阅读说明：本技术 一种直升机主桨毂安装工装及使用方法 (Helicopter main hub mounting tool and using method ) 是由 毛永杰 项洪涛 黄康华 聂发兴 苏贵鸿 徐志鹏 于 2021-07-30 设计创作，主要内容包括：本发明属于直升机总装集成装配技术领域,特别涉及一种直升机主桨毂安装工装及使用方法,包括悬挂起吊环、旋转销轴、第一旋转销轴孔、第二旋转销轴孔、杠杆架、承力骨架、桨毂连接点,承力骨架固定连接在杠杆架底部,桨毂连接点的数量与直升机主桨毂支臂数量匹配,桨毂连接点连接在承力骨架底部,且桨毂连接点位于同一平面上,杠杆架上设置有第一旋转销轴孔、第二旋转销轴孔,第一旋转销轴孔的几何中心位于承力骨架几何中心上方,第一旋转销轴孔与第二旋转销轴孔几何中心的连线位于桨毂连接点所组成平面图形的对称平面内,且第一旋转销轴孔与第二旋转销轴孔几何中心的连线与桨毂连接点所组成的平面图形平行,与现有技术相比,本发明实现高精度花键轴孔对接的核心是消除轴孔角度偏差,保证待装配主桨毂起吊后在空中自动调整好装配位姿、保证孔轴中线同心。(The invention belongs to the technical field of helicopter final assembly integrated assembly, and particularly relates to a mounting tool and a using method for a main propeller hub of a helicopter, which comprises a suspension lifting ring, a rotating pin shaft, a first rotating pin shaft hole, a second rotating pin shaft hole, a lever frame, a bearing framework and propeller hub connecting points, wherein the bearing framework is fixedly connected to the bottom of the lever frame, the quantity of the propeller hub connecting points is matched with the quantity of support arms of the main propeller hub of the helicopter, the propeller hub connecting points are connected to the bottom of the bearing framework, the propeller hub connecting points are positioned on the same plane, the lever frame is provided with the first rotating pin shaft hole and the second rotating pin shaft hole, the geometric center of the first rotating pin shaft hole is positioned above the geometric center of the bearing framework, the connecting line of the geometric centers of the first rotating pin shaft hole and the second rotating pin shaft hole is positioned in the symmetrical plane of a plane figure formed by the propeller hub connecting points, and the connecting line of the geometric centers of the first rotating pin shaft hole and the second rotating pin shaft hole is parallel to the plane figure formed by the propeller hub connecting points, compared with the prior art, the key for realizing the high-precision spline shaft hole butt joint is to eliminate the angle deviation of the shaft hole, ensure that the assembly pose is automatically adjusted in the air after the main propeller hub to be assembled is lifted, and ensure that the center lines of the shaft holes are concentric.)

1. The utility model provides a helicopter owner propeller hub installation frock which characterized in that: comprises a rotary pin shaft (2), a first rotary pin shaft hole (3), a second rotary pin shaft hole (4), a lever frame (5), a bearing framework (6) and a hub connection point (7), wherein the bearing framework (6) is fixedly connected to the bottom of the lever frame (5), the hub connection point (7) is connected to the bottom of the bearing framework (6), the number of the hub connection points (7) is matched with the number of the main hub support arms of the helicopter, all the hub connection points (7) are positioned on the same plane, the lever frame (5) is provided with a first rotary pin shaft hole (3) and a second rotary pin shaft hole (4), the geometric center of the first rotary pin shaft hole (3) is positioned above the geometric center of the bearing framework (6), and the connecting line of the geometric centers of the first rotary pin shaft hole (3) and the second rotary pin shaft hole (4) is positioned in the symmetrical plane of the plane figure formed by the hub connection points (7), and the connecting line of the geometric centers of the first rotating pin hole (3) and the second rotating pin hole (4) is parallel to the plane figure formed by the connecting points (7) of the propeller hubs.

2. The helicopter main hub installation tool of claim 1, characterized in that: the hanging ring is characterized by further comprising a hanging ring (1), wherein the hanging ring (1) is hinged to a first rotating pin shaft hole (3) or a second rotating pin shaft hole (4) through a rotating pin shaft (2) to form a shaft hole rotating pair.

3. The helicopter main hub installation tool of claim 1, characterized in that: the number of the hub connecting points (7) is more than three, and the specific number is determined according to the number of the helicopter main hub support arms.

4. The helicopter main hub installation tool of claim 1, characterized in that: the length of a connecting line of the geometric centers of the first rotating pin shaft hole (3) and the second rotating pin shaft hole (4) is L.

