A helicopter horizontal tail stepless angle adjustment tilting mechanism

Abstract

The present application provides a helicopter horizontal tail stepless angle tilting mechanism, comprising: a rotating shaft assembly, which is arranged on the front main frame of the fuselage, and the rotating shaft assembly is connected to the front joint of the horizontal tail; an angle adjustment assembly, which is arranged on the rear main frame of the fuselage, and the angle adjustment assembly is connected to the rear joint of the horizontal tail; wherein, the horizontal tail can be adjusted steplessly around the rotating shaft assembly through the angle adjustment assembly; the rotating shaft assembly comprises: a cylindrical nut, which is arranged in the front main frame of the fuselage; a transition piece, which is arranged on the front main frame of the fuselage; wherein one side of the transition piece is an arc surface, and the other side is a plane; a first connecting bolt, one end of which passes through the front joint of the horizontal tail, the transition piece and the front main frame of the fuselage in sequence, and is connected to the cylindrical nut; the present application can realize stepless adjustment of the horizontal tail angle, make full use of the internal space of the body structure, and realize the arbitrary installation angle adjustment requirements of the helicopter horizontal tail.

Description

Technical Field

[0001] The present application belongs to the technical field of helicopter structures, and in particular relates to a stepless angle adjustment and tilting mechanism for a helicopter horizontal tail. Background Art

[0002] During the pre-research phase, to better verify the impact of the horizontal tail mounting angle on the helicopter's longitudinal stability and maneuverability, the aerodynamic requirements of the model required the horizontal tail mounting mechanism to have an angle adjustment function. Based on existing experience in the helicopter industry, horizontal tails are typically connected to the main fuselage structure via single- and double-ear joints, and the horizontal tail mounting mechanism itself does not have the ability to precisely adjust the angle.

[0003] Therefore, the present application proposes a horizontal tail stepless angle adjustment and tilting mechanism capable of achieving fine adjustment of the horizontal tail angle. Summary of the Invention

[0004] In response to the above technical problems, the present application provides a helicopter horizontal tail stepless angle adjustment and tilting mechanism, comprising:

[0005] A shaft assembly is provided on the front main frame of the fuselage and is connected to the front joint of the horizontal tail;

[0006] An angle adjustment assembly is provided on the rear main frame of the fuselage and is connected to the rear joint of the horizontal tail;

[0007] The horizontal tail can be adjusted in an infinitely variable manner around the rotating shaft assembly through the angle adjustment assembly.

[0008] Preferably, the shaft assembly comprises:

[0009] a cylindrical nut, disposed in the front main frame of the fuselage;

[0010] A transition piece is provided on the front main frame of the fuselage; wherein one side of the transition piece is an arc surface and the other side is a plane;

[0011] A first connecting bolt, one end of which passes through the front joint of the horizontal tail, the transition piece and the front main frame of the fuselage in sequence, and is connected to the cylindrical nut.

[0012] Preferably, the front main frame of the fuselage includes:

[0013] An edge strip, wherein a first fan-shaped hole is provided on the edge strip;

[0014] a web connected below the flange;

[0015] The boss is connected to the edge strip and the web respectively; wherein, a mounting hole is provided on the boss, the mounting hole is connected to the fan-shaped hole, a second fan-shaped hole is provided on the arc surface of the transition piece, and the first fan-shaped hole corresponds to the second fan-shaped hole in position.

[0016] Preferably, the cylindrical nut is arranged in the mounting hole, the horizontal surface of the transition piece contacts the edge strip, and the horizontal tail front joint is provided with an arc surface matching the arc surface of the transition piece;

[0017] The front joint of the horizontal tail can rotate along the arc surface of the transition piece, the bolt can rotate in the first sector-shaped hole and the second sector-shaped hole, and the cylindrical nut can rotate in the mounting hole.

[0018] Preferably, a first sliding groove and a through hole are provided on the rear main frame of the fuselage, and a second sliding groove is provided on the rear joint of the horizontal tail.

[0019] Preferably, the angle adjustment assembly comprises:

[0020] a sliding component, disposed in the first sliding groove;

[0021] a lifting rod, one end of which is connected to the slider, and the other end of which passes through the through hole;

[0022] a second connecting bolt, one end of which is capable of passing through the second sliding groove and the sliding component;

[0023] an adjusting nut, disposed at the other end of the lifting rod, and used to adjust the height of the lifting rod;

[0024] A fixing nut is provided at the other end of the lifting rod, and the fixing nut is used to lock the adjusting nut.

[0025] Preferably, the sliding component is a "J"-shaped structure, comprising a cavity and sliders arranged on both sides of the cavity, the sliders being provided with a first circular hole and a second circular hole, and the horizontal tail rear joint being arranged in the cavity.

