Mounting and connecting structure of aero-engine

Abstract

The invention discloses an aero-engine mounting and connecting structure, and relates to the field of aviation safety, the aero-engine mounting and connecting structure comprises a bottom beam, the top of the bottom beam is fixedly connected with a top beam, a plurality of connecting beams are fixedly connected between the bottom beam and the top beam at equal intervals, and a front fulcrum mounting groove is formed in the position, close to the front portion, of the top of the bottom beam in a penetrating mode; the rear portion of the bottom of the bottom beam is fixedly connected with a rear fulcrum connecting block, the top of the top beam is provided with a redundant structure, the redundant structure comprises two first redundant rods and two second redundant rods, the front portion of the top of the top beam is fixedly connected with a first fixing block, and the top of the first fixing block is rotationally connected with a first hanging rod. The rear portion of the top of the top beam is fixedly connected with a second fixing block, and the two sides of the second fixing block are rotationally connected with second hanging rods. By arranging the redundant structure, when the top beam or the bottom beam is broken accidentally, the fixing plate can still be connected with the unbroken part, the connection stability is ensured, and the flight safety is greatly improved.

Description

Technical Field

[0001] The invention relates to the field of aviation safety, and in particular to a mounting and connecting structure of an aviation engine. Background Art

[0002] The aircraft engine hanger is an important component in the aircraft structure. It 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 ensures the thermal expansion and vibration isolation between the engine and the fuselage during flight.

[0003] However, the aircraft engine hanger connects the engine to the wing of the passenger aircraft by a fixed connection. Therefore, when the engine is running and vibrates, the fixed hanger can only rigidly transmit the impact force and cannot disperse the stress, which easily causes the stress concentration at the connection part. In the long run, it will cause serious structural damage to the wing of the passenger aircraft and the hanger structure itself, greatly shorten its service life, and increase maintenance costs and safety risks. Therefore, the present invention proposes an installation and connection structure for an aircraft engine. Summary of the invention

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

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

[0006] An aircraft engine mounting and connecting structure comprises a bottom beam, the top of the bottom beam is fixedly connected to a top beam, a plurality of connecting beams are fixedly connected between the bottom beam and the top beam at equal intervals, a front support point mounting groove is provided through the front portion of the top of the bottom beam, a rear support point connecting block is fixedly connected to the rear portion of the bottom of the bottom beam, and a redundant structure is provided on the top of the top beam;

[0007] The redundant structure includes two redundant rods 1 and two redundant rods 2, the top of the top beam is fixedly connected to a first fixed block near the front, the top of the first fixed block is rotatably connected to a suspension rod 1, the top of the top beam is fixedly connected to a second fixed block near the rear, both sides of the second fixed block are rotatably connected to suspension rods 2, the two redundant rods 1 are respectively rotatably connected to both sides of the bottom beam and near the front, the two redundant rods 2 are respectively rotatably connected to both sides of the bottom beam and near the rear, the top of the suspension rod 1 and the sides away from the tops of the two redundant rods 2 are rotatably connected to a third fixed block, and a floating structure is provided on the top of the third fixed block.

[0008] As a further solution of the present invention, a fourth fixed block is fixedly connected to the rear of the rearmost connecting beam, the rear of the fourth fixed block is rotatably connected to the suspension rod three, and the top of the suspension rod three is also rotatably connected to the third fixed 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 the two connecting rods 1 and between the two connecting rods 2 and the two connecting rods 1. When the aircraft engine vibrates or shakes, the springs expand and contract as the connecting rods rotate, converting the vibration or shaking kinetic energy into elastic potential energy and storing and slowly releasing it, thereby reducing the impact force transmitted to the wings and other connecting parts of the passenger aircraft, and working in conjunction with redundant rods, suspension rods, etc. to create a more stable flight environment for the aircraft; they can also adjust their own state in real time according to forces of different directions and sizes, evenly disperse the force, avoid local stress concentration, and extend the service life of the entire installation connection structure;

[0023] The connecting rod 1 is designed to be a rotatable structure consisting of a straight rod 1, a straight rod 2 and two rotating joints. When the connection between the front fixed plate and the wing of the passenger plane is abnormal and the engine falls and pulls the connecting rod 1, the two rotating joints fall and rotate accordingly, driving the straight rod 1 and the straight rod 2 to rotate, thereby removing the force of the engine falling, avoiding the breakage of the connecting rod 1, maintaining a certain connection stability, and creating conditions for subsequent emergency treatment;

