Aircraft servo for high heat flow area and preparation method thereof

Abstract

The present invention relates to an aircraft servo and a method for preparing the same, and in particular to an aircraft servo for use in high heat flow areas and a method for preparing the same, which solves the problem in the prior art that the rudder shaft is subjected to overheating due to the gap heat flow, resulting in uncertainty in the strength and stiffness of the rudder shaft, and serious damage to the connection between the horizontal rudder and the rudder cabin. The aircraft servo for use in high heat flow areas of the present invention comprises a horizontal rudder, a rudder cabin, and a rudder shaft, one end of the rudder shaft is fixedly connected to the horizontal rudder, and the other end is rotatably connected to the rudder cabin, an outer thermal insulation ring and an inner thermal insulation ring are sleeved on the rudder shaft between the horizontal rudder and the rudder cabin; one end face of the outer thermal insulation ring is fixedly connected to the bottom face of the horizontal rudder, and a first annular groove is provided on the other end face around the position of the rudder shaft, the inner thermal insulation ring is arranged in the first annular groove, a second annular groove is provided on the outer surface of the rudder cabin around the rudder shaft, and the other end face of the outer thermal insulation ring is matched with the second annular groove.

Description

Technical Field

[0001] The present invention relates to an aircraft steering gear and a preparation method thereof, and in particular to an aircraft steering gear used in a high heat flow area and a preparation method thereof. Background Art

[0002] During flight, the surface of an aircraft will be severely affected by aerodynamic heating. The connection between the horizontal rudder and the servo will be affected by gap heat flow, which will cause the rudder shaft to overheat due to the gap heat flow, resulting in uncertainty in the strength and stiffness of the rudder shaft. As the flight speed of the aircraft increases, the gap heat flow will cause more serious damage to the rudder shaft at the connection between the horizontal rudder and the rudder cabin. Summary of the Invention

[0003] The purpose of the present invention is to solve the shortcomings in the prior art of gap heat flow, which causes the rudder shaft to be overheated due to the gap heat flow, resulting in uncertain strength and stiffness of the rudder shaft, and serious damage to the connection between the horizontal rudder and the rudder cabin, and to provide an aircraft servo for high heat flow areas and a preparation method thereof.

[0004] To achieve the above objectives, the present invention provides the following technical solutions:

[0005] The present invention provides an aircraft servo for a high heat flow area, comprising a horizontal rudder, a rudder cabin and a rudder shaft, one end of the rudder shaft is fixedly connected to the horizontal rudder, and the other end is rotatably connected to the rudder cabin. The special feature of the rudder shaft is that it also comprises an outer thermal insulation ring and an inner thermal insulation ring, the outer thermal insulation ring and the inner thermal insulation ring are sleeved on the rudder shaft between the horizontal rudder and the rudder cabin; one end face of the outer thermal insulation ring is fixedly connected to the bottom face of the horizontal rudder, and a first annular groove is provided on the other end face around the position of the rudder shaft, the inner thermal insulation ring is arranged in the first annular groove, and the end face of the inner thermal insulation ring is flush with the other end face of the outer thermal insulation ring; a second annular groove is provided on the outer surface of the rudder cabin around the rudder shaft, the other end face of the outer thermal insulation ring is matched with the second annular groove, and a second gap and a third gap are respectively left between the outer side face of the outer thermal insulation ring and the inner side face of the second annular groove, and between the other end face of the outer thermal insulation ring and the groove bottom of the second annular groove.

[0006] Furthermore, a gap of 0.5-1 mm is provided between the inner side surface of the outer insulation ring and the rudder shaft, and between the inner side surface of the inner insulation ring and the rudder shaft, so as to further reduce heat transfer generated by the outer insulation ring and the inner insulation ring.

[0007] Furthermore, the spacing of the second gap is 1-1.5 mm; the spacing is adjusted according to the thermal adaptation requirements of the material;

[0008] The spacing of the first gap is 2±0.5mm;

[0009] The spacing of the third gap is less than 1 mm.

[0010] Furthermore, it also includes a connecting structure arranged on one end surface of the outer thermal insulation ring, and the outer thermal insulation ring is fixedly connected to the bottom surface of the horizontal rudder through the connecting structure.

