Double-layer annular force bearing device and loading platform for helicopter propeller hub central part

Abstract

The invention discloses a double-layer annular bearing device and a loading platform for a helicopter propeller hub central piece, and the double-layer annular bearing device comprises an inner ring bearing rack and an outer ring bearing rack which are concentrically arranged, and the inner ring bearing rack and the outer ring bearing rack are both arranged to be of a regular polyhedral annular body structure and are manufactured and formed in a reinforced concrete pouring mode; the outer ring bearing rack is formed by surrounding first and second bearing racks which are alternately arranged, and the inner ring bearing rack is formed by surrounding third and fourth bearing racks which are alternately arranged; the bearing racks at the corresponding positions of the inner ring bearing rack and the outer ring bearing rack are arranged in parallel; the first heavy frame is used for bearing shimmy force loading of the propeller hub central part, and the second heavy frame is used for bearing centrifugal force loading of the propeller hub central part; the third heavy frame and the second heavy frame are arranged in parallel and used for bearing damping force of the propeller hub center piece, and a rectangular groove hole is formed in the fourth heavy frame and used for avoiding the shimmy force loading mechanism. The problem that it is difficult to use an existing welded type steel frame bearing platform to achieve fatigue test loading of the propeller hub center piece of the heavy helicopter is solved.

Description

Technical Field

[0001] The present invention relates to the field of, but is not limited to, helicopter hub center piece testing technology, and in particular to a double-layer annular load-bearing device and a loading platform for a helicopter hub center piece. Background Art

[0002] As one of the core components of the helicopter rotor system, the hub centerpiece is a key stress-bearing component on the helicopter. It bears the centrifugal force, lift, flapping force, swing force, and damping force transmitted by the blades, and its stress conditions are very complex. Therefore, the fatigue life of the hub centerpiece directly affects the service life of the entire helicopter, and its performance directly affects the strength and flight safety of the helicopter.

[0003] The heavy-duty helicopter is my country's first 40-ton fully independently developed multi-purpose transport helicopter, with a take-off weight far greater than the existing maximum tonnage of 13-ton helicopters. The blade hub is expanded from the original 5 arms to 7 arms, the elastic bearing is changed from the original single ball flexible elastic bearing to a combined elastic bearing, and the blade length is twice that of the 13-ton blade, which makes the hub centerpiece of the heavy-duty helicopter bear a greater load. Therefore, the existing ordinary welded steel frame bearing platform for the conventional ball flexible hub centerpiece can no longer meet the loading requirements of the fatigue test of the 100-ton heavy hub centerpiece. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned problems, an embodiment of the present invention provides a double-layer annular load-bearing device and loading platform for a helicopter hub center piece, so as to solve the problem that the existing ordinary welded steel frame bearing platform for the conventional spherical flexible hub center piece is difficult to use the existing welded steel frame bearing platform to achieve fatigue test loading because the hub center piece of a heavy helicopter bears a greater load than that of existing models of helicopters.

[0005] Technical solution of the present invention: In a first aspect, an embodiment of the present invention provides a double-layer annular load-bearing device for a helicopter hub central component, comprising: an inner ring load-bearing stand and an outer ring load-bearing stand arranged concentrically;

[0006] The inner ring load-bearing frame and the outer ring load-bearing frame are respectively manufactured by reinforced concrete casting, and the inner ring load-bearing frame and the outer ring load-bearing frame are both arranged as regular polyhedral annular structures, the outer ring load-bearing frame is formed by the alternately arranged first load-bearing frame 1 and the second load-bearing frame 2, and the inner ring load-bearing frame is formed by the alternately arranged third load-bearing frame 3 and the fourth load-bearing frame 4; and the load-bearing frames at corresponding positions of the inner ring load-bearing frame and the outer ring load-bearing frame are arranged in parallel;

[0007] The first load-bearing frame 1 is used to bear the swing force loading of the central part of the hub, and the second load-bearing frame 2 is used to bear the centrifugal force loading of the central part of the hub;

[0008] The third bearing frame 3 of the inner ring bearing frame is arranged in parallel with the second bearing frame 2 of the outer ring bearing frame, and is used to bear the damping force of the hub central part. The fourth bearing frame 4 is provided with a rectangular slot 4-1 for avoiding the swing force loading mechanism.