[0024] Placement grooves and anti-breaking chains are set inside the boom 1, boom 2, boom 3, redundant boom 1 and redundant boom 2, and the anti-breaking chains are in a relaxed state. When these components break accidentally, the anti-breaking chains will be tightened so that the fixed plate and the top beam or the bottom beam can still be connected through the anti-breaking chains to maintain a temporary critical connection state. In extreme emergency situations, they can quickly intervene to bear part of the pulling force to prevent the engine from instantly detaching and avoid catastrophic impact on the fuselage of the passenger aircraft, thereby ensuring flight safety in all aspects. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0026] Figure 2 A redundant structure display diagram of a mounting connection structure of an aircraft engine according to the present invention;

[0027] Figure 3 This is a rear perspective view of a redundant structure of an aircraft engine mounting connection structure of the present invention;

[0028] Figure 4 A floating structure display diagram of an aircraft engine mounting connection structure of the present invention;

[0029] Figure 5 This is a disassembled view of a floating structure of an aircraft engine installation connection structure of the present invention;

[0030] Figure 6 It is a dissected and exploded diagram of a connection groove 1 and a connection block 1 of an aircraft engine mounting connection structure of the present invention;

[0031] Figure 7 This is a disassembled view of two rotating joints and a connecting block of an aircraft engine installation connection structure of the present invention;

[0032] Figure 8 This is a structural diagram showing a stud and two nuts of an aircraft engine installation connection structure of the present invention;

[0033] Fig. 9 This is a dissected diagram of a hanger rod of an aircraft engine mounting connection structure according to the present invention.

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

[0035] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0036] like Figure 1 - Fig. 9 As shown, an installation and connection structure of an aircraft engine comprises a bottom beam 1, a top beam 2 is fixedly connected to the top of the bottom beam 1, a plurality of connection beams 3 are fixedly connected between the bottom beam 1 and the top beam 2 at equal intervals, a front support point installation groove 4 is penetrated through the front part of the top of the bottom beam 1, a rear support point 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 redundant rods 12 and two redundant rods 2 13. The top of the top beam 2 is fixedly connected to the first fixed block 8 at the front, the top of the first fixed block 8 is rotatably connected to the suspension rod 1 9, the top of the top beam 2 is fixedly connected to the second fixed block 10 at the rear, and both sides of the second fixed block 10 are rotatably connected to the suspension rod 2 11. The two redundant rods 12 are respectively rotatably connected to the two sides of the bottom beam 1 and at the front, and the two redundant rods 2 13 are respectively rotatably connected to the two sides of the bottom beam 1 and at the rear, the top of the suspension rod 9 and the sides away from the tops of the two redundant rods 2 13 are rotatably connected to the third fixed block 15, and the top of the third fixed block 15 is provided with a floating structure 7.

[0038] In actual operation, the front fulcrum mounting groove 4 and the rear fulcrum connecting block 5 are connected to the front mounting section and the rear mounting section of the aircraft engine through an external connecting component, so that the connection between the bottom beam 1 and the aircraft engine is completed, and then the four fixing plates 18 are connected to the wing of the passenger aircraft through a plurality of studs 22. At this time, the aircraft engine can be connected to the wing of the passenger aircraft.

[0039] Specifically, when the aircraft engine generates vibration during operation, the suspension rod 1 9, the two suspension rods 2 11, the suspension rod 3 14, the two redundant rods 1 12 and the two redundant rods 2 13 will rotate slightly, and the effect of buffering and shock absorption is achieved by rotating. The coordinated rotation of these components can change the force transmission path, disperse the impact force generated by the vibration of the aircraft engine to 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 connecting beam 3 caused by vibration impact;

[0040] In addition, the symmetrical arrangement of the redundant rod 1 12 and the redundant rod 2 13 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 an unexpected failure occurs in one of the redundant rods 12 or the redundant rod 2 13, the remaining redundant components can still maintain the basic buffering and shock absorbing functions, thereby ensuring the reliability of the connection between the aircraft engine and the wing of the passenger aircraft. Moreover, since each fixing plate 18 is connected to 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 is accidentally broken, the fixing plate 18 can still be connected to the unbroken top beam 2 or bottom beam 1, thereby ensuring the stability of the connection between the aircraft engine and the wing of the passenger aircraft.

