Aircraft inlet drive mechanism with servo-adjustable throat

Abstract

The application relates to the field of aerospace, in particular to a plane air inlet transmission mechanism capable of servo adjusting a throat flow, which comprises a gear transmission mechanism, a four-bar mechanism, a lightweight plate, a motor and a support column; the gear transmission mechanism comprises a driving pinion and four driven gear wheels which are in mesh with the driving pinion; the four-bar mechanism comprises four lead screws, a sliding table, and a sliding block connected with the sliding table; the sliding block is fixedly connected with a connecting rod; the lead screws are connected with the driven shaft systems and the driven gear wheels one by one through the lightweight plate; the lead screws are fixedly arranged at the ends of the connecting rod; the motor drives the driving pinion to rotate through the lightweight plate; and the support column is fixedly arranged below the lightweight plate. The plane air inlet transmission mechanism can servo change the flow of the plane air inlet, has a stable structure, is simple to operate, and has high air inlet flow control precision.

Description

Technical Field

[0001] This invention relates to the aerospace field, and more specifically to an aircraft air intake transmission mechanism with servo-adjustable throat flow. Background Technology

[0002] An aircraft air intake transmission mechanism refers to a mechanical device used to control the opening, closing, and adjustment of the aircraft's air intake. Its main principle is to control the opening, closing, and position of the air intake through an actuator to regulate the airflow within the intake duct. This allows the size of the air intake to be adjusted according to the aircraft's flight conditions and the engine's required air volume, ensuring the engine receives adequate airflow.

[0003] In the current market, aircraft air intake drive mechanisms typically employ high-precision actuators and advanced control systems to ensure accurate control of the air intake's position and size. Furthermore, to enhance reliability, multiple sensors and redundant designs are usually employed.

[0004] Traditional aircraft air intake drive mechanisms may suffer from low precision, failing to accurately control the intake airflow. This can lead to insufficient or excessive engine air intake, impacting aircraft performance and fuel efficiency. Secondly, some traditional mechanisms exhibit slow response times when adjusting intake airflow, unable to meet the rapid airflow adjustment needs of aircraft under varying flight conditions. Furthermore, traditional mechanisms may lack stability, potentially failing to maintain stable operation under harsh weather conditions or flight environments. Moreover, some traditional mechanisms require manual intervention for adjustment, hindering automated flow control and increasing operational complexity. Summary of the Invention

[0005] The purpose of this invention is to provide a servo-adjustable airflow transmission mechanism for an aircraft air intake. The position of the lower plate can be changed by rotating a servo motor, and self-locking can be achieved at any position. This not only makes the structure more stable, but also allows for servo-adjustable airflow in the aircraft air intake.

[0006] To achieve the above objectives, the present invention provides the following technical solution: an aircraft air intake transmission mechanism capable of servo-adjustable throat flow, comprising a gear transmission mechanism, a four-bar linkage, a lightweight plate, a motor, and a support column; the gear transmission mechanism includes a driving pinion and four driven large gears meshing with the driving pinion; the four-bar linkage includes four lead screws, a slide, and a slider connected to the slide; the slider is fixedly connected to a connecting rod; the lead screw passes through the lightweight plate and is connected to the driven large gears one-to-one via a driven shaft system; the lead screw is fixed to the end of the connecting rod; the motor passes through the lightweight plate and drives the driving pinion to rotate; the support column is fixedly disposed below the lightweight plate for fixing the transmission mechanism to the air intake.

[0007] Furthermore, the driven shaft system includes a bearing, a washer, a retaining ring, and a bearing housing; each of the driven large gears is fitted with the bearing; the retaining ring is located below the bearing housing and cooperates with the driven large gear to play a limiting role.

[0008] Furthermore, the driven large gear is provided with a ball nut that mates with it. ； The ball nut and the lead screw are connected by ball contact; the bearing housing is fixed to the lightweight plate by washers and screws.

