A partition-sealed vane-type aviation actuator

Abstract

The present invention provides a partition-sealed vane-type aviation actuator, which relates to the technical field of aviation equipment; the partition-sealed vane-type aviation actuator includes a cylinder block, a front end cover and a rear end cover provided at both ends of the cylinder block, and a vane shaft penetrating the cylinder block; at least one fixed vane is provided on the inner wall of the cylinder block, and at least one moving vane is provided on the outer periphery of the vane shaft. Installation grooves are respectively formed on the fixed vane and the moving vane, and a sealing assembly is embedded in each installation groove. The sealing assembly includes an elastic seal and a wear-resistant seal. The elastic seal is attached to the bottom surface of the installation groove, and the wear-resistant seal is attached to the outer side surface of the elastic seal. Through holes are respectively provided at both ends of the wear-resistant seal, and corresponding process columns passing through the through holes are provided on the elastic seal. In the natural state, the diameter of the process column is smaller than the aperture of the through hole, and the process column protrudes from the wear-resistant seal. The partition-sealed vane-type aviation actuator of the present invention has a good sealing effect.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation actuators, and specifically, to a vane-type aviation actuator with partitioned sealing. Background Art

[0002] The traditional aircraft rudder surface control mainly relies on a linear hydraulic actuator of the cylinder type. The advantages of this actuator are simple structure, easy sealing, low processing cost, and reasonable failure modes. However, the linear hydraulic actuator composed of a traditional cylinder needs to convert the linear motion into a rotational motion through a rocker arm structure, and the rocker arm requires a large installation space, resulting in a fairing that needs to bulge on the aircraft surface.

[0003] Currently, some aviation equipment has adopted a vane-type aviation actuator to directly output a large torque to drive the deflection of the aircraft rudder surface. Structurally, it is coaxial with the rudder surface drive shaft and can be completely built into the wing, thus avoiding the appearance of a bulging fairing on the aircraft and meeting the design requirements of the new generation of aircraft. In this type of aviation actuator, each moving vane and each fixed vane divide the cylinder body into multiple cavities, and by adjusting the oil pressure in each cavity, each moving vane rotates, thereby causing the output shaft to rotate.

[0004] However, this type of actuator has the following defects: The seals of the moving vane and the fixed vane are both simple door shapes. It is easy for the two ends of the door-shaped seal structure to cause leakage in the end grooves during actual operation because it is difficult for the seal to form sufficient pre-pressure with the groove, affecting the performance of the actuator. Summary of the Invention

[0005] For this reason, the present invention proposes a vane-type aviation actuator with partitioned sealing to enable the actuator to have a better sealing effect.

[0006] The technical solution of the present invention is as follows:

[0007] A vane-type aviation actuator with partitioned sealing, comprising a cylinder body, a front end cover and a rear end cover provided at both ends of the cylinder body, and a vane shaft passing through the cylinder body, the front end cover and the rear end cover. At least one fixed vane is provided on the inner wall of the cylinder body, and at least one moving vane is provided on the outer periphery of the vane shaft. It further includes:

[0008] An installation groove is formed on the fixed vane and / or the moving vane, and the installation groove includes a first groove section located on the outer side surface of the fixed vane and / or the moving vane, and two second groove sections connected to the first groove section and provided on the two end surfaces of the fixed vane and / or the moving vane;

[0009] The sealing assembly includes an elastic seal and a wear-resistant seal. The elastic seal fits against the bottom surface of the mounting groove, and the wear-resistant seal fits against the outer side surface of the elastic seal. Through holes are respectively provided at both ends of the wear-resistant seal, and corresponding process posts passing through the through holes are provided on the elastic seal. In the natural state, the diameter of the process post is smaller than the aperture of the through hole, and the process post protrudes from the wear-resistant seal. After installation, the process post is compressed and expanded to squeeze the inner wall of the through hole, so as to increase the pressing force between the wear-resistant seal and the wall surface of the mounting groove.

[0010] Further, the cross-section of the mounting groove perpendicular to its own length direction is rectangular, and circular grooves are respectively formed at both ends of the mounting groove. The diameter of the groove is larger than the width of the mounting groove. The elastic seal and the wear-resistant seal have ends adapted to the shape of the groove, and the through hole and the process post are both concentric with the groove.

