Large helicopter tail beam fairing

Abstract

According to the large helicopter tail beam fairing, a fairing body in the fairing is of a honeycomb sandwich structure, and quick-release lock nails and spring pieces used for fixing the quick-release lock nails are installed on the fairing body; the quick-release lock seat is fixed on the quick-release lock seat bracket in a riveting manner; one side of the hinge assembly is in threaded connection with the fairing body, and the other side of the hinge assembly is in threaded connection with the tail beam platform. The fairing body is installed on the tail beam platform, the right side of the heading is hinged to the tail beam platform through a hinge assembly, and the left side of the heading is connected with the tail beam platform through a quick-release lock assembly; one side of the fixed pull rod assembly is screwed with the fairing body, and the other side is screwed with the tail beam platform; one side of the adjusting pull rod assembly is screwed with the fairing body, and the other side is screwed with the tail beam platform; the tail beam fairing can be rapidly opened and closed, accidental closing can be prevented, and operation of maintenance personnel is facilitated; and in case of crosswind or other emergencies, the tail beam fairing can be prevented from being closed accidentally, and the operation safety of maintenance personnel is improved.

Description

Technical Field

[0001] The invention belongs to the field of helicopter structure design, and in particular relates to a large helicopter tail beam fairing. Background Art

[0002] Traditional layout helicopters need to have a tail rotor on the rear side of the heading to balance the torque of the main rotor and achieve steering control of the fuselage. Because the diameter of the helicopter main rotor is usually large, it is usually necessary to set a larger tail beam and inclined beam structure to keep the tail rotor away from the influence of the main rotor. In order to provide power to the tail rotor, it is usually necessary to use a transmission system to transmit the engine power from the main reduction area of ​​the fuselage to the tail rotor. In order to provide protection for the traditional system, a tail beam fairing is usually required in the tail beam area.

[0003] For large helicopters, the tail boom fairing is usually large and high off the ground. A large tail boom fairing that is high off the ground will increase the difficulty of use and maintenance. When the tail boom fairing needs to be opened and closed, a work ladder is required and it is difficult to operate on one side. At least two people are required to cooperate on both sides of the tail boom fairing or people are required to move back and forth on both sides of the fairing. In crosswinds or other sudden situations, the tail boom fairing may also be accidentally closed, reducing the operating safety of maintenance personnel. Summary of the invention

[0004] In order to solve the problem that the tail boom fairing in the prior art cannot meet the requirements of rapid opening and closing and preventing accidental closure, the present invention provides a tail boom fairing that can be opened and closed quickly and prevent accidental closure based on the basic requirements of rapid opening and closing and preventing accidental closure of the tail boom fairing of a large helicopter. The technical solution is as follows:

[0005] In a first aspect, a large helicopter tail boom fairing is provided, comprising: a fairing body 1, a fixed tie rod assembly 6, an adjustment tie rod assembly 8, a hinge assembly 5, and a quick release lock assembly; the quick release lock assembly is composed of a quick release lock seat 16 and a quick release lock pin 15;

[0006] The fairing body 1 is a honeycomb sandwich structure, on which a quick-release lock pin 15 and a spring sheet 4 for fixing the quick-release lock pin 15 are installed;

[0007] The quick release lock seat 16 is fixed to the quick release lock seat bracket 7 by riveting;

[0008] One side of the hinge assembly 5 is screwed to the fairing body 1, and the other side is screwed to the tail beam platform 9.

[0009] The fairing body 1 is installed on the tail beam platform 9, and is hinged to the tail beam platform 9 on the right side of the heading through the hinge assembly 5, and is connected to the tail beam platform 9 on the left side of the heading through the quick release lock assembly;

[0010] One side of the fixed rod assembly 6 is screwed to the fairing body 1 , and the other side is screwed to the tail beam platform 9 ; one side of the adjustable rod assembly 8 is screwed to the fairing body 1 , and the other side is screwed to the tail beam platform 9 .

