阅读说明：本技术 一种直升机四桨叶旋翼折叠系统及折叠方法 (Four-blade rotor folding system and method for helicopter ) 是由 李满福 王鉴 林展 于 2020-10-30 设计创作，主要内容包括：本发明属于直升机旋翼技术领域,具体涉及一种直升机四桨叶旋翼折叠系统及折叠方法。通过将桨毂分成两部分,其中一部分与旋翼轴固定连接,另一部分可以在作动器驱动下绕旋翼轴轴线旋转,桨毂的每部分连接两片桨叶,这两部分可以相对转动使桨叶变距轴线之间的角度减小至45度以内,旋翼轴可定位在确定的方位角上,使两片桨叶之间构成小于45度角的角平分线与直升机航向重合,将大幅降低四桨叶旋翼折叠系统的复杂度,并且能够实现旋翼快速折叠,操作简便。(The invention belongs to the technical field of helicopter rotors, and particularly relates to a four-blade rotor folding system and a four-blade rotor folding method for a helicopter. The hub is divided into two parts, one part is fixedly connected with the rotor shaft, the other part can rotate around the axis of the rotor shaft under the drive of the actuator, each part of the hub is connected with two blades, the two parts can rotate relatively to reduce the angle between the variable pitch axes of the blades to within 45 degrees, the rotor shaft can be positioned on a determined azimuth angle, an angular bisector forming an angle smaller than 45 degrees between the two blades is coincided with the course of a helicopter, the complexity of a four-blade rotor folding system is greatly reduced, the rotor can be folded quickly, and the operation is simple and convenient.)

1. A four-blade rotor folding system of a helicopter is characterized by comprising blades (1), a hub (2) and an actuator (3),

the hub (2) is of a cross structure integrally and has a cross center C, the hub (2) comprises four hub support arms, the blades (1) are fixedly connected with free ends of the four hub support arms, the four hub support arms are respectively connected with each other in a linear mode in pairs to respectively form a rotor wing rotating part (200) and a rotor wing fixing part (100), the rotor wing fixing part (100) is arranged in the direction of the course direction of the helicopter, and the rotor wing rotating part (200) can rotate around the cross center C;

the actuator (3) comprises an actuator extension rod (4) and an actuator body (5), the actuator extension rod (4) and the actuator body (5) are respectively arranged at two ends of the actuator (3), the actuator extension rod (4) is mechanically connected with the actuator body (5), and the actuator extension rod (4) is driven to stretch through the actuator body (5); the arbitrary one end of actuator (3) with rotor fixed part (100) rotates and is connected, the other end with rotor rotates portion (200) and rotates and be connected.

2. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the end of the actuator extension rod (4) of said actuator (3) is rotatably connected to the hub of said rotor-holding portion (100), and the actuator body (5) of said actuator (3) is rotatably connected to the blade to which said rotor-turning portion (200) is connected.

3. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the end of the actuator extension rod (4) of said actuator (3) is rotatably connected to the blade in said rotor-holding portion (100), and in that the actuator body (5) of said actuator (3) is rotatably connected to the blade in said rotor-turning portion (200).

4. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the end of the actuator projecting rod (4) of said actuator (3) is rotatably connected to the blade in said rotor-holding portion (100), and the actuator body (5) of said actuator (3) is rotatably connected to the hub in said rotor-turning portion (200).

5. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the end of the actuator extension rod (4) of said actuator (3) is rotatably connected to the hub of said rotor-holding portion (100), and in that the actuator body (5) of said actuator (3) is rotatably connected to the hub of said rotor-turning portion (200).

6. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the actuator body (5) of said actuator (3) is rotatably connected to the blade in said rotor-holding portion (100), and the actuator extension rod (4) end of said actuator (3) is rotatably connected to the hub in said rotor-rotating portion (200).

7. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the actuator body (5) of said actuator (3) is rotatably connected to the blades of said rotor-mounting portion (100), and the actuator extension rod (4) end of said actuator (3) is rotatably connected to the blades of said rotor-mounting portion (200).

