Rotor system stopper, rotor system and helicopter

Abstract

The invention relates to a rotor system stopper, a rotor system and a helicopter, belongs to the technical field of space flight and aviation, and solves the problems that a centrifugal stopper in the prior art is complex in shape, large in required installation space or high in cost. The device comprises a fixed part and a swinging assembly, the fixing piece is fixed to the transmission shaft and rotates along with the transmission shaft. The swing assembly is hinged to the fixing piece and swings around a hinge shaft of the swing assembly and the fixing piece, and the axis of the hinge shaft is located in the plane perpendicular to the transmission shaft. The swing assembly comprises a pendulum bob, a swing rod and a limiting piece. One end of the swing rod is hinged to the outside of the fixing piece. The other end of the pendulum bob is a suspension end, and the pendulum bob is arranged at the suspension end; the limiting piece is fixed to the end, close to the fixing piece, of the swing rod and can swing along with the swing rod. When the swing angle of the swing rod is 0 degree, the limiting piece can support the propeller hub. The limiting device is simple in structure, small in needed installation space and low in cost.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a rotor system limiter, a rotor system and a helicopter. Background Art

[0002] Centrifugal limiters are commonly used in helicopter rotor systems. They use centrifugal force to switch the mechanism between different positions, limit the blade swing angle range, protect the rotor system components, and ensure flight safety. The centrifugal limiters in the prior art have complex shapes, require large installation space, and are relatively expensive. Summary of the invention

[0003] In view of the above analysis, the embodiments of the present invention are intended to provide a rotor system limiter, a rotor system and a helicopter, so as to solve the problems of the centrifugal limiter in the prior art, such as complex shape, large installation space and high cost.

[0004] The purpose of the present invention is mainly achieved through the following technical solutions:

[0005] A first aspect of the present invention provides a rotor system restraint, comprising a fixing member and a swing assembly;

[0006] The fixing member is fixed to the transmission shaft of the helicopter and rotates with the transmission shaft; the swing assembly is hinged to the fixing member, the swing assembly swings around the hinge shaft between the swing assembly and the fixing member, and the axis of the hinge shaft is located in a plane perpendicular to the transmission shaft;

[0007] The swing assembly includes a pendulum, a swing rod and a limiter; the first end of the swing rod is hinged to the fixing member; the second end is a suspension end, and the pendulum is arranged at the suspension end;

[0008] The limit member is fixed to the first end of the swing rod, and the limit member swings along with the swing rod; when the swing angle of the swing rod is 0°, the limit member supports the hub of the rotor system.

[0009] Furthermore, the limiting member includes a connecting portion and a supporting portion; the connecting portion further has a U-shaped notch; and two ends of the connecting portion are fixed to the swing rod;

[0010] The support portion is a plate-shaped structure; the outer side surface of the support portion is a support surface;

[0011] When the swing angle of the swing arm is 0°, the support portion is perpendicular to the axis of the transmission shaft to support the propeller hub.

[0012] Furthermore, the two ends of the connecting portion have arc surfaces; the supporting surface is an arc surface;

[0013] The shape and size of the arcuate surface of the support surface satisfy the following requirements: when the swing angle of the limiter is 0°, the center of the arcuate surface of the support surface is lower than the lower bottom surface of the support part.

[0014] Furthermore, the fixing member includes a working portion, and the working portion has a protruding structure; the protruding structures are arranged at intervals, and the number of the protruding structures is the same as the number of blades of the rotor system.

[0015] Furthermore, the protruding structure is partially accommodated in the notch; the rocker arm is a U-shaped rod, and the U-shaped rod includes a middle rod and two side rods; the middle rod of the rocker arm is hinged to the protruding structure; and a hinge hole is provided at the hinge between the protruding structure and the rocker arm.