[0011] Optionally, a metal insert 13 for connecting hinges in the hinge assembly 5 and fixing the tie rod assembly 6 and adjusting the supports in the tie rod assembly 8 is pre-embedded on the fairing body 1 to improve local rigidity.

[0012] Optionally, the hinge assembly 5 includes a fairing side hinge 11 and a tail beam platform side hinge 12, which are connected by pins. The fairing side hinge 11 is fixed to the fairing body 1 by a metal insert 13 by screwing, and the tail beam platform side hinge 12 is fixed to the tail beam platform 9 by a metal insert 13 by screwing.

[0013] Optionally, the fairing body 1 includes: a front tail boom fairing 3 and a rear tail boom fairing 10; the front tail boom fairing 3 is located in front of the tail boom platform 9 and connected to the middle fuselage; the rear tail boom fairing 10 is located in the rear of the tail boom platform 9 and in front of the middle reduction fairing 2.

[0014] Optionally, the fixed tie rod assembly 6 is composed of a first fairing side support 61, a first upper tie rod assembly 62, a first lower tie rod assembly 63 and a first tail beam platform side support 64; the first fairing side support 61 and the first upper tie rod assembly 62 are connected by a quick stop pin 14; the first upper tie rod assembly 62 and the first lower tie rod assembly 63 are connected by a pin; the first lower tie rod assembly 63 and the first tail beam platform side support 64 are connected by a pin;

[0015] A mechanical limiting structure is provided in the joint connection area between the first upper tie rod assembly 62 and the first lower tie rod assembly 63, for limiting the rotation angle of the first lower tie rod assembly 63 to not exceed the maximum rotation angle.

[0016] Optionally, the adjusting rod assembly 8 is composed of a second fairing side support 81, a second upper rod assembly 82, a second lower rod assembly 83 and a second tail beam platform side support 84; the second fairing side support 81 and the second upper rod assembly 82 are connected by a quick stop pin 14; the second upper rod assembly 82 and the second lower rod assembly 83 are connected by a pin; the second lower rod assembly 83 and the second tail beam platform side support 84 are connected by a pin;

[0017] A mechanical limit structure is provided at the joint connection area between the second upper tie rod assembly 82 and the second lower tie rod assembly 83 to limit the rotation angle of the second lower tie rod assembly 83 to not exceed the maximum rotation angle;

[0018] The second lower tie rod assembly 83 is provided with a threaded adjustment structure for adjusting the length of the second lower tie rod assembly 83 at intervals of a thread pitch P, so as to facilitate matching the length of the adjustable tie rod assembly 8 with the length of the fixed tie rod assembly 6 .

[0019] Optionally, the mechanical limiting structure is composed of an upper pull rod assembly joint 17 and a lower pull rod assembly joint 18, which are connected by a pin; the upper pull rod assembly joint 17 is a double-ear form, and the lower pull rod assembly joint 18 is a single-ear form; after the upper pull rod assembly joint 17 and the lower pull rod assembly joint 18 are rotated relative to each other to a certain angle, the single-ear ear piece of the lower pull rod assembly joint 18 and the bottom of the double-ear ear piece of the upper pull rod assembly joint 17 contact each other to limit the position.

[0020] Optionally, the threaded adjustment structure is composed of a threaded tie rod joint 22, a threaded fixing joint 20, a lower tie rod 19, a stop washer 23 and a locking nut 21;

[0021] The threaded fixing joint 20 is integrated with the lower tie rod 19 by riveting or screwing; the threaded tie rod joint 22 is fixed in the threaded fixing joint 20 by threaded connection; the stop washer 23 and the locking nut 21 are installed between the threaded fixing joint 20 and the threaded tie rod joint 22; the threaded tie rod joint 22 is rotated to adjust the length of the second lower tie rod assembly 83 to an appropriate length, and then the rotating threaded tie rod joint 22 is locked on the threaded fixing joint 20 by the locking nut 21 and the stop washer 23 to prevent loosening.

