CN115783240A - A Helicopter Composite Vertical Stabilizer - Google Patents

Abstract

The application provides a vertical stabilizer of helicopter composite structure, includes: the rudder surface comprises a sandwich structure; the side end plate comprises a frame beam structure and a sandwich structure, wherein the rudder surface is movably connected with the side end plate, and the side end plate is fixedly connected with the end rib of the horizontal stabilizing surface; the application provides a pair of high-speed helicopter composite structure perpendicular stabilizer has contained frame beam structure and sandwich type structure simultaneously, has both simplified perpendicular stabilizer's constitution, has reduced its assembly degree of difficulty, has made things convenient for the dismantlement maintenance of activity rudder face erection joint, has shortened its construction bolt's length again, has reduced the moment of flexure that the bolt bore.

Description

A Helicopter Composite Vertical Stabilizer

technical field

The application belongs to the technical field of helicopter structure design, and in particular relates to a composite configuration vertical stabilizer of a high-speed helicopter.

Background technique

In the field of high-speed helicopter design, in order to solve the assembly problem of the vertical stabilizer with a narrow airfoil, designers usually design it as a sandwich structure. Provide connection joints that can be easily disassembled for maintenance. At the same time, since a bolt that runs through the entire thickness of the vertical stabilizer is needed to fix the vertical stabilizer to the horizontal stabilizer, the bolt bears a large bending moment, which virtually increases the diameter and weight of the bolt.

Or in order to solve the problem of too long bolts, it is necessary to embed metal inserts in the sandwich structure, and open countersunk holes on the inserts, so that the bolts sink into the inserts, and then block the countersunk holes of the inserts with plugging caps , On the one hand, this increases the complexity of the process. On the other hand, it is not convenient to observe the bolts in daily maintenance because the bolts are sunk into the insert.

The vertical stabilizer of a helicopter is usually installed on the metal angle material riveted on the horizontal stabilizer surface. Since the angle material protrudes from the aerodynamic shape surface, on the one hand, it will destroy the overall aesthetics of the helicopter, and on the other hand, it will have an adverse effect on the aerodynamic characteristics of the helicopter. For For high-speed helicopters, this disadvantage is even more obvious.

Contents of the invention

In view of the above technical problems, the application provides a vertical stabilizer of a helicopter composite configuration, including:

Rudder surfaces, including sandwich construction;

The side end plate includes a frame beam structure and a sandwich structure, wherein the rudder surface is movably connected to the side end plate, and the side end plate is fixedly connected to the end rib of the horizontal stabilizer.

Preferably, the side end panels include:

The half section of the side end plate, including the frame beam structure;

The lower half of the side end plate includes a sandwich structure; wherein, the half of the side end plate is riveted to the lower half of the side end plate.

Preferably, the frame and beam structure includes:

front beam;

a rear beam, the rear beam is connected to the front beam through a lower end rib, a middle rib and an upper end rib;

The skin covers the front beam, the rear beam, the lower end rib, the middle rib and the upper end rib.

Preferably, the sandwich structure includes:

Composite I-beams;

a foam interlayer bonded to the glue;

A composite skin overlies the composite I-beam and foam sandwich.

Preferably, the rudder surface and the side end plates are determined by partitioning the vertical stabilizer based on the maneuverability, stability, manufacturability and simplicity of structural force transmission of the aircraft.

Preferably, the upper half of the side end plate and the lower half of the side end plate are determined by partitioning the side end plate based on the maneuverability, stability, manufacturability and simplicity of structural force transmission of the aircraft.

Preferably, the front beam includes:

The upper half of the front beam is set at the aerodynamic pressure center of the airfoil;

The lower half of the front beam is connected to the upper half of the front beam, wherein the lower half of the front beam is perpendicular to the end rib chord line of the horizontal stabilizer;

The backrest includes:

The upper half of the rear beam, the arrangement of the upper half of the rear beam is determined based on the hinge joint of the rudder surface;

The lower half of the rear beam is connected to the upper half of the rear beam, wherein the lower half of the rear beam is perpendicular to the end rib chord line of the horizontal stabilizer.

Preferably, the rudder surface is connected to the upper half of the rear beam through a hinge joint; the side end plate is connected to a cylindrical nut fixed inside the end rib of the horizontal stabilizer through bolts.

