CN104875898A - Tail jet nozzle assembly used for airplane and airplane with same - Google Patents

Abstract

The invention discloses an aircraft tail nozzle assembly and an aircraft with the same. The aircraft tail nozzle assembly includes: an exhaust pipe, one end of which is connected to the aircraft engine; an adapter section, one end of which is connected to the other end of the exhaust pipe; a tail nozzle, which is connected to the The other end is pivotally connected, wherein, the exhaust pipe and the transition section are used to transfer the jet discharged from the aircraft engine to the tail nozzle, and the tail nozzle is connected to the rotary The connection section is relatively pivoted to control the discharge direction of the jet when it is discharged from the tail nozzle. In the aircraft tail nozzle assembly of the present invention, the tail nozzle is pivotally connected to the other end of the transition section, so that the flow rate of the jet when it is discharged from the tail nozzle is controlled by pivoting relative to the transition section. Discharge direction, so as to control the direction of the torque provided by the jet to the aircraft, so that the tail nozzle can provide the aircraft with omni-directional torque.

Description

Aircraft tail nozzle assembly and aircraft with same

technical field

The invention relates to the technical field of aircraft, in particular to an aircraft tail nozzle assembly and an aircraft with the same.

Background technique

The tail nozzle of the existing aircraft usually only has the maneuverability to provide the aircraft with the maneuverability in the pitch direction, and does not possess the omnidirectional maneuverability.

Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Contents of the invention

It is an object of the present invention to provide an aircraft tail nozzle assembly which overcomes or at least alleviates at least one of the aforementioned disadvantages of the prior art.

To achieve the above purpose, the present invention provides an aircraft tail nozzle assembly. The aircraft tail nozzle assembly includes: an exhaust pipe, one end of the exhaust pipe is connected to the aircraft engine; an adapter section, one end of the adapter section is connected to the other end of the exhaust pipe; the tail nozzle pipe, the tail nozzle is pivotally connected to the other end of the transition section, wherein the exhaust pipe and the transition section are used to transfer the jet exhaust from the aircraft engine to the The tail nozzle, the tail nozzle controls the discharge direction of the jet when it is discharged from the tail nozzle by pivoting relative to the transition section, so as to control the torque provided by the jet to the aircraft direction.

Preferably, the end surface of the end of the tail nozzle connected to the transition section is adapted to the shape of the end surface of the transition section connected to the tail nozzle, so that the tail nozzle and the The transition sections are sealed and connected to each other; the shape of the end surface of the other end of the tail nozzle is suitable for the direction of the force provided by the jet to the aircraft when the jet is discharged from the tail nozzle. The flight direction is at an angle; the shape of the tail nozzle is a curved shape, which can make the jet gas entering the tail nozzle meander in the tail nozzle and then be discharged.

Preferably, the shape of the exhaust pipe is a curved shape, so that the jet gas discharged from the aircraft engine entering the exhaust pipe can meander in the exhaust pipe and then be transferred to the transition section.

Preferably, the shape of the transition section is a curved shape, so that the jet gas discharged from the aircraft engine entering the exhaust pipe can meander in the exhaust pipe and then be delivered to the tail nozzle.

Preferably, the tail nozzle, the exhaust pipe and the transition section are all S-shaped bends.

Preferably, there is an included angle between the central axis of the transition section and the axis of the aircraft engine.

Preferably, the tail nozzle includes the outer wall of the tail nozzle and the inner wall of the tail nozzle, the inner wall of the tail nozzle is provided with a first limit groove and a second limit groove; the transition section is provided with a transfer The first limit groove of the transition section and the second limit groove of the transfer section; wherein, the first limit groove of the transfer section is matched with the first limit groove through the first rolling bearing, and the second limit groove of the transfer section The limiting groove cooperates with the second limiting groove through the second rolling bearing, so that the transition section is relatively pivotally connected to the tail nozzle.