5. The helicopter main hub installation tool of claim 4, characterized in that: the method for determining the length L of the connecting line of the geometric centers of the first rotating pin shaft hole (3) and the second rotating pin shaft hole (4) comprises the steps of measuring the gravity center position of a main hub to be installed by using a gravity center measuring system in advance, calculating the distance H from the gravity center of the main hub to be installed to the geometric center of the first rotating pin shaft hole (3), and calculating the length L of the connecting line of the geometric centers of the first rotating pin shaft hole (3) and the second rotating pin shaft hole (4) according to the formula L which is H tan theta, wherein theta is the forward inclination angle of a rotor shaft.

6. The helicopter main hub installation tool of claim 1, characterized in that: the bearing framework (6) is a steel pipe.

7. The helicopter main hub installation tool of claim 2, characterized in that: be bronze bush is all installed to first rotatory key shaft hole (3), second rotatory key shaft hole (4) inside.

8. The use method of the helicopter main hub installation tool according to any one of claims 1 to 7, characterized by comprising the following steps: the method comprises the following steps:

1) the suspension hoisting ring (1) and the rotating pin shaft (2) are arranged in a first rotating pin shaft hole (3), and the propeller hub connecting points (7) are correspondingly connected with the main propeller hub supporting arms respectively to ensure firmness;

2) a hoisting ring (1) is hung, the main propeller hub is stably hoisted, the levelness of the main propeller hub is corrected by a quadrant instrument, and the levelness of the main propeller hub is ensured;

3) putting down the main propeller hub, detaching the suspension lifting ring (1) and the rotating pin shaft (2), loading the detached suspension lifting ring and the rotating pin shaft into a second rotating pin shaft hole (4), stably lifting the main propeller hub, placing a quadrant instrument along the connecting line direction of the geometric centers of the first rotating pin shaft hole (3) and the second rotating pin shaft hole (4), measuring the aerial inclination angle of the main propeller hub, and checking that the aerial inclination angle of the main propeller hub is consistent with the forward inclination angle theta of the rotor shaft;

4) and (3) hoisting the main hub to a position right above the rotor shaft by using a helicopter main hub installation tool, descending the main hub to slowly approach the rotor shaft after the main hub is stable in the air, aligning the spline and lacking teeth, installing the main hub in place along the direction of a forward rake angle theta of the rotor shaft in a clockwise manner, and then finely adjusting and fastening to complete the butt joint installation of the main hub and the rotor shaft.

Technical Field

The invention belongs to the technical field of helicopter final assembly integrated assembly, and particularly relates to a mounting tool for a main hub of a helicopter and a using method of the mounting tool.

Background

The main rotor is a key component of the helicopter, not only provides lift force and advancing force for the helicopter, but also provides longitudinal and transverse operating moments of the helicopter, and the main rotor and the tail rotor jointly act to realize course operation of the helicopter. The basic structural form of the main rotor is that a plurality of blades are connected with a main rotor hub, the main rotor hub is matched with a rotor shaft external spline through a central internal spline of the main rotor hub, the main rotor hub belongs to a typical spline shaft hole assembly structure, a rotor shaft extends out of the top of a main speed reducer and is used as an output shaft of the main speed reducer to drive the main rotor hub to rotate, in order to avoid that a body is in an overlarge negative attack angle state at a high speed, the axis of the rotor can be forwards inclined by an angle relative to the vertical line of the horizontal axis of the body, and the angle is called the forward inclination angle of the rotor shaft, and is shown in figure 1.

The technical difficulties faced are:

because the rotor shaft has a forward inclination angle (namely the rotor shaft forward inclination angle), and the main hub is in a horizontal state and the center of the hub is vertical to the ground when being hoisted conventionally, in the process of assembling and butting the main hub and the rotor shaft, the center of the main hub and the center line of the rotor shaft are not coaxial to generate angle deviation, the deviation value is the rotor shaft forward inclination angle, meanwhile, the high-precision spline fit relation, the larger weight of the hub and the top operation mode of the machine body further increase the assembling and butting difficulty, the spline shaft hole is easy to block and wedge, the assembling cannot be continued, the rotor shaft or the main hub can be seriously damaged by the spline fit, and the initial damage easily forms an initial fatigue source under the flight load action of high stress level, so that the fatigue fracture of components is caused, and the flight safety is seriously influenced;

in conclusion, the key for realizing the high-precision spline shaft hole butt joint is to eliminate the angle deviation of the shaft hole, ensure that the assembly pose is automatically adjusted in the air after the main propeller hub to be assembled is lifted, and ensure that the central lines of the shaft holes are concentric, which is the faced technical difficulty.