[0026] Preferably, the lifting rod comprises a threaded rod; and the angle adjustment assembly further comprises:

[0027] a sliding bushing, disposed in the second sliding groove;

[0028] Among them, the second connecting bolt passes through the first circular hole, the sliding bushing and the second circular hole in sequence; when the adjusting nut is rotated, the height of the lifting rod is adjusted, and at the same time, the sliding bushing slides in the second sliding groove, and the slider slides in the first sliding groove, thereby driving the horizontal tail rear joint to rotate.

[0029] Preferably, the first chute includes:

[0030] a first sub-chute, for accommodating the slider;

[0031] The second sub-slot is parallel to the first sub-slot, and the second sub-slot is used to accommodate the slider.

[0032] Beneficial technical effects of this application:

[0033] 1. This application embeds the horizontal tail angle adjustment and tilting mechanism shaft assembly into the fuselage structure using a barrel nut, fully utilizing the internal space of the fuselage structure and reducing the impact of protruding structures and shapes on aerodynamics;

[0034] 2. The present invention adds a sliding bushing to the slideway of the rear joint of the horizontal tail to avoid direct line contact between the connecting bolt and the slideway, thus avoiding wear and tear of the mechanism;

[0035] 3. The present application can adjust any angle steplessly according to the requirements of the horizontal tail installation, thus solving the problem that the existing helicopter horizontal tail installation mechanism itself cannot adjust the angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 A schematic diagram of installing a horizontal tail on a helicopter provided in an embodiment of the present application;

[0037] Figure 2 This is a simplified example of a horizontal tail angle adjustment and tilting mechanism provided in an embodiment of the present application. Figure 1

[0038] Figure 3 This is a simplified example of a horizontal tail angle adjustment and tilting mechanism provided in an embodiment of the present application. Figure 2 ;

[0039] Figure 4 is a schematic diagram of a rotating shaft assembly provided in an embodiment of the present application;

[0040] Figure 5 is a schematic diagram of an angle adjustment component provided in an embodiment of the present application;

[0041] Among them, 1-horizontal tail; 101-horizontal tail front joint; 102-horizontal tail rear joint; 2-horizontal tail tilt mechanism; 3-rotating shaft assembly; 301-first connecting bolt; 302-transition piece; 303-cylinder nut; 4-front fuselage main frame; 5-angle adjustment assembly; 501-lifting rod; 502-sliding component; 503-first slide groove; 504-second slide groove; 505-sliding bushing; 506-second connecting bolt; 507-adjusting nut; 508-fixing nut; 6-rear fuselage main frame. DETAILED DESCRIPTION

[0042] In an embodiment of the present application, the present application provides a mechanism that can achieve stepless adjustment of the horizontal tail installation angle, meeting the demand for stepless adjustment of different horizontal tail installation angles.

[0043] The schematic diagram of the installation of the horizontal tail 1 on the helicopter and the schematic diagram of the horizontal tail angle adjustment and tilting mechanism are as follows: Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 5 shown.

[0044] Furthermore, the angle adjustment and tilting mechanism of the horizontal tail 1 includes a shaft assembly 3 and an angle adjustment assembly 5. The shaft assembly 3 is embedded in the front main frame 4 of the fuselage through a cylindrical nut 303. The installation angle of the horizontal tail 1 is adjusted through the angle adjustment assembly 5 as needed.

[0045] In the embodiments of this application, Figure 3 and Figure 4 As shown, the shaft assembly 3 consists of the tailplane front joint 101, a first connecting bolt 301, a transition piece 302, a cylindrical nut 303, and the fuselage front main frame 4. The cylindrical nut 303 is inserted into the mounting hole of the fuselage front main frame 4, and the angle is adjusted by rotating the cylindrical nut 303 around the axis of the mounting hole. The transition piece 302 mounted on the fuselage front main frame 4 mates with the arc surface on the tailplane front joint 101. Both the fuselage front main frame 4 and the transition piece 302 are provided with fan-shaped holes, allowing the tailplane front joint 101 to rotate with the cylindrical nut 303. The first connecting bolt 301 passes through the fuselage front main frame 4, the transition piece 302, and the tailplane front joint 101, connecting the cylindrical nut to complete the installation of the shaft assembly 3.

[0046] In the embodiments of this application, Figure 3 and Figure 5 As shown, the angle adjustment assembly 5 comprises the rear fuselage main frame 6, the rear tail joint 102, a sliding bushing 505, a second connecting bolt 506, a lifting rod 501, an adjusting nut 507, and a fixing nut 508. The sliding bushing 505 engages with the second guide groove 504 of the rear tail joint 102 to slide along the second guide groove 504. The sliding member 502 engages with the first guide groove 503 of the rear fuselage main frame 6 to move up and down along the first guide groove 503. The second connecting bolt 506 connects the sliding member 502, the sliding bushing 505, the rear tail joint 102, and the rear fuselage main frame 6.

