An installation and connection structure of an aero-engine

Abstract

The present invention discloses an installation and connection structure for an aeroengine. The present invention relates to the field of aviation safety and includes a bottom beam. A top beam is fixedly connected to the top of the bottom beam. A number of connecting beams are fixedly connected at equal intervals between the bottom beam and the top beam. A front fulcrum installation groove is penetratingly opened at the front part of the top of the bottom beam. A rear fulcrum connection block is fixedly connected to the rear part of the bottom of the bottom beam. A redundant structure is provided on the top of the top beam. The redundant structure includes two redundant rods one and two redundant rods two. A first fixing block is fixedly connected to the front part of the top of the top beam. A suspension rod one is rotatably connected to the top of the first fixing block. A second fixing block is fixedly connected to the rear part of the top of the top beam. Suspension rods two are rotatably connected to both sides of the second fixing block. By setting the redundant structure in the present invention, when the top beam or the bottom beam breaks accidentally, the fixing plate can still be connected to the unbroken part, ensuring the connection stability and greatly improving the flight safety.

Description

Technical Field

[0001] The present invention relates to the field of aviation safety, and particularly relates to an installation and connection structure of an aero-engine. Background Art

[0002] The aero-engine pylon is an important component in the aircraft structure, which is used to securely fix the engine under the wing or fuselage and provide necessary support and connection. It not only bears the gravity and thrust of the engine, but also needs to ensure the thermal expansion and vibration isolation between the engine and the fuselage during flight;

[0003] However, the aero-engine pylon is connected to the passenger aircraft wing in a fixed connection manner. Therefore, when the engine operates and generates vibrations, the fixed pylon can only conduct the impact force rigidly and cannot disperse the stress, which is extremely likely to cause stress concentration at the connection part. Over time, it will cause serious structural damage to the passenger aircraft wing and the pylon itself, greatly shortening its service life and increasing the maintenance cost and safety risk. Therefore, the present invention proposes an installation and connection structure of an aero-engine. Summary of the Invention

[0004] The main purpose of the present invention is to provide an installation and connection structure of an aero-engine, which can effectively solve the technical problems in the background art.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] An installation and connection structure of an aero-engine, including a bottom beam, a top beam is fixedly connected to the top of the bottom beam, and a plurality of connecting beams are fixedly connected at equal intervals between the bottom beam and the top beam. A front fulcrum installation groove is penetrated and opened at the front part of the top of the bottom beam, and a rear fulcrum connection block is fixedly connected to the rear part of the bottom of the bottom beam. A redundant structure is arranged on the top of the top beam;

[0007] The redundant structure includes two redundant rods one and two redundant rods two. A first fixing block is fixedly connected to the front part of the top of the top beam, and a hanging rod one is rotatably connected to the top of the first fixing block. A second fixing block is fixedly connected to the rear part of the top of the top beam, and hanging rods two are rotatably connected to both sides of the second fixing block. The two redundant rods one are respectively rotatably connected to both sides of the bottom beam and at the front part, and the two redundant rods two are respectively rotatably connected to both sides of the bottom beam and at the rear part. The top of the hanging rod one and the far sides of the tops of the two redundant rods two are rotatably connected to a third fixing block, and a floating structure is arranged on the top of the third fixing block.

[0008] As a further solution of the present invention, a fourth fixing block is fixedly connected to the rear part of the last connecting beam, a hanging rod three is rotatably connected to the rear part of the fourth fixing block, and the top of the hanging rod three is also rotatably connected to a third fixing block.

[0009] As a further solution of the present invention, the adjacent sides of the two redundant rods 1 are rotatably connected to the two sides of the suspension rod 1 respectively, and the distant sides of the two suspension rods 2 are rotatably connected to the adjacent sides of the two redundant rods 2 respectively.

