An aircraft engine cockpit installation structure

Abstract

The present invention relates to the field of engine mounting brackets, and discloses an aviation engine cabin mounting structure, comprising: a spliced ​​bracket; a middle fixing piece; a middle-end vibration absorbing mechanism, wherein the middle-end vibration absorbing mechanism comprises a torsional vibration buffer mechanism fixedly connected to the middle fixing piece and a plurality of three-way comprehensive vibration buffer mechanisms connected to the torsional vibration buffer mechanism, wherein the other ends of the plurality of three-way comprehensive vibration buffer mechanisms are respectively connected to a plurality of parallel connecting parts, and the three-way comprehensive vibration buffer mechanisms are used to offset the three-way comprehensive vibration transmitted from the parallel connecting parts; the mounting bracket of the present invention has a detachable connection between a fixed end and a supporting end, and is assisted by a middle-end vibration absorbing mechanism, so that vibrations generated by different parts of the engine can be adaptively absorbed, and when a large degree of local damage occurs in daily use, the number of replacement components can be reduced, and the maintenance cost can be effectively reduced, and the overall vibration absorbing effect is better.

Description

Technical Field

[0001] The invention relates to the field of engine mounting brackets, and more specifically, to an aircraft engine cabin mounting structure. Background Art

[0002] The engine mounting bracket in the field of small UAVs is arranged according to the aircraft's engine design. It is generally connected to the engine on the vibration reduction system of the aircraft's firewall wall panel, reliably connecting and fixing the power unit to the aircraft nacelle to ensure the stability of the power unit's established posture on the aircraft, while reducing the transmission of engine vibration and oscillation to the cabin.

[0003] Existing engine mounting brackets are mostly one-piece structures consisting of a fixed end and a supporting end. The supporting end needs to have a certain vibration absorption and buffering effect while realizing the supporting connection. However, this type of mounting bracket absorbs vibrations based on the metal properties of the mounting bracket itself, and has a certain fatigue loss coefficient. When the engine is in a working state, the losses of different parts inside the engine are different, which will also cause different degrees of vibration generated in each part when the engine is in a working state, which will also cause different losses on the mounting bracket. This can easily lead to the overall replacement of the one-piece mounting bracket due to excessive local losses, resulting in excessively high maintenance costs. At the same time, its own metal properties cannot be adjusted and cannot adapt to the different degrees of vibration generated by the engine. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine cabin installation structure in order to solve the above-mentioned problem.

[0005] The present invention provides an aircraft engine cabin installation structure, comprising:

[0006] A spliced ​​bracket, the spliced ​​bracket comprising a fixing portion, a plurality of connecting ears integrally formed on the fixing portion, a plurality of supporting portions detachably connected to the fixing portion, and a parallel connecting portion integrally formed at the other end of the supporting portion, wherein the plurality of connecting ears and supporting portions are evenly distributed on the fixing portion, and the plurality of parallel connecting portions are parallel to the fixing portion;

[0007] A middle fixing member, wherein the middle fixing member is fixedly connected to the fixing portion, and the middle fixing member and the fixing portion are coaxially arranged;

[0008] A mid-end vibration absorbing mechanism, the mid-end vibration absorbing mechanism includes a torsional vibration buffer mechanism fixedly connected to a middle fixing member and a plurality of three-way integrated vibration buffer mechanisms connected to the torsional vibration buffer mechanism, the other ends of the plurality of three-way integrated vibration buffer mechanisms are respectively connected to a plurality of parallel connecting parts, the three-way integrated vibration buffer mechanism is used to offset the three-way integrated vibration transmitted from the parallel connecting parts, and the torsional vibration buffer mechanism is used to offset the torsional vibration transmitted from the parallel connecting parts and the three-way integrated vibration buffer mechanism.

[0009] As a further optimization scheme of the present invention, the torsional vibration buffer mechanism includes a middle supporting rod fixedly connected to the middle fixing member, a plurality of sliding connection components arranged on the middle supporting rod, and a plurality of sub-connected torsional vibration elimination components arranged on the middle supporting rod, and the plurality of sub-connected torsional vibration elimination components are all connected to the corresponding sliding connection components, one end of the three-way integrated vibration buffer mechanism is hinged on the sliding connection component, and the sub-connected torsional vibration elimination component is used to offset the torsional vibration transmitted to the sliding connection component by the three-way integrated vibration buffer mechanism.