[0011] Furthermore, the connecting structure is a connecting plate, which is provided with a first through hole and is used to be sleeved on the rudder shaft. A side of the connecting plate close to the rudder cabin is connected to an end surface of the outer heat insulation ring, and a first gap is formed between a side surface of the connecting plate and an outer surface of the rudder cabin.

[0012] The bottom surface of the horizontal rudder is provided with a lower edge pad and a lower sealing plate; one side of the lower edge pad is connected to the bottom surface of the horizontal rudder, and the other side is connected to the lower sealing plate. The lower sealing plate is provided with a long hole corresponding to the connecting plate, and the connecting plate is embedded in the long hole; the lower edge pad is provided with a second through hole for being sleeved on the rudder shaft;

[0013] The connecting plate and the lower edge pad are provided with multiple mounting holes at both ends along the length of the horizontal rudder bottom surface. The bottom surface of the horizontal rudder is provided with corresponding threaded holes. The connecting plate, the lower edge pad, and the bottom surface of the horizontal rudder are fixedly connected by screws passing through the corresponding mounting holes and threaded holes. The outer surface of the lower edge pad is configured to mate with the bottom surface of the horizontal rudder, ensuring a sealed and heat-insulating connection between the lower edge pad and the bottom surface of the horizontal rudder.

[0014] Furthermore, the material of the outer insulation ring, connecting plate, lower sealing plate and lower edge pad is C / SiC-HfC or C / SiC-ZrC or C / SiC-Si, and other materials with good heat resistance can also be used. At the same time, the material used will deform less when heated, thereby improving the compactness of the structure.

[0015] The material of the inner insulation ring is quartz or thermogel, and the material heat transfer performance of the inner insulation ring is poor, which further improves the heat protection effect of the rudder shaft.

[0016] The surface of the rudder cabin is provided with aerogel for heat insulation.

[0017] At the same time, a method for preparing the aircraft servo for use in a high heat flow area is also provided, which is special in that it comprises the following steps:

[0018] S1. The inner insulation ring is fixed to the first annular groove of the outer insulation ring to form a heat-proof structure, the inner insulation ring and the outer insulation ring are coaxially arranged; the bottom surface of the horizontal rudder is fixedly connected to one end of the rudder shaft;

[0019] S2. The heat-resistant structure is mounted on the rudder shaft, and one end of the outer insulation ring is fixedly connected to the bottom surface of the horizontal rudder;

[0020] S3. Connect the other end of the rudder shaft to the rudder cabin. The rudder cabin is provided with a second annular groove around the rudder shaft. The heat protection structure is located between the horizontal rudder and the rudder cabin. The other end face of the outer heat insulation ring is matched with the second annular groove, and a second gap and a third gap are left between the outer heat insulation ring and the second annular groove.

[0021] Furthermore, in S2, the outer insulation ring is fixedly connected to the bottom surface of the horizontal rudder through a connecting plate, a lower sealing plate, and a lower edge pad. One side of the connecting plate is connected to an end face of the outer insulation ring. A long hole is provided on the lower sealing plate corresponding to the connecting plate. The connecting plate is embedded in the long hole. The other side of the connecting plate is connected to the lower edge pad, and the lower edge pad is fixedly connected to the bottom surface of the horizontal rudder. The connecting plate and the lower edge pad are respectively provided with a first through hole and a second through hole for being sleeved on the rudder shaft.

[0022] Furthermore, in S1, the inner insulation ring is fixedly connected to the outer insulation ring by high-temperature glue;

[0023] In S2, the outer insulation ring and the connecting plate are an integrated structure, and the lower sealing plate, the lower edge pad and the horizontal rudder are an integrated structure.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention provides a heat-proof structure formed by an outer insulation ring and an inner insulation ring on the rudder shaft between the steering gear and the rudder cabin, thereby reducing the gap heat flow that directly contacts the rudder shaft. By reducing the gap heat flow, the problem of uncertain rudder shaft strength and rigidity caused by gap thermal overheating of the metal rudder shaft is solved. At the same time, the outer insulation ring and the rudder cabin form a second gap and a third gap, which prolongs the distance that the heat flow moves to the rudder shaft. By prolonging the heat flow movement distance, the temperature of the small amount of heat flow that contacts the rudder shaft can be reduced.