[0016] Furthermore, the vertical distance from the center of the pendulum to the axis of the hinge hole of the protruding structure is the effective swing length of the pendulum; the effective swing length of the pendulum satisfies the formula:

[0017] P≥1.1(W 2 g 2 / (EMB) 2 ω 4 -B 2 ) 1 / 2

[0018] Wherein, P is the effective swing length of the pendulum, in m; W is the distance between the axis of the mounting hole of the limiter and the outermost edge of the support surface, in m; B is the distance between the axis of the hinge hole of the protruding structure and the axis of the transmission shaft, in m; ω is the rotation speed of the transmission shaft, in rad / s; M is the distance between the axis of the mounting hole of the limiter and the bottom surface of the support portion, in m; E is the distance between the outer side surface of the protruding structure and the axis of the transmission shaft, in m; g is the acceleration due to gravity, in m / s 2 ).

[0019] Furthermore, the fixing member further comprises an inner sleeve and an elastic layer, the inner sleeve is fixedly connected to the transmission shaft, and the elastic layer is arranged between the inner sleeve and the working part.

[0020] Furthermore, it also includes an elastic body; the elastic body is arranged between two adjacent swing rods, and / or between the swing rod and the fixing member.

[0021] A second aspect of the present invention provides a rotor system, comprising a hub, a blade and the rotor system limiter;

[0022] The rotor system limiter is arranged at the upper part or the lower part of the hub.

[0023] A third aspect of the present invention provides a helicopter comprising the above-mentioned rotor system.

[0024] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0025] (1) In the limiter of the present invention, one end of the rocker arm is hinged to a fixing part fixed to the transmission shaft, and the other end is suspended. The pendulum is arranged at the suspended end of the rocker arm. The rocker arm swings due to the gravity and centrifugal force of the pendulum, driving the limiting part fixed to its hinged end to swing around the plane where the fixing part is located. When encountering a gust of wind, the transmission shaft speed decreases, the pendulum drops, the blades and their components are lifted up and fall, and hit the outer plane of the limiting part, which can limit the swinging angle of the blades and prevent the blades from hitting the fuselage, causing damage to the blades or the fuselage. Compared with the prior art, the limiter of the present invention is composed of a pendulum, a rocker arm, a limiting part and a fixing part, which simplifies the structure of the limiter, reduces the installation space required for the limiter, and ensures the working reliability of the limiter.

[0026] (2) In the present invention, the support of the propeller hub by the limiter and the limitation of the swing amplitude of the blade are achieved through the swing angle of the rocker arm. The limiter includes a connecting portion and a supporting portion. The connecting portion is fixed to the near hinge end of the rocker arm so that the limiter swings with the rocker arm; the supporting portion is arranged in the tangential direction of the connecting portion; when the swing angle of the rocker arm is 0°, the supporting portion is perpendicular to the axis of the transmission shaft to support the propeller hub.

[0027] (3) In order to ensure that the limiter works reliably, the shape and size of the arcuate surface of the support surface are set in the present invention to meet the following requirements: when the swing angle of the limiter is 0°, the center of the arcuate surface of the support surface is lower than the bottom surface of the support portion. The distance from the pendulum to the swing center should not be too long, otherwise the blade may hit the pendulum during the swinging process. Under the same centrifugal force, the shorter the distance from the pendulum to the swing center, the larger the mass of the pendulum is required, which increases the deadweight of the fuselage. Compared with the prior art, the present invention sets the relationship between the effective length of the pendulum and the parameters of the hub and the blades, so that the structure of the limiter is more optimized.

[0028] (4) Compared with the prior art, the fixing member in the present invention includes an elastic layer, which provides a buffer for the impact force of the blade, reduces the impact load transmitted to the hub, and reduces the damage to the blade.

[0029] (5) The elastic body is arranged between two adjacent pendulum rods, and / or between the pendulum rod and the fixed part. When the pendulum and the pendulum rod swing to 90 degrees, the pendulum is tightened. When the speed decreases and the pendulum begins to droop, the elastic body accelerates the drooping speed of the pendulum, so that the limiter quickly reaches the supporting state for the propeller hub, thereby improving the working reliability of the limiter.