[0010] As a further optimization scheme of the present invention, the sliding connection assembly includes an arc-shaped limit slide groove arranged on the outer wall of the middle supporting rod and a limit slide block slidably connected to the inside of the arc-shaped limit slide groove. One end of the three-way integrated vibration buffer mechanism is hinged to the limit slide block, and the slave torsional vibration elimination components are all arranged in the arc-shaped limit slide groove.

[0011] As a further optimization scheme of the present invention, the linked torsional vibration elimination component includes two telescopic bags symmetrically connected on the inner walls at both ends of the arc-shaped limiting slide groove, a spring arranged in the telescopic bag, a main cavity arranged inside the middle supporting rod, two branch cavities and two exhaust cavities, one end of several branch cavities are connected to the main cavity, and the other end of the branch cavity is respectively connected to the corresponding telescopic bag, the other end of the telescopic bag is fixedly connected to the limiting slider, the internal space of the telescopic bag is connected to the outside through the exhaust cavity, and the main cavity is connected to the three-way comprehensive vibration buffer mechanism.

[0012] As a further optimization solution of the present invention, a one-way valve is provided in the exhaust cavity, and the one-way valve is used to adjust the air pressure threshold inside the telescopic bladder.

[0013] As a further optimization scheme of the present invention, the three-way integrated vibration buffer mechanism includes an elastic telescopic buffer component, a telescopic pump air component arranged inside the elastic telescopic buffer component, a one-way pump air control component arranged inside the elastic telescopic buffer component, and a hose connected between the elastic telescopic buffer component and the middle supporting rod. The output end of the one-way pump air control component is connected to the connected torsional vibration elimination component through the hose, and the input end of the one-way pump air control component is connected to the outside world.

[0014] As a further optimization scheme of the present invention, the elastic telescopic buffer assembly includes a hollow sleeve rod, a piston rod slidably connected in the hollow sleeve rod, a hinged frame hinged at the other end of the piston rod, and a spring connected between the piston rod and the inner wall of the hollow sleeve rod, and the hollow sleeve rod is hinged to the limiting slider.

[0015] As a further optimization scheme of the present invention, the telescopic pump air assembly includes a telescopic bellows connected between the piston rod and the inner wall of the hollow sleeve rod, the telescopic bellows is wrapped around the outside of spring two, and a sealed pump air chamber is formed between the piston rod, the hollow sleeve rod and the telescopic bellows. The one-way pump air control assembly is connected to the sealed pump air chamber. When the volume of the sealed pump air chamber is reduced, it is used to pump the internal gas into the hose from the output end of the one-way pump air control assembly. When the volume of the sealed pump air chamber is increased, it is used to pump air into the input end of the one-way pump air control assembly.

[0016] As a further optimization scheme of the present invention, the one-way pump air control component includes a T-shaped cavity arranged inside the hollow sleeve rod, a partition 1 fixedly connected to the inner wall at the input end of the T-shaped cavity, a plurality of air holes 1 arranged on the partition 1, a plastic sealing sheet 1 connected to the partition 1, a partition 2 fixedly connected to the inner wall near the output end of the T-shaped cavity, a plurality of air holes 2 arranged on the partition 2, and a plastic sealing sheet 2 connected to the air holes 2, the plastic sealing sheet 1 has only one end connected to the end surface of the partition 1 close to the partition 2, and the plastic sealing sheet 1 covers the plurality of air holes 1, the plastic sealing sheet 2 has only one end connected to the end surface of the partition 2 away from the partition 1, and the plastic sealing sheet 2 covers the plurality of air holes 2, and the output end of the T-shaped cavity is connected to the hose.

[0017] The beneficial effects of the present invention are as follows: the mounting bracket of the present invention has a detachable connection between the fixed end and the supporting end, and is assisted by a mid-end vibration absorption mechanism, which can adaptively absorb the vibrations generated by different parts of the engine, and in daily use, when a large degree of local damage occurs, the number of replacement components can be reduced, which can effectively reduce maintenance costs, and the overall vibration absorption effect is better. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 The present invention Figure 1 The main view;

[0020] Figure 3 The present invention Figure 2 The cross-sectional view at AA in FIG.