[0041] Since the suspension rod 1 9 and the suspension rod 2 11 and the other connecting components are all connected in a rotating manner, when the top beam 2 and the bottom beam 1 are broken, each connecting component can be rotated, so that each connecting component and the aircraft engine are connected in a suspended manner, so that the aircraft engine will not fall.

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

[0043] In this embodiment, the adjacent sides of the two redundant rods 12 are rotationally connected to the two sides of the suspension rod 1 9 respectively, and the distant sides of the two suspension rods 2 11 are rotationally connected to the adjacent sides of the two redundant rods 2 13 respectively.

[0044] In this embodiment, the floating structure 7 includes two connecting rods 16 and two connecting rods 2 17. The connecting rod 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 23 is provided inside one end of the connecting rod 16 on one side, and a connecting block 24 is fixedly connected to one end of the connecting rod 16 on the other side, and the connecting block 24 is located inside the connecting groove 23. The other end of the connecting rod 16 on the other side, one end of the connecting rod 17 on one side and the other end of the connecting rod 17 on the other side are all 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 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 1 24 and the connecting groove 1 23 and between the three pairs of connecting blocks 26 and the connecting groove 2 25, the outer surface of the rotating shaft 30 is fixedly connected to a limiting block 28 at the top and the bottom, and the outer surface of the rotating shaft 30 is fixedly connected to a limiting block 29 and is located between the two limiting blocks 1 28.

[0045] Specifically, when the aircraft engine shakes, its two connecting rods 16 and two connecting rods 17 respectively shake slightly relative to each other along the four rotating shafts 30, so as to further optimize the buffering and shock absorption and finely adjust the force distribution. This small shaking between each other can "fine-tune" the shaking impact force from different directions in real time. The limit block 1 28 and the limit block 2 29 can effectively prevent the connecting rod 16 and the connecting rod 2 17 from separating from the rotating shaft 30 during the shaking process, thereby ensuring the integrity of the structure.

[0046] In this embodiment, the tops of the four rotating shafts 30 are fixedly connected to the fixing plate 18, and the four corners of the fixing plate 18 are threaded with studs 22. 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 squeezed against the bottom of the fixing plate 18, and the two nuts 35 are also squeezed against each other.

[0047] Specifically, the two thread grooves with opposite thread directions on the outer surface of the stud 22 and the two nuts 35 matched therewith realize a dual fastening function. During the operation of the aircraft, the connection parts are very easy to loosen due to factors such as engine vibration and airflow impact. This design can effectively cope with this problem. The nut 35 on the top is squeezed against the bottom of the fixing plate 18, and the two nuts 35 are squeezed against each other, forming a tight locking structure, which greatly reduces the risk of loosening of the stud 22 due to vibration and ensures the long-term reliability of the connection.

[0048] In this embodiment, a spring 21 is fixedly connected between the two connecting rods 16 and between the two connecting rods 17 and the two connecting rods 16 .

[0049] Specifically, when the aircraft engine vibrates or shakes, the spring 21 will expand and contract as the connecting rod 1 16 and the connecting rod 2 17 rotate slightly, converting the kinetic energy generated by the vibration or shaking into elastic potential energy and storing it, and then slowly releasing it, thereby effectively reducing the impact force transmitted to the wings of the passenger aircraft and other connecting parts, and cooperating with the redundant rod 1 12, the redundant rod 2 13, the suspension rod 1 9, the suspension rod 2 11, and the suspension rod 3 14 to provide a more stable flight environment for the aircraft. In addition, the spring 21 between the two connecting rods 16 and between the two connecting rods 27 and the two connecting rods 1 16 can adjust its own state in real time according to forces of different directions and sizes, so that the force is evenly dispersed between the connecting rods and the parts connected thereto, avoiding local stress concentration, reducing the risk of damage to parts due to overload, and extending the service life of the entire installation and connection structure.

[0050] In this embodiment, the connecting rod 16 is composed of a straight rod 19, a straight rod 20 and two rotating joints 31. The two rotating joints 31 are respectively connected to the adjacent ends of the straight rod 19 and the straight rod 20. The interior of the rotating joint 31 connected to the straight rod 19 is provided with rotating grooves 33 running through both sides, and the interior of the rotating joint 31 connected to the straight rod 20 is also provided with rotating grooves 33 running through the top and bottom. A connecting block 32 is provided between the two rotating joints 31, and the outer surface of the connecting block 32 is fixedly connected to a rotating rod 34 at the top, bottom and both sides.