Preferably, the aircraft tail nozzle assembly further includes a driving steering device, the driving steering device is arranged on the aircraft and connected to the outer wall of the tail nozzle, and is used to drive the tail nozzle relative to the The transition section rotates.

The present invention also provides an aircraft, which includes the above-mentioned aircraft tail nozzle assembly, and the aircraft tail nozzle assembly is in two groups.

Preferably, the included angle between the central axis of the transition section of one group of the aircraft tail nozzle assembly and the axis of the aircraft engine is 15 degrees to 30 degrees, and the other group of the aircraft tail nozzles The included angle between the central axis of the transition section of the assembly and the axis of the aircraft engine is 15° to 30°.

In the aircraft tail nozzle assembly of the present invention, the tail nozzle is pivotally connected to the other end of the transition section, so that the flow rate of the jet when it is discharged from the tail nozzle is controlled by pivoting relative to the transition section. Discharge direction, so as to control the direction of the torque provided by the jet to the aircraft, so that the tail nozzle can provide the aircraft with omni-directional torque.

Description of drawings

Fig. 1 is a schematic structural view of an aircraft tail nozzle assembly according to an embodiment of the present invention.

FIG. 2 is a schematic diagram of the connection structure between the tail nozzle and the adapter of the aircraft tail nozzle assembly shown in FIG. 1 .

Fig. 3 is a structural schematic diagram of the tail nozzle and the driving steering device in the aircraft tail nozzle assembly shown in Fig. 1 .

Reference signs:

1 exhaust pipe 5 drive steering 2 Airplane engine 6 first rolling bearing 3 transition section 7 Second rolling bearing 4 tail nozzle 41 Outer wall of tail nozzle 42 Inner wall of tail nozzle

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.

The aircraft tail nozzle assembly of the present invention includes an exhaust pipe, a transition section and a tail nozzle. in,

One end of the exhaust pipe is connected with the aircraft engine, the other end is connected with the transition section, and the other end of the transition section is pivotally connected with the tail nozzle. The exhaust pipe and the transition section are used to transfer the jet discharged from the aircraft engine to the tail nozzle, and the tail nozzle controls the discharge direction of the jet when it is discharged from the tail nozzle by pivoting relative to the transition section, thereby controlling The direction of the moment the jet provides to the aircraft.

In the aircraft tail nozzle assembly of the present invention, the tail nozzle is pivotally connected to the other end of the transition section, so that the flow rate of the jet when it is discharged from the tail nozzle is controlled by pivoting relative to the transition section. Discharge direction, so as to control the direction of the torque provided by the jet to the aircraft, so that the tail nozzle can provide the aircraft with omni-directional torque.

Fig. 1 is a schematic structural view of an aircraft tail nozzle assembly according to an embodiment of the present invention. FIG. 2 is a schematic diagram of the connection structure between the tail nozzle and the adapter of the aircraft tail nozzle assembly shown in FIG. 1 . Fig. 3 is a structural schematic diagram of the tail nozzle and the driving steering device in the aircraft tail nozzle assembly shown in Fig. 1 .

The aircraft tail nozzle assembly shown in FIG. 1 includes an exhaust pipe 1 , an adapter section 3 , a driving steering device 5 and a tail nozzle 4 .

Referring to FIG. 1 , the shape of the exhaust pipe 1 is a curved shape, so that the jet gas discharged from the aircraft engine 2 entering the exhaust pipe 1 can meander in the exhaust pipe 1 and then be transferred to the transition section 3 . Specifically, in this embodiment, the shape of the exhaust pipe 1 is S-shaped.

Referring to FIG. 1 , the shape of the transition section 3 is curved, so that the jet gas discharged from the aircraft engine 2 entering the exhaust pipe 1 can be delivered to the tail nozzle 4 after meandering in the exhaust pipe 1 . Specifically, in this embodiment, the shape of the transition section 3 is S-shaped.