[0010] As a further solution of the present invention, the floating structure includes two connecting rods 1 and two connecting rods 2, the connecting rod 1 on one side is rotatably connected to the top of the third fixed block on the front, the connecting rod 2 on the other side is rotatably connected to the top of the third fixed block on the other side, the connecting rod 2 on the other side is rotatably connected to the top of the third fixed block on the rear, the connecting rod 2 on one side is rotatably connected to the top of the third fixed block on one side, a connecting groove 1 is provided at one end of the connecting rod 1 on one side, and a connecting block 1 is fixedly connected to one end of the connecting rod 1 on the other side, the connecting block 1 is located inside the connecting groove 1, and the connecting block 1 is located inside the connecting groove 1. The other end of the connecting rod one on one side, one end of the connecting rod two on one side and the other end of the connecting rod two on the other side are all fixedly connected with a connecting block two, the other end of the connecting rod one on the other side, the other end of the connecting rod two on one side and one end of the connecting rod two on the other side are all provided with a connecting groove two, the three connecting blocks two are respectively located inside the three connecting grooves two, a rotating shaft is rotatably connected between the connecting block one and the connecting groove one and between the three pairs of connecting blocks two and the connecting groove two, the outer surface of the rotating shaft is fixedly connected with a limiting block one at the top and the bottom, and the outer surface of the rotating shaft is located between the two limiting blocks one and is fixedly connected with a limiting block two.

[0011] As a further solution of the present invention, the tops of the four rotating shafts are fixedly connected to a fixing plate, and studs are threaded through the four corners of the fixing plate. The outer surfaces of the studs are respectively provided with two thread grooves with opposite thread directions near the top and the bottom. The outer surfaces of the studs are respectively threadedly connected to two nuts through the two thread grooves, and the nut near the top is squeezed against the bottom of the fixing plate, and the two nuts are also squeezed against each other.

[0012] As a further solution of the present invention, a spring is fixedly connected between the two connecting rods 1 and between the two connecting rods 2 and the two connecting rods 1.

[0013] As a further solution of the present invention, the connecting rod 1 is composed of a straight rod 1, a straight rod 2 and two rotating joints, and the two rotating joints are respectively connected to the adjacent ends of the straight rod 1 and the straight rod 2. The interior of the rotating joint connected to the straight rod 1 is provided with rotating grooves running through both sides, and the interior of the rotating joint connected to the straight rod 2 is also provided with rotating grooves running through the top and bottom. A connecting block is arranged between the two rotating joints, and the outer surface of the connecting block is fixedly connected to rotating rods at the top, bottom and both sides.

[0014] As a further solution of the present invention, the connecting block is connected to the two rotating grooves through four rotating rods, the top and bottom of the rotating joint connected to the straight rod one are in an open state, and the two sides of the rotating joint connected to the straight rod two are in an open state.

[0015] As a further solution of the present invention, the interiors of the suspension rod 1, suspension rod 2, suspension rod 3, redundant rod 1 and redundant rod 2 are all provided with placement grooves, and an anti-breaking chain is fixedly connected between the top and bottom of the placement groove, and the anti-breaking chain is in a relaxed state.

[0016] The beneficial effects of the present invention are as follows:

[0017] By setting up a redundant structure, the redundant rods 1 and 2 are arranged symmetrically, which not only enhances the ability of the entire installation connection structure to cope with vibrations in different directions, but also provides additional safety protection. Even if a redundant rod fails unexpectedly, the remaining redundant components can still maintain the basic buffering and shock absorption functions to ensure the reliability of the connection between the aircraft engine and the wing of the passenger aircraft. Each fixing plate is connected to the top beam and the bottom beam at the same time to achieve redundancy and fault tolerance. When the top beam or the bottom beam breaks accidentally, the fixing plate can still be connected to the unbroken part to ensure the connection stability, greatly improving flight safety.

[0018] When the aircraft engine generates vibration during operation, the first boom, the second boom, the third boom, the two redundant booms 1 and the two redundant booms 2 will rotate slightly to achieve the effect of buffering and shock absorption. The coordinated rotation of these components can change the force transmission path and disperse the impact force generated by the vibration of the aircraft engine to multiple directions, avoiding excessive stress concentration at a certain connection point, effectively reducing the risk of structural damage to the bottom beam, top beam and connecting beam caused by vibration impact, and greatly improving flight safety.