[0009] Furthermore, it also includes a fourth pipe wall, a second pipe wall, a first pipe wall, a third pipe wall, and a fifth pipe wall that are connected in sequence; the first pipe wall is fixedly installed below the support column.

[0010] Furthermore, the fourth pipe wall, the second pipe wall, the first pipe wall, the third pipe wall, and the fifth pipe wall are connected sequentially by hinges; the sidewalls that contact the first pipe wall and the second pipe wall, the first pipe wall and the third pipe wall, the second pipe wall and the fourth pipe wall, and the third pipe wall and the fifth pipe wall are mutually cooperating arcs.

[0011] Furthermore, the first pipe wall is provided with hollow weight-reducing holes arranged at intervals; the second, third, fourth, and fifth pipe walls are provided with hollow weight-reducing holes arranged in sequence; and the outer edge of the lightweight plate is provided with a notch.

[0012] Furthermore, a first connecting seat is fixed on the edge of one side of the first pipe wall and the second pipe wall, and a second connecting seat corresponding to the first connecting seat is fixed on the edge of the opposite side; a second connecting seat is provided on the edges of both opposite sides of the third pipe wall; a first connecting seat is fixed on the edge of one side of the fourth pipe wall and the fifth pipe wall; the positions of the first connecting seat and the second connecting seat correspond to each other.

[0013] Furthermore, the hinge includes a first hinge bearing, a second hinge bearing, a hinge shaft, a bushing, and a bushing; the hinge shaft passes sequentially through a first connecting seat, a first hinge bearing, a second connecting seat, a bushing, a second hinge bearing, and a bushing; the bushing is fixed to the first connecting seat by a hinge screw.

[0014] Furthermore, the hollow weight-reducing hole is hexagonal honeycomb-shaped; the notch is semi-circular.

[0015] Furthermore, the driven large gear can move up and down along the lead screw.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] 1. A servo-adjustable throat flow transmission mechanism for aircraft air intake is provided, which is driven by a servo motor and can achieve high-precision control of air intake flow.

[0018] 2. This invention uses a gear transmission mechanism and a four-bar linkage, which has a simple structure, fast transmission speed, and fast response speed, and can meet the aircraft's need for rapid adjustment of intake airflow under different flight conditions.

[0019] 3. The transmission mechanism proposed in this invention can self-lock and hover at any position, and adopts multi-point synchronous drive, resulting in high stability;

[0020] 4. This invention only requires controlling the rotation of the motor to adjust the size of the space, thereby changing the air intake flow rate. No manual intervention is required for adjustment, and the operation is simple. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings of the embodiments will be briefly described below. Obviously, the drawings described below only relate to some embodiments of the present invention and are not intended to limit the present invention.

[0022] Figure 1 This is a schematic diagram of the overall structure of an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0023] Figure 2 This is a schematic diagram of the structure connecting a lightweight plate, a motor, and a support column in an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0024] Figure 3 This is a schematic diagram of the structure of a lightweight plate connected to a motor and a drive pinion in an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0025] Figure 4 This is a schematic diagram of the driven shaft system of a servo-adjustable throat flow transmission mechanism for an aircraft air intake.

[0026] Figure 5 This is a schematic diagram of a lightweight plate for an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0027] Figure 6 An exploded view of an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0028] Figure 7 This is a front view of the transmission mechanism of an aircraft air intake transmission mechanism with servo-adjustable throat flow, connecting it to the first pipe wall and the second pipe wall.

[0029] Figure 8 This is a schematic diagram of the connection between the transmission mechanism and the first and second pipe walls of a servo-adjustable throat flow transmission mechanism for an aircraft air intake.

[0030] Figure 9 This is a schematic diagram of the hinge structure of an aircraft air intake transmission mechanism that can servo-adjust the throat flow.

[0031] Figure 10 A cross-sectional view of the hinge structure of an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0032] Figure 11 A schematic diagram of the structure of the first pipe wall of an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0033] Figure 12 This is a schematic diagram of the structure of the second pipe wall of an aircraft air intake transmission mechanism with servo-adjustable throat flow.