[0021] Figure 4It is a diagram showing the coordination between the torsional vibration buffer mechanism and the three-way integrated vibration buffer mechanism of the present invention;

[0022] Figure 5 The present invention Figure 4 Enlarged view at center C;

[0023] Figure 6 The present invention Figure 4 Magnified view at D in the middle;

[0024] Figure 7 The present invention Figure 1 Right view of;

[0025] Figure 8 The present invention Figure 7 The cross-sectional view at BB in FIG.

[0026] Fig. 9 The present invention Figure 8 A magnified view of point E in FIG.

[0027] Fig.10 It is a structural schematic diagram of the one-way valve of the present invention.

[0028] In the figure: 1, spliced ​​bracket; 101, fixing part; 102, connecting ear piece; 103, supporting part; 104, parallel connecting part; 2, middle fixing part; 3, middle end vibration absorption mechanism; 31, torsional vibration buffer mechanism; 3101, middle bearing rod; 3102, arc-shaped limit slide groove; 3103, limit slide block; 3104, main cavity; 3105, telescopic capsule; 3106, branch cavity; 3107, exhaust cavity; 3108, single 3109, spring one; 32, three-way integrated vibration buffer mechanism; 3201, hollow sleeve rod; 3202, piston rod; 3203, hinged frame; 3204, telescopic bellows; 3205, spring two; 3206, T-shaped cavity; 3207, partition one; 3208, air hole one; 3209, plastic sealing piece one; 3210, partition two; 3211, air hole two; 3212, plastic sealing piece two; 3213, hose. DETAILED DESCRIPTION

[0029] The subject matter described herein will now be discussed with reference to example embodiments. It should be understood that the discussion of these embodiments is only intended to enable those skilled in the art to better understand and implement the subject matter described herein. In addition, the features described relative to some examples may also be combined in other examples.

[0030] like Figure 1-Figure 3 as well as Figure 7 As shown, an aircraft engine cabin installation structure includes:

[0031] The spliced ​​bracket 1 includes a fixing portion 101, a plurality of connecting ear pieces 102 integrally formed on the fixing portion 101, a plurality of supporting portions 103 detachably connected to the fixing portion 101, and a parallel connecting portion 104 integrally formed at the other end of the supporting portion 103, wherein the plurality of connecting ear pieces 102 and the supporting portion 103 are evenly distributed on the fixing portion 101, and the plurality of parallel connecting portions 104 are parallel to the fixing portion 101;

[0032] A middle fixing member 2, which is fixedly connected to the fixing portion 101, and the middle fixing member 2 and the fixing portion 101 are coaxially arranged;

[0033] The middle-end vibration absorbing mechanism 3 includes a torsional vibration buffer mechanism 31 fixedly connected to the middle fixing member 2 and a plurality of three-way comprehensive vibration buffer mechanisms 32 connected to the torsional vibration buffer mechanism 31. The other ends of the plurality of three-way comprehensive vibration buffer mechanisms 32 are respectively connected to a plurality of parallel connection parts 104. The three-way comprehensive vibration buffer mechanism 32 is used to offset the three-way comprehensive vibration transmitted from the parallel connection part 104. The torsional vibration buffer mechanism 31 is used to offset the torsional vibration transmitted from the parallel connection part 104 and the three-way comprehensive vibration buffer mechanism 32.

[0034] It should be noted that when installing the aircraft engine, the parallel connection part 104 on the corresponding support part 103 is first connected to the engine connection, and then the fixing part 101 is connected to the plurality of support parts 103, and finally the fixing part 101 is connected to the cockpit of the fuselage, so as to fix the connection between the aircraft engine and the fuselage. When the aircraft engine is working, the vibration generated along the X, Y, Z axis and the center axis of the engine is transmitted to the plurality of three-way integrated vibration buffer mechanisms 32, and the vibration is reduced by the three-way integrated vibration buffer mechanisms 32 and the torsional vibration. The buffer mechanism 31 offsets the vibration generated by the engine, and each three-way integrated vibration buffer mechanism 32 offsets vibrations to different degrees. The three-way integrated vibration buffer mechanism 32 and the torsional vibration buffer mechanism 31 can adaptively adjust their buffering performance according to the different degrees of vibration generated by each part of the engine to reduce the loss of their own metal properties, thereby effectively improving the stability and service life of the overall structure, and some of the support parts 103, parallel connection parts 104, and three-way integrated vibration buffer mechanisms 32 can be replaced in a targeted manner, thereby effectively reducing maintenance costs.