[0019] The suspension rod, redundant rod and other connecting components are set to a rotating connection mode. When the top beam and the bottom beam are broken, each connecting component can be rotated to form a suspension connection between the engine and the connecting component to prevent the engine from falling, buy more response time for the aircraft in extreme situations, and effectively reduce the probability of catastrophic consequences;

[0020] By setting up a floating structure consisting of two connecting rods 1 and 2, four rotating shafts, limit blocks 1 and 2, when the aircraft engine shakes, the two connecting rods shake slightly relative to each other along the four rotating shafts, which can "fine-tune" the shaking impact force from different directions in real time, finely adjust the force distribution, and further optimize the buffering and shock absorption effect; the limit blocks effectively prevent the connecting rods from separating from the rotating shafts, ensure the structural integrity, and maintain good buffering performance;

[0021] Two thread grooves with opposite thread directions are set on the studs at the four corners of the top fixing plates of the four shafts, and two nuts are matched. The top nut is pressed against the bottom of the fixing plate and the two nuts are pressed against each other, realizing a double tightening function, effectively coping with the problem of loose connection caused by engine vibration, airflow impact, etc., ensuring long-term reliability of the connection and reducing maintenance frequency;

[0022] Springs are arranged between two first connecting rods, between two second connecting rods and the two first connecting rods. When the aero-engine vibrates or sways, the springs rotate and deform with the connecting rods, converting the kinetic energy of vibration or sway into elastic potential energy for storage and slow release, reducing the impact force transmitted to the passenger aircraft wing and other connecting components, and cooperating with redundant rods, suspension rods, etc. to create a smoother flight environment for the aircraft; it can also adjust its own state in real time according to forces of different directions and magnitudes, evenly disperse the forces, avoid local stress concentration, and extend the service life of the entire installation and connection structure;

[0023] The first connecting rod is designed as a rotatable structure composed of a first straight rod, a second straight rod and two rotating joints. When the connection between the front fixing plate and the passenger aircraft wing is abnormal and the engine sags and pulls the first connecting rod, the two rotating joints sag and rotate accordingly, driving the first straight rod and the second straight rod to rotate, removing the downward acting force of the engine, preventing the first connecting rod from breaking, maintaining a certain connection stability, and creating conditions for subsequent emergency handling;

[0024] Placement grooves and anti-break chains are arranged inside the first suspension rod, the second suspension rod, the third suspension rod, the first redundant rod and the second redundant rod, and the anti-break chains are in a slack state. When these components break accidentally, the anti-break chains will tighten, so that the fixing plate and the top beam or the bottom beam can still be connected through the anti-break chains, maintaining a temporary key connection state. In extreme emergencies, it can quickly intervene to bear part of the tension, prevent the engine from detaching instantly, and avoid catastrophic impact on the passenger aircraft fuselage, comprehensively ensuring flight safety. Description of the Drawings

[0025] Figure 1 It is a schematic diagram of the overall structure of an installation and connection structure of an aero-engine according to the present invention;

[0026] Figure 2 It is a display diagram of the redundant structure of an installation and connection structure of an aero-engine according to the present invention;

[0027] Figure 3 It is a rear view diagram of the redundant structure of an installation and connection structure of an aero-engine according to the present invention;

[0028] Figure 4 It is a display diagram of the floating structure of an installation and connection structure of an aero-engine according to the present invention;

[0029] Figure 5 It is a split diagram of the floating structure of an installation and connection structure of an aero-engine according to the present invention;

[0030] Figure 6 It is an analytical split diagram of the first connection groove and the first connection block of an installation and connection structure of an aero-engine according to the present invention;

[0031] Figure 7 It is a split diagram of the two rotating joints and the connecting block of an installation and connection structure of an aero-engine according to the present invention;

[0032] Figure 8 This is a diagram showing the stud and two nut structures of the installation and connection structure of an aero-engine according to the present invention;

[0033] Figure 9 This is an exploded view of the first suspension rod of the installation and connection structure of an aero-engine according to the present invention.

[0034] In the figure: 1, bottom beam; 2, top beam; 3, connecting beam; 4, front fulcrum installation groove; 5, rear fulcrum connection block; 6, redundant structure; 7, floating structure; 8, first fixing block; 9, first suspension rod; 10, second fixing block; 11, second suspension rod; 12, first redundant rod; 13, second redundant rod; 14, third suspension rod; 15, third fixing block; 16, first connecting rod; 17, second connecting rod; 18, fixing plate; 19, first straight rod; 20, second straight rod; 21, spring; 22, stud; 23, first connecting groove; 24, first connecting block; 25, second connecting groove; 26, second connecting block; 27, fourth fixing block; 28, first limiting block; 29, second limiting block; 30, rotating shaft; 31, rotating joint; 32, connecting block; 33, rotating groove; 34, rotating rod; 35, nut; 36, placing groove; 37, anti-breaking chain. Detailed implementation manners

[0035] In order to make the technical means, creative features, achieved purposes and functions of the present invention easy to understand, the present invention will be further described below in conjunction with specific implementation manners.