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

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

[0053] In this embodiment, a placement groove 36 is opened inside the suspension rod 1 9, the suspension rod 2 11, the suspension rod 3 14, the redundant rod 1 12 and the redundant rod 2 13, and an anti-breaking chain 37 is fixedly connected between the top and the bottom of the placement groove 36, and the anti-breaking chain 37 is in a relaxed state.

[0054] Specifically, when the boom 1 9, the boom 2 11, the boom 3 14, the redundant rod 1 12 and the redundant rod 2 13 break accidentally, the anti-break chains 37 inside each of 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 anti-break chains 37, so as to maintain a temporary and critical connection state, and strive for a safe landing opportunity for the aircraft. In extreme emergencies, even if the main load-bearing components such as the boom 1 9 and the redundant rod 12 break and fail, the anti-break chains 37 can quickly intervene and assume part of the pulling force to prevent the engine from being instantly detached due to complete loss of connection, thereby avoiding catastrophic impact damage to the fuselage of the passenger aircraft.

[0055] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, and these changes and improvements all fall within the scope of the present invention to be protected.

Claims

1. An aircraft engine mounting connection structure, comprising a bottom beam (1), a top beam (2) being fixedly connected to the top of the bottom beam (1), and a plurality of connection beams (3) being fixedly connected at equal intervals between the bottom beam (1) and the top beam (2), characterized in that: A front support point installation groove (4) is provided through the front portion of the top of the bottom beam (1), a rear support point connection block (5) is fixedly connected to the rear portion of the bottom of the bottom beam (1), and a redundant structure (6) is provided on the top of the top beam (2); The redundant structure (6) comprises two redundant rods 1 (12) and two redundant rods 2 (13); a first fixed block (8) is fixedly connected to the front of the top of the top beam (2); a suspension rod 1 (9) is rotatably connected to the top of the first fixed block (8); a second fixed block (10) is fixedly connected to the rear of the top of the top beam (2); suspension rods 2 (11) are rotatably connected to both sides of the second fixed block (10); the two redundant rods 1 (12) are rotatably connected to both sides of the bottom beam (1) and the front; the two redundant rods 2 (13) are rotatably connected to both sides of the bottom beam (1) and the rear; the top of the suspension rod 1 (9) and the two redundant rods 2 (13) are rotatably connected to the sides away from each other; a third fixed block (15) is rotatably connected to the top of the third fixed block (15); a floating structure (7) is provided on the top of the third fixed block (15).

2. The mounting and connecting structure of an aircraft engine according to claim 1, characterized in that: The rear part of the rearmost connecting beam (3) is fixedly connected with a fourth fixing block (27), the rear part of the fourth fixing block (27) is rotatably connected with a suspension rod three (14), and the top of the suspension rod three (14) is also rotatably connected with a third fixing block (15).

3. The mounting and connecting structure of an aircraft engine according to claim 1, characterized in that: The adjacent sides of the two redundant rods 1 (12) are rotatably connected to the two sides of the suspension rod 1 (9), and the distant sides of the two suspension rods 2 (11) are rotatably connected to the adjacent sides of the two redundant rods 2 (13).

4. The mounting and connecting structure of an aircraft engine 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 aircraft engine installation and connection structure 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 mounting and connecting structure of an aircraft 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 aircraft engine installation and connection structure 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 mounting and connecting structure of an aircraft engine according to claim 7, characterized in that: The connecting block (32) is connected to the two rotating grooves (33) through four rotating rods (34), the top and bottom of the rotating joint (31) connected to the straight rod 1 (19) are in an open state, and the two sides of the rotating joint (31) connected to the straight rod 2 (20) are in an open state.

9. The aircraft engine installation and connection structure according to claim 1, characterized in that: The interiors of the suspension rod 1 (9), the suspension rod 2 (11), the suspension rod 3 (14), the redundant rod 1 (12) and the redundant rod 2 (13) are all provided with placement grooves (36), and an anti-breaking chain (37) is fixedly connected between the top and the bottom of the placement groove (36), and the anti-breaking chain (37) is in a relaxed state.

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