Two-dimensional vector device with high control efficiency

Abstract

The utility model provides a high-control-efficiency two-dimensional vector device which comprises a fixing support installed at the tail of a turbojet engine and a connecting sleeve coaxially arranged outside the fixing support in a sleeving mode, a tail nozzle is erected at the tail end of the fixing support, a drainage structure is arranged at the air inlet end of the tail nozzle, and a flow guide plate is embedded in the tail end of the tail nozzle; a vector ring is coaxially and movably connected to the outer side of the tail nozzle, a gap is formed between the vector ring and the tail nozzle, the vector ring is connected with the fixed support through a first rotating shaft, the vector ring is connected with the tail nozzle through a second rotating shaft, and the first rotating shaft and the second rotating shaft are both arranged in the radial direction of the vector ring; a driving mechanism is mounted on the outer wall of the connecting sleeve, is connected with the tail nozzle and is used for driving the tail nozzle to rotate around the first rotating shaft and / or the second rotating shaft. According to the scheme, large deflection torque is provided within a small deflection angle, and the device has the advantages of being small in size, simple in structure, easy to assemble, high in efficiency and the like.

Description

Technical Field

[0001] This application relates to the field of vector devices, and more particularly to a two-dimensional vector device with high control efficiency. Background Technology

[0002] In recent years, the popularity of small manned aircraft has surged, with various forms of aircraft emerging on the market, such as flying skateboards, flying wings, flying backpacks, and flying motorcycles. Turbojet engines, with their advantages of light weight and high thrust, are an excellent power unit; they consume aviation kerosene for power, have high energy density, and are relatively safe to use. Therefore, turbojet engines are highly suitable as the power source for manned aircraft. However, limitations imposed by environmental temperature, engine structure, response delays, and the need to ensure thrust consistency across multiple engines pose significant challenges to the attitude stability of small manned aircraft using multiple turbojet engines during vertical takeoff.

[0003] To achieve aircraft control and flight maneuverability, vectoring mechanisms are introduced to adjust the direction and magnitude of thrust from turbojet engines. However, the vectoring mechanisms currently used in turbojet engines generally suffer from problems such as large weight, large size, complex structure, and difficult assembly, especially low deflection efficiency, making it difficult to meet the requirements for flight attitude stability and maneuver control. Utility Model Content

[0004] To address the shortcomings of the prior art, this application provides a two-dimensional vector device with high control efficiency, which achieves a large deflection torque within a small deflection angle, and has the advantages of miniaturization, simple structure, easy assembly and high efficiency.

[0005] To achieve the above objectives, the present invention employs the following technology:

[0006] A two-dimensional vector device with high control efficiency includes a fixed bracket installed at the tail of a turbojet engine and a connecting sleeve coaxially sleeved outside the fixed bracket. The tail end of the fixed bracket is provided with a tail nozzle, the air inlet end of the tail nozzle is provided with a flow guiding structure, and the tail end of the tail nozzle is embedded with a guide plate.

[0007] A vector ring is movably connected coaxially to the outer side of the tail nozzle, and there is a gap between the vector ring and the tail nozzle. The vector ring is connected to the fixed bracket through a first rotating shaft, and the vector ring is connected to the tail nozzle through a second rotating shaft. Both the first rotating shaft and the second rotating shaft are arranged radially along the vector ring.

[0008] A drive mechanism is installed on the outer wall of the connecting sleeve. The drive mechanism is connected to the tail nozzle and is used to drive the tail nozzle to rotate around the first rotating shaft and / or the second rotating shaft.

[0009] Furthermore, there are two drive mechanisms, including a servo motor, a connecting rod, and a servo arm. The output shaft of the servo motor is connected to one end of the servo arm, the other end of the servo arm is hinged to one end of the connecting rod, and the other end of the connecting rod is hinged to the outer wall of the tail nozzle.

[0010] Furthermore, the servos of both drive mechanisms are mounted on the outer wall of the connecting sleeve, with their output shafts at the same height and perpendicular to the axis of the connecting sleeve.

[0011] Furthermore, the horizontal angle formed by the axes of the first and second rotating shafts is 90 degrees.

[0012] Furthermore, the output shaft axes of the two drive mechanisms are perpendicular, the first shaft is parallel to the output shaft of one of the servos, and the second shaft is parallel to the output shaft of the other servo.

[0013] Furthermore, a servo bracket is installed on the outer wall of the connecting sleeve, and the servo is mounted on the servo bracket.

[0014] Furthermore, the servo mount includes an arc plate that fits against the outer wall of the connecting sleeve and mounting plates formed at both ends of the arc plate. The two mounting plates are perpendicular, and the servo is mounted on the mounting plates.

[0015] Furthermore, the deflector is a cross-shaped plate.