Beneficial technical effect of the application:

This application provides a high-speed helicopter composite configuration vertical stabilizer, which includes a frame beam structure and a sandwich structure, which not only simplifies the composition of the vertical stabilizer, reduces the difficulty of its assembly, and facilitates the installation of joints on the movable rudder surface The disassembly and maintenance of the utility model shortens the length of its installation bolts and reduces the bending moment on the bolts.

Description of drawings

Fig. 1 is a structural schematic diagram of a vertical stabilizer of a helicopter composite configuration provided by the embodiment of the present application;

Fig. 2 is a schematic diagram of the half-section structure of the side end plate provided by the embodiment of the present application;

Fig. 3 is the enlarged view of I place in Fig. 2 that the embodiment of the application provides;

Fig. 4 is a cross-sectional view at A-A in Fig. 3 provided by the embodiment of the present application.

Detailed ways

Please refer to Figures 1-4. This application provides a composite vertical stabilizer for high-speed helicopters, which includes a frame-beam structure and a sandwich structure, which not only simplifies the composition of the vertical stabilizer, but also reduces its assembly difficulty. The dismantling and maintenance of the movable rudder surface installation joint is facilitated, the length of its installation bolt is shortened, and the bending moment borne by the bolt is reduced. At the same time, it provides a vertical stabilizer installation method, which not only improves the overall aesthetics of the helicopter, but also maintains the aerodynamic characteristics of the helicopter.

In the embodiment of this application, this application provides a high-speed helicopter composite configuration vertical stabilizer and its installation. The present invention divides the vertical stabilizer into rudder surfaces and side end plates according to different functions, wherein the side end plates are fixed on the horizontal stabilizer. On the ribs at the end of the face.

It should be noted that, considering various factors such as the different stress forms of the side end plates, the maintenance of the rudder surface installation joints, the disassembly of the side end plates, and the manipulation of the rudder surface, the side end plates are further subdivided into side end plates half and the lower half of the side end plate. Among them, the rudder surface is a sandwich structure, which is fixed to the half-section rear beam on the side end plate through two sets of hinge joints.

Among them, the half section of the side end plate is a frame beam structure, which is composed of front beam, rear beam, lower end rib, middle rib, upper end rib and skin. The arrangement of the half-section of the front beam on the side end plate comprehensively considers the position of the aerodynamic pressure center and the position of the installation point of the side end plate on the horizontal stabilizer. The arrangement of the rear beam of the side end plate takes comprehensive consideration of the installation and maintenance of the rudder surface and the position of the installation point of the side end plate on the horizontal stabilizer.

Furthermore, the arrangement of the middle ribs takes into account the load transmission, the installation of the rudder surface control mechanism and the movement space, etc. The skin is to be riveted on beams and ribs to facilitate load transmission. At the same time, in order to facilitate the installation and maintenance of the rudder surface control mechanism, a detachable cover may be provided on the skin.

In a feasible implementation manner, the lower half of the side end plate is a sandwich structure, riveted to the half of the side end plate. There is no unique way to subdivide the side end plate into the half section and the lower half section of the side end plate, and various factors such as load transmission, structural weight, and manufacturability should be considered comprehensively. The vertical stabilizer is mounted in barrel nuts secured to the end ribs of the horizontal stabilizer.

Specifically, the application consists of the rudder surface, the half section of the side end plate, the lower half of the side end plate, etc.; the half section of the side end plate and the lower half of the side end plate are designed as different structural forms, respectively frame Beam structure, sandwich structure; the side end plate is fixed in the cylindrical nut installed on the end rib of the horizontal stabilizer, which reduces the influence on the aerodynamic characteristics of the aircraft caused by the installation of the side end plate in the past. The block method of the vertical stabilizer is not unique and is not limited here.

In other embodiments of the present application, as shown in accompanying drawings 1 to 4, the present application consists of the rudder I, the half section II of the side end plate, and the lower half section III of the side end plate, wherein the half section II of the side end plate is The frame beam structure consists of the upper half of the front beam 1, the lower half of the front beam 2, the upper half of the rear beam 3, the lower half of the rear beam 4, the lower rib 5, the middle rib 6, the upper rib 7, the first skin 8, The second skin is composed of 9 and so on.