[0022] Among them, when the tail beam fairing is closed, the quick release lock pin 15 is rotated clockwise on the left side of the fuselage heading to disconnect the connection between the fairing body 1 and the tail beam platform 9, and the fairing body 1 is flipped up. When the first upper tie rod assembly 62 and the first lower tie rod assembly 63 in the fixed tie rod assembly 6 and the second upper tie rod assembly 82 and the second lower tie rod assembly 83 in the adjustment tie rod assembly 8 move to the same straight line, the tail beam fairing is opened and stabilized to an angle that meets maintenance requirements and can be opened and closed on one side of the heading on the left side. When the tail beam fairing is open, adjust the posture of the fixed tie rod assembly 6 and the adjustment tie rod assembly 8, close the fairing body 1 downward, rotate the quick release lock pin 15 counterclockwise, and establish a connection between the tail beam fairing and the tail beam platform 9.

[0023] Among them, when the tail boom fairing is in the maximum open state, if the crosswind direction is heading to the right, the fixed rod assembly 6 and the adjusting rod assembly 8 are in a tensioned state, and the tail boom fairing is in a stable state; if the crosswind direction is heading to the left or an emergency occurs, such as misoperation or helicopter shaking, the fairing tends to close downward, and the fixed rod assembly 6 in a tensioned state continues to rotate downward at the connection between the first upper rod assembly 62 and the first lower rod assembly 63, and the adjusting rod assembly 8 in a tensioned state continues to rotate downward at the connection between the second upper rod assembly 82 and the second lower rod assembly 83. Mechanical limiting occurs at the connection between the first upper rod assembly 62 and the first lower rod assembly 63 and at the connection between the second upper rod assembly 82 and the second lower rod assembly 83, thereby preventing the fairing body 1 from continuing to close.

[0024] The beneficial effects of the present invention are at least:

[0025] The present invention is based on the basic requirements of fast opening and closing of the tail boom fairing of a large helicopter and preventing accidental closure, and provides a tail boom fairing that can be quickly opened and closed, can prevent accidental closure and is easy for maintenance personnel to operate. In the event of crosswind or other sudden situations, the tail boom fairing can be prevented from accidentally closing, thereby improving the operating safety of maintenance personnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a schematic diagram of the present invention in a closed state;

[0027] Figure 2 is a schematic diagram of the present invention in an open state;

[0028] Figure 3 It is a schematic diagram of the connection hinge of the present invention;

[0029] Figure 4 is a schematic diagram of a metal insert of the present invention;

[0030] Figure 5 is a schematic diagram of a fixed tie rod assembly of the present invention;

[0031] Figure 6 is a schematic diagram of the adjusting pull rod assembly of the present invention;

[0032] Figure 7 This is a schematic diagram of the installation of the quick-release nail and the spring sheet of the present invention;

[0033] Figure 8 This is a schematic diagram of the installation of the quick release lock seat of the present invention;

[0034] Fig. 9 It is a schematic diagram of the limiting structure of the present invention in a non-limiting state;

[0035] Fig.10 It is a schematic diagram of the limiting structure of the present invention in a limiting state;

[0036] Fig.11 It is a schematic cross-sectional view of the threaded adjustment structure in the adjustment rod assembly of the present invention;

[0037] Fig.12 It is a schematic diagram of the opening process of the present invention (the lower pull rod 19 assembly rotates 30°);

[0038] Fig.13 is a schematic diagram of the present invention when it is opened to the maximum state (the fixed pull rod assembly and the adjustable pull rod assembly are in a tensioned state, and the first lower pull rod assembly and the second lower pull rod assembly are rotated about 75 degrees);

[0039] Fig.14 It is a schematic diagram of the present invention falling back from the maximum open state to the mechanical limit state (the first lower pull rod assembly and the second lower pull rod assembly rotate about 80 degrees).