[0009] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0010] A plurality of oscillating parallel rail grooves 1 - 1 with the same spacing are vertically provided on each first bearing frame 1 of the outer ring bearing frame, and are used to install the oscillating force loading mechanism on the oscillating parallel rail grooves 1 - 1 by fixing bolts.

[0011] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0012] The sway parallel rail groove 1-1 of each first load-bearing frame 1 is fixed with a sway force loading support by bolts, and the sway force loading actuator is installed on the sway force loading support, and the sway force loading angle of the sway force loading actuator is adjusted by adjusting the position of the sway force loading support on the sway parallel rail groove 1-1;

[0013] One end of the wire rope in the swing force loading mechanism is connected to the swing force loading actuator, and the other end passes through the rectangular slot 4-1 of the fourth load-bearing frame 4 at the corresponding position and is connected to the hub central part to implement swing force load loading.

[0014] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0015] A circular through hole 2-1 is formed in the middle of each second bearing frame 2 of the outer ring bearing frame, and a plurality of threaded holes are evenly distributed around each circular through hole 2-1, for passing a centrifugal force loading mechanism through the circular through hole 2-1, and fixing the centrifugal force loading mechanism to the second bearing frame 2 by bolts;

[0016] The third load-bearing frame 3 of the inner ring load-bearing frame is provided with upper and lower through holes 3 - 2 for the upper and lower steel cables of the centrifugal force loading mechanism at corresponding positions to pass through without interfering with the third load-bearing frame 3 .

[0017] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0018] After the piston rod of the centrifugal force loading actuator passes through the circular through hole 2-1 of each second load-bearing frame 2 from the outside, the centrifugal force loading actuator is fixed to the second load-bearing frame 2 by multiple bolts evenly distributed circumferentially. One end of the steel wire rope of the centrifugal force loading mechanism is connected to the centrifugal force loading actuator, and the other end is connected to the hub central part after passing through the hole 3-2 to implement centrifugal load loading.

[0019] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0020] A plurality of damping parallel grooves 3-1 with the same spacing are vertically formed on each third bearing frame 3 of the inner ring bearing frame, and are used to install the damping force loading mechanism on the damping parallel grooves 3-1 by fixing bolts.

[0021] Optionally, in the double-layer annular load-bearing device for the helicopter hub centerpiece as described above,

[0022] The damping parallel track groove 3-1 of each third load-bearing frame 3 is fixedly installed with a damping force loading support by bolts, and the damping force loading actuator is installed on the damping force loading support, and the damping force loading angle of the damping force loading actuator is adjusted by adjusting the position of the damping force loading support on the damping parallel track groove 3-1;

[0023] One end of the loading connecting rod in the damping force loading mechanism is connected to the damping force loading actuator, and the other end is connected to the hub center piece to implement damping force load loading.

[0024] Optionally, in the double-layer annular load-bearing device for the helicopter hub center piece as described above, the hub center piece for loading has 7 arms,

[0025] The inner ring load-bearing frame and the outer ring load-bearing frame are arranged as a regular tetradecahedral ring structure, and respectively have 7 first load-bearing frames 1, 7 second load-bearing frames 2, 7 third load-bearing frames 3 and 7 fourth load-bearing frames 4.

[0026] In a second aspect, an embodiment of the present invention further provides a loading platform for a helicopter hub centerpiece, comprising:

[0027] A double-layer annular load-bearing device for a helicopter hub center piece as described in any one of the above, and a horizontal loading mechanism for loading a helicopter hub center piece;

[0028] Wherein, the horizontal loading mechanism includes: a centrifugal force loading mechanism, a swing force loading mechanism and a damping force loading mechanism.