[0035] In an optional embodiment, if Figure 2-Figure 5 as well as Figure 8-Figure 10As shown, the torsional vibration buffer mechanism 31 includes a middle supporting rod 3101 fixedly connected to the middle fixing member 2, a plurality of sliding connection components arranged on the middle supporting rod 3101, and a plurality of sub-connected torsional vibration elimination components arranged on the middle supporting rod 3101, and the plurality of sub-connected torsional vibration elimination components are all connected to the corresponding sliding connection components, one end of the three-way integrated vibration buffer mechanism 32 is hinged on the sliding connection component, and the sub-connected torsional vibration elimination component is used to offset the torsional vibration transmitted to the sliding connection component by the three-way integrated vibration buffer mechanism 32.

[0036] The sliding connection component includes an arc-shaped limit groove 3102 arranged on the outer wall of the middle supporting rod 3101 and a limit slider 3103 slidably connected to the inside of the arc-shaped limit groove 3102. One end of the three-way integrated vibration buffer mechanism 32 is hinged to the limit slider 3103, and the connected torsional vibration elimination components are all arranged in the arc-shaped limit groove 3102.

[0037] The linked torsional vibration elimination component includes two telescopic capsules 3105 symmetrically connected on the inner walls at both ends of the arc-shaped limiting slide groove 3102, a spring 3109 arranged in the telescopic capsule 3105, a main cavity 3104 arranged inside the middle supporting rod 3101, two branch cavities 3106 and two exhaust cavities 3107, one end of each of the branch cavities 3106 is connected to the main cavity 3104, and the other ends of the branch cavities 3106 are respectively connected to the corresponding telescopic capsules 3105, the other end of the telescopic capsule 3105 is fixedly connected to the limiting slider 3103, the internal space of the telescopic capsule 3105 is connected to the outside through the exhaust cavity 3107, and the main cavity 3104 is connected to the three-way comprehensive vibration buffer mechanism 32.

[0038] A one-way valve 3108 is provided in the exhaust cavity 3107 , and the one-way valve 3108 is used to adjust the air pressure threshold inside the telescopic bag 3105 .

[0039] It should be noted that when the parallel connection part 104 is affected by the vibration of the engine, such as the vibrations generated in the three directions of X, Y, and Z, when they are integrated to the parallel connection part 104, they can be buffered by the elastic expansion and contraction buffer of the three-way integrated vibration buffer mechanism 32 and the slave torsional vibration elimination component in the torsional vibration buffer mechanism 31 respectively. When the three-way integrated vibration buffer mechanism 32 is affected by the integrated vibration and drives the torsional vibration buffer mechanism 31 to vibrate along the circumferential direction of the middle support rod 3101, the limit slider 3103 is affected by the three-way integrated vibration buffer mechanism 32 and vibrates back and forth along the arc-shaped limit slide groove 3102. In this process, the limit slider 31 can be adjusted by the telescopic capsule 3105 and the spring 1 3109 inside it. 03's vibration is buffered, which includes two buffering methods. One is the metal property buffering of the spring 3109, and the other is the air pressure change caused by the pressure of the gas inside the telescopic bag 3105 to provide a buffering effect. When the vibration transmitted by the parallel connection part 104 becomes more severe, the impact on the three-way integrated vibration buffer mechanism 32 also becomes more severe. The gas in the telescopic bag 3105 can be discharged from the one-way valve 3108 at the exhaust cavity 3107, and the three-way integrated vibration buffer mechanism 32 can continuously pump gas into the telescopic bag 3105 during buffering, so that the telescopic bag 3105 can always maintain a stable gas buffering function, thereby effectively reducing the loss of metal buffer components such as the spring 3109.

[0040] In an optional embodiment, if Figure 3-Figure 4 as well as Figure 6 As shown, the three-way integrated vibration buffer mechanism 32 includes an elastic telescopic buffer component, a telescopic pump air component arranged inside the elastic telescopic buffer component, a one-way pump air control component arranged inside the elastic telescopic buffer component, and a hose 3213 connected between the elastic telescopic buffer component and the middle supporting rod 3101. The output end of the one-way pump air control component is connected to the connected torsional vibration elimination component through the hose 3213, and the input end of the one-way pump air control component is connected to the outside world.