[0040] Among them, 1-tail beam fairing body, 2-middle reduction fairing, 3-tail beam front fairing, 4-spring sheet, 5-hinge assembly, 6-fixed pull rod assembly, 7-quick release lock seat, 16 bracket, 8-adjustment pull rod assembly, 9-tail beam platform, 10-tail beam rear fairing, 11-fairing side hinge, 12-tail beam platform side hinge, 13-metal insert, 14-quick stop pin, 61-first fairing side support, 62-first upper pull rod assembly, 63-first lower tie rod assembly, 64-first tail beam platform side support, 81-second fairing side support, 82-second upper tie rod assembly, 83-second lower tie rod assembly, 84-second tail beam platform side support, 15-quick release locking pin, 16-quick release locking seat, 17-upper tie rod assembly joint, 18-lower tie rod assembly joint, 19-lower tie rod, 20-threaded fixing joint, 21-locking nut, 22-threaded tie rod joint, 23-stop washer. DETAILED DESCRIPTION

[0041] The present invention is further described in detail below through specific implementation modes and drawings.

[0042] The invention is based on the basic requirements of fast opening and closing and preventing accidental closure of a large helicopter tail boom fairing, and provides a tail boom fairing which can be quickly opened and closed, can prevent accidental closure and is convenient for maintenance personnel to operate.

[0043] See also Figure 1 , Figure 2 An embodiment of the present invention provides a large helicopter tail beam fairing, comprising: a fairing body 1, a fixed tie rod assembly 6, an adjustment tie rod assembly 8, a hinge assembly 5, and a quick release lock assembly. The quick release lock assembly is composed of a quick release lock seat 16 and a quick release lock pin 15.

[0044] See also Figure 1 , Figure 2The fairing body 1 is composed of a tail beam front fairing 3 and a tail beam rear fairing 10, both of which are honeycomb sandwich structures. The tail beam front fairing 3 is located in front of the tail beam platform 9 and connected to the middle fuselage; the tail beam rear fairing 10 is located in the rear of the tail beam platform 9 and in front of the middle fairing 2. The present invention divides the fairing body 1 into two parts, the front and the rear, but this block division is not the only or necessary way and can be adjusted according to actual needs.

[0045] See also Figure 2 , Figure 7 A quick-release locking pin 15 and a spring sheet 4 for fixing the quick-release locking pin 15 are installed on the fairing body 1.

[0046] See also Figure 4 In order to improve the local rigidity of the connection area, a metal insert 13 for connecting the hinges in the hinge assembly 5 and fixing the tie rod assembly 6 and adjusting the support in the tie rod assembly 8 is pre-embedded on the fairing body 1.

[0047] See also Figure 2 , Figure 8 The quick release lock seat 16 is fixed on the quick release lock seat bracket 7 by riveting.

[0048] See also Figure 2 , Figure 3 The hinge assembly 5 consists of a fairing side hinge 11 and a tail beam platform side hinge 12, which are connected by pins. The fairing side hinge 11 is fixed to the fairing body 1 by a metal insert 13 in a screw connection form, and the tail beam platform side hinge 12 is fixed to the tail beam platform 9 by a metal insert 13 in a screw connection form.

[0049] See also Figure 5 The fixed tie rod assembly 6 is composed of a first fairing side support 61, a first upper tie rod assembly 62, a first lower tie rod assembly 63 and a first tail beam platform side support 64; the first fairing side support 61 and the first upper tie rod assembly 62 are connected by a quick stop pin 14; the first upper tie rod assembly 62 and the first lower tie rod assembly 63 are connected by a pin; the first lower tie rod assembly 63 and the first tail beam platform side support 64 are connected by a pin;

[0050] See also Figure 6 The adjusting rod assembly 8 is composed of a second fairing side support 81, a second upper rod assembly 82, a second lower rod assembly 83 and a second tail beam platform side support 84; the second fairing side support 81 and the second upper rod assembly 82 are connected by a quick stop pin 14; the second upper rod assembly 82 and the second lower rod assembly 83 are connected by a pin; the second lower rod assembly 83 and the second tail beam platform side support 84 are connected by a pin;