Disclosure of Invention

The purpose of the invention is as follows: the helicopter main hub mounting tool and the using method are provided to solve the problems in the prior art.

The technical scheme of the invention is as follows:

a helicopter main hub installation tool comprises a suspension lifting ring, a rotating pin shaft, a first rotating pin shaft hole, a second rotating pin shaft hole, a lever frame, a bearing framework and a hub connection point, the bearing framework is fixedly connected to the bottom of the lever frame, the hub connection points are connected to the bottom of the bearing framework, the number of the hub connection points is matched with the number of the main hub support arms of the helicopter, and all the propeller hub connection points are positioned on the same plane, the lever frame is provided with a first rotating pin shaft hole and a second rotating pin shaft hole, the geometric center of the first rotating pin shaft hole is positioned above the geometric center of the bearing framework, the connecting line of the geometric centers of the first rotating pin shaft hole and the second rotating pin shaft hole is positioned in the symmetrical plane of a plane figure formed by connecting points of the propeller hubs, and the connecting line of the geometric centers of the first rotating pin shaft hole and the second rotating pin shaft hole is parallel to a plane figure formed by connecting points of the propeller hubs.

And the suspension lifting ring is hinged on the first rotating pin shaft hole or the second rotating pin shaft hole through a rotating pin shaft to form a shaft hole rotating pair.

Furthermore, the number of the hub connection points is more than three, and the specific number is determined according to the number of the helicopter main hub support arms.

Furthermore, the length of a connecting line of the geometric centers of the first rotating pin hole and the second rotating pin hole is L.

Furthermore, the method for determining the length L of the connection line between the geometric centers of the first and second pivot pin holes is to measure the position of the center of gravity of the main hub to be installed in advance by using a center-of-gravity measurement system, calculate the distance H from the center of gravity of the main hub to be installed to the geometric center of the first pivot pin hole, and calculate the length L of the connection line between the geometric centers of the first and second pivot pin holes according to the formula L ═ H ═ tan θ, where θ is the rotor shaft forward tilt angle.

Furthermore, the bearing framework is a steel pipe, so that the weight is favorably reduced, and the rigidity of the bearing framework is ensured.

Furthermore, beryllium bronze bushings are mounted inside the first rotating pin hole and the second rotating pin hole, so that abrasion and clamping stagnation of the shaft hole rotating pair are prevented, and flexible movement is guaranteed.

A use method of a helicopter main hub installation tool comprises the following steps:

1) the suspension hoisting ring and the rotating pin shaft are arranged in a first rotating pin shaft hole, and the propeller hub connecting points are correspondingly connected with the main propeller hub supporting arm respectively to ensure firmness;

2) hanging a lifting ring, stably lifting the main propeller hub, correcting the levelness of the main propeller hub by using a quadrant instrument, and ensuring the levelness of the main propeller hub;

3) putting down the main propeller hub, dismounting the suspension lifting ring and the rotating pin shaft, installing the suspension lifting ring and the rotating pin shaft into a second rotating pin shaft hole, stably lifting the main propeller hub, placing the quadrant instrument along the connecting line direction of the geometric centers of the first rotating pin shaft hole and the second rotating pin shaft hole, measuring the aerial inclination angle of the main propeller hub, and checking that the aerial inclination angle of the main propeller hub is consistent with the forward inclination angle theta of the rotor shaft;

4) and (3) hoisting the main hub to a position right above the rotor shaft by using a helicopter main hub installation tool, descending the main hub to slowly approach the rotor shaft after the main hub is stable in the air, aligning the spline and lacking teeth, installing the main hub in place along the direction of a forward rake angle theta of the rotor shaft in a clockwise manner, and then finely adjusting and fastening to complete the butt joint installation of the main hub and the rotor shaft.

The invention has the beneficial effects that: compared with the prior art, the key for realizing the high-precision spline shaft hole butt joint is to eliminate the angle deviation of the shaft hole, ensure that the assembly pose is automatically adjusted in the air after the main propeller hub to be assembled is lifted, and ensure that the center lines of the shaft holes are concentric.

Drawings

FIG. 1 is a schematic view of a helicopter main hub configuration;

FIG. 2 is a schematic view of the tooling structure of the present invention;

FIG. 3 is a schematic view of the tool of the present invention in a state of being lifted by the first rotation pin hole 3;

fig. 4 is a schematic view showing a state in which the tool of the present invention is lifted by using the second pivot pin hole 4.