[0041] It should be noted that, as mentioned above, when the three-way integrated vibration buffer mechanism 32 is subjected to the vibration transmission of the parallel connection part 104, the elastic telescopic buffer component therein will buffer the vibration of the parallel connection part 104, and during the buffering process, perform a reciprocating telescopic process with an indefinite stroke, and continuously adjust the volume size inside the telescopic pump air component during the reciprocating telescopic process, so that while providing a gas buffering effect, new gas can be continuously pumped in from the outside to replenish the gas inside the telescopic pump air component and the telescopic bladder 3105, thereby providing a stable gas-assisted buffering effect.

[0042] In an optional embodiment, if Figure 3-Figure 4As shown, the elastic telescopic buffer assembly includes a hollow sleeve rod 3201, a piston rod 3202 slidably connected in the hollow sleeve rod 3201, a hinge frame 3203 hinged at the other end of the piston rod 3202, and a spring 3205 connected between the piston rod 3202 and the inner wall of the hollow sleeve rod 3201. The hollow sleeve rod 3201 is hinged to the limit slider 3103.

[0043] It should be noted that, as mentioned above, when the elastic telescopic buffer assembly is affected by vibration and begins to reciprocate, the piston rod 3202 therein can move along the central axis of the hollow sleeve rod 3201 and compress the spring 2 3205 during the movement. The vibration energy transmitted to the piston rod 3202 by the parallel connection part 104 is absorbed through the deformation of the spring 2 3205, thereby effectively reducing the impact of the vibration on the body, and effectively improving the stability of the body during flight.

[0044] In an optional embodiment, if Figure 3-Figure 4 As shown, the telescopic pump air assembly includes a telescopic bellows 3204 connected between the piston rod 3202 and the inner wall of the hollow sleeve rod 3201, the telescopic bellows 3204 is wrapped around the outside of the spring 2 3205, and a sealed pump air chamber is formed between the piston rod 3202, the hollow sleeve rod 3201 and the telescopic bellows 3204. The one-way pump air control assembly is connected to the sealed pump air chamber. When the volume of the sealed pump air chamber is reduced, it is used to pump the internal gas from the output end of the one-way pump air control assembly into the hose 3213. When the volume of the sealed pump air chamber is increased, it is used to pump air from the input end of the one-way pump air control assembly.

[0045] It should be noted that when the piston rod 3202 moves along the central axis of the hollow sleeve rod 3201, the telescopic bellows 3204 can be continuously compressed and stretched. When the telescopic bellows 3204 is compressed, its internal volume decreases, generating positive pressure. While providing gas buffering, the gas can be discharged into the one-way pump gas control component, and the gas is introduced into the hose 3213 through the one-way pump gas control component, and flows through the main cavity 3104 and the branch cavity 3106 and then enters the telescopic capsule 3105, so that the telescopic capsule 3105 and the telescopic bellows 3204 construct an overall gas buffering flow path, and when the telescopic bellows 3204 recovers from the compressed state to the initial state or the stretched state, its internal volume increases, generating positive pressure, thereby pumping external gas from the input end of the one-way pump gas control component, thereby realizing a new round of gas buffering gas replenishment process.

[0046] In an optional embodiment, if Figure 3-Figure 4 as well as Figure 6As shown, the one-way pump air control assembly includes a T-shaped cavity 3206 disposed inside the hollow sleeve rod 3201, a partition 1 3207 fixedly connected to the inner wall at the input end of the T-shaped cavity 3206, a plurality of air holes 1 3208 disposed on the partition 1 3207, a plastic sealing sheet 1 3209 connected to the partition 1 3207, a partition 2 3210 fixedly connected to the inner wall near the output end of the T-shaped cavity 3206, a plurality of air holes 2 3211 disposed on the partition 2 3210, and a plastic sealing sheet 1 3209 connected to the partition 1 3207. A plastic sealing sheet 2 3212 is provided on the air hole 2 3211, only one end of the plastic sealing sheet 1 3209 is connected to the end face of the partition 1 3207 close to the partition 2 3210, and the plastic sealing sheet 1 3209 covers a number of air holes 1 3208, only one end of the plastic sealing sheet 2 3212 is connected to the end face of the partition 2 3210 away from the partition 1 3207, and the plastic sealing sheet 2 3212 covers a number of air holes 2 3211, and the output end of the T-shaped cavity 3206 is connected to the hose 3213.