[0029] Optionally, in a loading platform for a helicopter hub centerpiece as described above,

[0030] The shimmy force loading mechanism realizes different shimmy force loading angles by moving the shimmy parallel track groove 1-1 to different installation positions;

[0031] The damping force loading mechanism realizes different damping force loading angles by moving the damping parallel track groove 3-1 to different installation positions;

[0032] The steel wire rope of the centrifugal force loading mechanism passes through the through hole 3 - 2 of the third load-bearing frame 3 at the corresponding position, and is connected to the centrifugal force loading actuator on the second load-bearing frame 2 at the corresponding position, thereby realizing centrifugal force load loading.

[0033] Beneficial effects of the present invention: The embodiment of the present invention provides a double-layer annular load-bearing device and loading platform for the central part of a helicopter hub. Since the existing ordinary welded steel frame load-bearing platform can no longer meet the large load requirements of the central part of a heavy helicopter hub in terms of load-bearing, and in view of the large load loading test requirements of the central part of a heavy helicopter hub, the embodiment of the present invention utilizes a combination of a steel frame structure and a concrete structure to form a double-layer annular load-bearing device that can be used for a three-way loading test of a large load of 100 tons; the double-layer annular load-bearing device includes a concentrically arranged inner ring load-bearing stand and an outer ring load-bearing stand; the use of the double-layer annular load-bearing device can meet the centrifugal force, swing force and damper force loading of multiple arm hub central parts. The embodiment of the present invention has the following beneficial effects:

[0034] First, the structural form of the double-layer annular load-bearing device improves the connection strength, enhances the overall rigidity, and greatly improves the load-bearing capacity of the load-bearing device to meet the load loading requirements of the central part of the heavy-duty propeller hub;

[0035] Second, the use of this double-layer annular load-bearing device can truly and accurately simulate the boundary conditions and load characteristics of the helicopter hub centerpiece, filling the gap in the field of fatigue test devices for 100-ton helicopter hub centerpieces in China and improving the strength test level of my country's helicopters;

[0036] Third, the double-layer annular load-bearing structure is used to carry out fatigue tests on the central parts of heavy-duty propeller hubs. In the tests, it can withstand the coordinated loading of a large load of hundreds of tons in the fatigue tests on the central parts of heavy-duty propeller hubs. The test bench has high strength, and the three-way loads do not interfere with each other.

[0037] Fourth, the use of this double-layer annular load-bearing device can meet the centrifugal force, swing force and damper force loading of multiple arm hub central parts. The test bench has a simple structure, and its strength and rigidity can well meet the test loading requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0039] Figure 1 A schematic diagram of the overall structure of a double-layer annular load-bearing device for a helicopter hub center piece provided by an embodiment of the present invention;

[0040] Figure 2 for Figure 1 A schematic top view of an inner ring load-bearing stand and an outer ring load-bearing stand in a double-layer annular load-bearing device for a helicopter hub centerpiece provided in the illustrated embodiment;

[0041] Figure 3 A schematic diagram of the overall structure of a loading platform for a helicopter hub centerpiece provided in an embodiment of the present invention. Specific implementation plan

[0042] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0043] The above background technology has explained that for the existing ordinary welded steel frame bearing platform of the conventional spherical flexible hub center piece, it is difficult to use the existing welded steel frame bearing platform to achieve its fatigue test loading problem because the hub center piece of the heavy helicopter bears a greater load than the existing model helicopters.

[0044] In order to solve the above problems, the present invention provides a double-layer annular load-bearing device and a loading platform for a helicopter hub center piece, which can meet the load loading requirements of a heavy-duty helicopter hub center piece.

[0045] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0046] Figure 1 The overall structural diagram of a double-layer annular load-bearing device for a helicopter hub center piece provided by an embodiment of the present invention is shown in FIG. Figure 2 for Figure 1 The embodiment shown is a top view of the inner ring bearing frame and the outer ring bearing frame in the double-layer annular bearing device for the central part of the helicopter hub. Figure 1 and Figure 2 As shown, the double-layer annular load-bearing device provided in an embodiment of the present invention includes: an inner ring load-bearing frame and an outer ring load-bearing frame which are concentrically arranged.