Detailed Description

The technical solution is further described in detail below with reference to the accompanying drawings and the detailed description.

The invention is a helicopter main hub soft and low damage assembly process and elaborates the design scheme of the used tool, the basic principle is based on the basic characteristic of the gravity center of the rigid body, namely the gravity center position is only related to the shape of the rigid body and the distribution of the internal mass of the rigid body, as long as the shape and the internal mass distribution of the rigid body are not changed, the gravity center position of the rigid body is always fixed, meanwhile, because the gravity direction is vertical downwards, when the rigid body is suspended and placed by a suspension method, the gravity center is always right below the suspension point, the suspension tool is designed according to the basic principle, during the main hub is lifted by the special suspension tool, the pose adjustment can be automatically completed, the main hub is ensured to be consistent and coaxial with the front inclination angle of the rotor shaft in the air, the angular deviation generated by different shafts is eliminated, the soft and flexible shaft hole, the low damage and the design of the used tool under the condition of high centering are realized, Low damage assembly;

as shown in figure 2, the invention provides a helicopter main hub installation tool, which comprises a suspension lifting ring 1, a rotating pin shaft 2, a first rotating pin shaft hole 3, a second rotating pin shaft hole 4, a lever frame 5, a bearing framework 6 and a hub connection point 7, wherein the suspension lifting ring 1 is of a U-shaped structure, two ends of an opening of the suspension lifting ring are hinged on the first rotating pin shaft hole 3 or the second rotating pin shaft hole 4 on the lever frame 5 through the rotating pin shaft 2 to form a shaft hole rotating pair, the suspension lifting ring 1 is used for being connected with an external lifting device, the caliber of the U-shaped opening of the suspension lifting ring is matched with the size of a hook to ensure that the hook cannot slide in the suspension lifting ring 1, the lever frame 5 is of an elliptic column structure, but is not limited to the structural form, the bearing framework 6 is fixedly connected to the bottom of the lever frame 5, the bearing framework 6 comprises a main shaft, a plurality of support shafts and a connecting column shaft, and the main shaft is positioned at the center of the bearing framework 6, the support shafts are fixedly connected with the bottom of the lever frame 5, one ends of the support shafts are connected to the main shaft, the other ends of the support shafts are connected to the connecting column shafts, and the support shafts are fixed between the adjacent connecting column shafts; the bearing framework 6 is a steel pipe, so that the weight is favorably reduced, and the rigidity of the bearing framework 6 is ensured; the hub connection points 7 are connected to the bottom of the bearing framework 6, namely the hub connection points 7 are respectively connected to the lower end of a connecting column shaft of the bearing framework 6, the end parts of the hub connection points 7 are connecting rings and are used for being sleeved on a main hub during lifting, and the number of all the hub connection points 7 is matched with that of the main hub support arms of the helicopter; and all hub connection points 7 are located on the same plane, which is parallel to the main hub plane, so that the main hub can be lifted smoothly.

In addition, a first rotating pin shaft hole 3 and a second rotating pin shaft hole 4 are arranged on the lever frame 5, the geometric center of the first rotating pin shaft hole 3 is positioned above the geometric center of the force bearing framework 6, the connecting line of the geometric centers of the first rotating pin shaft hole 3 and the second rotating pin shaft hole 4 is positioned in the symmetrical plane of the plane figure formed by the propeller hub connecting points 7, and the connecting line of the geometric centers of the first rotating pin shaft hole 3 and the second rotating pin shaft hole 4 is parallel to the plane figure formed by the propeller hub connecting points 7; the stability of the main grain hub is ensured during hoisting.

Furthermore, the length of the connecting line between the geometric centers of the first rotating pin hole 3 and the second rotating pin hole 4 is L, and the determination method of L is to measure the position of the center of gravity of the main hub to be installed by using a center-of-gravity measurement system in advance, calculate the distance H from the center of gravity to the geometric center of the first rotating pin hole 3, and calculate the length of the connecting line between the geometric centers of the first rotating pin hole 3 and the second rotating pin hole 4 as L according to the formula L ═ tan θ, wherein θ is the rotor shaft forward inclination angle. Be bronze bush is all installed to first rotatory pin shaft hole 3, second rotatory pin shaft hole 4 inside, prevent wearing and tearing, the jamming of shaft hole revolute pair, guarantee nimble motion.

