Control surface diagonal linkages and methods

Abstract

The application provides a control surface diagonal linkage device and method in the field of aircraft structure design, which comprises a missile body structure, an air rudder, a gas rudder surface, an air rudder sliding block, a gas rudder sliding block, a sliding groove rod and a sliding groove rod shaft, the air rudder is slidably connected to the sliding groove rod through the air rudder sliding block, the gas rudder surface is slidably connected to the sliding groove rod through the gas rudder sliding block, the air rudder and the gas rudder surface are respectively connected to the missile body structure, the sliding groove rod is connected to the missile body structure through the sliding groove rod shaft, and the sliding groove rod freely rotates around the sliding groove rod shaft. The 3 fixed shafts and 2 sliding blocks are diagonally linked, the transmission ratio of the air rudder and the gas rudder can be flexibly designed under the requirement of small size, the transmission relationship between the gas rudder and the air rudder can meet the actual control requirement by adjusting the rotation shaft point position and the relative size relationship between the sliding block and the rotation shaft point position, the sliding groove rod and the sliding groove rod shaft are matched, the air rudder and the gas rudder are reliably linked, and the method is simple and reliable.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design, and more specifically, to a control rudder diagonal linkage device and method thereof. Background Technology

[0002] At low initial speeds, the effectiveness of aerodynamic control surfaces is limited. For aircraft requiring significant maneuverability, aerodynamic control surfaces cannot provide sufficient control torque during this initial phase. Gas turbine control surfaces, utilizing the engine's exhaust gas flow field, can provide the necessary control torque during the initial stages of flight. Due to limited internal space, gas turbine control surfaces typically share a control source with aerodynamic control surfaces, achieved through a linkage mechanism. Current linkage mechanisms often employ rocker arm-linkage connections (parallelograms), but the transmission ratio is fixed at 1:1. Aerodynamic control surfaces are usually limited by deflection angles, preventing gas turbine control surfaces from reaching their maximum effectiveness. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the purpose of this invention is to provide a control rudder face diagonal linkage device and method, which enables flexible design of the transmission ratio of air rudders and gas rudders with relatively small size requirements.

[0004] According to the present invention, a control rudder surface diagonal linkage device includes: a projectile structure, an air rudder, a gas rudder surface, an air rudder slider, a gas rudder slider, a slide bar, and a slide bar shaft. The air rudder is slidably connected to the slide bar via the air rudder slider, and the gas rudder surface is slidably connected to the slide bar via the gas rudder slider. The air rudder and the gas rudder surface are respectively connected to the projectile structure. The slide bar is connected to the projectile structure via the slide bar shaft, and the slide bar can rotate freely around the slide bar shaft.

[0005] Preferably, the air rudder slider and the gas rudder slider are respectively placed in the groove of the slide bar, and the air rudder slider and the gas rudder slider slide freely along the groove.

[0006] Preferably, the air rudder and the gas rudder surfaces rotate around the rotation axis to achieve deflection.

[0007] Preferably, the slide bar shaft is located between the air rudder shaft and the gas rudder surface shaft.

[0008] Preferably, the positions of the air rudder pivot, the gas rudder pivot, and the slide bar pivot are kept on the same horizontal line.

[0009] Preferably, the midpoints of the air rudder slider, the gas rudder slider, and the slide bar axis are kept on the same straight line.

[0010] Preferably, the transmission relationship between the air rudder and the gas rudder is adjusted by the relative dimensions of the pivot point, the slide bar pivot point, the air rudder slider, and the gas rudder slider.

[0011] Preferably, the air rudder slider and the gas rudder slider are mounted on the air rudder and gas rudder surfaces, respectively.

[0012] Preferably, the gas-fuel control surfaces and the air control surfaces are diagonally connected to both sides of the projectile structure.

[0013] The present invention also provides a linkage method for controlling the diagonal linkage device of the control surface, including the following specific operation steps:

[0014] S1. The air rudder is deflected at a certain angle by the missile control system, and the air rudder slider rotates around the air rudder axis accordingly.

[0015] S2. The rotation of the air rudder slider drives the slide bar to rotate around the slide bar axis.

[0016] S3. The rotation of the slide bar causes the gas control surface slider to slide along the slide bar.

[0017] S4. The sliding of the gas rudder surface slider drives the rotation of the gas rudder surface to achieve linkage between the air rudder and the gas rudder.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] (1) The present invention uses a 3 fixed-axis 2 slider diagonal linkage design to achieve flexible design of transmission ratio of air rudder and gas rudder under small size requirements;

[0020] (2) By adjusting the position of the rotating shaft and the relative size relationship between the slider and the rotating shaft, the transmission relationship between the gas rudder and the air rudder can meet the actual control requirements.

[0021] (3) The present invention achieves reliable linkage between the air rudder and the gas rudder through the cooperation of the slide bar and the slide bar shaft. The method is simple and reliable. Attached Figure Description

[0022] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0023] Figure 1 This is a schematic diagram of the structure of the present invention;

[0024] Figure 2 This is a side view of the present invention.