[0011] Further, the end of the wear-resistant seal and the groove are in interference fit.

[0012] Further, the material of the elastic seal is rubber, and the material of the wear-resistant seal is polytetrafluoroethylene.

[0013] Further, a first annular groove concentric with the cylinder block is provided on the end surface of the cylinder block for fitting with the front end cover; a second annular groove concentric with the cylinder block is provided on the end surface of the cylinder block for fitting with the rear end cover, and O-ring seals are respectively installed in the first annular groove and the second annular groove.

[0014] Further, the output end of the vane shaft is a smooth shaft, or a keyway is provided on the output end; a threaded hole and a blind hole for installing an angle sensor are provided at the other end of the vane shaft.

[0015] Further, at least two fixed vanes are provided on the inner wall of the cylinder block, and moving vanes respectively inserted between adjacent two of the fixed vanes are provided on the vane shaft. Each moving vane divides the cavity between adjacent two fixed vanes into a first oil chamber and a second oil chamber, so as to rotate the vane shaft through the pressure difference on both sides of the moving vane; and a plurality of annular end face seal grooves are provided on the end faces of the front end cover and / or the rear end cover close to the cylinder block. The projection of the cavity on the front end cover or the rear end cover is located inside the corresponding end face seal groove, and end face seals are respectively installed in each end face seal groove.

[0016] Further, the end face seal includes two arc-shaped segments concentric with the cylinder block, and two connecting segments respectively connecting the two ends of the two arc-shaped segments. The diameter of the outer arc-shaped segment is greater than the diameter of the inner hole of the cylinder block, and the diameter of the inner arc-shaped segment is less than the diameter of the shoulder of the blade shaft where the fixed blade is installed. The two connecting segments correspond to and are opposite to two adjacent fixed blades, and the two connecting segments on each fixed blade are respectively disposed on both sides of the seal assembly.

[0017] Further, the cross-section of the end face seal groove perpendicular to its own length direction is rectangular. The shape of the end face seal is matched with that of the end face seal groove, and the material of the end face seal is polyurethane.

[0018] Further, Gleitrings are respectively installed between the blade shaft and the shaft holes of the front end cover, and between the blade shaft and the shaft holes of the rear end cover.

[0019] The working principle and beneficial effects of the present invention are as follows:

[0020] The vane-type aviation actuator with partitioned seals provided by the present invention is provided with a "C"-shaped installation groove on the moving vane and / or the fixed vane, and a seal assembly is embedded in the installation groove. The seal assembly includes an elastic seal member that fits against the bottom surface of the installation groove, and a wear-resistant seal member disposed outside the elastic seal member. When the elastic seal member is subjected to lateral pressure, it can deform, thereby increasing the pressing force between the elastic seal member and the bottom surface of the installation groove, between the elastic seal member and the wear-resistant seal member, and between the wear-resistant seal member and the contact surface outside it, improving the sealing effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be further described in detail below with reference to the drawings and specific embodiments.

[0022] Figure 1 It is a front view cross-sectional view of the vane-type aviation actuator with partitioned seals provided by an embodiment of the present invention;

[0023] Figure 2 It is a side view cross-sectional view of the vane-type aviation actuator with partitioned seals provided by an embodiment of the present invention;

[0024] Figure 3 It is a front view of the cooperation between the cylinder block and the blade shaft provided by an embodiment of the present invention;

[0025] Figure 4 It is an internal structure diagram of the vane-type aviation actuator with partitioned seals provided by an embodiment of the present invention;

[0026] Figure 5 It is Figure 4 a partial enlarged view of part A in

[0027] Figure 6 Schematic diagram of the relative positions of the sealing assembly, end face seal, and O-ring provided by the embodiment of the present invention;

[0028] Figure 7 Stereogram of the sealing assembly provided by the embodiment of the present invention;

[0029] Figure 8 Exploded view of the sealing assembly provided by the embodiment of the present invention;

[0030] Figure 9 Cross-sectional view of the cooperation between the sealing assembly, stationary vane, and vane shaft provided by the embodiment of the present invention;

[0031] Figure 10 is Figure 9 Partial enlarged view at position B in

[0032] In the figure: 100, cylinder block; 110, stationary vane; 101, first groove section; 102, second groove section; 103, cavity; 200, front end cover; 300, rear end cover; 400, vane shaft; 410, moving vane; 500, sealing assembly; 510, elastic seal; 520, wear-resistant seal; 501, through hole; 511, process column; 610, first O-ring; 620, second O-ring; 700, end face seal; 710, arc section; 720, connecting section; 800, Gleitring. Detailed implementation manners

[0033] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present invention.