[0047] It should be noted that, as mentioned above, when the internal volume of the telescopic bellows 3204 decreases and the air pressure increases, a positive pressure is generated, and the positive pressure acts on the plastic sealing sheet 1 3209, so that the plastic sealing sheet 1 3209 is tightly pressed on the partition 1 3207 and seals the plurality of air holes 1 3208, so that the gas cannot be discharged from the air holes 1 3208 to the outside, and the plastic sealing sheet 2 3212 is bent and deformed under the positive pressure, so that the plurality of air holes 2 3211 are connected with the hose 3213, and the gas is discharged from the hose 3213 into the telescopic bag 3105. Similarly, when the telescopic bellows When the internal volume of 3204 increases and the air pressure decreases, negative pressure is generated. When the negative pressure acts on the second plastic sealing sheet 3212, the second plastic sealing sheet 3212 can be tightly attached to the second partition 3210 and seal the multiple air holes 3211. When acting on the first plastic sealing sheet 3209, it can bend toward the inside of the T-shaped cavity 3206, so that the T-shaped cavity 3206 is connected with the outside air through the multiple air holes 3208, and the outside air is continuously pumped into the T-shaped cavity 3206 and the telescopic bellows 3204 under the action of negative pressure, so as to provide a stable amount of gas for subsequent buffering.

[0048] The present embodiment is described above, but the present embodiment is not limited to the above-mentioned specific implementation manner. The above-mentioned specific implementation manner is merely illustrative and not restrictive. Under the guidance of the present embodiment, ordinary technicians in this field can also make many forms, which are all within the protection of the present embodiment.

Claims

1. An aircraft engine cabin installation structure, characterized in that: include: A spliced ​​bracket (1), the spliced ​​bracket (1) comprising a fixing portion (101), a plurality of connecting ear pieces (102) integrally formed on the fixing portion (101), a plurality of supporting portions (103) detachably connected to the fixing portion (101), and a parallel connecting portion (104) integrally formed at the other end of the supporting portion (103), wherein the plurality of connecting ear pieces (102) and the supporting portion (103) are evenly distributed on the fixing portion (101), and the plurality of parallel connecting portions (104) are parallel to the fixing portion (101); A middle fixing member (2), wherein the middle fixing member (2) is fixedly connected to the fixing portion (101), and the middle fixing member (2) and the fixing portion (101) are coaxially arranged; A middle-end vibration absorbing mechanism (3), the middle-end vibration absorbing mechanism (3) comprising a torsional vibration buffer mechanism (31) fixedly connected to the middle fixing member (2) and a plurality of three-way integrated vibration buffer mechanisms (32) connected to the torsional vibration buffer mechanism (31), the other ends of the plurality of three-way integrated vibration buffer mechanisms (32) being respectively connected to a plurality of parallel connecting parts (104), the three-way integrated vibration buffer mechanisms (32) being used to offset the three-way integrated vibration transmitted from the parallel connecting parts (104), and the torsional vibration buffer mechanisms (31) being used to offset the torsional vibration transmitted from the parallel connecting parts (104) and the three-way integrated vibration buffer mechanisms (32).

2. The aircraft engine cabin installation structure according to claim 1, characterized in that: The torsional vibration buffer mechanism (31) comprises a middle support rod (3101) fixedly connected to a middle fixing member (2), a plurality of sliding connection components arranged on the middle support rod (3101), and a plurality of secondary torsional vibration elimination components arranged on the middle support rod (3101), wherein the secondary torsional vibration elimination components are all connected to corresponding sliding connection components, one end of the three-way integrated vibration buffer mechanism (32) is hinged on the sliding connection component, and the secondary torsional vibration elimination component is used to offset the torsional vibration transmitted from the three-way integrated vibration buffer mechanism (32) to the sliding connection component.

