Heavy-duty helicopter six-support-arm rotor system for rotor model wind tunnel test

Abstract

The invention discloses a heavy-duty helicopter six-support-arm rotor wing system for a rotor wing model wind tunnel test, and belongs to the field of heavy-duty helicopter rotor wing systems. The device comprises a propeller hub central part assembly, a propeller clamp assembly, an automatic inclinator assembly, a damper, a variable-pitch rocker arm, a variable-pitch pull rod and a rotating part, an upward-swinging limiting stopper is arranged at the top of a propeller hub central part, a downward-swinging limiting stopper is installed on a rotor shaft and arranged at the bottom of the propeller hub central part, the propeller clamp assembly is installed on the propeller hub central part, and the automatic inclinator assembly is installed on the propeller hub central part. The rotor shaft located below the downward swing limiter is sleeved with an automatic inclinator assembly, the two ends of the damper are connected with the propeller clamp assembly and the propeller hub center piece respectively, the variable-pitch rocker arm is installed on the propeller clamp assembly, and the two ends of the variable-pitch pull rod are connected with the variable-pitch rocker arm and the automatic inclinator assembly respectively. The two ends of the belt rotating piece are connected with the upward swing limiting stopper and the automatic inclinator assembly respectively. The requirement of heavy taking-off weight of the heavy helicopter is met, a rotor wing model test can be carried out in a wind tunnel, and the safety and reliability of a rotor wing system are improved.

Description

Technical Field

[0001] The invention relates to a heavy helicopter six-arm rotor system for rotor model wind tunnel testing, belonging to the field of heavy helicopter rotor systems. Background Art

[0002] Heavy-duty helicopters can not only transport large military equipment, carry out rapid deployment of troops, supply combat materials such as weapons and ammunition, and conduct combat search and rescue, but also evacuate trapped or wounded personnel in major disaster relief operations, playing a significant role in the military and civilian fields. As the core component of a helicopter, the rotor system can directly affect the aerodynamic performance, reliability, and flight quality of the helicopter, and is the technical core of helicopter research and development. The rotor model wind tunnel test has always been an important means to study rotor performance, aerodynamic characteristics, and aerodynamic interference characteristics, and to provide quantitative aerodynamic data for helicopter model design. However, most conventional helicopter rotor systems currently have four-arm or five-arm structures, which cannot meet the requirements of heavy-duty helicopters for large take-off weights. At the same time, due to the complex structure and large size, rotor model tests cannot be carried out in wind tunnels.

[0003] Therefore, it is urgent to propose a heavy helicopter six-arm rotor system for rotor model wind tunnel testing to solve the above technical problems. Summary of the invention

[0004] The purpose of the present invention is to provide a heavy helicopter six-arm rotor system for rotor model wind tunnel testing, which meets the requirement of heavy helicopter take-off weight and can perform rotor model testing in a wind tunnel. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0005] The technical solution of the present invention: A six-arm rotor system for a heavy helicopter used for a rotor model wind tunnel test comprises a hub central component assembly, a propeller clamp assembly, an automatic tilt device assembly, a damper, a pitch rocker arm, a pitch pull rod and a belt rotating member, wherein the hub central component assembly comprises a hub central component, an upswing limiter, a downswing limiter and a rotor shaft, the rotor shaft is mounted with the hub central component, the top of the hub central component is provided with an upswing limiter, the downswing limiter is mounted on the rotor shaft and arranged at the bottom of the hub central component, the hub central component, the upswing limiter, the downswing limiter and the rotor shaft are arranged coaxially, the propeller clamp assembly is mounted on the hub central component, the automatic tilt device assembly is sleeved on the rotor shaft below the downswing limiter, the two ends of the damper are respectively connected to the propeller clamp assembly and the hub central component, the pitch rocker arm is mounted on the propeller clamp assembly, the two ends of the pitch pull rod are respectively connected to the pitch rocker arm and the automatic tilt device assembly, and the two ends of the belt rotating member are respectively connected to the downswing limiter and the automatic tilt device assembly.