[0051] See also Fig. 9 , Fig.10 The joint connection area of ​​the first upper tie rod assembly 62 and the first lower tie rod assembly 63, and the joint connection area of ​​the second upper tie rod assembly 82 and the second lower tie rod assembly 83 are all provided with a mechanical limit structure for limiting the rotation angle of the first lower tie rod assembly 63 and the second lower tie rod assembly 83 to not exceed the maximum rotation angle;

[0052] See also Fig.11 The second lower tie rod assembly 83 is provided with a threaded adjustment structure for adjusting the length of the second lower tie rod assembly 83 at intervals of pitch P, so as to match the length of the adjusting tie rod assembly 8 with the length of the fixed tie rod assembly 6. The threaded fixed joint 20 is integrally formed with the lower tie rod 19 by riveting or screwing; the threaded tie rod joint 22 is fixed in the threaded fixed joint 20 by threaded connection; the stop washer 23 and the locking nut 21 are installed between the threaded fixed joint 20 and the threaded tie rod joint 22; after the threaded tie rod joint 22 is rotated to adjust the length of the second lower tie rod assembly 83 to a suitable length, the rotating threaded tie rod joint 22 is locked on the threaded fixed joint 20 by the locking nut 21 and the stop washer 23 to prevent loosening.

[0053] See also Fig.12 , Fig.13 , when the tail boom fairing is closed, rotate the quick-release lock pin 15 clockwise on the left side of the fuselage heading to disconnect the connection between the fairing body 1 and the tail boom platform 9, and flip the fairing body 1 upward. When the first upper tie rod assembly 62 and the first lower tie rod assembly 63 in the fixed tie rod assembly 6 and the second upper tie rod assembly 82 and the second lower tie rod assembly 83 in the adjusting tie rod assembly 8 move to the same straight line, the tail boom fairing is stabilized at a certain opening angle that can realize unilateral opening and closing operation; when the tail boom fairing is opened, adjust the posture of the fixed tie rod assembly 6 and the adjusting tie rod assembly 8, close the fairing body 1 downward, rotate the quick-release lock pin 15 counterclockwise, and establish a connection between the tail boom fairing and the tail boom platform 9.

[0054] See also Fig.13 , Fig.14When the tail boom fairing is in the maximum open state, if the crosswind direction is heading to the right, the fixed rod assembly 6 and the adjusting rod assembly 8 are in a tensioned state, and the tail boom fairing is in a stable state; if the crosswind direction is heading to the left or an emergency occurs, such as misoperation or helicopter shaking, the fairing tends to close downward, and the fixed rod assembly 6 in a tensioned state continues to rotate downward at the connection between the first upper rod assembly 62 and the first lower rod assembly 63, and the adjusting rod assembly 8 in a tensioned state continues to rotate downward at the connection between the second upper rod assembly 82 and the second lower rod assembly 83, and mechanical limiting occurs at the connection between the first upper rod assembly 62 and the first lower rod assembly 63 and at the connection between the second upper rod assembly 82 and the second lower rod assembly 83, thereby preventing the fairing body 1 from continuing to close.

[0055] The present invention provides a large helicopter tail boom fairing that can realize the function of facilitating operation by maintenance personnel. The tail boom fairing of a large helicopter is usually large in size and high off the ground. A tail boom fairing that is large in size and high off the ground will increase the difficulty of use and maintenance. When the tail boom fairing needs to be opened and closed, a work ladder is required and it is difficult to operate on one side. At least two personnel are required to cooperate on both sides of the tail boom fairing or personnel are required to move back and forth on both sides of the fairing. The present invention can control the opening angle of the tail boom fairing by setting a fixed pull rod assembly 6 and an adjustable pull rod assembly 8, so that the tail boom fairing is opened and stabilized to an angle that meets maintenance requirements and can be opened and closed on the left side of the heading. The present invention greatly improves the convenience of personnel operation during maintenance of the tail boom fairing of a large helicopter. The maintenance personnel only need to open and close the fairing on the left side of the heading. The present invention generally provides a quick stop pin 14. When the fairing needs to be fully opened under certain special circumstances, the quick stop pin 14 on the first fairing side support 61 and the second fairing side support 81 can be pulled out to quickly disconnect the connection between the fixed pull rod assembly 6 and the fairing body 1, and the adjustment pull rod assembly 8 and the fairing body 1, so as to fully open the fairing, thereby retaining the function of fully opening the tail boom fairing.