3. The aircraft engine cabin installation structure according to claim 2, characterized in that: The sliding connection component comprises an arc-shaped limit slide groove (3102) arranged on the outer wall of the middle supporting rod (3101) and a limit slide block (3103) slidably connected to the inside of the arc-shaped limit slide groove (3102); one end of the three-way integrated vibration buffer mechanism (32) is hinged to the limit slide block (3103); and the slave torsional vibration elimination components are all arranged in the arc-shaped limit slide groove (3102).

4. The aircraft engine cabin installation structure according to claim 3, characterized in that: The slave torsional vibration elimination component comprises two telescopic capsules (3105) symmetrically connected to the inner walls at both ends of the arc-shaped limit slide groove (3102), a spring (3109) arranged in the telescopic capsule (3105), a main cavity (3104) arranged in the middle supporting rod (3101), two branch cavities (3106) and two exhaust cavities (3107), one end of a plurality of the branch cavities (3106) are connected to the main cavity (3104), the other end of the branch cavity (3106) is respectively connected to the corresponding telescopic capsule (3105), the other end of the telescopic capsule (3105) is fixedly connected to the limit slide block (3103), the internal space of the telescopic capsule (3105) is connected to the outside through the exhaust cavity (3107), and the main cavity (3104) is connected to the three-way comprehensive vibration buffer mechanism (32).

5. The aircraft engine cabin installation structure according to claim 4, characterized in that: A one-way valve (3108) is provided in the exhaust cavity (3107), and the one-way valve (3108) is used to adjust the air pressure threshold inside the telescopic bag (3105).

6. The aircraft engine cabin installation structure according to claim 5, characterized in that: The three-way integrated vibration buffer mechanism (32) comprises an elastic telescopic buffer component, a telescopic pump air component arranged inside the elastic telescopic buffer component, a one-way pump air control component arranged inside the elastic telescopic buffer component, and a hose (3213) connected between the elastic telescopic buffer component and the middle supporting rod (3101); the output end of the one-way pump air control component is connected to the slave torsional vibration elimination component through the hose (3213), and the input end of the one-way pump air control component is connected to the outside.

7. The aircraft engine cabin installation structure according to claim 6, characterized in that: The elastic telescopic buffer assembly comprises a hollow sleeve rod (3201), a piston rod (3202) slidably connected inside the hollow sleeve rod (3201), a hinge frame (3203) hinged to the other end of the piston rod (3202), and a second spring (3205) connected between the piston rod (3202) and the inner wall of the hollow sleeve rod (3201); the hollow sleeve rod (3201) is hinged to a limit slider (3103).

8. The aircraft engine cabin installation structure according to claim 7, characterized in that: The telescopic pump air component includes a telescopic bellows (3204) connected between the piston rod (3202) and the inner wall of the hollow sleeve rod (3201), the telescopic bellows (3204) is wrapped around the outside of the second spring (3205), and a sealed pump air chamber is formed between the piston rod (3202), the hollow sleeve rod (3201) and the telescopic bellows (3204). The one-way pump air control component is connected to the sealed pump air chamber. When the volume of the sealed pump air chamber is reduced, the internal gas thereof is pumped into the hose (3213) from the output end of the one-way pump air control component. When the volume of the sealed pump air chamber is increased, air is pumped into the one-way pump air chamber from the input end of the one-way pump air control component.

9. The aircraft engine cabin installation structure according to claim 8, characterized in that: The one-way pump air control assembly comprises a T-shaped cavity (3206) disposed inside the hollow sleeve (3201), a partition plate (3207) fixedly connected to the inner wall at the input end of the T-shaped cavity (3206), a plurality of air holes (3208) disposed on the partition plate (3207), a plastic sealing sheet (3209) connected to the partition plate (3207), a partition plate (3210) fixedly connected to the inner wall near the output end of the T-shaped cavity (3206), a plurality of air holes (3211) disposed on the partition plate (3210), and a plurality of air holes (3212) connected to the air holes (3213). The plastic sealing sheet (3209) is connected to the end face of the partition (3207) close to the partition (3210) at only one end, and the plastic sealing sheet (3209) covers a plurality of air holes (3208); the plastic sealing sheet (3212) is connected to the end face of the partition (3210) away from the partition (3207) at only one end, and the plastic sealing sheet (3212) covers a plurality of air holes (3211); the output end of the T-shaped cavity (3206) is connected to the hose (3213).

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