[0034] The structure and working principle of the vane-type aviation actuator of the present invention are as Figure 1As shown in the figure, a plurality of fixed vanes 110 are provided on the inner wall of the cylinder block 100. Rotating vanes 410 are provided on the vane shaft 400 and are respectively located between two adjacent fixed vanes 110. The rotating vanes 410 divide the cavity between two adjacent fixed vanes 110 into a first oil chamber 104 and a second oil chamber 105. A first hydraulic oil port 106 and a second hydraulic oil port 107 are provided on the cylinder block. Among them, the first hydraulic oil port 106 is communicated with one of the first oil chambers 104, and each of the first oil chambers 104 is communicated through a first through hole formed on the vane shaft 400, so that the oil pressures in each of the first oil chambers 104 are equal. The second hydraulic oil port 107 is communicated with one of the second oil chambers 105, and each of the second oil chambers 105 is communicated through a second through hole formed on the vane shaft 400, so that the oil pressures in each of the second oil chambers 105 are equal. By making there be a pressure difference between the first oil chamber 104 and the second oil chamber 105 on both sides of the rotating vane 410, it is possible to drive each rotating vane 410, that is, the vane shaft 400, to rotate.

[0035] From the working principle of the above-mentioned aviation actuator, it can be seen that in order to ensure the performance of the vane-type aviation actuator, good sealing effects are required both between the first oil chamber 104 and the second oil chamber 105 on both sides of the rotating vane 410 and between the cavities on both sides of each fixed vane 110.

[0036] Therefore, the present embodiment provides a vane-type aviation actuator with partitioned sealing, which will be simply referred to as a vane-type aviation actuator hereinafter. Refer to Figure 2 and Figure 3 As shown in the figure, the vane-type aviation actuator includes a cylinder block 100, a front end cover 200 and a rear end cover 300 provided at both ends of the cylinder block 100, and a vane shaft 400 passing through the cylinder block 100, the front end cover 200 and the rear end cover 300. At least one fixed vane 110 is provided on the inner wall of the cylinder block 100, and at least one rotating vane 410 is provided on the outer periphery of the vane shaft 400.

[0037] Refer to Figures 3 to 6As shown, in this embodiment, mounting grooves are respectively formed on the stationary blade 110 and the moving blade 410. Taking the mounting groove formed on the stationary blade 110 as an example, it includes a first groove section 101 located on the outer side surface of the stationary blade 110, and two second groove sections 102 that are connected to the first groove section 101 and are provided on the two end surfaces of the stationary blade 110. Among them, the outer side surface of the stationary blade 110 refers to the side surface close to the blade shaft 400, and the two end surfaces respectively refer to the end surfaces facing the front end cover 200 and the rear end cover 300. The mounting groove formed on the moving blade 410 includes a first groove section 101 located on the outer side surface of the moving blade 410, and second groove sections 102 that are connected to the first groove section 101 and are provided on the two end surfaces of the moving blade 410. Among them, the outer side surface of the moving blade 410 refers to the side surface close to the inner wall of the cylinder block 100, and the two end surfaces respectively refer to the end surfaces facing the front end cover 200 and the rear end cover 300.

[0038] In this embodiment, a sealing assembly 500 is respectively installed in each mounting groove. Refer to Figures 4 to 8 As shown, the sealing assembly 500 includes an elastic seal 510 and a wear-resistant seal 520. Among them, the elastic seal 510 is attached to the bottom surface of the mounting groove, and the wear-resistant seal 520 is attached to the outer side surface of the elastic seal 510. Through holes 501 are respectively provided at both ends of the wear-resistant seal 520, and corresponding process posts 511 passing through the through holes 501 are provided on the elastic seal 510. In the natural state, the diameter of the process post 511 is smaller than the aperture of the through hole 501, and the process post 511 protrudes from the wear-resistant seal 520.