[0030] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the following content, and some advantages can be obvious from the description or understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained through the contents particularly pointed out in the text and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0032] Figure 1 It is a structural schematic diagram of the limiter of Example 1;

[0033] Figure 2 is a schematic structural diagram of a fixing member of Example 1;

[0034] Figure 3 It is a structural schematic diagram of the position limiting member of Example 1;

[0035] Figure 4 is a schematic diagram of the limiter of Example 1 when the pendulum is drooping;

[0036] Figure 5 Schematic diagram of the parameter structure of the limiter of Example 1;

[0037] Figure 6 This is a schematic diagram of the parameter structure of the protruding structure of Example 1;

[0038] Figure 7 Schematic diagram of the parameter structure of the effective swing length of the pendulum when the swing angle is 0° in Example 1;

[0039] Figure 8 Schematic diagram of the parameter structure of the effective swing length of the pendulum when the swing angle is 90° in Example 1;

[0040] Fig. 9 It is a structural schematic diagram of the parameters of the stopper and the distance from the hub plane to the fuselage of Example 1;

[0041] Fig.10 This is a schematic diagram of the state of the limiter of Example 2 when the blade rotates at high speed;

[0042] Fig.11 Schematic diagram of the state of the limiter of Example 2 when the blade rotates at a low speed.

[0043] Reference numerals:

[0044] 1-fixing part, 11-inner sleeve, 12-elastic layer, 13-working part, 131-protruding structure, 1311-hinge hole; 2-swinging assembly, 21-pendulum, 22-rocker, 23-limiting part, 231-connecting part, 2311-mounting hole, 232-supporting part, 2321-supporting surface, 3-elastic body, 4-blade, 5-hub. DETAILED DESCRIPTION

[0045] The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0046] Example 1

[0047] A specific embodiment of this embodiment, such as Figure 1 As shown, a rotor system limiter is disclosed, including a fixing member 1 and a swing assembly 2.

[0048] The fixing member 1 is fixed to the transmission shaft and rotates with the transmission shaft. The swing component 2 is hinged to the fixing member 1 and can swing up and down around the plane where the fixing member 1 is located.

[0049] like Figure 2 As shown, the fixing member 1 includes a working portion 13, and the working portion 13 has a protruding structure 131. The protruding structures 131 are arranged at intervals. Specifically, the number of the protruding structures 131 is the same as the number of the rotors. The protruding structure 131 is provided with a through hinge hole for hingedly connecting the swing assembly 2. Specifically, the axis of the hinge hole is perpendicular to the axis direction of the transmission shaft. Exemplarily, the protruding structure 131 protrudes toward the outer edge of the fixing member 1, and the upper part of the protruding structure 131 is semi-cylindrical and the lower part is a rectangular parallelepiped. There is a through hinge hole in the middle of the semi-cylinder.

[0050] Furthermore, the fixing member 1 also includes an inner sleeve 11 and an elastic layer 12. The inner sleeve 11 is arranged inside the fixing member 1 and is used to be fixedly connected to the transmission shaft. The elastic layer 12 is arranged between the inner sleeve 11 and the working part 13. Compared with the prior art, the fixing member 1 in this embodiment includes the elastic layer 12. When the blade 4 and the components hit the limiter, the elastic layer 12 can provide a buffer for the impact force of the blade 4 and the components, reduce the impact load transmitted to the hub 5, and reduce the damage to the blade 4 and the components.

[0051] like Figure 3 As shown, the swing assembly 2 includes a pendulum 21, a swing rod 22 and a stopper 23. The first end of the swing rod 22 is hinged to the protruding structure 131, and the swing rod 22 passes through the hinge hole 1311, and can swing around the plane where the fixing member 1 is located; the second end is a suspension end, and the pendulum 21 is arranged at the suspension end. During the swinging motion of the swing assembly 2, the gravity and centrifugal force of the pendulum 21 cause the swing assembly 2 to fall from the highest height.