[0056] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A large helicopter tail boom fairing, characterized in that: include: A fairing body (1), a fixed pull rod assembly (6), an adjustable pull rod assembly (8), a hinge assembly (5), and a quick-release lock assembly; the quick-release lock assembly is composed of a quick-release lock seat (16) and a quick-release lock pin (15); The fairing body (1) is a honeycomb sandwich structure, on which a quick-release lock pin (15) and a spring sheet (4) for fixing the quick-release lock pin (15) are installed; the quick-release lock seat (16) is fixed to the quick-release lock seat bracket (7) by riveting; one side of the hinge assembly (5) is screwed to the fairing body (1), and the other side is screwed to the tail beam platform (9); the fairing body (1) is installed on the tail beam platform (9), and a hinged relationship is established between the hinge assembly (5) and the tail beam platform (9) on the right side of the heading, and a connection is established between the fairing body (1) and the tail beam platform (9) on the left side of the heading through the quick-release lock assembly; one side of the fixed pull rod assembly (6) is screwed to the fairing body (1), and the other side is screwed to the tail beam platform (9); one side of the adjustable pull rod assembly (8) is screwed to the fairing body (1), and the other side is screwed to the tail beam platform (9).

2. The large helicopter tail boom fairing according to claim 1, characterized in that: A metal insert (13) for connecting hinges in a hinge assembly (5) and fixing a tie rod assembly (6) and adjusting a support in a tie rod assembly (8) is pre-buried on the fairing body (1).

3. The large helicopter tail boom fairing according to claim 2, characterized in that: The hinge assembly (5) comprises a fairing side hinge (11) and a tail beam platform side hinge (12), which are connected by pins. The fairing side hinge (11) is fixed to the fairing body (1) by screwing through a metal insert (13), and the tail beam platform side hinge (12) is fixed to the tail beam platform (9) by screwing through a metal insert (13).

4. The large helicopter tail boom fairing according to claim 1, characterized in that: The fairing body (1) comprises: a tail beam front fairing (3) and a tail beam rear fairing (10); the tail beam front fairing (3) is located at the front side of the tail beam platform (9) and connected to the middle fuselage; the tail beam rear fairing (10) is located at the rear side of the tail beam platform (9) and in front of the middle reduction fairing (2).

5. The large helicopter tail boom fairing according to claim 1, characterized in that: The fixed tie rod assembly (6) is composed of a first fairing side support (61), a first upper tie rod assembly (62), a first lower tie rod assembly (63) and a first tail beam platform side support (64); the first fairing side support (61) and the first upper tie rod assembly (62) are connected by a quick stop pin (14); the first upper tie rod assembly (62) and the first lower tie rod assembly (63) are connected by a pin; the first lower tie rod assembly (63) and the first tail beam platform side support (64) are connected by a pin; A mechanical limiting structure is provided in the joint connection area between the first upper pull rod assembly (62) and the first lower pull rod assembly (63), for limiting the rotation angle of the first lower pull rod assembly (63) to not exceed a maximum rotation angle.

