Binary thrust vector control surface of aircraft

Abstract

The invention belongs to the technical field of aerospace, and particularly relates to a binary thrust vector control surface, an upper wall, two side walls, a lower wall and a nozzle of an aircraft, a nozzle channel is defined by the upper wall, the two side walls and the lower wall, the nozzle is arranged in the nozzle channel, the lower wall comprises a fixed bearing section and a vector control surface hinged to the fixed bearing section, and the vector control surface is arranged in the nozzle channel. The vector control surface is driven by a connecting rod mechanism to deflect up and down and located behind an engine tail nozzle, and the efficiency of the control surface can be effectively improved through engine jet injection. The installation position is located at the tail of the aircraft, the farther from the center of gravity is, efficient control surface efficiency can be obtained through a long force arm, and the course control capacity of layout is improved. Meanwhile, a certain distance is reserved from the engine, the temperature is reduced to about 200 DEG C and is far away from the ultra-high-temperature environment, the service life is prolonged, and the design difficulty and the use cost are reduced.

Description

Technical Field

[0001] The present application belongs to the field of aerospace technology, and in particular relates to a dual thrust vector control surface of an aircraft. Background Art

[0002] For aircraft that require a certain degree of maneuverability, there are generally problems with insufficient nose-down capability at high angles of attack and excessive static instability in takeoff and landing configurations. To address these issues, most aircraft adjust their heading and attitude by setting a rudder or installing a vector engine. The rudder is close to the center of gravity of the aircraft, resulting in a small pitch moment and low efficiency; the vector engine has high adjustment efficiency, but the tail nozzle adjustment plate is in an ultra-high temperature environment of over 1000° for a long time, and is subjected to extremely high thermal and mechanical loads (high temperature, high pressure, high speed, vibration, thermal shock), with severe ablation and poor durability, making the design difficult and costly. Summary of the invention

[0003] In order to solve the above problems, the present application provides a dual thrust vector control surface of an aircraft, comprising:

[0004] The upper wall, the two side walls, the lower wall and the nozzle,

[0005] The upper wall, the two side walls and the lower wall form a nozzle channel, and the nozzle is placed in the nozzle channel, wherein the lower wall includes a fixed bearing section and a vector rudder surface hinged on the fixed bearing section, and the vector rudder surface is driven to deflect up and down by a connecting rod mechanism.

[0006] Preferably, the upper end of the vector rudder surface is fixedly hinged on the fixed bearing section, and the lower end is hinged to the rudder surface control rod, and the rudder surface control rod is hinged to the driving device, and the driving device drives the vector rudder surface to deflect up and down through the rudder surface control rod.

[0007] Preferably, the rudder surface control rod is connected to a sealing plate via a follower connecting rod, and the sealing plate is overlapped between the vector rudder surface and the fuselage skin.

[0008] Preferably, the sealing plate is fixedly connected to the follower connecting rod, and the follower connecting rod is fixedly connected to the rudder surface control rod, so that the sealing plate follows the movement of the rudder surface control rod and then overlaps with the vector rudder surface throughout the deflection process.

[0009] Preferably, the sealing plate is detachably connected to the follower connecting rod to facilitate replacement of the sealing plate.

[0010] Preferably, the sealing plate is connected to the follower connecting rod by bolts.

[0011] Preferably, the vector control surface is a wedge-shaped structure, including an outer skin, an inner skin and ribs between the outer skin and the inner skin.

[0012] Preferably, the inner skin is made of aluminum alloy, and the outer skin and ribs are made of composite materials.

[0013] Preferably, the inner skin surface is covered with a ceramic-based thermal insulation coating.

[0014] Preferably, the vector control surface is located a certain distance axially rearward of the nozzle.

[0015] Preferably, the certain distance satisfies that the temperature at the location of the vector rudder surface is less than 200 degrees.

[0016] The advantages of this application include: being located behind the tail nozzle of the engine, the engine jet can be effectively used to improve the efficiency of the control surface; the installation position is located at the tail of the aircraft, and the farther away from the center of gravity, the more efficient the control surface efficiency can be obtained through a longer lever arm, and the heading control ability of the layout can be improved. At the same time, it is at a certain distance from the engine, the temperature is reduced to about 200°, away from the ultra-high temperature environment, the service life is increased, and the design difficulty and use cost are reduced.

[0017] The inner skin of the rudder is covered with a ceramic-based thermal insulation coating to reduce the internal temperature. The ribs and outer skin are made of composite materials to significantly reduce the weight of the rudder. At the same time, a follow-up sealing structure is set at the front edge of the rudder. The structure is simple. The sealing plate is connected by a follow-up connecting rod and the rudder control rod. It can follow the deflection of the rudder to achieve seam sealing, ensure the continuity of the aerodynamic shape of the fuselage, and improve the aerodynamic performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a side cross-sectional view of the tail of an aircraft according to a preferred embodiment of the present application.

[0019] Figure 2 This is an axial view of the tail of an aircraft according to a preferred embodiment of the present application.

[0020] Figure 3 This is a simplified diagram of the vector control surface structure of a preferred embodiment of the present application.

[0021] Figure 4 This is a schematic diagram of a vector control surface in a preferred embodiment of the present application. DETAILED DESCRIPTION

[0022] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0023] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0024] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0025] like Figure 1-Figure 4 As shown, the present application provides a dual thrust vector control surface of an aircraft, comprising:

[0026] The upper wall 3, the two side walls 4, the lower wall and the nozzle 2,

[0027] The upper wall 3, the two side walls 4 and the lower wall form a nozzle channel, and the nozzle 2 is placed in the nozzle channel, wherein the lower wall includes a fixed bearing section and a vector rudder surface 1 hinged on the fixed bearing section, and the vector rudder surface 1 is driven to deflect up and down by a connecting rod mechanism.