[0026] 2. In the present invention, a gap of 0.5-1 mm is set between the inner side surface of the outer insulation ring and the inner side surface of the inner insulation ring and the rudder shaft. The gap between the inner side surface of the inner insulation ring and the rudder shaft is a heat-blocking gap, which prevents the outer insulation ring and the inner insulation ring from directly transferring heat to the rudder shaft.

[0027] 3. In the present invention, the spacing of the second gap is 1-1.5mm, and the spacing of the third gap is less than 1mm. On the basis of ensuring the normal rotation of the heat protection structure around the rudder axis, the spacing is minimized as much as possible to reduce the heat flow in the gap and improve the heat protection effect; at the same time, the heat flow passes through the first gap, the second gap and the third gap in sequence, and a buffer is generated after multiple turns, so that the flow speed is greatly reduced, which also has the effect of reducing the heat flow in the gap.

[0028] 4. In the present invention, the outer and inner insulation layers are made of different materials. The outer layer has good temperature resistance and is not easily deformed when directly exposed to high-temperature heat flow, while the inner insulation layer has poor thermal conductivity, which reduces heat transfer. The outer insulation layer is made of hafnium-modified ceramic-based composite materials (C / SiC-HfC), zirconium-modified ceramic-based composite materials (C / SiC-ZrC), or silicon-modified ceramic-based composite materials (C / SiC-Si), which have good resistance to high-temperature ablation. The ceramic-based composite materials prepared by CVI technology have good mechanical properties and can meet the mechanical property requirements of the outer insulation layer. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a structural diagram of an embodiment of the present invention;

[0030] Figure 2 yes Figure 1 A schematic diagram of the enlarged structure at point A;

[0031] Figure 3 Schematic diagram of the structure of the heat protection structure, connecting plate, lower sealing plate and lower edge pad in an embodiment of the present invention;

[0032] Figure 4 This is an exploded view of the heat protection structure, connecting plate, lower sealing plate and lower edge pad in an embodiment of the present invention;

[0033] Figure 5 Schematic diagram of a heat protection structure according to an embodiment of the present invention; a is a front view of the heat protection structure, b is a top view of the heat protection structure, c is a left view of the heat protection structure, and d is a cross-sectional view of the heat protection structure;

[0034] Description of reference numerals:

[0035] 1-horizontal rudder, 2-rudder shaft, 31-first gap, 32-second gap, 33-third gap, 4-aerogel, 5-outer insulation ring, 51-first annular groove, 52-connecting plate, 6-inner insulation ring, 7-rudder compartment, 71-second annular groove, 8-screw, 9-lower sealing plate, 10-lower edge pad. DETAILED DESCRIPTION

[0036] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments:

[0037] The aircraft servo for high heat flow area of the present invention is as follows: Figure 1 As shown, it includes a horizontal rudder 1, a rudder cabin 7, a rudder shaft 2, and an outer insulation ring 5 and an inner insulation ring 6 on the rudder shaft 2 between the horizontal rudder 1 and the rudder cabin 7. The outer insulation ring 5 and the inner insulation ring 6 form a heat-proof structure. One end of the rudder shaft 2 is fixedly connected to the horizontal rudder 1, and the other end is rotatably connected to the rudder cabin 7.