[0039] Taking the stationary blade 110 as an example, in order to prevent hydraulic oil from leaking from one side of the stationary blade 110 to the other side, it is necessary to prevent hydraulic oil from leaking through the gaps between the stationary blade 110 and the inner wall of the blade shaft 400, between the stationary blade 110 and the front end cover 200, and between the stationary blade 110 and the rear end cover 300. In this embodiment, by providing the above-mentioned mounting groove and the sealing assembly 500, first, as Figure 9 and Figure 10 shown, when the hydraulic oil squeezes the elastic seal 510 from the side of the elastic seal 510 in the C direction on the high-pressure side, the elastic seal 510 will have a deformation in the depth direction of the mounting groove, that is, the D direction. This deformation can increase the pressing force between the elastic seal 510 and the bottom surface of the mounting groove, the pressing force between the elastic seal 510 and the wear-resistant seal 520, and the pressing force between the outer side surface of the wear-resistant seal 520 and the blade shaft 400. So that the contact pressure between the wear-resistant seal 520 and the front end cover 200, the blade shaft 400 and the rear end cover 300, between the wear-resistant seal 520 and the elastic seal 510, and between the elastic seal 510 and the bottom surface of the mounting groove is always higher than the oil pressure of the hydraulic oil, thereby avoiding the leakage of hydraulic oil.

[0040] Secondly, by providing the through holes 501 and the process columns 511 as described above, after the cylinder block 100, the front end cover 200, and the rear end cover 300 are installed together, the process columns 511 will be squeezed by the front end cover 200 or the rear end cover 300. The process columns 511 will be compressed and expanded, causing their diameters to increase. After the diameters of the process columns 511 increase, they will exert a thrust on the inner wall of the through holes 501, thereby causing the wear-resistant seal 520 to expand outwards, thereby increasing the pressing force between the wear-resistant seal 520 and the side wall surface of the installation groove, and improving the sealing effect between the wear-resistant seal 520 and the side wall of the installation groove.

[0041] In this embodiment, referring to Figures 5 to 8 As shown, the cross-section of the above-mentioned installation groove perpendicular to its own length direction is rectangular, and circular grooves are respectively formed at both ends of the installation groove, and the diameter of the groove is larger than the width of the installation groove. The above-mentioned elastic seal 510 and wear-resistant seal 520 respectively have ends adapted to the shape of the groove, and the above-mentioned through holes 501 and process columns 511 are both concentrically arranged with the groove.

[0042] In this embodiment, by providing a circular groove and setting the ends of the elastic seal 510 and the wear-resistant seal 520 to be circular and matching the groove. On the one hand, when the process column 511 is compressed and the wear-resistant seal 520 is squeezed by the process column 511 and expands outwards, its expansion can be more uniform, thereby improving the sealing effect between the wear-resistant seal 520 and the side wall surface of the installation groove. On the other hand, when designing the seal assembly 500, the length of the section of the seal assembly 500 for installation in the second groove section 102 can be set to be slightly less than the length of the second groove section 102. After the seal assembly 500 is embedded in the installation groove, a pulling force can be applied to the seal assembly 500 for installation in the first groove section 101 to improve the sealing effect between the seal assembly 500 and the installation groove.

[0043] In this embodiment, the end of the above-mentioned wear-resistant seal 520 and the groove preferably adopt an interference fit to improve the sealing effect between the wear-resistant seal 520 and the side wall of the installation groove. In this embodiment, the material of the above-mentioned elastic seal 510 is rubber, and the material of the wear-resistant seal 520 is polytetrafluoroethylene.

[0044] In some embodiments, the above-mentioned installation groove and seal assembly 500 may also be provided only on the stationary blade 110, and the moving blade 410 adopts an existing sealing structure; or the above-mentioned installation groove and seal assembly 500 may be provided only on the moving blade 410, and the stationary blade 110 adopts an existing sealing structure. Among them, the existing sealing structure can refer to the prior art and will not be elaborated here.