[0047] like Figure 1 and Figure 2As shown, the inner ring load-bearing frame and the outer ring load-bearing frame are respectively manufactured by reinforced concrete casting, and the inner ring load-bearing frame and the outer ring load-bearing frame are both arranged as regular polyhedral annular structures, the outer ring load-bearing frame is formed by the alternately arranged first load-bearing frame 1 and the second load-bearing frame 2, and the inner ring load-bearing frame is formed by the alternately arranged third load-bearing frame 3 and the fourth load-bearing frame 4; as shown Figure 2 The top view of the inner ring load-bearing stand and the outer ring load-bearing stand is shown. Figure 2 In the figure, the inner and outer ring bearing frames are arranged concentrically as a regular polyhedral annular structure as an example. In addition, the bearing frames at corresponding positions of the inner ring bearing frame and the outer ring bearing frame are arranged in parallel.

[0048] The first load-bearing frame 1 in the embodiment of the present invention is used to bear the swing force loading of the central part of the hub, and the second load-bearing frame 2 is used to bear the centrifugal force loading of the central part of the hub; and the third load-bearing frame 3 of the inner ring load-bearing frame is arranged in parallel with the second load-bearing frame 2 of the outer ring load-bearing frame, and is used to bear the damping force of the central part of the hub. The fourth load-bearing frame 4 is provided with a rectangular slot 4-1 for avoiding the swing force loading mechanism.

[0049] In one implementation of the embodiment of the present invention, a plurality of swing parallel grooves 1-1 with the same spacing are vertically opened on each first bearing frame 1 of the outer ring bearing frame, which are used to install the swing force loading mechanism on the swing parallel grooves 1-1 by fixing bolts.

[0050] In this implementation, the swing parallel rail groove 1-1 of each first load-bearing frame 1 is fixed with a swing force loading support by bolts, and the swing force loading actuator is installed on the swing force loading support. The swing force loading angle of the swing force loading actuator is adjusted by adjusting the position of the swing force loading support on the swing parallel rail groove 1-1.

[0051] In the specific implementation of this implementation, one end of the wire rope in the swing force loading mechanism is connected to the swing force loading actuator, and the other end passes through the rectangular slot 4-1 of the fourth load-bearing frame 4 at the corresponding position and is connected to the hub central part to implement the swing force load loading; Figure 1 shown.

[0052] In one implementation of the embodiment of the present invention, a circular through hole 2-1 is opened in the middle position of each second bearing frame 2 of the outer ring bearing frame, and each circular through hole 2-1 is evenly distributed with multiple threaded holes around it, which are used to pass the centrifugal force loading mechanism through the circular through hole 2-1, and fix the centrifugal force loading mechanism to the second bearing frame 2 by bolts.

[0053] In this implementation, the third load-bearing frame 3 of the inner ring load-bearing frame is provided with upper and lower through holes 3 - 2 for the upper and lower steel cables of the centrifugal force loading mechanism at corresponding positions to pass through without interfering with the third load-bearing frame 3 .

[0054] In the specific implementation of this implementation, after the piston rod of the centrifugal force loading actuator passes through the circular through hole 2-1 of each second bearing frame 2 from the outside, the centrifugal force loading actuator is fixed to the second bearing frame 2 by a plurality of bolts evenly distributed in the circumferential direction, one end of the steel wire rope of the centrifugal force loading mechanism is connected to the centrifugal force loading actuator, and the other end is connected to the central part of the hub after passing through the hole 3-2 to implement centrifugal load loading; Figure 1 shown.

[0055] In one implementation of the embodiment of the present invention, a plurality of damping parallel grooves 3-1 with equal spacing are vertically opened on each third bearing frame 3 of the inner ring bearing frame, for installing a damping force loading mechanism on the damping parallel grooves 3-1 by fixing bolts.