[0034] In the diagram: 1-Slide table; 2-Slider; 3, 6, 9, 12-Driven large gear; 4-Connecting rod; 5-Lead screw; 7-Lightweight plate; 8-Ball nut; 10-Support column; 11-Driving pinion; 13-Bearing seat; 14-Bearing; 15-Washer; 16-Snap ring; 17-Screw; 18-Washer; 19-Fourth pipe wall; 20-Second pipe wall; 21-First pipe wall; 22-Third pipe wall; 23-Fifth pipe wall; 24-Second connecting seat; 25-First connecting seat; 26-First hinge bearing; 27-Second hinge bearing; 28-Hinge shaft; 29-Busset; 30-Bushole sleeve; 31-Hinge screw; 32-Wall; 33-Motor. Detailed Implementation

[0035] The invention will be further illustrated below through specific embodiments:

[0036] See Figure 1-3A servo-adjustable airflow transmission mechanism for an aircraft air intake includes a gear transmission mechanism, a four-bar linkage, a lightweight plate, a motor, and a support column. The gear transmission mechanism includes a driving pinion and four driven large gears meshing with the driving pinion for transmitting power and rotational speed. The four-bar linkage includes four lead screws, a slide, and a slider connected to the slide. A connecting rod is fixedly connected to the slider. The slide is fastened to a wall with screws. The lead screws pass through the lightweight plate and are connected to the driven large gears one-to-one via driven shafts. The lead screws are fixed to the ends of the connecting rods. The motor passes through the lightweight plate and drives the driving pinion to rotate. The support column is fixedly located below the lightweight plate to fix the transmission mechanism to the air intake.

[0037] See Figure 4 , 6 The driven shaft system includes two or more bearings, a washer, a retaining ring, and a bearing housing; each driven large gear is fitted with one of the bearings; the retaining ring is located below the bearing housing and cooperates with the driven large gear to limit its movement. The driven large gear can move up and down along the lead screw.

[0038] The driven large gear is provided with a ball nut that mates with it. ； The ball nut and the lead screw are connected by ball contact; the bearing housing is fixedly mounted on the lightweight plate by washers and screws.

[0039] See Figure 7-10 It also includes a fourth pipe wall, a second pipe wall, a first pipe wall, a third pipe wall, and a fifth pipe wall that are connected in sequence; the first pipe wall is fixedly installed below the support column.

[0040] The fourth pipe wall, the second pipe wall, the first pipe wall, the third pipe wall, and the fifth pipe wall are connected sequentially by hinges; the side walls that contact the first pipe wall and the second pipe wall, the first pipe wall and the third pipe wall, the second pipe wall and the fourth pipe wall, and the third pipe wall and the fifth pipe wall are mutually fitting arcs.

[0041] The first pipe wall is provided with hollow weight-reducing holes arranged at intervals; the second, third, fourth, and fifth pipe walls are provided with hollow weight-reducing holes arranged in sequence; and the outer edge of the lightweight plate is provided with a notch.

[0042] A first connecting seat is fixed on one edge of the first pipe wall and the second pipe wall, and a second connecting seat corresponding to the first connecting seat is fixed on the edge of the opposite side; a second connecting seat is provided on the edges of both opposite sides of the third pipe wall; a first connecting seat is fixed on one edge of the fourth pipe wall and the fifth pipe wall; the positions of the first connecting seat and the second connecting seat correspond to each other.

[0043] The hinge includes a first hinge bearing, a second hinge bearing, a hinge shaft, a bushing, and a bushing; the hinge shaft passes sequentially through a first connecting seat, a first hinge bearing, a second connecting seat, a bushing, a second hinge bearing, and a bushing; the bushing is fixed to the first connecting seat by a hinge screw.

[0044] See Figure 5 , 11 12. The hollow weight-reducing hole is hexagonal honeycomb-shaped; the notch is semi-circular. When the motor is working, the driving pinion rotates, and due to gear meshing, it drives the driven large gear to rotate. During the rotation of the pinion, the lead screw moves up and down, causing the position of the pipe wall to change, thereby changing the exhaust volume of the aircraft air intake.