[0045] Referring to Figure 2 and Figure 4As shown, in this embodiment, a first annular groove concentric with the cylinder block 100 is provided on the end face of the cylinder block 100 for fitting with the front end cover 200, and a first O-ring seal 610 is installed in the first annular groove. By providing the first O-ring seal 610, it is possible to prevent hydraulic oil from leaking between the contact surfaces of the cylinder block 100 and the front end cover 200. And a second annular groove concentric with the cylinder block 100 is provided on the end face of the cylinder block 100 for fitting with the rear end cover 300, and a second O-ring seal 620 is installed in the second annular groove. By providing the second O-ring seal 620, it is possible to prevent hydraulic oil from leaking between the contact surfaces of the cylinder block 100 and the rear end cover 300.

[0046] In this embodiment, referring to Figure 3 As shown, the number of fixed vanes 110 in the cylinder block 100 is two. Two annular end face seal grooves are provided on the end face of the front end cover 200 close to the cylinder block 100. The projections of the two cavities 103 formed by the two fixed vanes 110 on the end face of the front end cover 200 are correspondingly located inside the two end face seal grooves, and end face seals 700 are respectively installed in the end face seal grooves. Specifically, each pair of adjacent hydraulic cavities of each moving vane 410 of the vane shaft 400 is divided into a group in the end face area. As Figure 3 shown, the end face seal 700 separates the cavities on both sides of a moving vane 410 from other cavities in the end face area. The end face seal groove provided on the end face of the rear end cover 300 close to the cylinder block 100 has the same principle and will not be elaborated here.

[0047] A preferred structure of the end face seal 700 is as Figure 3 shown. It includes two arc segments 710 concentric with the cylinder block 100, and connecting segments 720 connecting the two ends of the two arc segments respectively. Among them, the diameter of the outer arc segment 710 is larger than the inner diameter of the cylinder block 100, and the diameter of the inner arc segment 710 is smaller than the diameter of the shoulder of the vane shaft 400, and the two connecting segments 720 are opposite to the two fixed vanes 110. And referring to Figure 3 shown, the two connecting segments 720 on each fixed vane 110 are respectively located on both sides of the seal assembly 500 on the fixed vane 110.

[0048] In this embodiment, by providing the above-mentioned end face seal 700, when the vane shaft 400 rotates, there is relative sliding between the shoulder face of the vane shaft 400 and the end face seal 700, that is, the two form a sliding seal. At the position where the cylinder block 100 is connected to the front end cover 200 or the rear end cover 300, the end face seal 700 is a static seal. By providing the end face seal 700, it is possible to prevent hydraulic oil from leaking in areas close to the vane of the cylinder block 100, such as the end face of the cylinder block 100 and the shoulder of the vane shaft 400, thus having good sealing performance. Moreover, since the end face seal 700 divides each cavity 103 into independent areas, it can preferably prevent the leakage of hydraulic oil between two adjacent cavities 103.

[0049] In some embodiments, the number of fixed vanes 110 can also be three or more, and the number of end face seal grooves is correspondingly three or more. In some embodiments, the end face seal groove can also be provided only on the front end cover 200 or the rear end cover 300, and an existing sealing method can be adopted on the rear end cover 300 or the front end cover 200 accordingly.

[0050] In this embodiment, the cross-section of the end face seal groove perpendicular to its own length direction is rectangular, and the shape of the end face seal 700 matches the end face seal groove. In some embodiments, the cross-section of the end face seal groove can also be a truncated circle, etc. In this embodiment, the material of the end face seal 700 is polyurethane.

[0051] Reference Figure 2 As shown, in this embodiment, wear rings 800 are respectively installed between the shaft hole of the vane shaft 400 and the front end cover 200, and between the shaft hole of the vane shaft 400 and the rear end cover 300. To prevent hydraulic oil from leaking between the shaft hole of the vane shaft 400 and the front end cover 200, or between the shaft hole of the vane shaft 400 and the rear end cover 300. It should be noted that the wear ring 800 can adopt existing products, and its structure and working principle will not be elaborated here.

[0052] In this embodiment, the output end of the vane shaft 400 is a smooth shaft, or a keyway is provided on the output end; the output shaft is connected to the rudder surface by means of interference fit, spline or flat key, etc. A threaded hole and a blind hole for installing an angle sensor are provided at the other end of the vane shaft 400 to feedback the swing angle of the actuator by means of the angle sensor. Among them, the method of installing the angle sensor on the shaft through the threaded hole and the blind hole can refer to the existing technology, and it will not be elaborated here.