[0006] Preferably: the propeller clamp assembly includes a blade clamp, an elastic bearing and a limit stop block, one side of the blade clamp is a blade support arm, and the other side of the blade clamp is a U-shaped support arm, limit stops are arranged on the top and bottom of the U-shaped support arm, and an elastic bearing is clamped in the middle of the U-shaped support arm, and the elastic bearing and the limit stop block are fixed on the U-shaped support arm through the propeller clamp fixing bolts, and the hub central part has a plurality of connecting clamp arms, which are sleeved in the U-shaped support arm and are clamped and connected to the elastic bearing through the elastic bearing connecting bolts.

[0007] Preferably: the automatic tilt mechanism assembly includes a rotating ring, a rotating ring pressure cover, a non-rotating ring pressure cover, a retaining ring, a guide cylinder, a ball joint, a thin-walled bearing and a non-rotating ring, the guide cylinder is sleeved on the rotor shaft, the outer side of the guide cylinder is slidingly sleeved with a ball joint, the non-rotating ring pressure cover is fixedly installed on the top of the non-rotating ring, the inner sides of the non-rotating ring pressure cover and the non-rotating ring are both matched with the outer spherical surface of the ball joint, the rotating ring pressure cover is installed on the top of the rotating ring, the inner side of the rotating ring is installed on the outer side of the non-rotating ring through a thin-walled bearing, and retaining rings are also provided on the outer sides of the top and bottom of the guide cylinder.

[0008] Preferably, the pitch-changing rocker arm is connected to the inner wall surface of the blade clamp by bolts.

[0009] Preferably, the lower end of the belt rotating member is connected to the rotating ring via bolts.

[0010] Preferably, it also includes an anti-twist arm, and both ends of the anti-twist arm are respectively fixedly connected to the support arm of the non-rotating ring and the bottom end of the guide cylinder.

[0011] The present invention has the following beneficial effects: 1. The present invention adopts a six-arm hub structure, which can meet the requirements of heavy helicopters with large take-off weight and high transportation efficiency.

[0012] 2. The present invention adopts elastic bearings to replace the flapping hinge, swing hinge and pitch hinge of the traditional articulated rotor, which reduces the structural size and the number of parts and is suitable for wind tunnel tests of heavy helicopter rotor models.

[0013] 3. The present invention designs an upward swing limiter and a downward swing limiter on the hub, which provide limit protection for the flapping motion of the blades and improve the safety and reliability of the rotor system. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a stereoscopic view of a six-arm rotor system of a heavy helicopter used for rotor model wind tunnel testing; Figure 2 This is the matching installation drawing of the hub centerpiece assembly; Figure 3 is a schematic diagram of the structure of the paddle clamp assembly; Figure 4 is an exploded view of the paddle clamp assembly; Figure 5 is a perspective view of the paddle clamp assembly; Figure 6 It is the matching installation drawing of the automatic tilter assembly; Figure 7 This is the installation diagram of the paddle clamp assembly and the connecting clamp arm; Figure 8 This is the installation diagram of the swivel and rotating ring.

[0015] In the figure: 1-1-hub central piece assembly, 1-2-propeller clamp assembly, 1-3-automatic tilt device assembly, 1-hub central piece, 2-upward swing limiter, 3-downward swing limiter, 4-rotor shaft, 5-blade clamp, 6-elastic bearing, 7-limit block, 8-damper, 9-pitch rocker arm, 10-pitch pull rod, 11-swivel piece, 12-anti-torsion arm, 13-rotating ring, 14-rotating ring pressure cover, 15-non-rotating ring pressure cover, 16-retaining ring, 17-guide cylinder, 18-ball joint, 19-thin-wall bearing, 20-non-rotating ring, 101-connecting clamp arm, 501-U-shaped support arm, 502-propeller clamp fixing bolt, 601-elastic bearing connecting bolt. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0017] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: a fixed connection is selected as a welding connection, and a detachable connection is selected as a hinge connection.