[0052] Exemplarily, the swing rod 22 is a U-shaped structure, the middle rod of the swing rod 22 is used to be inserted into the hinge hole 1311, and the two side rods of the swing rod 22 are used to swing. The length of the two side rods is the effective length of the swing rod 22.

[0053] The limiting member 23 is fixed to the first end of the swing rod 22 near the fixing member 1 and can swing along with the swing rod 22. Figure 4 The swing angle of the middle swing rod 22 is 0°. At this time, the limiting member 23 can support the hub 5 .

[0054] The stopper 23 includes a connecting portion 231. The two ends of the connecting portion 231 have arc surfaces, and the bottom surface is a plane. The connecting portion 231 has a U-shaped notch. Exemplarily, the U-shaped notch is arranged in the middle of the connecting portion 231, and the two ends of the notch have mounting holes 2311, and the middle rod of the swing rod 22 is inserted into the mounting hole 2311 and fixed. The upper part of the protruding structure 131 is accommodated in the notch.

[0055] The stopper 23 also includes a support portion 232. The support portion 232 is a plate-like structure, which is extended to one side of the connection portion 231 along the tangent direction of the arc surface of the connection portion 231. The outer side surface of the support portion 232 is a support surface 2321, which is used to support the hub 5. Preferably, the support surface 2321 is set to a smooth 1 / 4 arc surface. When the blade assembly hits the support surface 2321, the arc surface can make the force on the support surface 2321 be directed downward or obliquely downward, so that the stopper 23 can be reliably docked on the fixing member 1.

[0056] When the transmission shaft runs at high speed, the centrifugal force of the pendulum 21 drives the pendulum 22 to swing to a height perpendicular to the axis of the transmission shaft, and the swing angle of the pendulum 22 is 90°. Figure 1 At this time, the lower support part 232 driven by the swing rod 22 is parallel to the axis of the transmission shaft, and the limiter 23 does not affect the normal operation of the hub 5, the blade 4 and the components. When the transmission shaft runs at a low speed, Figure 4 As shown, the gravity of the pendulum 21 drives the pendulum 22 to descend and be parallel to the axis of the transmission shaft, and the swing angle of the pendulum 22 is 0°. At this time, the lower support portion 232 driven by the pendulum 22 is perpendicular to the axis of the transmission shaft, the support portion 232 protrudes outward, and the support surface 2321 supports the falling blades 4 and components.

[0057] Furthermore, if Figure 5 and Figure 6As shown, in order to ensure reliable operation of the stopper 23, the shape and size of the arcuate surface of the support surface 2321 satisfy the following requirements: when the swing angle of the stopper 23 is 0°, the center of the arcuate surface of the support surface 2321 is lower than the lower bottom surface of the support portion 232, that is, the height difference H between the two is ≥ 0. At the same time, in order to prevent the inner edge point of the bottom surface of the connecting portion 231 from interfering with the edge of the adjacent surface of the protruding structure 131 when the stopper 23 swings, thereby affecting the operation of the stopper 23, the straight-line distance between the inner edge point of the bottom surface of the connecting portion 231 and the axis of the mounting hole of the connecting portion 231 is set to L, and the distance between the inner edge of the protruding structure 131 and the axis of the hinge hole 1311 of the protruding structure 131 is set to D, then L ≥ D.