[0038] One end surface of the outer heat-insulating ring 5 is fixedly connected to the bottom surface of the horizontal rudder 1 through a connecting structure. Figure 3 and Figure 4 As shown, the connection structure is a connecting plate 52, which is provided with a first through hole for being sleeved on the rudder shaft 2. The side of the connecting plate 52 close to the rudder cabin 7 is connected to an end face of the outer heat insulation ring 5, and a first gap 31 is formed between the surface of the side of the connecting plate 52 close to the rudder cabin 7 and the rudder cabin 7. The spacing of the first gap 31 is 2±0.5mm; the bottom surface of the horizontal rudder 1 is provided with a lower edge pad 10 and a lower sealing plate 9; one side of the lower edge pad 10 is connected to the bottom surface of the horizontal rudder, and the other side is connected to the lower sealing plate 9. The lower sealing plate 9 is provided with a long hole corresponding to the connecting plate 52, and the connecting plate 5 2 is embedded in the long hole; a second through hole is provided on the lower edge pad 10 for being sleeved on the rudder shaft 2; a plurality of mounting holes are correspondingly provided at both ends along the length direction of the bottom surface of the horizontal rudder 1 on the connecting plate 52 and the lower edge pad 10, and corresponding threaded holes are opened on the bottom surface of the horizontal rudder 1. The connecting plate 52, the lower edge pad 10 and the bottom surface of the horizontal rudder 1 are fixedly connected by screws 8 passing through the corresponding mounting holes and threaded holes; the outer surface of the lower edge pad 10 is matched with the bottom surface of the horizontal rudder 1 to form better thermal insulation and sealing protection for the rudder shaft 2 at the connection between the lower edge pad 10 and the horizontal rudder 1.

[0039] A first annular groove 51 is provided on the other end surface of the outer heat-insulating ring 5 around the rudder shaft 2. Figure 5 As shown, the inner heat-insulating ring 6 is arranged in the first annular groove 51, and the end face of the inner heat-insulating ring 6 is flush with the other end face of the outer heat-insulating ring 5. A gap of 0.5-1 mm is set between the inner side face of the outer heat-insulating ring 5 and the rudder shaft 2, and between the inner side face of the inner heat-insulating ring 6 and the rudder shaft 2 to avoid heat transfer caused by direct contact between the heat-proof structure and the rudder shaft 2; the surface of the rudder cabin 7 is provided with a second annular groove 71 around the rudder shaft 2, as shown in FIG. Figure 2 As shown, the other end face of the outer thermal insulation ring 5 is arranged in cooperation with the second annular groove 71, and aerogel 4 is provided on the surface of the rudder compartment 7 for thermal insulation; a second gap 32 and a third gap 33 are respectively left between the outer side face of the outer thermal insulation ring 5 and the inner side face of the second annular groove 71, and between the other end face of the outer thermal insulation ring 5 and the groove bottom of the second annular groove 71. The spacing of the second gap 32 is 1-1.5 mm, and the spacing of the third gap 33 is less than 1 mm, which has a heat-proof effect while ensuring that the horizontal rudder 1 rotates normally around the rudder shaft 2. The first gap 31, the second gap 32, and the third gap 33 extend the distance for the external heat flow to enter the rudder shaft 2, effectively reducing the temperature of the heat flow contacting the rudder shaft 2. At the same time, by reducing the sizes of the first gap 31, the second gap 32, and the third gap 33, the heat flow rate contacting the rudder shaft 2 is limited. The sizes of the first gap 31, the second gap 32, and the third gap 33 are determined according to the structural dimensions of the outer thermal insulation ring 5 and its thermal adaptation requirements, leaving space for thermal expansion and contraction.

[0040] The outer thermal insulation ring 5, connecting plate 52, lower sealing plate 9 and lower edge pad 10 are made of hafnium-modified ceramic-based composite material (C / SiC-HfC) or zirconium-modified ceramic-based composite material (C / SiC-ZrC) or silicon-modified ceramic-based composite material (C / SiC-Si). The hafnium-modified ceramic-based composite material has a temperature resistance of up to 2400°C, the zirconium-modified ceramic-based composite material has a temperature resistance of up to 2200°C, and the silicon-modified ceramic-based composite material has a temperature resistance of up to 1600°C-1700°C. They all have a high temperature tolerance and are not easily deformed when directly exposed to heat flow, which is conducive to structural stability. The inner thermal insulation ring 6 is made of quartz, thermal gel or other materials with low thermal conductivity, and the heat transfer to the rudder shaft 2 is reduced through the inner thermal insulation ring 6.