[0056] In this implementation, the damping parallel rail groove 3-1 of each third bearing frame 3 is fixed with a damping force loading support by bolts, and the damping force loading actuator is installed on the damping force loading support. The damping force loading angle of the damping force loading actuator is adjusted by adjusting the position of the damping force loading support on the damping parallel rail groove 3-1.

[0057] In a specific implementation of this implementation, one end of the loading connecting rod in the damping force loading mechanism is connected to the damping force loading actuator, and the other end is connected to the hub center piece to implement damping force load loading; Figure 1 shown.

[0058] In one implementation of the embodiment of the present invention, it is considered that in the fatigue test of the central part of the main rotor hub of a heavy helicopter, the loads borne by the load-bearing device generally include centrifugal force, swing force, flapping force and damping force, etc.; wherein the centrifugal force, swing force and damping force are applied to the central part through a horizontal loading mechanism, and the flapping force is applied to the central part through a vertical loading mechanism. In order to achieve the coordinated loading requirements of the horizontal centrifugal force, swing force and damper force in the fatigue test of the central part of the 7-arm rotor hub of a heavy helicopter, the inner and outer double-layer annular load-bearing rigs designed in the embodiment of the present invention can meet the fatigue test requirements of the central part of the rotor hub of a heavy helicopter.

[0059] Since the hub central piece used for loading has 7 arms, the inner ring load-bearing frame and the outer ring load-bearing frame are arranged as a regular tetradecahedral annular structure, respectively having 7 first load-bearing frames 1, 7 second load-bearing frames 2, 7 third load-bearing frames 3 and 7 fourth load-bearing frames 4.

[0060] Based on the double-layer annular load-bearing device for the central piece of a helicopter hub provided by an embodiment of the present invention, an embodiment of the present invention further provides a loading platform for the central piece of a helicopter hub, Figure 3 The overall structural diagram of a loading platform for a helicopter hub centerpiece provided by an embodiment of the present invention, the loading platform comprises:

[0061] like Figure 1 and Figure 2 The embodiment shown provides a double-layer annular load-bearing device for the helicopter hub center piece, and a horizontal loading mechanism for loading the helicopter hub center piece. The horizontal loading mechanism in this embodiment includes: a centrifugal force loading mechanism, a swing force loading mechanism and a damping force loading mechanism.

[0062] In the embodiment of the present invention, the swing force loading mechanism realizes different swing force loading angles by moving the swing parallel rail groove 1-1 to different installation positions; the damping force loading mechanism realizes different damping force loading angles by moving the damping parallel rail groove 3-1 to different installation positions; the steel wire rope of the centrifugal force loading mechanism passes through the through hole 3-2 of the third bearing frame 3 at the corresponding position, and is connected to the centrifugal force loading actuator on the second bearing frame 2 at the corresponding position, thereby realizing centrifugal force load loading.

[0063] The embodiment of the present invention provides a double-layer annular load-bearing device and loading platform for the central part of a helicopter hub. Since the existing common welded steel frame load-bearing platform can no longer meet the large load requirements of the central part of a heavy helicopter hub in terms of load-bearing, and in view of the large load loading test requirements of the central part of a heavy helicopter hub, the embodiment of the present invention utilizes a combination of a steel frame structure and a concrete structure to form a double-layer annular load-bearing device that can be used for a 100-ton large load three-way loading test; the double-layer annular load-bearing device includes an inner ring load-bearing stand and an outer ring load-bearing stand that are concentrically arranged; the use of the double-layer annular load-bearing device can meet the centrifugal force, swing force and damper force loading of multiple arm hub central parts. The embodiment of the present invention has the following beneficial effects:

[0064] First, the structural form of the double-layer annular load-bearing device improves the connection strength, enhances the overall rigidity, and greatly improves the load-bearing capacity of the load-bearing device to meet the load loading requirements of the central part of the heavy-duty propeller hub;

[0065] Second, the use of this double-layer annular load-bearing device can truly and accurately simulate the boundary conditions and load characteristics of the helicopter hub centerpiece, filling the gap in the field of fatigue test devices for 100-ton helicopter hub centerpieces in China and improving the strength test level of my country's helicopters;

[0066] Third, the double-layer annular load-bearing structure is used to carry out fatigue tests on the central parts of heavy-duty propeller hubs. In the tests, it can withstand the coordinated loading of a large load of hundreds of tons in the fatigue tests on the central parts of heavy-duty propeller hubs. The test bench has high strength, and the three-way loads do not interfere with each other.