[0036] As Figure 1 - Figure 9 shown, an installation and connection structure of an aero-engine includes a bottom beam 1, a top beam 2 is fixedly connected to the top of the bottom beam 1, a plurality of connecting beams 3 are fixedly connected at equal intervals between the bottom beam 1 and the top beam 2, a front fulcrum installation groove 4 is penetrated and opened at the front part of the top of the bottom beam 1, a rear fulcrum connection block 5 is fixedly connected to the rear part of the bottom of the bottom beam 1, and a redundant structure 6 is arranged on the top of the top beam 2;

[0037] The redundant structure 6 includes two first redundant rods 12 and two second redundant rods 13. A first fixing block 8 is fixedly connected to the front part of the top of the top beam 2. A first suspension rod 9 is rotatably connected to the top of the first fixing block 8. A second fixing block 10 is fixedly connected to the rear part of the top of the top beam 2. Two second suspension rods 11 are rotatably connected to both sides of the second fixing block 10. The two first redundant rods 12 are respectively rotatably connected to both sides of the bottom beam 1 and at the front part, and the two second redundant rods 13 are respectively rotatably connected to both sides of the bottom beam 1 and at the rear part. The top of the first suspension rod 9 and the far sides of the tops of the two second redundant rods 13 are both rotatably connected to a third fixing block 15, and a floating structure 7 is arranged on the top of the third fixing block 15.

[0038] During the actual operation process, the front fulcrum installation groove 4 and the rear fulcrum connection block 5 are connected to the front installation joint and the rear installation joint of the aeroengine through an external connection component, so that the bottom beam 1 is connected to the aeroengine. Then, the four fixing plates 18 are connected to the passenger aircraft wing through a plurality of studs 22. At this time, the aeroengine is connected to the passenger aircraft wing.

[0039] Specifically, when the aeroengine operates and generates vibrations, the first suspension rod 9, the two second suspension rods 11, the third suspension rod 14, the two redundant rods 12 and the two redundant rods 13 will rotate slightly. Through rotation, the effect of buffering and shock absorption is achieved. The coordinated rotation of these components can change the force transmission path, disperse the impact force generated by the aeroengine vibration in multiple directions, avoid excessive stress concentration at a certain connection part, and effectively reduce the risk of structural damage to the bottom beam 1, the top beam 2 and the connection beam 3 caused by vibration shock.

[0040] In addition, the symmetrical arrangement of the redundant rod 12 and the redundant rod 13 not only enhances the ability of the entire installation and connection structure to cope with vibrations in different directions, but also provides additional safety guarantees. Even if one of the redundant rods 12 or the redundant rod 13 has an accidental failure, the remaining redundant components can still maintain the basic buffering and shock absorption function, ensuring the reliability of the connection between the aeroengine and the passenger aircraft wing. And since each fixing plate 18 is connected to both the top beam 2 and the bottom beam 1 at the same time, the purpose of redundancy and fault tolerance is achieved. Even if the top beam 2 or the bottom beam 1 breaks accidentally, the fixing plate 18 can still be connected to the unbroken top beam 2 or bottom beam 1 to ensure the connection stability between the aeroengine and the passenger aircraft wing.

[0041] Since the first suspension rod 9, the second suspension rod 11 and the other connection components are all in a rotational connection manner, when both the top beam 2 and the bottom beam 1 are broken, each connection component can rotate, so that the connection between each connection component and the aeroengine is a suspended connection manner, preventing the aeroengine from falling.

[0042] In this embodiment, a fourth fixing block 27 is fixedly connected to the rear part of the connection beam 3 closest to the rear. The rear part of the fourth fixing block 27 is rotatably connected to a third suspension rod 14, and the top of the third suspension rod 14 is also rotatably connected to a third fixing block 15.

[0043] In this embodiment, the closer sides of the two redundant rods 12 near the top are respectively rotatably connected to both sides of the first suspension rod 9, and the farther sides of the two second suspension rods 11 near the top are respectively rotatably connected to the closer sides of the two redundant rods 13.