[0047] The lifting rod 501 passes through the rear main frame 6 and is connected to the adjusting nut 507. Rotating the adjusting nut 507 causes the lifting rod 501 to slide along the first slide groove 503, thereby causing the sliding bushing 505 to slide in the second slide groove 504, ultimately rotating the horizontal stabilizer 1 about the shaft assembly 3. After the horizontal stabilizer 1 is rotated to a specific installation angle, the angle is fixed by tightening the fixing nut 508.

[0048] It should be noted that, in the present application, the horizontal tail angle adjustment tilt mechanism shaft assembly 3 is embedded into the front main frame 4 of the fuselage using a cylindrical nut 303, making full use of the internal space of the front main frame 4 of the fuselage, and reducing the impact of the protruding structure and protruding appearance on aerodynamics; the present application adopts the method of adding a sliding bushing 505 to the second slide groove 504 of the horizontal tail rear joint 102 to avoid direct line contact between the second connecting bolt and the second slide groove 504, thereby avoiding wear of the mechanism during movement; the present application can adjust any angle steplessly according to the installation requirements of the horizontal tail, thereby solving the problem that the existing helicopter horizontal tail installation mechanism itself cannot adjust the angle.

[0049] It should be noted that the helicopter's horizontal tail tilting mechanism has been successfully applied during the development of a certain type of military helicopter.

Claims

1. A helicopter horizontal tail stepless angle adjustment tilting mechanism, characterized in that: include: A shaft assembly is provided on the front main frame of the fuselage and is connected to the front joint of the horizontal tail; An angle adjustment assembly is provided on the rear main frame of the fuselage and is connected to the rear joint of the horizontal tail; The horizontal tail can be adjusted steplessly around the rotating shaft assembly through the angle adjustment assembly; a first slide groove and a through hole are provided on the rear main frame of the fuselage, and a second slide groove is provided on the rear joint of the horizontal tail; The angle adjustment component includes: a sliding component, disposed in the first sliding groove; a lifting rod, one end of which is connected to the slider, and the other end of which passes through the through hole; a second connecting bolt, one end of which is capable of passing through the second sliding groove and the sliding component; A sliding bushing is arranged in the second sliding groove; the sliding bushing slides in the second sliding groove, and the sliding block slides in the first sliding groove, thereby driving the horizontal tail rear joint to rotate.

2. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 1, characterized in that: The rotating shaft assembly comprises: a cylindrical nut, disposed in the front main frame of the fuselage; A transition piece is provided on the front main frame of the fuselage; wherein one side of the transition piece is an arc surface and the other side is a plane; A first connecting bolt, one end of which passes through the front joint of the horizontal tail, the transition piece and the front main frame of the fuselage in sequence, and is connected to the cylindrical nut.

3. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 2, characterized in that: The front main frame of the fuselage includes: An edge strip, wherein a first fan-shaped hole is provided on the edge strip; a web connected below the flange; The boss is connected to the edge strip and the web respectively; wherein, a mounting hole is provided on the boss, the mounting hole is connected to the fan-shaped hole, a second fan-shaped hole is provided on the arc surface of the transition piece, and the first fan-shaped hole corresponds to the second fan-shaped hole in position.

4. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 3, characterized in that: The cylindrical nut is arranged in the mounting hole, the horizontal surface of the transition piece contacts the edge strip, and the horizontal tail front joint is provided with an arc surface matching the arc surface of the transition piece; The front joint of the horizontal tail can rotate along the arc surface of the transition piece, the bolt can rotate in the first sector-shaped hole and the second sector-shaped hole, and the cylindrical nut can rotate in the mounting hole.

5. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 4, characterized in that: The angle adjustment assembly further includes: an adjusting nut, disposed at the other end of the lifting rod, and used to adjust the height of the lifting rod; A fixing nut is provided at the other end of the lifting rod, and the fixing nut is used to lock the adjusting nut.

6. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 5, characterized in that: The sliding component is a "J"-shaped structure, comprising a cavity and sliders arranged on both sides of the cavity, the sliders being provided with a first circular hole and a second circular hole, and the horizontal tail rear joint being arranged in the cavity.

7. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 6, characterized in that: The lifting rod includes a threaded rod; Wherein, the second connecting bolt passes through the first circular hole, the sliding bushing and the second circular hole in sequence; when the adjusting nut is rotated, the height of the lifting rod is adjusted.

8. The helicopter horizontal tail stepless angle adjustment and tilting mechanism according to claim 7, characterized in that: The first chute includes: a first sub-chute, for accommodating the slider; The second sub-slot is parallel to the first sub-slot, and the second sub-slot is used to accommodate the slider.

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