[0067] Fourth, the use of this double-layer annular load-bearing device can meet the centrifugal force, swing force and damper force loading of multiple arm hub central parts. The test bench has a simple structure, and its strength and rigidity can well meet the test loading requirements.

[0068] The double-layer annular load-bearing device and loading platform for the helicopter hub center piece provided by the embodiment of the present invention are schematically described below through a specific embodiment.

[0069] Example

[0070] In the fatigue test of the centerpiece of the main rotor hub of a heavy helicopter, the loads borne by the load-bearing device generally include centrifugal force, oscillating force, flapping force and damping force, etc. Among them, the centrifugal force, oscillating force and damping force are applied to the centerpiece through the horizontal loading mechanism, and the flapping force is applied to the centerpiece through the vertical loading mechanism.

[0071] In order to achieve the coordinated loading requirements of horizontal centrifugal force, swing force and damper force in the fatigue test of the central part of the 7-arm hub of a heavy helicopter, the inner and outer double-layer annular load-bearing test bench designed in the embodiment of the present invention can meet the fatigue test requirements of the central part of the heavy helicopter hub.

[0072] Reference Figures 1 to 3 As shown, this embodiment provides a loading platform for the central part of a helicopter hub, the loading platform includes a double-layer annular load-bearing device and various horizontal loading mechanisms; wherein the double-layer annular load-bearing device is an inner and outer ring-shaped load-bearing platform structure with fourteen regular faces formed by reinforced concrete, and the angle occupied by each face is evenly divided, each of which is 25.71 degrees. The inner and outer load-bearing platforms are respectively composed of concrete, square steel, and steel bars interwoven with each other.

[0073] The outer ring load-bearing frame of the double-layer annular load-bearing device is formed by alternating the first load-bearing frame 1 and the second load-bearing frame 2 of different structures, which are used to apply centrifugal force and swing force; it has 7 arms, each of which is loaded with centrifugal force and swing force. The inner ring load-bearing frame of the double-layer annular load-bearing device is formed by alternating the third load-bearing frame 3 and the fourth load-bearing frame 4 of different structures, which are used to apply damping force; it has 7 arms, each of which is loaded with damping force.

[0074] like Figures 1 to 3 As shown, seven of the fourteen faces of the outer ring bearing frame are arranged at intervals as the first bearing frame 1 of the same structure. The first bearing frame 1 is provided with a plurality of swing parallel rail grooves 1-1 with the same spacing in the vertical direction, and the swing force loading mechanism can be installed on the swing parallel rail groove 1-1 by fixing bolts. In addition, according to the loading requirements, the swing force loading mechanism can be moved to different installation positions on the swing parallel rail groove 1-1 to achieve different swing force loading angles.

[0075] like Figures 1 to 3As shown, seven of the fourteen faces of the outer ring load-bearing frame are arranged at intervals to form a second load-bearing frame 2 of the same structure. A circular through hole 2-1 is opened in the middle position of the second load-bearing frame 2. Each circular through hole 2-1 is evenly distributed around a plurality of threaded holes for passing a centrifugal force loading mechanism through the circular through hole 2-1, and fixing the centrifugal force loading mechanism to the second load-bearing frame 2 by bolts.

[0076] like Figures 1 to 3 As shown, seven of the fourteen faces of the inner ring bearing frame are arranged at intervals to form a third bearing frame 3 of the same structure. A plurality of damping parallel grooves 3-1 with the same spacing are vertically opened on the third bearing frame 3. The damper force loading mechanism is installed on the damping parallel groove 3-1 by fixing bolts. The damper force loading angle can be changed at the installation position of the damping parallel groove 3-1 according to the loading requirements to achieve different loading angle requirements.