[0044] In this embodiment, the floating structure 7 includes two first connecting rods 16 and two second connecting rods 17. One of the first connecting rods 16 on one side is rotatably connected to the top of the front third fixing block 15, and one of the second connecting rods 17 on the other side is rotatably connected to the top of the third fixing block 15 on the other side and at the rear. One of the second connecting rods 17 on one side is rotatably connected to the top of the third fixing block 15 on one side. An inner connection groove one 23 is formed at one end of the first connecting rod 16 on one side. One end of the first connecting rod 16 on the other side is fixedly connected with a connection block one 24, and the connection block one 24 is located inside the connection groove one 23. The other ends of the first connecting rod 16 on one side, one end of the second connecting rod 17 on one side, and the other ends of the second connecting rods 17 on the other side are all fixedly connected with connection blocks two 26. The other ends of the first connecting rod 16 on the other side, the other ends of the second connecting rods 17 on one side, and one end of the second connecting rods 17 on the other side are all provided with connection grooves two 25. The three connection blocks two 26 are respectively located inside the three connection grooves two 25. A rotating shaft 30 is rotatably connected between the connection block one 24 and the connection groove one 23 and between the three pairs of connection blocks two 26 and the connection grooves two 25. Limiting blocks one 28 are fixedly connected to the top and bottom of the outer surface of the rotating shaft 30, and a limiting block two 29 is fixedly connected to the outer surface of the rotating shaft 30 and between the two limiting blocks one 28.

[0045] Specifically, when the aeroengine shakes, the two first connecting rods 16 and the two second connecting rods 17 respectively shake slightly along the four rotating shafts 30, so as to further optimize the buffering and shock absorption and finely adjust the force distribution. This small-amplitude shaking between each other can perform real-time "fine-tuning" on the shaking impact forces from different directions. The limiting blocks one 28 and the limiting blocks two 29 can effectively prevent the first connecting rod 16 and the second connecting rod 17 from separating from the rotating shaft 30 during the shaking process, ensuring the integrity of the structure.

[0046] In this embodiment, fixing plates 18 are fixedly connected to the tops of the four rotating shafts 30. Studs 22 are threadedly penetrated through the four corners of the fixing plates 18. Thread grooves with opposite thread directions are respectively formed at the top and bottom of the outer surface of the studs 22. Two nuts 35 are respectively threadedly connected to the outer surface of the studs 22 through the two thread grooves. The nut 35 at the top abuts against the bottom of the fixing plate 18, and the two nuts 35 also abut against each other.

[0047] Specifically, the two thread grooves with opposite thread directions formed on the outer surface of the stud 22 and the two nuts 35 cooperating therewith achieve a double fastening function. During the operation of the aircraft, due to factors such as engine vibration and air flow impact, the connection part is extremely prone to loosening. However, this design can effectively cope with it. The nut 35 at the top presses against the bottom of the fixed plate 18, and the two nuts 35 press against each other, forming a tight locking structure, greatly reducing the risk of the stud 22 loosening due to vibration and ensuring the long-term reliability of the connection.

[0048] In this embodiment, springs 21 are fixedly connected between the two first connecting rods 16 and between the two second connecting rods 17 and the two first connecting rods 16.

[0049] Specifically, when the aeroengine vibrates or shakes, the spring 21 will stretch and deform along with the small-angle rotation of the first connecting rod 16 and the second connecting rod 17, converting the kinetic energy generated by the vibration or shake into elastic potential energy and storing it, and then slowly releasing it, thereby effectively reducing the impact force transmitted to the passenger aircraft wing and other connecting components. Cooperating with the redundant rod one 12, the redundant rod two 13, the suspension rod one 9, the suspension rod two 11, and the suspension rod three 14, it provides a smoother flight environment for the aircraft. Moreover, the springs 21 between the two first connecting rods 16 and between the two second connecting rods 17 and the two first connecting rods 16 can adjust their own states in real time according to forces in different directions and magnitudes, evenly dispersing the forces among the connecting rods and the components connected thereto, avoiding local stress concentration, reducing the risk of component damage due to overload, and extending the service life of the entire installation and connection structure.

