A simple two-dimensional vector nozzle

Abstract

A simple two-dimensional vector nozzle relates to the field of turbojet or turbofan engine power control, specifically to a device for controlling the thrust direction of the engine. The mechanism includes components such as a support, a cylindrical sleeve, a large push rod, a conical sleeve, and a small push rod. The support can be fixed to the engine or other structural parts around the engine to fix the entire mechanism. The cylindrical sleeve rotates relative to the support via large ball bearings on both sides. The large push rod is welded to the cylindrical sleeve. The conical sleeve is connected to the cylindrical sleeve via a small ball bearing through an axial fit and rotates relative to the cylindrical sleeve. The small push rod is welded to the wall of the conical sleeve. By driving the large push rod and the small push rod to move simultaneously, the cylindrical sleeve and the conical sleeve are driven to rotate simultaneously, achieving compound motion of the vector nozzle in two degrees of freedom, front-to-back and left-to-right, and realizing thrust direction control.

Description

Technical Field

[0001] The present invention relates to the field of turbojet or turbofan engine power control, and in particular to a device for controlling the thrust direction of an engine. Background Art

[0002] Turbofans and turbojets, as the primary power plants in the aviation industry, have achieved significant development. Two- and three-axis vectoring engines utilize a flow control system installed on the tail nozzle to redirect the high-temperature, high-pressure combustion gas, thereby altering the overall thrust profile. Currently, fighter jets utilize two- and three-axis vectoring systems for power control, but these systems are extremely large. Existing two-axis vectoring nozzles are typically rectangular or comprised of four rotating adjustment plates, resulting in a complex structure.

[0003] For low-altitude subsonic flight units, micro turbojets or turbofan engines do not have suitable vector devices to control the direction of thrust deflection. It is an essential technical indicator that the airborne flight unit can perform attitude and heading angle control. To achieve this technical indicator, a binary vector device is generally used.

[0004] The existing binary vector device used for power control of fighter jets is not suitable for use in micro (or small) turbojet engines and turbofan engines in low-altitude areas due to its complex structure and heavy overall weight. Summary of the Invention

[0005] The technical problems to be solved by the present invention are:

[0006] The present invention aims to solve the existing technical gaps and provide a binary vector mechanism which can control the thrust direction of a micro or small turbojet engine and has a small load weight and a simple structure.

[0007] The technical solution adopted by the present invention to solve the above technical problems is: content of the certificate.

[0008] A simple binary vector nozzle includes a pair of supports and a binary vector nozzle body, which is connected to the engine or engine peripheral components via the pair of supports; the binary vector nozzle body includes a first-stage sleeve, a first-stage push rod, a second-stage sleeve, and a second-stage push rod;

[0009] A pair of supports are symmetrically mounted on the side wall of one end of the first-stage sleeve. Each support is rotatably connected to the first-stage sleeve through a corresponding first-stage rotating component. The first-stage push rod is mounted on the outer side wall of the first-stage sleeve at 90 degrees to each support. The axes of the two first-stage rotating components are coaxial.

[0010] The other end of the primary sleeve is rotatably connected to the head end of the secondary sleeve through two symmetrically arranged secondary rotating parts. The axes of the two secondary rotating parts are coaxial, and the axis of the secondary rotating part is perpendicular to the axis of the primary rotating part.

[0011] The secondary push rod is installed on the outer wall of the middle part of the secondary sleeve. When viewed from the end of the binary vector nozzle body, the secondary push rod is set at 90 degrees to the primary push rod.

[0012] By driving the first-stage push rod and / or the second-stage push rod to move individually or simultaneously, the first-stage sleeve and the second-stage sleeve are driven to rotate individually or simultaneously, so as to realize the forward and backward or left and right movement of the binary vector nozzle body, or the compound movement of the forward and backward and left and right two degrees of freedom, thereby realizing the thrust direction control.

[0013] The primary rotating component adopts a large ball bearing, and the secondary rotating component adopts a small ball bearing.

[0014] When the primary sleeve is coaxial with the secondary sleeve, the first end of the secondary sleeve is placed inside the other end of the primary sleeve, and there is a certain distance between the two to provide space when the secondary sleeve rotates relative to the primary sleeve.

[0015] When the primary sleeve is coaxial with the secondary sleeve, the axial height of the first end of the secondary sleeve extending into the other end of the primary sleeve and the distance between the two are determined according to the deflection angle requirement.