Among them, the rudder I and the lower half of the side end plate III are sandwich structures. The upper half of the front beam 1 is arranged at the aerodynamic pressure center of the airfoil, which improves the efficiency of bearing and transmitting aerodynamic loads. The arrangement of the upper half section 3 of the rear beam mainly considers the installation and maintenance of the rudder surface hinge joints, and the distance between the web surface and the rudder surface should not be too far or too close. Too far will increase the additional bending moment of the hinge joint lugs. It is beneficial to the lightweight design of the structural weight, and if it is too close, it is easy to cause the rudder surface to interfere with the rear spar web surface.

In this embodiment, the distance between the web surface of the upper half of the rear beam and the rudder surface is required to be 5-10 mm. The lower half section 2 of the front beam and the lower half section 4 of the back beam are perpendicular to the chord line of the flat end rib 11, which is convenient for the arrangement and installation of the barrel nut 12.

Wherein, the middle rib 6 is arranged at the bending place of the front beam and the rear beam, and should be as close as possible to the hinge joint of the rudder surface, so as to facilitate the transmission of the load of the rudder surface. The lower half of the front beam 3, the lower half of the rear beam 4, the lower end rib 5, the middle rib 6, and the skin 9 form a closed box section, which is not only convenient for load transmission, but also provides installation and movement space for the rudder surface control mechanism, and is convenient. The removal and inspection of side end plate bolts 10 are carried out.

The application provides a high-speed helicopter composite configuration vertical stabilizer and its installation, which not only simplifies the composition of the vertical stabilizer, reduces the difficulty of its assembly, facilitates the disassembly and maintenance of the movable rudder surface installation joint, but also shortens the length of the installation bolts. The length reduces the bending moment on the bolt. At the same time, it provides a vertical stabilizer installation method, which not only improves the overall aesthetics of the helicopter, but also maintains the aerodynamic characteristics of the helicopter.

Claims (8)

1. A helicopter composite configuration vertical stabilizer comprising:

the rudder surface comprises a sandwich structure;

and the side end plate comprises a frame beam structure and a sandwich structure, wherein the rudder surface is movably connected with the side end plate, and the side end plate is fixedly connected with the horizontal stabilizing surface end rib.

2. A helicopter composite configuration vertical stabilizer according to claim 1, wherein said side end plates comprise:

the upper half section of the side end plate comprises a frame beam structure;

the lower half section of the side end plate comprises a sandwich structure; and the upper half section of the side end plate is riveted with the lower half section of the side end plate.

3. A helicopter composite configuration vertical stabilizer according to claim 2, wherein said frame beam structure comprises:

a front beam;

a rear beam connected with the front beam by a lower end rib, a middle rib and an upper end rib;

and the skin covers the front beam, the rear beam, the lower end rib, the middle rib and the upper end rib.

4. A helicopter composite configuration vertical stabilizer according to claim 3, characterized in that said sandwich structure comprises:

a composite i-beam;

a foam interlayer bonded to the adhesive;

and the composite material skin covers the composite material I-beam and the foam interlayer.

5. A helicopter composite configuration vertical stabilizer according to claim 2, characterized in that said rudder surfaces and said side end plates are zoned based on the maneuverability, stability, manufacturability and structural force transfer simplicity of the aircraft.

6. A helicopter composite configuration vertical stabilizer according to claim 5, wherein said side end plate upper half and side end plate lower half are determined in sections based on the maneuverability, stability, manufacturability, and structural force transfer simplicity of the aircraft.

7. A helicopter composite configuration vertical stabilizer according to claim 3, wherein said front beam comprises:

the upper half section of the front beam is arranged at the pneumatic pressure center of the wing profile;

the lower half section of the front beam is connected with the upper half section of the front beam, and the lower half section of the front beam is vertical to a chord line of an end rib of the horizontal stabilizing surface;

the back beam includes:

a rear upper beam half, the arrangement of which is determined based on the hinge joint of the rudder surface;

and the lower half section of the back beam is connected with the upper half section of the back beam, wherein the lower half section of the back beam is vertical to a chord line of the end rib of the horizontal stabilizing surface.

8. A helicopter composite profile vertical stabilizer according to claim 7, wherein said rudder surface is connected to said rear beam upper half by a hinge joint; the side end plate is connected with a cylindrical nut fixed inside the horizontal stabilizing face end rib through a bolt.

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