[0077] Two waist-shaped through holes 3-2 are respectively opened on the damping parallel rail groove 3-1 to ensure that the steel wire rope is connected to the centrifugal force loading mechanism and the hub central part.

[0078] like Figures 1 to 3 As shown, the other seven surfaces arranged at intervals among the fourteen surfaces of the inner ring load-bearing frame are fourth load-bearing frames 4 of the same structure. A rectangular groove 4-1 is opened on each of the fourth load-bearing frames 4 to ensure that the wire rope connects the swing force loading mechanism and the hub central part.

[0079] Based on the double-layer annular load-bearing device of the above structure, such as Figure 3 As shown, first, the swing force loading support is fixed to the swing parallel track groove 1-1 by bolts, the actuator is installed on the swing force loading support, and the angle of the actuator is adjusted to meet the swing force loading angle requirements of the fatigue test. One end of the wire rope is connected to the swing force loading actuator, and the other end passes through the rectangular slot 4-1 and is connected to the hub center piece to implement the swing force load loading.

[0080] Then, after the piston rod of the centrifugal force loading actuator passes through the circular through hole 2-1 from the outside, the centrifugal force loading actuator is fixed to the second load-bearing frame 2 by multiple bolts evenly distributed circumferentially. One end of the steel wire rope of the centrifugal force loading mechanism is connected to the centrifugal force loading actuator, and the other end is connected to the central part of the hub after passing through the hole 3-2 to implement centrifugal load loading.

[0081] Finally, fix the damper force loading support on the damping parallel rail groove 3-1 with bolts, install the actuator on the damper force loading support, adjust the angle of the actuator to meet the damper force loading angle requirements of the fatigue test, connect one end of the loading connecting rod to the damper force loading actuator, and connect the other end to the hub center piece to implement the damper force load loading.

[0082] In summary, the inner and outer double ring fourteen-sided annular load-bearing device proposed in the embodiment of the present invention solves the centrifugal force, swing force and damper force loading problems of the seven arms of the central part of the heavy helicopter hub, and at the same time improves the versatility of the load-bearing frame. The strength and stiffness of the load-bearing frame can effectively guarantee the requirements of the 100-ton large load fatigue test, providing a basis for the fatigue life of the central part of the heavy helicopter hub.

[0083] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A double-layer annular load-bearing device for a helicopter hub centerpiece, characterized in that: include: Concentrically arranged inner ring load-bearing frame and outer ring load-bearing frame; The inner ring load-bearing frame and the outer ring load-bearing frame are respectively manufactured by reinforced concrete casting, and both the inner ring load-bearing frame and the outer ring load-bearing frame are arranged as regular polyhedral annular structures. The outer ring load-bearing frame is formed by surrounding a first load-bearing frame (1) and a second load-bearing frame (2) arranged alternately, and the inner ring load-bearing frame is formed by surrounding a third load-bearing frame (3) and a fourth load-bearing frame (4) arranged alternately; and the load-bearing frames at corresponding positions of the inner ring load-bearing frame and the outer ring load-bearing frame are arranged in parallel; The first load-bearing frame (1) is used to bear the swing force loading of the central part of the hub, and the second load-bearing frame (2) is used to bear the centrifugal force loading of the central part of the hub; The third load-bearing frame (3) of the inner ring load-bearing frame is arranged in parallel with the second load-bearing frame (2) of the outer ring load-bearing frame, and is used to bear the damping force of the hub central part. The fourth load-bearing frame (4) is provided with a rectangular slot (4-1) for avoiding the swing force loading mechanism.

2. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 1, characterized in that: A plurality of oscillating parallel rail grooves (1-1) with the same spacing are vertically provided on each first bearing frame (1) of the outer ring bearing frame, and are used for installing a oscillating force loading mechanism on the oscillating parallel rail grooves (1-1) by means of fixing bolts.

3. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 2, characterized in that: The sway parallel track groove (1-1) of each first load-bearing frame (1) is fixedly mounted with a sway force loading support by means of bolts, and a sway force loading actuator is mounted on the sway force loading support, and the sway force loading angle of the sway force loading actuator is adjusted by adjusting the position of the sway force loading support on the sway parallel track groove (1-1); One end of the wire rope in the swing force loading mechanism is connected to the swing force loading actuator, and the other end passes through the rectangular slot (4-1) of the fourth load-bearing frame (4) at the corresponding position and is connected to the hub central part to implement swing force load loading.

4. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 1, characterized in that: A circular through hole (2-1) is formed in the middle of each second bearing frame (2) of the outer ring bearing frame, and a plurality of threaded holes are evenly distributed around each circular through hole (2-1) for passing a centrifugal force loading mechanism through the circular through hole (2-1) and fixing the centrifugal force loading mechanism to the second bearing frame (2) by bolts; The third load-bearing frame (3) of the inner ring load-bearing frame is provided with upper and lower through holes (3-2) for passing the upper and lower steel cables of the centrifugal force loading mechanism at corresponding positions without interfering with the third load-bearing frame (3).

5. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 4, characterized in that: After the piston rod of the centrifugal force loading actuator passes through the circular through hole (2-1) of each second load-bearing frame (2) from the outside, the centrifugal force loading actuator is fixed to the second load-bearing frame (2) by means of a plurality of bolts evenly distributed in the circumferential direction; one end of the steel wire rope of the centrifugal force loading mechanism is connected to the centrifugal force loading actuator, and the other end is connected to the hub central component after passing through the hole (3-2) to implement centrifugal force load loading.

6. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 1, characterized in that: A plurality of damping parallel track grooves (3-1) with the same spacing are vertically provided on each third load-bearing frame (3) of the inner ring load-bearing frame, and are used to install a damping force loading mechanism on the damping parallel track grooves (3-1) by means of fixing bolts.

7. The double-layer annular load-bearing device for the helicopter hub centerpiece according to claim 6, characterized in that: The damping parallel track groove (3-1) of each third load-bearing frame (3) is fixedly mounted with a damping force loading support by means of bolts, and a damping force loading actuator is mounted on the damping force loading support, and the damping force loading angle of the damping force loading actuator is adjusted by adjusting the position of the damping force loading support on the damping parallel track groove (3-1); One end of the loading connecting rod in the damping force loading mechanism is connected to the damping force loading actuator, and the other end is connected to the hub center piece to implement damping force load loading.

8. The double-layer annular load-bearing device for a helicopter hub centerpiece according to any one of claims 1 to 7, characterized in that: The hub centerpiece for loading has 7 arms. The inner ring load-bearing frame and the outer ring load-bearing frame are arranged as a regular tetradecahedral annular structure, and respectively have 7 first load-bearing frames (1), 7 second load-bearing frames (2), 7 third load-bearing frames (3) and 7 fourth load-bearing frames (4).

9. A loading platform for a helicopter hub centerpiece, characterized in that: include: A double-layer annular load-bearing device for a helicopter hub center piece according to any one of claims 1 to 8, and a horizontal loading mechanism for loading a helicopter hub center piece; Wherein, the horizontal loading mechanism includes: a centrifugal force loading mechanism, a swing force loading mechanism and a damping force loading mechanism.

10. The loading platform for the helicopter hub centerpiece according to claim 9, characterized in that: The shimmy force loading mechanism realizes different shimmy force loading angles by moving to different installation positions in the shimmy parallel track groove (1-1); The damping force loading mechanism realizes different damping force loading angles by moving to different installation positions in the damping parallel track groove (3-1); The steel wire rope of the centrifugal force loading mechanism passes through the through hole (3-2) of the third load-bearing frame (3) at the corresponding position and is connected to the centrifugal force loading actuator on the second load-bearing frame (2) at the corresponding position, thereby realizing centrifugal force load loading.

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