[0050] In this embodiment, the first connecting rod 16 is composed of a first straight rod 19, a second straight rod 20, and two rotating joints 31. The two rotating joints 31 are respectively connected to the closer ends of the first straight rod 19 and the second straight rod 20. Rotating grooves 33 are formed through both sides inside the rotating joint 31 connected to the first straight rod 19, and rotating grooves 33 are also formed through the top and bottom inside the rotating joint 31 connected to the second straight rod 20. An adapter block 32 is arranged between the two rotating joints 31, and rotating rods 34 are fixedly connected to the outer surface of the adapter block 32 at the top, bottom, and both sides.

[0051] Specifically, since the first connecting rod 16 is composed of the first straight rod 19, the second straight rod 20 and two rotating joints 31, the first connecting rod 16 itself is in a rotatable state. Therefore, when the front fixing plate 18 is suddenly separated from the airliner wing or only the front fixing plate 18 is connected to the airliner wing, due to gravity, the aeroengine will fall downward, pulling the two first connecting rods 16 downward. At this time, the two rotating joints 31 will rotate relative to each other as the aeroengine falls, causing the first straight rod 19 and the second straight rod 20 to rotate. Furthermore, the first connecting rod 16 unloads the force acting on it due to the sudden downward fall of the aeroengine by rotating itself, so that the first connecting rod 16 will not break and can still maintain a certain connection stability, buying precious time for subsequent emergency handling.

[0052] In this embodiment, the connecting block 32 is connected to the two rotating slots 33 through four rotating rods 34. The top and bottom of the rotating joint 31 connected to the first straight rod 19 are in an open state, and the two sides of the rotating joint 31 connected to the second straight rod 20 are in an open state.

[0053] In this embodiment, placing grooves 36 are formed inside the first suspension rod 9, the second suspension rod 11, the third suspension rod 14, the first redundant rod 12 and the second redundant rod 13. A break prevention chain 37 is fixedly connected between the top and bottom of the placing groove 36, and the break prevention chain 37 is in a slack state.

[0054] Specifically, when the first suspension rod 9, the second suspension rod 11, the third suspension rod 14, the first redundant rod 12 and the second redundant rod 13 are accidentally broken, the break prevention chains 37 inside them will be tightened, so that the fixing plate 18 and the top beam 2 or the bottom beam 1 can still be connected through the break prevention chains 37, thus maintaining a temporary and critical connection state and buying a chance for the plane to land safely. In extremely sudden situations, even if main load-bearing components such as the first suspension rod 9 and the first redundant rod 12 break and fail, the break prevention chains 37 can quickly intervene, bear part of the tension, prevent the engine from detaching instantly due to the complete loss of connection, and avoid catastrophic impact damage to the airliner fuselage.

[0055] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements fall within the scope of the present invention claimed.

Claims

1. An installation and connection structure of an aero-engine, comprising a bottom beam (1), wherein a top beam (2) is fixedly connected to the top of the bottom beam (1), and a plurality of connecting beams (3) are fixedly connected at equal intervals between the bottom beam (1) and the top beam (2), and the characteristics are as follows: The front part of the top of the bottom beam (1) is penetrated and provided with a front fulcrum installation groove (4), the rear part of the bottom of the bottom beam (1) is fixedly connected with a rear fulcrum connection block (5), and a redundant structure (6) is arranged on the top of the top beam (2); The redundant structure (6) includes two redundant rods one (12) and two redundant rods two (13). The front part of the top of the top beam (2) is fixedly connected with a first fixing block (8), the top of the first fixing block (8) is rotatably connected with a hanging rod one (9), the rear part of the top of the top beam (2) is fixedly connected with a second fixing block (10), and both sides of the second fixing block (10) are rotatably connected with hanging rods two (11). The two redundant rods one (12) are respectively rotatably connected to both sides of the bottom beam (1) and close to the front part, the two redundant rods two (13) are respectively rotatably connected to both sides of the bottom beam (1) and close to the rear part, the top of the hanging rod one (9) and the top of the two redundant rods two (13) on the far side are rotatably connected with a third fixing block (15), and a floating structure (7) is arranged on the top of the third fixing block (15).

2. The installation and connection structure of an aeroengine according to claim 1, characterized in that: The rear part of the connection beam (3) closest to the rear is fixedly connected with a fourth fixing block (27), the rear part of the fourth fixing block (27) is rotatably connected with a hanging rod three (14), and the top of the hanging rod three (14) is also rotatably connected with a third fixing block (15).

