A distributed electric ducted fan adjustable support structure

Abstract

The application relates to a distributed electric ducted fan adjustable support structure. The adjustable support structure is connected with an aircraft beam through front and rear double supporting points. The front supporting point is close to an air inlet end of a fan and is connected with the aircraft through a lifting driving element. The lifting driving element is composed of a cylinder, a bearing, a screw rod, a pin shaft and a rotating block, the cylinder is fixed with the bearing, the inner ring of the bearing is connected with the screw rod through threads, the screw rod is connected with the rotating block through the pin shaft, the rotating block is fixed with the fan, and the fan is adjustable in pitch when the screw rod moves up and down. The rear supporting point is located at an air outlet end of the fan and is connected with the aircraft through a support element. The support element is composed of a rotating block, a pin shaft, a motor support seat and two side plates, the rotating block is connected with the motor support seat through the pin shaft, the two side plates are connected on the two sides of the motor support seat, and the motor support seat and the side plates are provided with weight reduction grooves. The application utilizes the stability of a triangle to ensure the stability of the support structure and reduces the weight of the support structure through the weight reduction groove design.

Description

Technical Field

[0001] This invention belongs to the field of support structures, specifically relating to an adjustable support structure for a distributed electric ducted fan. Background Technology

[0002] With increasing emphasis on environmental protection, the concept of green aviation is gaining popularity, sparking a surge in the development of distributed electric ducted fans (DAFs). DDFs utilize electric propulsion systems, offering higher power density and faster response times compared to traditional fuel-powered systems. Simultaneously, electric propulsion reduces fuel consumption and emissions of greenhouse gases such as carbon dioxide, resulting in cleaner flight. The inherently lower noise levels of electric propulsion systems further reduce aircraft noise during takeoff, landing, and low-altitude flight, minimizing noise disturbance to the ground and surrounding residents. Therefore, providing more efficient and environmentally friendly flight performance through DDFs represents a crucial development direction for the future of aviation.

[0003] Distributed electric ducted fans (DAFs) distribute multiple small ducted fans at different locations on an aircraft, each driven by an electric motor. Considering that various errors such as manufacturing and assembly mistakes can lead to imbalances in the position and layout of the ducted fans during aircraft installation, this can affect flight performance. Imbalanced ducted fan installation results in unbalanced aerodynamic forces during flight, impacting stability and control. Furthermore, asymmetrical ducted fan installation alters the aircraft's aerodynamic characteristics, increasing drag and thus reducing performance and fuel economy. Therefore, an adjustable distributed electric ducted fan support structure design is necessary.

[0004] The following issues need to be considered in the support structure for distributed electric ducted fans: (1) How to ensure that the support structure can balance and transmit the forces and torques generated by the ducted fans distributed in different positions. (2) How to make the support structure as lightweight as possible while ensuring stability. (3) How to avoid the impact of unbalanced installation of ducted fans on aircraft performance. After reviewing existing patents and literature, no support structure that can solve the above three core problems was found. Therefore, it is necessary to design an adjustable support structure for distributed electric ducted fans to solve the above problems.

[0005] Chinese invention patent application CN202110163099.7 discloses an adaptive support mechanism for an aircraft engine. The support assembly includes two support members rotatably connected end-to-end and multiple drive members rotatably connected to the support members. The angle of the support mechanism is adjusted by driving the support members to rotate through the drive members. However, this angle adjustment mechanism has too many parts, resulting in excessive mass and making the support structure too heavy, which is not suitable for adjustable support structures for distributed electric ducted fans.

[0006] The existing literature “Wei Haolin, Fan Yunting, Fu Zixiang, et al. Lightweight design of aircraft engine support frame based on topology and size optimization [J]. Aviation Precision Manufacturing Technology, 2021, 57(04):1-6” shows a support structure designed as a tube frame structure to ensure structural lightweighting. However, the support component of the distributed electric ducted fan far from the air intake needs to support a motor with a large mass, and this tube frame structure is difficult to guarantee the stability of the support structure. Summary of the Invention

[0007] To overcome the shortcomings of existing technologies, this invention proposes a distributed electric ducted fan adjustable support structure, which overcomes the impact of unbalanced ducted fan installation on aircraft flight performance and ensures the stability and lightweight of the support structure.