[0058] In this embodiment, one end of the swing rod 22 is hinged to the fixing member 1 fixed to the transmission shaft, and the other end is suspended. The pendulum 21 is arranged at the suspension end of the swing rod 22. The swing rod 22 swings due to the gravity and centrifugal force of the pendulum 21, driving the limiter 23 fixed to its hinged end to swing around the plane where the fixing member 1 is located. When encountering a gust of wind, the transmission shaft speed decreases, the pendulum 21 drops, the blades 4 and their components rise and fall, and hit the outer plane of the limiter 23, which can limit the swinging angle of the blades 4 and prevent the blades 4 from hitting the fuselage, causing damage to the blades 4 or the fuselage. Compared with the prior art, the limiter of this embodiment is composed of the pendulum 21, the swing rod 22, the limiter 23 and the fixing member 1, which simplifies the structure of the limiter, reduces the installation space required for the limiter, and ensures the working reliability of the limiter.

[0059] The pendulum 21 drives the swing rod 22 to swing to realize the limiting function of the limiter. The vertical distance from the center of the pendulum 21 to the axis of the hinge hole 1311 of the protruding structure 131 is the effective swing length of the pendulum 21. Under the condition that the centrifugal force of the pendulum 21 is the same, if the effective swing length from the pendulum 21 to the swing center is too large, the possibility of the blade 4 hitting the pendulum 21 during the swinging process will increase; if the effective swing length from the pendulum 21 to the swing center is too small, the mass of the pendulum 21 needs to be increased, thereby increasing the deadweight of the fuselage. Therefore, it is necessary to set the effective swing length of the pendulum 21.

[0060] like Figure 7 and Figure 8 As shown, under the action of centrifugal force, the pendulum 21 drives the limiter 23 to rotate by 90-α.

[0061] tanα=mg / mω 2 r=g / ω 2 (B 2 +(Pcosα) 2 ) 1 / 2

[0062] Where: P is the effective swing length of the pendulum 21, m; m is the linear density of the blade 4, kg / m; R is the rotor radius, m; g is the acceleration due to gravity, kg·m / s 2 ; ω-rotational speed of the transmission shaft, rad / s; r-distance from the section of blade 4 to the center of rotation of the rotor, m; B-distance from the center axis of the hinge hole 1311 to the axis of the transmission shaft, m.

[0063] The support surface 2321 of the horizontal limiter 23 should not protrude from the outer side of the protruding structure 131. Setting the safety factor to 1.1, we can get

[0064] P≥1.1(W 2 g 2 / (EMB) 2 ω 4 -B 2 ) 1 / 2

[0065] Wherein, P is the effective swing length of the pendulum 21, m; W is the distance between the axis of the mounting hole 2311 of the limiter 23 and the outermost edge of the support surface 2311, m; B is the distance between the axis of the hinge hole 1311 of the protruding structure 131 and the axis of the transmission shaft, m; ω is the rotation speed of the transmission shaft, rad / s; M is the distance between the axis of the mounting hole 2311 of the limiter 23 and the bottom surface of the support portion 231, m; E is the distance between the outer side surface of the protruding structure 131 and the axis of the transmission shaft, m; g is the acceleration due to gravity, kg·m / s 2 .

[0066] When the rotor is at low speed or stationary, if there is a gust of wind, the blade 4 will rise and then fall. The drooping distance of the tip of the blade 4 during static bending under load is

[0067] d(R)=βmg(Rr 0 ) 2 / 2+5βmg(Rr 0 ) 4 / 24EI

[0068] Where: d(R)-the distance the blade tip sags when statically bending under load, m; r 0 -The distance from the blade 4 section to the rotor rotation center, m; m-Blade 4 linear density, kg / m; R-Rotor radius, m; g-Gravity acceleration, kg·m / s 2 ; β-load coefficient, no unit; EI-elastic modulus of blade 4, no unit.

[0069] like Fig. 9 As shown, in order to ensure that the tip of the blade 4 does not hit the fuselage, the following conditions must be met:

[0070] (R 0 )(B+Wr0 ) / T+Q≥d(R)

[0071] Wherein: W is the distance from the rotation axis of the limiter 23 to the edge of the support portion 232, m; T is the straight-line distance between the plane of the hub 5 and the bottom surface of the support portion 232 when the rocker arm 22 is 0°, m; B is the distance from the axis of the hinge hole 1311 of the protruding structure 131 to the axis of the transmission shaft, m; Q is the distance from the plane of the hub 5 to the fuselage.