[0018] Example: Combination Figure 1-Figure 8 The present embodiment is described. A heavy helicopter six-arm rotor system for rotor model wind tunnel testing in the present embodiment includes a hub center component assembly 1-1, a blade clamp assembly 1-2, an automatic tilt device assembly 1-3, a damper 8, a pitch rocker arm 9, a pitch pull rod 10 and a belt rotating component 11; The hub center piece assembly 1-1 comprises a hub center piece 1, an upward swing limiter 2, a downward swing limiter 3 and a rotor shaft 4. The hub center piece 1 is mounted on the rotor shaft 4 and is positioned with the rotor shaft 4 through a spline groove to transmit the torque of the rotor shaft 4 and the centrifugal force from the blades, and to provide an installation interface for the upward swing limiter 2 and the downward swing limiter 3. An upward swing limiter 2 is arranged on the top of the hub center piece 1. The upward swing limiter 2 and the hub center piece 1 are connected to the rotor shaft 4 through hinged hole bolts to prevent the blades from excessively swinging upward when they suddenly stop. The downward swing limiter 3 is mounted on the rotor shaft 4 through bolts and is arranged at the bottom of the hub center piece 1 to prevent the blades from excessively swinging downward under the action of their own weight when they suddenly stop. The hub center piece 1, the upward swing limiter 2, the downward swing limiter 3 and the rotor shaft 4 are arranged coaxially; The propeller clamp assembly 1-2 is mounted on the hub center piece 1, and the automatic tilt device assembly 1-3 is mounted on the rotor shaft 4 below the downswing limiter 3; The two ends of the damper 8 are respectively connected to the propeller clamp assembly 1-2 and the hub central part 1. Furthermore, one end of the damper 8 is connected to the propeller hub central part 1 through a rod end joint bearing and a bolt, and the other end is connected to the blade clamp 5 through a rod end joint bearing and a bolt, so as to avoid causing ground resonance and air resonance.

[0019] The variable pitch rocker arm 9 is installed on the blade clamp assembly 1-2. Furthermore, the variable pitch rocker arm 9 is connected to the inner wall surface of the blade clamp 5 by bolts to transmit the rotor control force.

[0020] The two ends of the pitch-changing rod 10 are respectively connected to the pitch-changing rocker arm 9 and the automatic tilt device assembly 1-3. Furthermore, one end of the pitch-changing rod 10 is connected to the rotating ring 13 through a rod end joint bearing, and the other end is connected to the pitch-changing rocker arm 9 through a rod end joint bearing, thereby realizing the pitch-changing movement of the blade.

[0021] The two ends of the belt swivel 11 are respectively connected to the downswing limiter 3 and the automatic tilt device assembly 1-3. Furthermore, the upper end of the belt swivel 11 is fixedly connected to the side of the downswing limiter 3 by bolts, and the lower end of the belt swivel 11 is connected to the rotating ring 13 by bolts to realize the synchronous rotation of the rotating ring 13 and the rotor shaft 4.

[0022] The blade clamp assembly 1-2 includes a blade clamp 5, an elastic bearing 6 and a limit stopper 7. One side of the blade clamp 5 is a blade support arm, and the other side of the blade clamp 5 is a U-shaped support arm 501. The top and bottom of the U-shaped support arm 501 are both provided with limit stoppers 7. The middle of the U-shaped support arm 501 is clamped with an elastic bearing 6. One end of the elastic bearing 6 and the limit stopper 7 are fixed to the U-shaped support arm 501 through a blade clamp fixing bolt 502. The hub central component 1 has a plurality of connecting clamp arms 101, such as Figure 1 As shown, the number of connecting clamp arms 101 in this embodiment is 6, which are arranged in a uniform array around the circumference. The connecting clamp arms 101 are sleeved in the U-shaped support arm 501, and are connected to the other end of the elastic bearing 6 by means of a groove clamping through an elastic bearing connecting bolt 601. The elastic bearing 6 is made of rubber and metal spacers that are vulcanized and bonded, and the pitch change movement of the blade is achieved and the blade load is transmitted through the shear elastic deformation of the rubber.