6. The large helicopter tail boom fairing according to claim 1, characterized in that: The adjusting rod assembly (8) is composed of a second fairing side support (81), a second upper rod assembly (82), a second lower rod assembly (83) and a second tail beam platform side support (84); the second fairing side support (81) and the second upper rod assembly (82) are connected by a quick stop pin (14); the second upper rod assembly (82) and the second lower rod assembly (83) are connected by a pin; the second lower rod assembly (83) and the second tail beam platform side support (84) are connected by a pin; A mechanical limit structure is provided in the joint connection area between the second upper pull rod assembly (82) and the second lower pull rod assembly (83) to limit the rotation angle of the second lower pull rod assembly (83) to not exceed the maximum rotation angle; The second lower tie rod assembly (83) is provided with a threaded adjustment structure for adjusting the length of the second lower tie rod assembly (83) at intervals of thread pitch P, so as to facilitate matching the length of the adjustable tie rod assembly 8 with the length of the fixed tie rod assembly (6).

7. The large helicopter tail boom fairing according to claim 5, characterized in that: The mechanical limiting structure is composed of an upper pull rod assembly joint (17) and a lower pull rod assembly joint (18), which are connected by a pin; the upper pull rod assembly joint (17) is a double-ear form, and the lower pull rod assembly joint (18) is a single-ear form; after the upper pull rod assembly joint (17) and the lower pull rod assembly joint (18) are relatively rotated to a certain angle, the single-ear ear piece of the lower pull rod assembly joint (18) contacts the bottom of the double-ear ear piece of the upper pull rod assembly joint (17) to limit the position.

8. The large helicopter tail boom fairing according to claim 6, characterized in that: The threaded adjustment structure is composed of a threaded tie rod joint (22), a threaded fixing joint (20), a lower tie rod (19), a stop washer (23) and a locking nut (21); The threaded fixing joint (20) is integrally connected with the lower tie rod (19) by riveting or screwing; the threaded tie rod joint (22) is fixed in the threaded fixing joint (20) by threaded connection; a stop washer (23) and a locking nut (21) are installed between the threaded fixing joint (20) and the threaded tie rod joint (22); after the threaded tie rod joint (22) is rotated to adjust the length of the second lower tie rod assembly (83) to an appropriate length, the rotating threaded tie rod joint (22) is locked on the threaded fixing joint (20) by the locking nut (21) and the stop washer (23).

9. The large helicopter tail boom fairing according to claim 1, characterized in that: When the tail boom fairing is in a closed state, the quick-release lock pin (15) is rotated clockwise on the left side of the fuselage heading to disconnect the connection between the fairing body (1) and the tail boom platform (9), and the fairing body (1) is flipped upward. When the first upper tie rod assembly (62) and the first lower tie rod assembly (63) in the fixed tie rod assembly (6) and the second upper tie rod assembly (82) and the second lower tie rod assembly (83) in the adjustment tie rod assembly (8) respectively move to be on the same straight line, the tail boom fairing is opened and stabilized to an angle that meets maintenance requirements and can be opened and closed on one side on the left side of the heading; When the tail beam fairing is in the open state, the postures of the fixed rod assembly (6) and the adjustment rod assembly (8) are adjusted, the fairing body (1) is closed downward, and the quick-release locking pin (15) is rotated counterclockwise to establish a connection between the tail beam fairing and the tail beam platform (9).

10. The large helicopter tail boom fairing according to claim 1, characterized in that: When the tail boom fairing is in the maximum open state, if the crosswind direction is heading to the right, the fixed tie rod assembly (6) and the adjustable tie rod assembly (8) are in a tensioned state, and the tail boom fairing is in a stable state; if the crosswind direction is heading to the left or an emergency occurs, the fairing tends to close downward, the fixed tie rod assembly (6) in the tensioned state continues to rotate downward at the connection between the first upper tie rod assembly (62) and the first lower tie rod assembly (63), and the adjustable tie rod assembly (8) in the tensioned state continues to rotate downward at the connection between the second upper tie rod assembly (82) and the second lower tie rod assembly (83), and mechanical limiting occurs at the connection between the first upper tie rod assembly (62) and the first lower tie rod assembly (63) and the connection between the second upper tie rod assembly (82) and the second lower tie rod assembly (83), thereby preventing the fairing body 1 from continuing to close.

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