected with a cutting machine (24). At the top of the outer side of the vertical frame (5), a second motor (25) is fixedly connected.

4. The annular cutting machine for processing the outer shell of a space equipment according to claim 1, characterized in that: The limiting sleeve (11) and the rubber anti-slip sheet (12) are equal in diameter to the aerospace shell body (6). The rubber anti-slip sheet (12) is made of rubber.

5. The annular cutting machine for processing the outer shell of a space equipment according to claim 2, wherein: The top of the round rod (16) is semi-circular and made of rubber. The round rod (16) is located in the inner cavity of the aerospace shell body (6) and is matched with the inner cavity of the aerospace shell body (6).

6. The annular cutting machine for processing the outer shell of a space equipment according to claim 3, wherein: The inner cavity in the middle of the connecting frame (17) is cross-shaped. The outer surface of the cross-shaped block (19) is adaptively clamped with the inner cavity in the middle of the connecting frame (17). The two sides of the outer surface of the threaded rod (21) are respectively movably connected with the two sides of the bottom of the inner cavity of the support platform (1).

7. The annular cutting machine for processing the outer shell of a space equipment according to claim 3, wherein: The output shaft end of the second motor (25) is fixedly connected with the outer side of the push rod (7).

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