[0016] Furthermore, the air intake structure of the tail nozzle is a skirt formed by its top extending obliquely upwards and outwards.

[0017] Furthermore, the fixed bracket is detachably connected to the tail of the turbojet engine, and the interface of the fixed bracket is used to match the tail structure of the turbojet engine.

[0018] The advantages of this utility model are: it has the advantages of miniaturization, simple structure and easy assembly. It also achieves a large deflection torque within a small deflection angle to improve deflection efficiency. It solves the problems of turbojet engines being limited by their own structure and response delay, and the inability to achieve thrust balance by relying on the speed adjustment of multiple engines, as well as the problem of difficulty in meeting the requirements of flight attitude stability and maneuver control. Attached Figure Description

[0019] The accompanying drawings described herein are merely illustrative of selected embodiments, not all possible implementations, and are not intended to limit the scope of this invention.

[0020] Figure 1 This is a perspective view of the overall structure of an embodiment of this application.

[0021] Figure 2 This is a schematic diagram of the bottom structure of an embodiment of this application.

[0022] Figure 3This is a top view of an embodiment of this application.

[0023] Figure 4 This is a schematic diagram of the tail nozzle structure according to an embodiment of this application.

[0024] Figure 5 This is a schematic diagram of the structure of an embodiment of this application when it is assembled with a turbojet engine. Detailed Implementation

[0025] To make the objectives, technical solutions and advantages of the present utility model clearer, the implementation methods of the present utility model will be described in detail below with reference to the accompanying drawings. However, the embodiments described in the present utility model are only some embodiments of the present utility model, and not all embodiments.

[0026] This application provides a two-dimensional vector device with high control efficiency, such as... Figures 1-5 As shown, it includes a fixed bracket 1 installed at the tail of the turbojet engine and a connecting sleeve 2 coaxially sleeved outside the fixed bracket 1. The tail end of the fixed bracket 1 is provided with a tail nozzle 5. The air inlet end of the tail nozzle 5 is provided with a flow guiding structure. The tail end of the tail nozzle 5 is embedded with a guide plate 51.

[0027] A vector ring 3 is movably connected coaxially to the outer side of the tail nozzle 5, and there is a gap between the vector ring 3 and the tail nozzle 5. The vector ring 3 is connected to the fixed bracket 1 through a first rotating shaft 7, and the vector ring 3 is connected to the tail nozzle 5 through a second rotating shaft 4. Both the first rotating shaft 7 and the second rotating shaft 4 are arranged radially along the vector ring 3.

[0028] A drive mechanism is installed on the outside of the connecting sleeve 2. The drive mechanism is connected to the tail nozzle and is used to drive the tail nozzle to rotate around the first rotating shaft and / or the second rotating shaft.

[0029] Specifically, such as Figures 1-3 As shown, there are two drive mechanisms, including a servo motor 9, a connecting rod 6, and a servo arm 8. The output shaft of the servo motor 9 is connected to one end of the servo arm 8, and the other end of the servo arm 8 is hinged to one end of the connecting rod 6. The other end of the connecting rod 6 is hinged to the outer wall of the tail nozzle 5. The servo motor 9 can be a fast-response servo motor made of non-metallic materials to reduce the weight of the overall structure.

[0030] Specifically, such as Figures 1-3 As shown, the servo motors 9 of both drive mechanisms are mounted on the outer wall of the connecting sleeve 2, with their output shafts at the same height and perpendicular to the axis of the connecting sleeve 2. More specifically, the connecting sleeve 2 is made of heat-insulating material to provide heat insulation protection for the servo motors 9, effectively increasing their lifespan.

[0031] Specifically, such as Figure 2As shown, the horizontal angle formed by the axes of the first rotating shaft 7 and the second rotating shaft 4 is 90 degrees, which allows the tail nozzle 5 to move freely in two directions, thereby achieving omnidirectional control around the thrust main shaft of the turbojet engine.

[0032] Specifically, such as Figure 2 and Figure 3 As shown, the output shafts of the two drive mechanisms' servo motors 9 are perpendicular. The first rotating shaft 7 is parallel to the output shaft of one of the servo motors 9, and the second rotating shaft 4 is parallel to the output shaft of the other servo motor 9. When one of the servo motors 9 drives its corresponding link 6 to move, it will cause the vector ring 3 and the tail nozzle 5 to rotate relative to the fixed bracket 1 around the first rotating shaft 7. When the other servo motor 9 drives its corresponding link 6 to move, it will cause the tail nozzle 5 to rotate relative to the vector ring 3 around the second rotating shaft 4.

[0033] Specifically, such as Figure 1 and Figure 2 As shown, a servo bracket 10 is mounted on the outer wall of the connecting sleeve 2, and the servo 9 is mounted on the servo bracket 10. The servo bracket 10 provides certain support and protection for the servo 9.