[0025] The diagram shows: 1. Projectile structure; 2. Air rudder; 3. Gas rudder surface; 4. Air rudder slider; 5. Gas rudder slider; 6. Slide bar; 7. Slide bar shaft. Detailed Implementation

[0026] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0027] Example 1

[0028] According to the present invention, a control rudder surface diagonal linkage device is provided, such as Figure 1 As shown, the system includes: a projectile structure 1, an air rudder 2, a gas turbine control surface 3, an air rudder slider 4, a gas turbine slider 5, a slide bar 6, and a slide bar shaft 7. The air rudder slider 4 and the gas turbine slider 5 are respectively placed within the slide grooves of the slide bar 6, and slide freely along the slide grooves. The gas turbine control surface 3 and the air rudder 2 are diagonally connected to both sides of the projectile structure 1. The air rudder slider 4 and the gas turbine slider 5 are respectively mounted on the air rudder 2 and the gas turbine control surface 3, and rotate around their respective axes to achieve deflection. The air rudder 2 is slidably connected to the slide bar 6 via the air rudder slider 4, and the gas turbine control surface 3 is slidably connected to the slide bar 6 via the gas turbine slider 5. Both the air rudder 2 and the gas turbine control surface 3 are connected to the projectile structure 1. The slide bar 6 is connected to the projectile structure 1 via the slide bar shaft 7, and rotates freely around the slide bar shaft 7. The slide bar shaft 7 is located between the rotation axes of the air rudder 2 and the gas turbine control surface 3.

[0029] like Figure 2 As shown, the pivot points of the air rudder 2, the gas rudder 3, and the slide bar shaft 7 are all on the same horizontal line, and the midpoints of the air rudder slider 4, the gas rudder slider 5, and the slide bar shaft 7 are all on the same straight line. By adjusting the pivot points and the relative dimensions of the sliders to the pivot points, the transmission relationship between the gas rudder 3 and the air rudder 2 can be made to meet the actual control requirements.

[0030] Working principle: such as Figure 2 As shown, the air rudder 2 rotates around its pivot point, the slide bar 6 rotates around its pivot point, and the gas rudder surface 3 rotates around its pivot point. Two fixed sliders are attached to the air rudder 2 and the gas rudder surface 3, which can slide along the slide bar 6 to form this system. That is, rotating the air rudder 2 at a certain angle can drive the gas rudder surface 3 to make corresponding movements.

[0031] Example 2

[0032] The present invention also provides a linkage method for controlling the diagonal linkage device of the control surface, including the following specific operation steps:

[0033] S1. The air rudder 2 is deflected at a certain angle by the missile control system, and the air rudder slider 4 rotates around the air rudder axis accordingly.

[0034] S2, the rotation of the air rudder slider 4 drives the slide bar 6 to rotate around the slide bar shaft 7;

[0035] S3, the rotation of the slide bar 6 causes the gas rudder surface slider 5 to slide along the slide bar 6;

[0036] S4. The sliding of the gas rudder surface slider 5 drives the rotation of the gas rudder surface 3 to achieve linkage between the air rudder and the gas rudder.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A control rudder surface diagonal linkage device, characterized in that, include: The projectile structure includes (1), air rudder (2), gas rudder surface (3), air rudder slider (4), gas rudder slider (5), slide bar (6), and slide bar shaft (7). The air rudder (2) is slidably connected to the slide bar (6) via the air rudder slider (4), and the gas rudder surface (3) is slidably connected to the slide bar (6) via the gas rudder slider (5). The air rudder (2) and the gas rudder surface (3) are respectively connected to the projectile structure (1). The slide bar (6) is connected to the projectile structure (1) via the slide bar shaft (7), and the slide bar (6) can rotate freely around the slide bar shaft (7). The air rudder slider (4) and the gas rudder slider (5) are respectively placed in the groove of the slide bar (6), and the air rudder slider (4) and the gas rudder slider (5) slide freely along the groove; The air rudder (2) and the gas rudder surface (3) rotate around the rotating shaft to achieve deflection, and the slide bar shaft (7) is located between the rotating shaft of the air rudder (2) and the rotating shaft of the gas rudder surface (3); The air rudder slider (4) and the gas rudder slider (5) are respectively mounted on the air rudder (2) and the gas rudder surface (3); The gas rudder (3) and the air rudder (2) are diagonally connected to both sides of the projectile structure (1); The transmission relationship between the air rudder (2) and the gas rudder surface (3) is adjusted by the relative dimensions of the pivot point of the air rudder (2), the pivot point of the gas rudder surface (3), the position of the slide bar shaft (7), the air rudder slider (4), and the gas rudder slider (5).

2. The control rudder surface diagonal linkage device according to claim 1, characterized in that, The pivot points of the air rudder (2), the pivot points of the gas rudder surface (3), and the pivot point of the slide bar (7) are kept on the same horizontal line.

3. The control rudder surface diagonal linkage device according to claim 1, characterized in that, The midpoints of the air rudder slider (4), the gas rudder slider (5), and the slide bar shaft (7) are all on the same straight line.

4. A linkage method employing the control rudder surface diagonal linkage device according to any one of claims 1-3, characterized in that, The specific operations include the following: S1. The air rudder (2) is deflected by a certain angle under the control of the missile control system, and the air rudder slider (4) rotates around the air rudder axis accordingly. S2, The air rudder slider (4) rotates, causing the slide bar (6) to rotate around the slide bar shaft (7); S3. The rotation of the slide bar (6) drives the gas rudder slider (5) to slide along the slide bar (6); S4. The gas rudder slider (5) slides and drives the gas rudder surface (3) to rotate, so as to realize the linkage between the air rudder (2) and the gas rudder.

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