[0053] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A partition-sealed vane-type aviation actuator, comprising a cylinder, a front cover and a rear cover arranged at both ends of the cylinder, and a vane shaft penetrating the cylinder, the front cover and the rear cover, wherein at least one fixed vane is arranged on the inner wall of the cylinder, and at least one moving vane is arranged on the outer periphery of the vane shaft, characterized in that: Also includes: A mounting groove is constructed on the stator blade and / or the moving blade, and the mounting groove includes a first groove section located on the outer side surface of the stator blade and / or the moving blade, and two second groove sections connected to the first groove section and arranged on two end surfaces of the stator blade and / or the moving blade; A sealing assembly, comprising an elastic seal and a wear-resistant seal, wherein the elastic seal is attached to the bottom surface of the installation groove, and the wear-resistant seal is attached to the outer side surface of the elastic seal; through holes are respectively provided on both ends of the wear-resistant seal, and a process column passing through the through holes is correspondingly provided on the elastic seal; in a natural state, the diameter of the process column is smaller than the aperture of the through hole, and the process column protrudes from the wear-resistant seal; after installation, the process column expands under pressure and squeezes the inner wall of the through hole to increase the pressing force between the wear-resistant seal and the wall of the installation groove; The cross-section of the mounting groove perpendicular to its own length direction is rectangular, and circular grooves are constructed at both ends of the mounting groove, the diameter of the groove is larger than the width of the mounting groove, the elastic seal and the wear-resistant seal have ends adapted to the shape of the groove, and the through hole and the process column are concentric with the groove.

2. The partition-sealed vane-type aero-actuator according to claim 1, characterized in that: The end of the wear-resistant seal is interference fit with the groove.

3. The partition-sealed vane-type aero-actuator according to claim 1, characterized in that: The elastic sealing component is made of rubber, and the wear-resistant sealing component is made of polytetrafluoroethylene.

4. The partition-sealed vane-type aerospace actuator according to claim 1, characterized in that: The end surface of the cylinder body used to fit with the front end cover is provided with a first annular groove concentric with the cylinder body; the end surface of the cylinder body used to fit with the rear end cover is provided with a second annular groove concentric with the cylinder body, and O-rings are respectively embedded in the first annular groove and the second annular groove.

5. The partition-sealed vane-type aero-actuator according to claim 1, characterized in that: The output end of the blade shaft is an optical axis, or a keyway is provided on the output end; the other end of the blade shaft is provided with a threaded hole and a blind hole for installing an angle sensor.

6. The partition-sealed vane-type aero-actuator according to any one of claims 1 to 5, characterized in that: At least two fixed blades are provided on the inner wall of the cylinder body, and moving blades are provided on the blade shaft, which are respectively inserted between two adjacent fixed blades, and each moving blade divides the cavity between two adjacent fixed blades into a first oil cavity and a second oil cavity, so that the blade shaft rotates through the pressure difference on both sides of the moving blade; and a plurality of annular end face sealing grooves are provided on the end face of the front end cover and / or the rear end cover close to the cylinder body, and the projection of the cavity on the front end cover or the rear end cover is located inside the corresponding end face sealing groove, and an end face seal is respectively embedded in each of the end face sealing grooves.

7. The partition-sealed vane-type aero-actuator according to claim 6, characterized in that: The end face seal includes two arc segments concentric with the cylinder body, and two connecting segments respectively connecting the two ends of the two arc segments, the diameter of the outer arc segment is larger than the diameter of the inner hole of the cylinder body, the diameter of the inner arc segment is smaller than the diameter of the shoulder of the blade shaft on which the stator blade is installed, and the two connecting segments correspond to two adjacent stator blades, and the two connecting segments on each stator blade are arranged on both sides of the sealing assembly.

8. The partition-sealed vane-type aero-actuator according to claim 6, characterized in that: The cross section of the end face sealing groove perpendicular to its own length direction is rectangular, the shape of the end face sealing member matches the end face sealing groove, and the material of the end face sealing member is polyurethane.

9. The partition-sealed vane-type aerospace actuator according to claim 1, characterized in that: Gray rings are respectively installed between the blade shaft and the shaft hole of the front end cover, and between the blade shaft and the shaft hole of the rear end cover.

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