The helicopter main hub mounting tool comprises the following steps before use, and comprises the following steps:

1) the invention adopts the technical method principle that: the basic characteristic of the center of gravity of the main propeller hub is utilized to automatically finish pose adjustment in the lifting process, the inclination angle of the main propeller hub in the air is ensured to be consistent and coaxial with the forward inclination angle of the rotor shaft, the angle deviation generated by different shafts is eliminated, and the shaft hole is assembled in a smooth and low-damage mode under the condition of high centering;

2) the assembling process method is realized by designing a hanging tool, firstly analyzing the structural form of a main hub to be assembled, if the main hub is a four-arm main hub, four hanging points are required to be uniformly distributed at the same position of each support arm, if the main hub is a five-arm main hub, five hanging points are required to be uniformly distributed at the same position of each support arm, if the main hub is a six-arm main hub, three hanging points are required to be uniformly distributed at the same position of three support arms, and the purpose is that the main hub can be stressed uniformly and the initial posture is horizontal after being hoisted by the hanging tool;

3) hanging tool design: because the basic principles are consistent, the assembly and hanging tool is only explained by taking a common six-support-arm main hub assembly and hanging tool as an example, the structural form of the assembly and hanging tool is shown in fig. 2, the assembly and hanging tool is mainly composed of a hanging lifting ring 1, a rotating pin shaft 2, a rotating pin shaft hole 3, a rotating pin shaft hole 4, a lever frame 5, a bearing framework 6 and a hub connecting point 7, wherein the bearing framework 6 and the hub connecting point 7 can be designed according to the specific structural form, size, weight and the like of the main hub to be assembled, and safety and reliability are guaranteed.

3.1) the core structure of hanging the frock is rotatory round pin axle 2, rotatory round pin axle hole 3, rotatory round pin axle hole 4, lever frame 5, and the key feature is: a. the rotating pin shaft 2 can respectively form a shaft hole rotating pair with the rotating pin shaft hole 3 and the rotating pin shaft hole 4, so that flexible rotation is ensured; b. the direction of the lever frame 5, namely the connection points 7 of the hubs are required to be symmetrically distributed around the lever frame 5 in the connection direction of the rotary pin hole 3 and the rotary pin hole 4; c. the center distance L between the two pin shaft holes of the rotating pin shaft hole 3 and the rotating pin shaft hole 4;

3.2) determining the center distance L between the two pin shaft holes of the rotary pin shaft hole 3 and the rotary pin shaft hole 4 with key characteristics, namely, a principle analysis diagram of a hanging tool, measuring the gravity center position in advance by using a gravity center measuring system, calculating the distance H between the gravity center and the plane of the pin shaft holes, and calculating the center distance L between the two pin shaft holes according to a formula L (H & tan theta), so that the center distance L between the two pin shaft holes with key characteristic sizes can be designed according to the adaptability of main hubs with different configurations and forward rake angles of rotor shafts, and the design of assembling and hanging of the main hubs of helicopters with different configurations is further completed.

The helicopter main hub mounting tool comprises the following steps before use, and comprises the following steps:

1) the suspension hoisting ring 1 and the rotating pin shaft 2 are arranged in a first rotating pin shaft hole 3, and the hub connecting point 7 is correspondingly connected with the main hub supporting arm respectively to ensure firmness;

2) hanging the lifting ring 1, stably lifting the main propeller hub, correcting the levelness of the main propeller hub by using a quadrant instrument, ensuring the levelness of the main propeller hub and zeroing the quadrant instrument; the main propeller hub is ensured to be horizontal;

3) putting down the main propeller hub, detaching the suspension lifting ring 1 and the rotating pin shaft 2, installing the suspension lifting ring and the rotating pin shaft 2 into the second rotating pin shaft hole 4, stably lifting the main propeller hub, placing the quadrant instrument along the connecting line direction of the geometric centers of the first rotating pin shaft hole 3 and the second rotating pin shaft hole 4, measuring the aerial inclination angle of the main propeller hub, and checking that the aerial inclination angle of the main propeller hub is consistent with the forward inclination angle theta of the rotor shaft;

4) and (3) hoisting the main hub to a position right above the rotor shaft by using a helicopter main hub installation tool, descending the main hub to slowly approach the rotor shaft after the main hub is stable in the air, aligning the spline and lacking teeth, installing the main hub in place along the direction of a forward rake angle theta of the rotor shaft in a clockwise manner, and then finely adjusting and fastening to complete the butt joint installation of the main hub and the rotor shaft.

5) The hanging tool designed and manufactured according to the method is successfully applied to a plurality of machine types, has good effect, and meets the installation requirements of smoothness and low damage of the main propeller hub;

the invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.