8. A four-blade rotor folding system for helicopters, according to claim 1, characterized in that the actuator body (5) of said actuator (3) is rotatably connected to the hub of said rotor-fixed part (100), and the end of the actuator extension rod (4) of said actuator (3) is rotatably connected to the hub of said rotor-rotating part (200).

9. A four-bladed rotor folding system for helicopters according to claim 1, characterized in that the actuator body (5) of said actuator (3) is rotatably connected to the hub of said rotor-fixed part (100), and the actuator extension rod (4) end of said actuator (3) is rotatably connected to the blades of said rotor-rotating part (200).

10. A method for folding a four-blade helicopter rotor, the four-blade helicopter rotor folding system according to claims 1 to 9, comprising the steps of:

s1: rotating a four-blade rotor of the helicopter to rotate the direction of the rotor fixing part (100) to a course direction;

s2: start actuator (3), drive actuator extension bar (4) flexible drive rotor rotation portion (200) rotate, realize that the rotor is folding.

Technical Field

The invention belongs to the technical field of helicopter rotors, and particularly relates to a four-blade rotor folding system and a four-blade rotor folding method for a helicopter.

Background

The rotor wing can be folded to reduce the required storage space of the helicopter, and the folded rotor wing is beneficial to storing a plurality of helicopters in a limited space. The existing rotor wing folding is that a plurality of blades installed in a rotor wing system are respectively folded, a plurality of actuators are needed to be used for realizing dead locking of a blade pitch of a hub supporting arm, dead locking of shimmy motion and the like, then folding is realized in the shimmy direction, if the rotor wing has N blades, the actuators are generally needed to be installed on the N-1 blades at least, the folding system is complex in structure, the folding process is more in steps, time consuming and long, and operation is difficult.

Disclosure of Invention

The purpose of the invention is as follows: aiming at the defects in the prior art, the folding of the rotor wing is realized through the relative rotation of the hubs divided into two parts, the complexity of a four-blade rotor wing folding system is greatly reduced, the rotor wing can be quickly folded, and the operation is simple and convenient.

The technical scheme of the invention is as follows: in order to achieve the above object, according to a first aspect of the present invention, there is provided a four-blade rotor folding system for a helicopter, comprising a blade (1), a hub (2), an actuator (3),

the hub (2) is of a cross structure integrally and has a cross center C, the hub (2) comprises four hub support arms, the blades (1) are fixedly connected with free ends of the four hub support arms, the four hub support arms are respectively connected with each other in a linear mode in pairs to respectively form a rotor wing rotating part (200) and a rotor wing fixing part (100), the rotor wing fixing part (100) is arranged in the direction of the course direction of the helicopter, and the rotor wing rotating part (200) can rotate around the cross center C;

the actuator (3) comprises an actuator extension rod (4) and an actuator body (5), the actuator extension rod (4) and the actuator body (5) are respectively arranged at two ends of the actuator (3), the actuator extension rod (4) is mechanically connected with the actuator body (5), and the actuator extension rod (4) is driven to stretch through the actuator body (5); the arbitrary one end of actuator (3) with rotor fixed part (100) rotates and is connected, the other end with rotor rotates portion (200) and rotates and be connected.

In one possible embodiment, the end of the actuator extension rod (4) of the actuator (3) is rotatably connected to the hub of the rotor fixing portion (100), and the actuator body (5) of the actuator (3) is rotatably connected to the blade connected to the rotor rotating portion (200).

In a possible embodiment, the end of the actuator extension rod (4) of the actuator (3) is rotatably connected with the blade connected with the rotor fixing part (100), and the actuator body (5) of the actuator (3) is rotatably connected with the blade connected with the rotor rotating part (200).

In one possible embodiment, the end of the actuator extension rod (4) of the actuator (3) is rotatably connected to the blade to which the rotor fixing part (100) is connected, and the actuator body (5) of the actuator (3) is rotatably connected to the hub of the rotor rotating part (200).

In one possible embodiment, the end of the actuator extension rod (4) of the actuator (3) is rotatably connected to the hub of the rotor fixing portion (100), and the actuator body (5) of the actuator (3) is rotatably connected to the hub of the rotor rotating portion (200).