[0041] The method for preparing an aircraft servo for use in a high heat flow region of the present invention comprises the following steps:

[0042] S1. The inner insulation ring 6 is fixed in the first annular groove 51 of the outer insulation ring 5 to form a heat-proof structure. The inner insulation ring 6 and the outer insulation ring 5 are coaxially arranged; the bottom surface of the horizontal rudder 1 is fixedly connected to one end of the rudder shaft 2; the inner insulation ring 6 is fixedly connected to the outer insulation ring 5 by high-temperature glue;

[0043] S2. The heat-resistant structure is provided on the rudder shaft 2, and one end surface of the outer insulation ring 5 is fixedly connected to the bottom surface of the horizontal rudder 1;

[0044] S3. Connect the other end of the rudder shaft 2 to the rudder cabin 7. The rudder cabin 7 is provided with a second annular groove 71 around the rudder shaft 2. The heat protection structure is located between the horizontal rudder 1 and the rudder cabin 7. The other end face of the outer heat insulation ring 5 is matched with the second annular groove 71, and a second gap 32 and a third gap 33 are left between the second annular groove 71.

[0045] In S2, the outer thermal insulation ring 5 is fixedly connected to the bottom surface of the horizontal rudder 1 via a connecting plate 52, a lower sealing plate 9, and a lower edge pad 10. One side of the connecting plate 52 is connected to one end surface of the outer thermal insulation ring 5. A long hole corresponding to the connecting plate 52 is provided on the lower sealing plate 9, and the connecting plate 52 is embedded in the long hole. The other side of the connecting plate 52 is connected to the lower edge pad 10, and the lower edge pad 10 is fixedly connected to the bottom surface of the horizontal rudder 1. The connecting plate 52 and the lower edge pad 10 are respectively provided with a first through hole and a second through hole for being mounted on the rudder shaft 2. This embodiment uses a CVI composite material molding process to prepare the outer thermal insulation ring 5, the connecting plate 52, the lower sealing plate 9, the lower edge pad 10, and the horizontal rudder. During the preparation process, the outer thermal insulation ring 5 and the connecting plate 52 are deposited into an integrated structure, and the lower sealing plate 9, the lower edge pad 10, and the horizontal rudder 1 are integrated into an integrated structure, thereby improving the stability and consistency of the structure.

Claims

1. An aircraft steering gear for use in a high heat flow area, comprising a horizontal rudder (1), a rudder cabin (7), and a rudder shaft (2), wherein one end of the rudder shaft (2) is fixedly connected to the horizontal rudder (1), and the other end is rotatably connected to the rudder cabin (7), and is characterized in that: It also includes an outer heat-insulating ring (5) and an inner heat-insulating ring (6), wherein the outer heat-insulating ring (5) and the inner heat-insulating ring (6) are sleeved on the rudder shaft (2) between the horizontal rudder (1) and the rudder cabin (7); One end surface of the outer heat-insulating ring (5) is fixedly connected to the bottom surface of the horizontal rudder (1), and a first annular groove (51) is provided on the other end surface around the rudder shaft (2). The inner heat-insulating ring (6) is arranged in the first annular groove (51), and the end surface of the inner heat-insulating ring (6) is flush with the other end surface of the outer heat-insulating ring (5); The outer surface of the rudder cabin (7) is provided with a second annular groove (71) around the rudder shaft (2), the other end surface of the outer heat-insulating ring (5) is matched with the second annular groove (71), and a second gap (32) and a third gap (33) are respectively left between the outer side surface of the outer heat-insulating ring (5) and the inner side surface of the second annular groove (71), and between the other end surface of the outer heat-insulating ring (5) and the groove bottom of the second annular groove (71).

2. The aircraft servo for high heat flow area according to claim 1, characterized in that: A gap of 0.5-1 mm is provided between the inner side surface of the outer heat-insulating ring (5) and the rudder shaft (2), and between the inner side surface of the inner heat-insulating ring (6) and the rudder shaft (2).

3. The aircraft servo for use in high heat flow areas according to claim 2, characterized in that: The spacing of the second gap (32) is 1-1.5 mm; The spacing of the third gap (33) is less than 1 mm.

4. The aircraft servo for use in high heat flow areas according to any one of claims 1 to 3, characterized in that: It also includes a connection structure provided on one end surface of the outer heat-insulating ring (5), and the outer heat-insulating ring (5) is fixedly connected to the bottom surface of the horizontal rudder (1) via the connection structure.