[0028] In some optional embodiments, the upper end of the vector rudder surface 1 is fixedly hinged on the fixed bearing section, and the lower end is hinged to the rudder surface control rod 5, and the rudder surface control rod 5 is hinged to the driving device, and the driving device drives the vector rudder surface 1 to deflect up and down through the rudder surface control rod 5.

[0029] In some optional embodiments, the control surface control rod 5 is connected to a sealing plate 7 via a follower connecting rod 6, and the sealing plate 7 is overlapped between the vector control surface 1 and the fuselage skin.

[0030] In some optional embodiments, the sealing plate 7 is fixedly connected to the follower connecting rod 6, and the follower connecting rod 6 is fixedly connected to the rudder surface control rod 5, so that the sealing plate 7 follows the movement of the rudder surface control rod 5, and then overlaps with the vector rudder surface 1 throughout the deflection process.

[0031] In some optional embodiments, the sealing plate 7 is detachably connected to the follower connecting rod 6 to facilitate replacement of the sealing plate 7 .

[0032] In some optional embodiments, the sealing plate 7 is connected to the follower connecting rod 6 by bolts.

[0033] In some optional embodiments, the vector control surface 1 is a wedge-shaped structure, including an outer skin, an inner skin, and ribs between the outer skin and the inner skin.

[0034] In some optional embodiments, the inner skin is made of aluminum alloy, and the outer skin and the ribs are made of composite materials.

[0035] In some optional embodiments, the inner skin surface is covered with a ceramic-based thermal insulation coating.

[0036] In some optional embodiments, the vector control surface 1 is located a certain distance axially rearward of the nozzle 2 .

[0037] In some optional implementations, the certain distance satisfies that the temperature at the location of the vector control surface 1 is less than 200 degrees.

[0038] The advantages of this application include: being located behind the tail nozzle of the engine, the engine jet can be effectively used to improve the efficiency of the control surface; the installation position is located at the tail of the aircraft, and the farther away from the center of gravity, the more efficient the control surface efficiency can be obtained through a longer lever arm, and the heading control ability of the layout can be improved. At the same time, it is at a certain distance from the engine, the temperature is reduced to about 200°, away from the ultra-high temperature environment, the service life is increased, and the design difficulty and use cost are reduced.

[0039] The inner skin of the rudder is covered with a ceramic-based thermal insulation coating to reduce the internal temperature. The ribs and outer skin are made of composite materials to significantly reduce the weight of the rudder. At the same time, a follow-up sealing structure is set at the front edge of the rudder. The structure is simple. The sealing plate is connected by a follow-up connecting rod and the rudder control rod. It can follow the deflection of the rudder to achieve seam sealing, ensure the continuity of the aerodynamic shape of the fuselage, and improve the aerodynamic performance of the aircraft.

[0040] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A dual thrust vectoring control surface for an aircraft, characterized in that: include: The upper wall (3), the two side walls (4), the lower wall and the nozzle (2), An upper wall (3), two side walls (4), and a lower wall form a nozzle channel, and a nozzle (2) is placed in the nozzle channel, wherein the lower wall comprises a fixed bearing section and a vector rudder surface (1) hinged on the fixed bearing section, and the vector rudder surface (1) is driven to deflect up and down by a connecting rod mechanism.

2. The dual thrust vectoring control surface of an aircraft according to claim 1, characterized in that: The upper end of the vector rudder surface (1) is fixedly hinged on the fixed bearing section, and the lower end is hinged to the rudder surface control rod (5). The rudder surface control rod (5) is hinged to the driving device, and the driving device drives the vector rudder surface (1) to deflect up and down through the rudder surface control rod (5).

3. The dual thrust vectoring control surface of an aircraft according to claim 1, characterized in that: The rudder surface control rod (5) is connected to a sealing plate (7) via a follower connecting rod (6), and the sealing plate (7) is overlapped between the vector rudder surface (1) and the fuselage skin.

4. The dual thrust vectoring control surface of an aircraft according to claim 3, characterized in that: The sealing plate (7) is fixedly connected to the follower connecting rod (6), and the follower connecting rod (6) is fixedly connected to the rudder surface control rod (5), so that the sealing plate (7) moves with the rudder surface control rod (5) and is then overlapped with the vector rudder surface (1) throughout the deflection process.

5. The dual thrust vectoring control surface for an aircraft according to claim 4, characterized in that: The sealing plate (7) is detachably connected to the follower connecting rod (6), so that the sealing plate (7) can be easily replaced.

6. The dual thrust vectoring control surface for an aircraft according to claim 5, characterized in that: The sealing plate (7) is connected to the follower connecting rod (6) via bolts.

7. The dual thrust vectoring control surface for an aircraft according to claim 1, characterized in that: The vector control surface (1) is a wedge-shaped structure, comprising an outer skin, an inner skin and ribs between the outer skin and the inner skin.

8. The dual-dimensional thrust vectoring control surface of an aircraft according to claim 7, characterized in that: The inner skin is made of aluminum alloy, and the outer skin and ribs are made of composite materials.

9. The dual thrust vectoring control surface for an aircraft according to claim 9, characterized in that: The inner skin surface is covered with a ceramic-based thermal insulation coating.

10. The dual-dimensional thrust vectoring control surface of an aircraft according to claim 1, characterized in that: The vector control surface (1) is located a certain distance axially backward from the nozzle (2).

11. The dual-dimensional thrust vectoring control surface of an aircraft according to claim 1, characterized in that: The certain distance satisfies that the temperature at the location of the vector control surface (1) is less than 200 degrees.

Images