[0072] It is found that the length of the limiter 23 from the rotation axis to the edge of the support portion 232 and the distance from the plane of the hub 5 to the fuselage satisfy the relationship:

[0073] W≥[βmg(Rr 0 ) 2 / 2+5βmg(Rr 0 ) 4 / 24EI-Q]T / (Rr 0 )-B+r 0

[0074] Furthermore, in order to ensure that the limiting member 23 has sufficient support force on the blade 4, the area of ​​the supporting portion 232 must meet the following conditions:

[0075] S≥βmg(Rr 0 ) 2 / 4[σ][T 2 +(B+Wr 0 ) 2 ] 1 / 2

[0076] Where: S-area of ​​the support portion 232, m 2 ; [σ]-allowable stress, Pa.

[0077] Compared with the prior art, the present embodiment sets up a relationship formula between the maximum distance from the rotating shaft of the limit member 23 to the supporting surface and the length of the blade 4, as well as a relationship between the area of ​​the supporting surface 2321 of the limit member 23 and parameters such as the blade 4, so as to ensure that the blade 4 maintains a safe distance from surrounding components during rotation, and avoids collision between the blade 4 and other components due to excessive rotation or displacement, thereby preventing damage to the blade 4 and related components, reducing safety risks, and ensuring the stable operation of the helicopter.

[0078] Furthermore, an elastic body 3 is included. The elastic body 3 is arranged between two adjacent pendulum rods 22, and / or between the pendulum rod 22 and the fixing member 1. When the pendulum 21 is tightened and the speed decreases, the pendulum 21 begins to droop, the elastic body 3 accelerates the drooping speed of the pendulum 21, so that the limiter 23 quickly reaches the supporting state for the propeller hub 5, thereby improving the working reliability of the limiter.

[0079] Example 2

[0080] A specific embodiment of the present invention discloses a rotor system, including blades 4, a hub 5 and the rotor system limiter described in Example 1.

[0081] The rotor system limiter is arranged at the upper part or the lower part of the hub 5. In this embodiment, the rotor system limiter is arranged at the lower part of the hub 5. Fig.10 As shown, when the rotor is rotating at high speed, the pendulum 21 is in an open state, and the swing angle is 90°. Fig.11 As shown, when the rotor rotates at a low speed or is stationary, the pendulum 21 is in a drooping state under the action of gravity and the elastic body 3, and the limiter 23 is in a working state, providing a docking and supporting function for the blade 4 and its components. When encountering a gust of wind, the blade 4 and its components are lifted up and fall, thereby hitting the supporting surface 2321 of the limiter 23, limiting the swinging angle of the blade 4 and preventing the blade 4 from hitting the fuselage. At the same time, the elastic layer 12 of the fixing member 1 provides a buffer for the impact force, reducing the impact load transmitted to the hub 5.

[0082] Compared with the prior art, the advantages of the rotor system of the embodiment of the present invention are the same as the advantages of the above-mentioned rotor system limiter, which will not be repeated here.

[0083] Example 3

[0084] A specific embodiment of the present invention discloses a helicopter, including the rotor system described in Example 2.

[0085] Compared with the prior art, the advantages of the helicopter of the embodiment of the present invention are the same as those of the above-mentioned rotor system, which will not be described in detail here.