In one possible embodiment, the actuator body (5) of the actuator (3) is rotatably connected to the blade to which the rotor fixing portion (100) is connected, and the actuator extension rod (4) end of the actuator (3) is rotatably connected to the hub of the rotor rotating portion (200).

In a possible embodiment, the actuator body (5) of the actuator (3) is rotatably connected to the blade connected to the rotor fixing portion (100), and the actuator extension rod (4) end of the actuator (3) is rotatably connected to the blade connected to the rotor rotating portion (200).

In one possible embodiment, the actuator body (5) of the actuator (3) is rotatably connected to the hub of the rotor fixing portion (100), and the actuator extension rod (4) end of the actuator (3) is rotatably connected to the hub of the rotor rotating portion (200).

In one possible embodiment, the actuator body (5) of the actuator (3) is rotatably connected to the hub of the rotor fixing portion (100), and the actuator extension rod (4) end of the actuator (3) is rotatably connected to the blade connected to the rotor rotating portion (200).

According to a second aspect of the present invention, there is provided a method for folding a four-blade rotor of a helicopter, which is implemented by the following steps:

s1: rotating a four-blade rotor of the helicopter to rotate the direction of the rotor fixing part (100) to a course direction;

s2: start actuator (3), drive actuator extension bar (4) flexible drive rotor rotation portion (200) rotate, realize that the rotor is folding.

In one possible embodiment, the angle between the rotor rotation part (200) and the rotor fixing part (100) ranges from 40 degrees to 45 degrees after folding.

The invention has the beneficial technical effects that: according to the invention, the hub is divided into two parts, one part is fixedly connected with the rotor shaft, the other part can rotate around the axis of the rotor shaft under the driving of the actuator, each part of the hub is connected with two blades, the two parts can rotate relatively to reduce the angle between the variable-pitch axes of the blades to be within 45 degrees, the rotor shaft can be positioned on a determined azimuth angle, an angular bisector forming an angle smaller than 45 degrees between the two blades is coincident with the course of a helicopter, the complexity of a four-blade rotor folding system is greatly reduced, the rotor can be folded quickly, and the operation is simple and convenient.

Drawings

FIG. 1 is a schematic view of a four-bladed rotor folding system for a helicopter according to the present invention

FIG. 2 is a schematic view of the folding process of the present invention

Wherein:

1-blade, 2-hub, 3-actuator, 4-actuator extension rod, 5-actuator body

100-rotor fixed part, 200-rotor rotating part

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

As shown in figure 1, the four-blade rotor folding system of the helicopter comprises blades (1), a hub (2) and an actuator (3),

the hub (2) is of a cross structure integrally and has a cross center C, the hub (2) comprises four hub support arms, the blades (1) are fixedly connected with free ends of the four hub support arms, the four hub support arms are respectively connected with each other in a linear mode in pairs to respectively form a rotor wing rotating part (200) and a rotor wing fixing part (100), the rotor wing fixing part (100) is arranged in the direction of the course direction of the helicopter, and the rotor wing rotating part (200) can rotate around the cross center C;

the actuator (3) comprises an actuator extension rod (4) and an actuator body (5), the actuator extension rod (4) and the actuator body (5) are respectively arranged at two ends of the actuator (3), the actuator extension rod (4) is mechanically connected with the actuator body (5), and the actuator extension rod (4) is driven to stretch through the actuator body (5); any end of the actuator (3) is rotatably connected with the rotor wing fixing part (100), and the other end of the actuator is rotatably connected with the rotor wing rotating part (200);

specifically, the end of an actuator extension rod (4) of the actuator (3) is rotatably connected with a hub in the rotor wing fixing part (100), and an actuator body (5) of the actuator (3) is rotatably connected with a blade connected with the rotor wing rotating part (200);

as shown in fig. 2, the present invention further provides a folding method of a four-blade rotor of a helicopter, which is implemented by the following steps:

s1: rotating a four-blade rotor of the helicopter to rotate the direction of the rotor fixing part (100) to a course direction;

s2: start actuator (3), drive actuator extension bar (4) flexible drive rotor rotation portion (200) rotates, realizes that the rotor is folding, after folding, rotor rotation portion (200) with contained angle between rotor fixed part (100) is 40.

While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.