In this embodiment, the exhaust duct 1 and the transition section 3 are smooth and transitional in appearance, and the end face of the end of the exhaust duct 1 connected to the aircraft engine is perpendicular to the engine axis (left-right direction in the figure), and the exhaust The end surface of the other end of the channel 1 is perpendicular to the centerline of the transition section 3 . The transition section 3 is cylindrical, and the two end surfaces of the two ends of the transition section are circular. Referring to FIG. 1 , in this embodiment, there is an included angle between the central axis of the transition section 3 and the axis of the aircraft engine 2 .

Referring to Fig. 1, in this embodiment, the end surface of the end face of the end nozzle 4 connected to the adapter section 3 is adapted to the shape of the end face of the end nozzle 4 connected to the adapter section 3, so that the tail nozzle 4 It is sealed and connected with the transition section 3; the shape of the end surface of the other end of the tail nozzle 4 is suitable for making the self-jet discharge from the tail nozzle 4, the direction of the force provided by the jet for the aircraft is at an angle to the flight direction of the aircraft . Specifically, in this embodiment, the section of the end is flat, and the ratio of the height (the up-down direction in the figure) to the width (the direction perpendicular to the paper in the figure) is 0.5-0.25.

Referring to FIG. 1 , the shape of the tail nozzle 4 is a curved shape, which can make the jet gas entering the tail nozzle 4 meander in the tail nozzle 4 and then be discharged. Specifically, in this embodiment, the shape of the tail nozzle 4 is S-shaped.

Referring to Fig. 1, in this embodiment, the tail nozzle 4 includes the outer wall 41 of the tail nozzle and the inner wall 42 of the tail nozzle, and the inner wall 42 of the tail nozzle is provided with a first limiting groove and a second limiting groove; 3 is provided with the first limit groove of the transfer section and the second limit groove of the transfer section; wherein, the first limit groove of the transfer section cooperates with the first limit groove through the first rolling bearing 6, and the first limit groove of the transfer section The second limiting groove cooperates with the second limiting groove through the second rolling bearing 7, so that the transition section 3 and the tail nozzle 4 are relatively pivotally connected.

In this embodiment, through the above-mentioned cooperation, the tail nozzle 4 and the transition section 3 are relatively pivoted, so as to control the discharge direction of the jet when it is discharged from the tail nozzle 4, and then achieve the purpose of controlling the torque provided by the jet to the aircraft. direction purpose.

Referring to FIG. 1 , in this embodiment, the aforementioned pivoting is controlled by setting a driving steering device 5 . Specifically, the driving and steering device 5 is arranged on the aircraft and is connected with the outer wall 41 of the tail nozzle for driving the tail nozzle 4 to rotate relative to the transition section 3 . More specifically, in this embodiment, there are two driving and steering devices 5 , and the outer wall of the tail nozzle 4 is provided with two lifting lugs, and the driving and steering devices 5 are respectively connected to one of the lifting lugs. The above-mentioned driving and steering device 5 performs telescopic movement through power, and converts the kinetic energy provided by the telescopic movement into the rotational moment of the tail nozzle.

In this embodiment, the driving steering device 5 is an actuator. It can be understood that the drive steering device can also use other devices as required. For example, hydraulic pistons, electric telescopic sleeves, connecting rods and other methods. As long as the purpose of the present invention can be achieved in this manner.

The present invention also provides an aircraft, which includes the above-mentioned aircraft tail nozzle assembly, and the aircraft tail nozzle assembly is in two groups.

Advantageously, the included angle between the central axis of the transition section 3 of one group of aircraft tail nozzle assemblies and the axis of the aircraft engine 2 is 15 degrees to 30 degrees, and the rotation angle of the other group of aircraft tail nozzle assemblies The included angle between the central axis of the connecting section 3 and the axis of the aircraft engine 2 is 15° to 30°.

It can be understood that if the above included angles are in the same coordinate system, if one set of included angles is positive, the other set of included angles will be negative.

Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: they can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and these The modification or replacement does not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (10)

1. A tail nozzle assembly for an aircraft, comprising: An exhaust pipe (1), one end of the exhaust pipe (1) is connected with the aircraft engine (2); A transition section (3), one end of the transition section (3) is connected to the other end of the exhaust pipe (1); A tail nozzle (4), the tail nozzle (4) is pivotally connected to the other end of the transition section (3), wherein, The exhaust pipe (1) and the transition section (3) are used to transfer the jet discharged from the aircraft engine (2) to the tail nozzle (4), and the tail nozzle (4) The discharge direction of the jet when it is discharged from the tail nozzle (4) is controlled by pivoting relative to the transition section (3), thereby controlling the direction of the moment provided by the jet to the aircraft. 2. aircraft tail nozzle assembly as claimed in claim 1, is characterized in that, the end face of one end that described tail nozzle (4) is connected with described transition section (3) is connected with described transition section (3) ) is adapted to the end face shape of one end connected to the tail nozzle (4), so that the tail nozzle (4) and the transition section (3) are sealed and connected to each other; the tail nozzle (4 ) The shape of the other end face of the other end is suitable for making from the jet when it is discharged from the tail nozzle (4), the direction of the force provided by the jet for the aircraft is at an angle to the direction of flight of the aircraft; the tail The shape of the nozzle pipe (4) is a curved shape, which can make the jet gas entering the tail nozzle pipe (4) meander in the tail nozzle pipe (4) and then be discharged. 3. aircraft tail nozzle assembly as claimed in claim 2, is characterized in that, the shape of described exhaust pipe (1) is curved shape, thereby can make the described aircraft that enters described exhaust pipe (1) The jet gas discharged from the engine (2) meanders in the exhaust pipe (1) and then is delivered to the transition section (3). 4. The aircraft tail nozzle assembly as claimed in claim 3, characterized in that, the shape of the transition section (3) is a curved shape, so that the aircraft entering the exhaust pipe (1) can The jet gas discharged from the engine (2) meanders in the exhaust pipe (1) and then is delivered to the tail nozzle (4). 5. The aircraft tail nozzle assembly according to claim 4, characterized in that, the tail nozzle (4), the exhaust pipe (1) and the transition section (3) are all S-shaped bends. 6. The aircraft tail nozzle assembly according to claim 5, characterized in that there is an included angle between the central axis of the transition section (3) and the axis of the aircraft engine (2). 7. aircraft tail nozzle assembly as claimed in claim 1, is characterized in that, described tail nozzle (4) comprises tail nozzle outer wall (41) and tail nozzle inner wall (42), and in described tail nozzle The wall (42) is provided with a first limiting groove and a second limiting groove; The transition section (3) is provided with a first limiting slot for the transition section and a second spacing slot for the transition section; wherein, the first spacing slot for the transition section and the first limiting slot for the transition section Through the cooperation of the first rolling bearing (6), the second limiting groove of the transfer section is matched with the second limiting groove through the second rolling bearing (7), so that the connecting section (3) and the tail nozzle The tubes (4) are relatively pivotally connected. 8. The aircraft tail nozzle assembly as claimed in claim 7, characterized in that, the aircraft tail nozzle assembly further comprises a driving steering device (5), and the driving steering device (5) is arranged on the aircraft and connected with the outer wall (41) of the tail nozzle to drive the tail nozzle (4) to rotate relative to the transition section (3). 9. An aircraft, characterized in that the aircraft comprises the aircraft tail nozzle assembly according to any one of claims 1 to 8, and the aircraft tail nozzle assemblies are in two groups. 10. The aircraft according to claim 9, characterized in that, the clamp between the central axis of the transition section (3) of one group of said aircraft tail nozzle assembly and the axis of said aircraft engine (2) The angle is 15 degrees to 30 degrees, and the angle between the central axis of the transition section (3) of the other set of said aircraft tail nozzle assembly and the axis of the aircraft engine (2) is 15 degrees to 30 degrees .