[0034] Specifically, such as Figure 1 and Figure 2 The servo mount 10 shown includes an arc plate that fits against the outer wall of the connecting sleeve 2 and mounting plates formed at both ends of the arc plate. The two mounting plates are perpendicular, and the servo 9 is mounted on the mounting plates.

[0035] Specifically, such as Figure 2 and Figure 4 As shown, the guide plate 51 is a cross-shaped plate, which increases the gas control surface to improve the deflection force.

[0036] Specifically, such as Figure 4 As shown, the air intake structure of the tail nozzle 5 is a skirt formed by its top extending obliquely upwards and outwards, which increases the air intake volume of the tail nozzle 5 to improve the deflection force.

[0037] Specifically, such as Figure 5 As shown, the fixed bracket 1 is detachably connected to the tail of the turbojet engine, and the interface of the fixed bracket 1 is used to match the tail structure of the turbojet engine, that is, no modification or customization of the engine is required. Since the other components are assembled based on the fixed bracket 1, if replacement is required during use, the presence of the fixed bracket 1 facilitates the separation of the entire device from the turbojet engine for quick replacement.

[0038] In application, the above description is only a preferred embodiment of this application and is not intended to limit this application. Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application.

Claims

1. A high control efficiency two-dimensional vector device, characterized by, The application relates to a fixed support (1) mounted on the tail of a turbojet engine and a connecting sleeve (2) coaxially sleeved on the outside of the fixed support (1), wherein the tail end of the fixed support (1) is provided with a tail nozzle (5), the air inlet end of the tail nozzle (5) is provided with a flow guide structure, and the tail end of the tail nozzle (5) is embedded with a flow guide plate (51). A vector ring (3) is coaxially movably connected to the outside of the tail nozzle (5), and the vector ring (3) has a spacing with the tail nozzle (5); the vector ring (3) is connected with the fixed support (1) through a first rotating shaft (7), and the vector ring (3) is connected with the tail nozzle (5) through a second rotating shaft (4); the first rotating shaft (7) and the second rotating shaft (4) are arranged along the radial direction of the vector ring (3). The outer wall of the connecting sleeve (2) is provided with a driving mechanism connected with the tail nozzle (5) and used for driving the tail nozzle (5) to rotate around the first rotating shaft (7) and / or the second rotating shaft (4).

2. A high control efficiency two-dimensional vector device according to claim 1, characterized in that, The driving mechanism has two, including a steering engine (9), a connecting rod (6) and a steering engine arm (8), the output shaft of the steering engine (9) is connected with one end of the steering engine arm (8), the other end of the steering engine arm (8) is hingedly connected with one end of the connecting rod (6), and the other end of the connecting rod (6) is hingedly connected with the outer wall of the tail nozzle (5).

3. A high control efficiency two-dimensional vector device according to claim 2, characterized in that, The steering engines (9) of the two driving mechanisms are arranged on the outer wall of the connecting sleeve (2) and have output shafts located at the same height and vertically arranged along the axial direction of the connecting sleeve (2).

4. A high control efficiency two-dimensional vector device according to claim 3, characterized in that, The horizontal included angle between the axes of the first rotating shaft (7) and the second rotating shaft (4) is 90 degrees.

5. A high control efficiency two-dimensional vector device according to claim 4, characterized in that, The output shafts of the steering engines (9) are vertically arranged, the first rotating shaft (7) is parallel to the output shaft of one of the steering engines (9), and the second rotating shaft (4) is parallel to the output shaft of the other steering engine (9).

6. A high control efficiency two-dimensional vector device according to claim 5, characterized in that, The outer wall of the connecting sleeve (2) is provided with a steering engine frame (10), and the steering engines (9) are arranged on the steering engine frame (10).

7. A high control efficiency two-dimensional vector device according to claim 6, characterized in that, The steering engine frame (10) comprises an arc plate arranged on the outer wall of the connecting sleeve (2) and two mounting plates formed at the two ends of the arc plate, the two mounting plates are vertically arranged, and the steering engines (9) are arranged on the mounting plates.

8. A high control efficiency two-dimensional vector device according to claim 1, characterized in that, The flow guide plate (51) is a cross-shaped plate.

9. A high control efficiency two-dimensional vector device according to claim 1, characterized in that, The flow guide structure of the air inlet end of the tail nozzle (5) is a skirt formed by extending the top of the air inlet end to the upper side of the outside.

10. A high control efficiency two-dimensional vector device according to claim 1, characterized in that, The fixed support (1) is detachably connected with the tail of the turbojet engine, and the interface of the fixed support (1) is matched with the tail structure of the turbojet engine.

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