[0045] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A servo-adjustable throat flow transmission mechanism for aircraft air intakes, characterized in that: The system includes a gear transmission mechanism, a four-bar linkage, a lightweight plate (7), a motor (33), and a support column (10). The gear transmission mechanism includes a driving pinion (11) and four driven large gears that mesh with the driving pinion (11). The four-bar linkage includes four lead screws (5), a slide (1), and a slider (2) connected to the slide (1). The slider (2) is fixedly connected to a connecting rod (4). The lead screw (5) passes through the lightweight plate (7) and is connected to the driven large gears one-to-one through the driven shaft system. The lead screw (5) is fixed at the end of the connecting rod (4). The motor (33) passes through the lightweight plate (7) and drives the driving pinion (11) to rotate. The support column (10) is fixedly installed below the lightweight plate (7) to fix the transmission mechanism on the air intake. The driven shaft system includes a bearing (14), a washer (15), a retaining ring (16), and a bearing housing (13); each of the driven large gears is fitted with the bearing (14); the retaining ring (16) is located below the bearing (14) and cooperates with the driven large gear to play a limiting role; It also includes a fourth pipe wall (19), a second pipe wall (20), a first pipe wall (21), a third pipe wall (22), and a fifth pipe wall (23) that are connected in sequence; the first pipe wall (21) is fixedly installed below the support column (10); The fourth pipe wall (19), the second pipe wall (20), the first pipe wall (21), the third pipe wall (22), and the fifth pipe wall (23) are connected in sequence by hinges; the side walls that contact the first pipe wall (21) and the second pipe wall (20), the first pipe wall (21) and the third pipe wall (22), the second pipe wall (20) and the fourth pipe wall (19), and the third pipe wall (22) and the fifth pipe wall (23) are mutually fitting arcs; The first pipe wall (21) is provided with hollow weight-reducing holes arranged at intervals; the second pipe wall (20), the third pipe wall (22), the fourth pipe wall (19), and the fifth pipe wall (23) are all provided with hollow weight-reducing holes arranged in sequence; the outer edge of the lightweight plate (7) is provided with a notch; The driven large gear can move up and down along the lead screw (5).

2. The aircraft inlet transmission mechanism with servo-adjustable throat flow according to claim 1, characterized in that: The driven large gear is provided with a ball nut (8) that mates with it; the ball nut (8) is connected to the lead screw (5) through ball contact; the bearing seat (13) is fixedly mounted on the lightweight plate (7) by a washer (18) and a screw (17).

3. The aircraft inlet transmission mechanism with servo-adjustable throat flow according to claim 1, characterized in that: A first connecting seat (25) is fixed on one side edge of the first pipe wall (21) and the second pipe wall (20), and a second connecting seat (24) corresponding to the first connecting seat (25) is fixed on the edge of the opposite side. A second connecting seat (24) is provided on the edges of the two opposite sides of the third pipe wall (22). A first connecting seat (25) is fixed on one side edge of the fourth pipe wall (19) and the fifth pipe wall (23). The positions of the first connecting seat (25) and the second connecting seat (24) correspond to each other.

4. The aircraft inlet transmission mechanism with servo-adjustable throat flow according to claim 1, characterized in that: The hinge includes a first hinge bearing (26), a second hinge bearing (27), a hinge shaft (28), a bushing (29), and a bushing (30); the hinge shaft passes sequentially through a first connecting seat (25), a first hinge bearing (26), a second connecting seat (24), a bushing (29), a second hinge bearing (27), and a bushing (30); the bushing (30) is fixed to the first connecting seat (25) by a hinge screw (31).

5. The aircraft air intake transmission mechanism with servo-adjustable throat flow according to claim 1, characterized in that: The hollow weight-reducing holes are hexagonal honeycomb-shaped; the notches are semi-circular arc-shaped.

Images