[0016] The primary sleeve is a cylindrical sleeve, and the secondary sleeve is a conical sleeve with a large head end and a small tail end.

[0017] The primary sleeve is a tapered sleeve that is smaller at one end close to the support and larger at the other end away from the support.

[0018] The first-stage push rod and the second-stage push rod have the same structure, including an integrally formed sleeve connecting portion for connecting to the first-stage sleeve or the second-stage sleeve and an H-shaped portion for connecting to the drive rod. The H-shaped portion is provided with a coaxial connecting hole away from the sleeve connecting portion, and the drive rod is hinged to the push rod through the connecting hole.

[0019] The first-stage push rod and the second-stage push rod are both provided with a weight-reducing structure.

[0020] The present invention has the following beneficial technical effects:

[0021] The present invention is a simple binary vector nozzle, which includes a support, a first-level sleeve, a first-level push rod, a second-level sleeve and a second-level push rod, etc. The support can be fixed to the engine or other structural parts around the engine to fix the entire mechanism, and the two supports distributed on both sides of the cylindrical sleeve play a supporting role.

[0022] The primary rotating component (cylindrical sleeve) rotates relative to the support via the primary rotating components (large ball bearings) on either side; the primary push rod is welded to the cylindrical sleeve; the secondary sleeve (tapered sleeve) is connected to the primary rotating component (cylindrical sleeve) via the secondary rotating component (small ball bearing) via an axial fit, allowing for relative rotation; the secondary push rod is welded to the wall of the secondary sleeve (tapered sleeve). As can be seen from the above description, the present invention has a simple structure and is easy to control. It achieves bidirectional swinging. Through structural design, the present invention minimizes energy loss in the binary vector nozzle, improving operational efficiency.

[0023] Compared to existing technologies, this invention achieves composite motion of the vectoring nozzle in two degrees of freedom, front-to-back and left-to-right, by driving the large and small push rods simultaneously, thereby driving the simultaneous rotation of the cylindrical and conical sleeves. This allows for thrust direction control. This simple binary vectoring nozzle deflects the cylindrical and conical sleeves by pushing the push rods, enabling thrust deflection in two directions within a two-dimensional plane.

[0024] The present invention is particularly suitable for micro or small turbojet engines and turbofan engines. It is a thrust direction adjustment mechanism for small turbojet engines, which solves the need for thrust direction adjustment control through a simple structural design. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the overall structure in an embodiment of the present invention. Figure 2 This is a schematic diagram of the support structure of the present invention. Figure 3 This is a schematic diagram of the push rod structure of the present invention. Figure 4 This is a schematic diagram of the cylindrical sleeve structure of the present invention. Figure 5 This is a schematic diagram of the tapered sleeve structure of the welding push rod of the present invention.

[0026] In the figure: support 1, large ball bearing 2, cylindrical sleeve 3, large push rod 4, small ball bearing 5, tapered sleeve 6, small push rod 7. DETAILED DESCRIPTION

[0027] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0028] like Figure 1The present invention provides a simple binary vector nozzle, comprising several components, including a support 1, a cylindrical sleeve 3, a large push rod 4, a conical sleeve 6 and a small push rod 7; the support 1 can be fixed to the engine or other structural parts around the engine to fix the entire mechanism; the cylindrical sleeve 3 rotates relative to the support 1 through the large ball bearings 2 on both sides; the large push rod 4 is welded to the cylindrical sleeve 3; the conical sleeve 6 is connected to the cylindrical sleeve 3 through the small ball bearing 5 through the shaft and rotates relatively; the small push rod 7 is welded to the wall of the conical sleeve 6.

[0029] The cylindrical sleeve rotates relative to the support via large ball bearings on either side. The large push rod is welded to the cylindrical sleeve. The tapered sleeve is connected to the cylindrical sleeve via a small ball bearing through a shaft fit, allowing relative rotation. The small push rod is welded to the wall of the tapered sleeve. By driving the large and small push rods simultaneously, the cylindrical and tapered sleeves rotate simultaneously, achieving compound motion of the vector nozzle in both forward and backward and left and right degrees of freedom, and realizing thrust direction control.