[0086] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A rotor system limiter, characterized in that: It comprises a fixing member (1) and a swinging assembly (2); The fixing member (1) is fixed to the transmission shaft of the helicopter and rotates with the transmission shaft; the swing assembly (2) is hinged to the fixing member (1), the swing assembly (2) swings around the hinge axis between the swing assembly (2) and the fixing member (1), and the axis of the hinge axis is located in a plane perpendicular to the transmission shaft; The swing assembly (2) comprises a pendulum (21), a swing rod (22) and a limiter (23); the first end of the swing rod (22) is hinged to the fixing member (1), and the second end is a suspension end, and the pendulum (21) is arranged on the suspension end; The limit member (23) is fixed to the first end of the swing rod (22), and the limit member (23) swings along with the swing rod (22); when the swing angle of the swing rod (22) is 0°, the limit member (23) supports the hub of the rotor system.

2. The rotor system restraint according to claim 1, characterized in that: The limiting member (23) comprises a connecting portion (231) and a supporting portion (232); the connecting portion (231) further comprises a U-shaped notch; two ends of the connecting portion (231) are fixed to the swing rod (22); The support portion (232) is a plate-shaped structure; the outer side surface of the support portion (232) is a support surface (2321); When the swing angle of the swing rod (22) is 0°, the support portion (232) is perpendicular to the axis of the transmission shaft to support the propeller hub.

3. The rotor system limiter according to claim 2, characterized in that: The two ends of the connecting portion (231) have arc surfaces; the supporting surface (2321) is an arc surface; The shape and size of the arcuate surface of the support surface (2321) satisfy the following requirements: when the swing angle of the limit member (23) is 0°, the center of the arcuate surface of the support surface (2321) is lower than the bottom surface of the support portion (232).

4. The rotor system limiter according to claim 3, characterized in that: The fixing member (1) comprises a working portion (13), wherein the working portion (13) has a protruding structure (131); the protruding structures (131) are arranged at intervals, and the number of the protruding structures (131) is the same as the number of blades of the rotor system.

5. The rotor system restraint according to claim 4, characterized in that: The protruding structure (131) is partially accommodated in the notch; the swing rod (22) is a U-shaped rod, and the U-shaped rod comprises a middle rod and two side rods; the middle rod of the swing rod (22) is hinged to the protruding structure (131); and a hinge hole (1311) is provided at the hinge between the protruding structure (131) and the swing rod (22).

6. The rotor system restraint according to claim 5, characterized in that: The vertical distance from the center of the pendulum (21) to the axis of the hinge hole (1311) of the protruding structure (131) is the effective swing length of the pendulum (21); the effective swing length of the pendulum (21) satisfies the formula: P≥1.1(W 2 g 2 / (E-M-B) 2 ω 4 -B 2 ) 1 / 2 Wherein, P is the effective swing length of the pendulum (21), unit (m); W is the distance between the axis of the mounting hole (2311) of the limiting member (23) and the outermost edge of the support surface (2321), unit (m); B is the distance between the axis of the hinge hole (1311) of the protruding structure (131) and the axis of the transmission shaft, unit (m); ω is the rotation speed of the transmission shaft, unit (rad / s); M is the distance between the axis of the mounting hole (2311) of the limiting member (23) and the bottom surface of the support portion (232), unit (m); E is the distance between the outer side surface of the protruding structure (131) and the axis of the transmission shaft, unit (m); g is the acceleration due to gravity, unit (m / s 2 ).

7. The rotor system restraint according to claim 4, characterized in that: The fixing member (1) further comprises an inner sleeve (11) and an elastic layer (12); the inner sleeve (11) is fixedly connected to the transmission shaft; and the elastic layer (12) is arranged between the inner sleeve (11) and the working part (13).

8. The rotor system restraint according to claim 5, characterized in that: It also comprises an elastic body (3); the elastic body (3) is arranged between two adjacent swing rods (22), and / or between the swing rod (22) and the fixing member (1).

9. A rotor system, characterized in that: It comprises a hub (5), a blade (4) and a rotor system limiter as claimed in any one of claims 1 to 8; The rotor system limiter is arranged at the upper part or the lower part of the hub (5).

10. A helicopter, characterized in that: Includes the rotor system as described in claim 9.

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