[0023] The automatic tilt mechanism assembly 1-3 includes a rotating ring 13, a rotating ring pressure cover 14, a non-rotating ring pressure cover 15, a retaining ring 16, a guide cylinder 17, a ball joint 18, a thin-walled bearing 19 and a non-rotating ring 20. The guide cylinder 17 is sleeved on the rotor shaft 4. Furthermore, the guide cylinder 17 is inserted from the bottom end of the rotor shaft 4 to cooperate with the rotor shaft 4. The outer side of the guide cylinder 17 is slidably sleeved with a ball joint 18. The ball joint 18 is inserted from the top end of the guide cylinder 17 and cooperates with the outer surface of the guide cylinder 17 through a sliding key. The non-rotating ring pressure cover 15 is fixedly installed on the top of the non-rotating ring 20 by means of hinged hole bolts. The inner sides of the rotating ring cover 15 and the non-rotating ring 20 are matched with the outer spherical surface of the ball joint 18. The rotating ring cover 14 is installed on the top of the rotating ring 13. The inner side of the rotating ring 13 is installed on the outer side of the non-rotating ring 20 through a thin-walled bearing 19. The outer ring of the thin-walled bearing 19 cooperates with the inner surface of the rotating ring 13 to achieve relative rotation. A retaining ring 16 is also provided on the outer side of the top and bottom of the guide cylinder 17. The retaining ring 16 is inserted from the top of the guide cylinder 17 and is respectively arranged at the top and bottom of the guide cylinder 17 to prevent the automatic recliner assembly 1-3 from moving beyond the limit and play a protective role.

[0024] The ball joint 18 can slide up and down along the outer surface of the guide tube 17 to realize the collective pitch control of the rotor. The rotating ring 13 and the non-rotating ring 20 can deflect together around the center of the ball joint 18 to realize the cyclic pitch control of the rotor. The rotating ring 13 can rotate relative to the non-rotating ring 20 and maintain the same plane angle with each other.

[0025] It also includes an anti-torsion arm 12, both ends of which are fixedly connected to the support arm of the non-rotating ring 20 and the bottom end of the guide cylinder 17 respectively. Furthermore, the upper end of the anti-torsion arm 12 is connected to the support arm of the non-rotating ring 20 by bolts, and the lower end of the anti-torsion arm 12 is fixedly connected to the bottom end of the guide cylinder 17 by bolts. When the non-rotating ring 20 moves around the ball joint 18, the torque is transmitted to the guide cylinder 17 through the anti-torsion arm 12, thereby limiting the rotation of the non-rotating ring 20 around the rotor axis without affecting the cyclic pitch change.

[0026] This embodiment adopts a six-arm hub structure, which can meet the requirements of heavy helicopters with large takeoff weight and high transportation efficiency; elastic bearings are used to replace the flapping hinges, swing hinges and variable pitch hinges of traditional articulated rotors, which reduces the structural size and the number of parts, and is suitable for wind tunnel tests of heavy helicopter rotor models. By designing an upward swing limiter and a downward swing limiter on the hub, limit protection is provided for the blade flapping motion, improving the safety and reliability of the entire rotor system.

[0027] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities based on the mathematical knowledge of arrangement and combination. Therefore, the present invention will no longer describe the technical solutions after arrangement and combination one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present invention.