3. The installation and connection structure of an aero-engine according to claim 1, characterized in that: The closer sides of the two redundant rods one (12) near the top are respectively rotatably connected with both sides of the hanging rod one (9), and the farther sides of the two hanging rods two (11) near the top are respectively rotatably connected with the closer sides of the two redundant rods two (13).

4. The installation and connection structure of an aeroengine according to claim 1, characterized in that: The floating structure (7) comprises two connecting rods 1 (16) and two connecting rods 2 (17), wherein the connecting rod 1 (16) on one side is rotatably connected to the top of the third fixed block (15) on the front, the connecting rod 2 (17) on the other side is rotatably connected to the top of the third fixed block (15) on the other side, the connecting rod 2 (17) on the other side is rotatably connected to the top of the third fixed block (15) on the rear, the connecting rod 2 (17) on one side is rotatably connected to the top of the third fixed block (15) on one side, a connecting groove 1 (23) is provided inside one end of the connecting rod 1 (16) on the one side, one end of the connecting rod 1 (16) on the other side is fixedly connected to a connecting block 1 (24), the connecting block 1 (24) is located inside the connecting groove 1 (23), and the other end of the connecting rod 1 (16) on the one side is fixedly connected to the connecting block 1 (24), the connecting block 1 (24) is located inside the connecting groove 1 (23), and the other end of the connecting rod 1 (16) on the one side is fixedly connected to the connecting block 1 (24), and the connecting block 1 (24) is located inside the connecting groove 1 (23). The first end of the connecting rod (17) and the second end of the connecting rod (17) are fixedly connected with a connecting block (26); the other end of the connecting rod (16) on the other side, the other end of the connecting rod (17) on one side and the one end of the connecting rod (17) on the other side are all provided with a connecting groove (25); the three connecting blocks (26) are respectively located inside the three connecting grooves (25); a rotating shaft (30) is rotatably connected between the connecting block (24) and the connecting groove (23) and between the three pairs of connecting blocks (26) and the connecting grooves (25); the outer surface of the rotating shaft (30) is fixedly connected with a limiting block (28) near the top and the bottom; the outer surface of the rotating shaft (30) is fixedly connected with a limiting block (29) and is located between the two limiting blocks (28).

5. The installation and connection structure of an aero-engine according to claim 4, characterized in that: The tops of the four rotating shafts (30) are fixedly connected to a fixing plate (18), and studs (22) are threadedly penetrated at the four corners of the fixing plate (18). The outer surfaces of the studs (22) are respectively provided with two thread grooves with opposite thread directions near the top and the bottom. The outer surfaces of the studs (22) are respectively threadedly connected to two nuts (35) through the two thread grooves, and the nuts (35) near the top are pressed against the bottom of the fixing plate (18), and the two nuts (35) are also pressed against each other.

6. The installation and connection structure of an aero-engine according to claim 4, characterized in that: A spring (21) is fixedly connected between the two connecting rods 1 (16) and between the two connecting rods 2 (17) and the two connecting rods 1 (16).

7. The installation and connection structure of an aero-engine according to claim 4, characterized in that: The connecting rod 1 (16) is composed of a straight rod 1 (19), a straight rod 2 (20) and two rotating joints (31). The two rotating joints (31) are respectively connected to the adjacent ends of the straight rod 1 (19) and the straight rod 2 (20). The rotating joint (31) connected to the straight rod 1 (19) has a rotating groove (33) extending through both sides thereof. The rotating joint (31) connected to the straight rod 2 (20) also has a rotating groove (33) extending through the top and bottom thereof. A connecting block (32) is provided between the two rotating joints (31). The outer surface of the connecting block (32) is fixedly connected to rotating rods (34) at the top, bottom and both sides thereof.

8. The installation and connection structure of an aeroengine according to claim 7, characterized in that: The connecting block (32) is connected to two rotating slots (33) through four rotating rods (34). The top and bottom of the rotating joint (31) connected to the first straight rod (19) are in an open state, and both sides of the rotating joint (31) connected to the second straight rod (20) are in an open state.

9. The installation and connection structure of an aeroengine according to claim 1, characterized in that: Placement slots (36) are provided inside the first hanging rod (9), the second hanging rod (11), the third hanging rod (14), the first redundant rod (12) and the second redundant rod (13). An anti-breaking chain (37) is fixedly connected between the top and the bottom of the placement slot (36), and the anti-breaking chain (37) is in a slack state.

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