5. The aircraft servo for use in high heat flow areas according to claim 4, characterized in that: The connecting structure is a connecting plate (52), the connecting plate (52) being provided with a first through hole for being sleeved on the rudder shaft (2), the side of the connecting plate (52) close to the rudder cabin (7) being connected to an end face of the outer heat insulating ring (5), and a first gap (31) being formed between a side surface of the connecting plate (52) and an outer surface of the rudder cabin (7); the spacing of the first gap (31) being 2±0.5 mm; The bottom surface of the horizontal rudder (1) is provided with a lower edge pad (10) and a lower sealing plate (9); one side of the lower edge pad (10) is connected to the bottom surface of the horizontal rudder (1), and the other side is connected to the lower sealing plate (9); the lower sealing plate (9) is provided with a long hole corresponding to the connecting plate (52), and the connecting plate (52) is embedded in the long hole; the lower edge pad (10) is provided with a second through hole for being sleeved on the rudder shaft (2); The connecting plate (52) and the lower edge pad (10) are provided with a plurality of mounting holes at both ends along the length direction of the bottom surface of the horizontal rudder (1), and the bottom surface of the horizontal rudder (1) is provided with corresponding threaded holes. The connecting plate (52), the lower edge pad (10) and the bottom surface of the horizontal rudder (1) are fixedly connected by screws (8) passing through the corresponding mounting holes and threaded holes; the outer surface of the lower edge pad (10) is matched with the bottom surface of the horizontal rudder (1).

6. The aircraft servo for use in high heat flow areas according to claim 5, characterized in that: The material of the outer heat-insulating ring (5), the connecting plate (52), the lower sealing plate (9) and the lower edge pad (10) is C / SiC-HfC or C / SiC-ZrC or C / SiC-Si; The material of the inner heat-insulating ring (6) is quartz or thermogel; The surface of the rudder cabin (7) is provided with aerogel (4).

7. A method for preparing an aircraft servo for use in a high heat flow area according to any one of claims 1 to 6, characterized in that: The following steps are involved: S1. The inner heat-insulating ring (6) is fixed in the first annular groove (51) of the outer heat-insulating ring (5) to form a heat-proof structure, and the inner heat-insulating ring (6) and the outer heat-insulating ring (5) are coaxially arranged; the bottom surface of the horizontal rudder (1) is fixedly connected to one end of the rudder shaft (2); S2. The heat-resistant structure is mounted on the rudder shaft (2), and one end surface of the outer heat-insulating ring (5) is fixedly connected to the bottom surface of the horizontal rudder (1); S3. The other end of the rudder shaft (2) is connected to the rudder cabin (7), and the rudder cabin (7) is provided with a second annular groove (71) around the rudder shaft (2). The heat-proof structure is located between the horizontal rudder (1) and the rudder cabin (7). The other end face of the outer heat-insulating ring (5) is matched with the second annular groove (71), and a second gap (32) and a third gap (33) are left between the outer heat-insulating ring (5) and the second annular groove (71).

8. The method for preparing an aircraft servo for use in a high heat flow area according to claim 7, characterized in that: In S2, the outer heat-insulating ring (5) is fixedly connected to the bottom surface of the horizontal rudder (1) through a connecting plate (52), a lower sealing plate (9), and a lower edge pad (10); one side of the connecting plate (52) is connected to an end surface of the outer heat-insulating ring (5); a long hole is provided on the lower sealing plate (9) corresponding to the connecting plate (52); the connecting plate (52) is embedded in the long hole; the other side of the connecting plate (52) is connected to the lower edge pad (10); and the lower edge pad (10) is fixedly connected to the bottom surface of the horizontal rudder (1); The connecting plate (52) and the lower edge pad (10) are respectively provided with a first through hole and a second through hole, which are used for being sleeved on the rudder shaft (2).

9. The method for preparing an aircraft servo for use in a high heat flow area according to claim 8, characterized in that: In S1, the inner insulation ring (6) is fixedly connected to the outer insulation ring (5) by high-temperature glue; In S2, the outer heat insulation ring (5) and the connecting plate (52) are an integrated structure, and the lower sealing plate (9), the lower edge pad (10) and the horizontal rudder (1) are an integrated structure.

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