[0030] The large ball bearings 2 on opposite sides of the cylindrical sleeve 3 rotate relative to the support. The large push rod 4 is welded to the cylindrical sleeve 3. The tapered sleeve 3 is connected to the cylindrical sleeve 3 via a small ball bearing through the shaft and rotates relative to it. The small push rod is welded to the wall of the tapered sleeve. By driving the large and small push rods to move simultaneously, the cylindrical and tapered sleeves rotate simultaneously, achieving compound motion of the vector nozzle in two degrees of freedom, front-to-back and left-to-right, and realizing thrust direction control.

[0031] By making the two sleeves rotate in perpendicular directions, the thrust can be deflected forward, backward, left, and right. The cylindrical sleeve structure can be changed to a conical structure to increase the deflection angle. The cylindrical sleeve structure can be changed according to the deflection angle required.

[0032] The working process of the present invention is as follows: During actual operation, by pushing the push rod 4, the cylindrical sleeve 3 can be controlled to swing forward and backward relative to the support 1; by pushing the push rod 7, the conical sleeve 6 can be controlled to swing left and right relative to the cylindrical sleeve 3, thereby controlling the deflection of the turbojet engine thrust in four directions: front, back, left, and right.

Claims

1. A simple binary vector nozzle, characterized by: The simple binary vector nozzle comprises a pair of supports (1) and a binary vector nozzle body, and the binary vector nozzle body is connected to an engine or a peripheral component of the engine via the pair of supports (1); the binary vector nozzle body comprises a first-stage sleeve (3), a first-stage push rod (4), a second-stage sleeve (6) and a second-stage push rod (7); A pair of supports (1) are symmetrically mounted on the side wall of one end of the first-stage sleeve (3); each support (1) is rotatably connected to the first-stage sleeve (3) through a corresponding first-stage rotating component (2); a first-stage push rod (4) is mounted on the outer side wall of the first-stage sleeve (3) at 90 degrees to each support (1); the axes of the two first-stage rotating components (2) are coaxial. The other end of the primary sleeve (3) is rotatably connected to the head end of the secondary sleeve (6) through two symmetrically arranged secondary rotating parts (5), the axes of the two secondary rotating parts (5) are coaxial, and the axis of the secondary rotating part (5) is perpendicular to the axis of the primary rotating part (2) in different planes. The secondary push rod (7) is mounted on the outer side wall of the middle portion of the secondary sleeve (6). When viewed from the end of the binary vector nozzle body, the secondary push rod (7) and the primary push rod (4) are arranged at a 90-degree angle. By driving the primary push rod (4) and / or the secondary push rod (7) to move individually or simultaneously, the primary sleeve (3) and the secondary sleeve (6) are driven to rotate individually or simultaneously, thereby realizing the forward and backward or left and right movement of the binary vector nozzle body, or the composite movement of the forward and backward and left and right two degrees of freedom, thereby realizing the thrust direction control; When the primary sleeve (3) and the secondary sleeve (6) are coaxial, the head end of the secondary sleeve (6) is placed inside the other end of the primary sleeve (3), and a certain distance is left between the two to provide space when the secondary sleeve (6) rotates relative to the primary sleeve (3); When the primary sleeve (3) and the secondary sleeve (6) are coaxial, the axial height of the first end of the secondary sleeve (6) extending into the other end of the primary sleeve (3) and the distance between the two are determined according to the deflection angle requirement.

2. A simple binary vector nozzle according to claim 1, characterized in that: The primary rotating component 2 adopts a large ball bearing, and the secondary rotating component (5) adopts a small ball bearing.

3. The simple binary vector nozzle according to claim 1, characterized in that: The primary sleeve (3) is a cylindrical sleeve, and the secondary sleeve (6) is a conical sleeve with a larger head end and a smaller tail end.

4. A simple binary vector nozzle according to claim 1 or 3, characterized in that: The primary sleeve (3) is a conical sleeve with a smaller end close to the support and a larger end away from the support.

5. A simple binary vector nozzle according to claim 1 or 3, characterized in that: The primary push rod (4) and the secondary push rod (7) have the same structure, including an integrally formed sleeve connecting portion for connecting to the primary sleeve or the secondary sleeve and an H-shaped portion for connecting to the drive rod. The H-shaped portion is provided with a coaxial connecting hole away from the sleeve connecting portion, and the drive rod is hinged to the push rod through the connecting hole.

6. The simple binary vector nozzle according to claim 5, characterized in that: The primary push rod (4) and the secondary push rod (7) are both provided with a weight-reducing structure.

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