[0028] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, 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 heavy helicopter six-arm rotor system for rotor model wind tunnel testing, characterized in that: The invention comprises a hub central component assembly (1-1), a blade clamp assembly (1-2), an automatic tilt device assembly (1-3), a damper (8), a pitch rocker arm (9), a pitch pull rod (10) and a rotating member (11). The hub central component assembly (1-1) comprises a hub central component (1), an upward swing limiter (2), a downward swing limiter (3) and a rotor shaft (4). The hub central component (1) is mounted on the rotor shaft (4). The upward swing limiter (2) is arranged on the top of the hub central component (1). The downward swing limiter (3) is mounted on the rotor shaft (4) and arranged at the bottom of the hub central component (1). The rotor shaft (4) is coaxially arranged with a positioner (2), a downswing limiter (3) and a rotor shaft (4); a propeller clamp assembly (1-2) is mounted on a hub central component (1); an automatic tilting device assembly (1-3) is mounted on the rotor shaft (4) below the downswing limiter (3); two ends of a damper (8) are respectively connected to the propeller clamp assembly (1-2) and the hub central component (1); a pitch-changing rocker arm (9) is mounted on the propeller clamp assembly (1-2); two ends of a pitch-changing pull rod (10) are respectively connected to the pitch-changing rocker arm (9) and the automatic tilting device assembly (1-3); and two ends of a rotating member (11) are respectively connected to the downswing limiter (3) and the automatic tilting device assembly (1-3).

2. The heavy helicopter six-arm rotor system for rotor model wind tunnel testing according to claim 1, characterized in that: The blade clamp assembly (1-2) comprises a blade clamp (5), an elastic bearing (6) and a limit stopper (7); one side of the blade clamp (5) is a blade support arm; the other side of the blade clamp (5) is a U-shaped support arm (501); the top and bottom of the U-shaped support arm (501) are both provided with limit stoppers (7); the middle of the U-shaped support arm (501) is clamped with an elastic bearing (6); the elastic bearing (6) and the limit stopper (7) are fixed to the U-shaped support arm (501) through blade clamp fixing bolts (502); the hub central component (1) has a plurality of connecting clamp arms (101); the connecting clamp arms (101) are sleeved in the U-shaped support arm (501) and are clamped and connected to the elastic bearing (6) through elastic bearing connecting bolts (601).

3. The heavy helicopter six-arm rotor system for rotor model wind tunnel testing according to claim 2, characterized in that: The automatic tilt mechanism assembly (1-3) comprises a rotating ring (13), a rotating ring pressure cover (14), a non-rotating ring pressure cover (15), a retaining ring (16), a guide tube (17), a ball joint (18), a thin-walled bearing (19) and a non-rotating ring (20). The guide tube (17) is sleeved on the rotor shaft (4). The outer side of the guide tube (17) is slidably sleeved with a ball joint (18). The non-rotating ring pressure cover (15) is fixedly mounted on the top of the non-rotating ring (20). The inner sides of the non-rotating ring pressure cover (15) and the non-rotating ring (20) are both matched with the outer spherical surface of the ball joint (18). The rotating ring pressure cover (14) is mounted on the top of the rotating ring (13). The inner side of the rotating ring (13) is mounted on the outer side of the non-rotating ring (20) via the thin-walled bearing (19). Retaining rings (16) are also arranged on the outer sides of the top and bottom of the guide tube (17).

4. The heavy helicopter six-arm rotor system for rotor model wind tunnel testing according to claim 3, characterized in that: The pitch-changing rocker arm (9) is connected to the inner wall surface of the blade clamp (5) via bolts.

5. The heavy helicopter six-arm rotor system for rotor model wind tunnel testing according to claim 4, characterized in that: The lower end of the belt rotating member (11) is connected to the rotating ring (13) via bolts.

6. The heavy helicopter six-arm rotor system for rotor model wind tunnel testing according to claim 5, characterized in that: It also includes an anti-twist arm (12), the two ends of which are respectively fixedly connected to the support arm of the non-rotating ring (20) and the bottom end of the guide cylinder (17).

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