[0008] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0009] An adjustable support structure for a distributed electric ducted fan includes: a cylinder, bearings, bearing bolts, a screw, a left-end pin, a left-end rotating block, bolts, a fan, a right-end rotating block, a right-end pin, a motor support base, a motor, and side plates. The lower end of the cylinder is fixed to the aircraft crossbeam. The outer ring of the bearing is positioned with the center bolt hole at the upper end of the cylinder via bearing bolts. The inner thread of the bearing inner ring engages with the outer thread of the screw. The upper end of the screw has a smooth hole connected to the lower end of the left-end rotating block via the left-end pin. The upper end of the left-end rotating block is positioned with the center bolt hole near the air intake end of the fan via bolts. The upper end of the right-end rotating block is positioned with the center bolt hole away from the air intake end of the fan via bolts. The lower end of the right-end rotating block is connected to the upper end of the motor support base via the right-end pin. The motor is horizontally fixed to the upper right end of the motor support base via bolts. The lower end of the motor support base is fixed to the aircraft crossbeam via bolts. The upper ends of the two side plates are respectively fixed to both ends of the motor support base via bolts. The lower ends of the two side plates are fixed to the aircraft crossbeam.

[0010] Furthermore, the upper ends of the two side plates are positioned relative to each other by bolts to the central threaded holes of the motor support base. The two side plates and the aircraft crossbeam form two triangles, increasing the stability of the support structure. Two symmetrical triangular weight-reducing grooves are cut in the middle of the side plates to minimize their weight while ensuring structural stability.

[0011] Furthermore, an electric motor is to be placed at the upper right end of the motor support base, and the aircraft crossbeam connected to the lower end is not a horizontal structure. Considering the stability of the structure and weight reduction, the motor support base is designed as a structure combining an I-beam and a triangle, which ensures the stability of the support structure and achieves the effect of weight reduction.

[0012] Furthermore, the adjustable support structure for the distributed electric ducted fan is a pitch-adjustable support structure. The adjustment process is as follows: the inner ring of the bearing is connected to the outer ring of the bearing through eight balls, ensuring that the inner ring of the bearing rotates without slipping; the internal thread of the inner ring of the bearing meshes with the external thread of the screw, and the rotation of the inner ring of the bearing drives the screw to slide up and down; the sliding of the screw drives the left-end pin and the left-end rotating block to slide; since the right-end pin is fixed longitudinally, the left-end rotating block and the right-end rotating block rotate relative to the left-end pin and the right-end pin, thereby realizing the pitch adjustment of the fan.

[0013] Furthermore, both the bearing's internal thread and the screw's external thread are left-hand threads with a pitch of 1mm. When the bearing's inner ring rotates clockwise one revolution, the screw moves upward by 1mm. Simultaneously, the centers of gravity of the left and right pins are on the same horizontal line. Therefore, assuming the distance between the centers of gravity of the left and right pins is y, and the bearing's inner ring rotates clockwise x revolutions, the fan's clockwise pitch adjustment angle α is: Similarly, the counterclockwise tilt adjustment angle of the fan can be obtained.

[0014] Furthermore, the right-end rotating block and the motor support seat have rounded rectangular slots as channels for the introduction of the motor's external wiring into the fan.

[0015] The beneficial effects of this invention include:

[0016] (1) The adjustable support structure of the distributed electric ducted fan of the present invention utilizes the stability of the triangle to balance and transmit the force and torque generated by the ducted fans distributed in different positions.

[0017] (2) The supporting structure is made lighter by opening weight-reducing grooves.

[0018] (3) The adjustable design of the electric ducted fan support structure in this invention improves the installation accuracy of the ducted fan and ensures the high-performance flight of the aircraft. Attached Figure Description

[0019] Figure 1 This is a front view of the adjustable support structure for the distributed electric ducted fan of the present invention;

[0020] Figure 2 This is a triaxial view of the adjustable support structure for the distributed electric ducted fan of the present invention.

[0021] Figure 3 An exploded view of the lifting drive component of the adjustable support structure for the distributed electric ducted fan of the present invention;

[0022] Figure 4 This is a cross-sectional view of the lifting drive component of the adjustable support structure for the distributed electric ducted fan of the present invention.

[0023] Figure 5The three views are of the motor support base and side plate of the adjustable support structure for the distributed electric ducted fan of the present invention.

[0024] Figure 6 This is a distribution diagram of the adjustable support structure for the distributed electric ducted fan of the present invention. Detailed Implementation

[0025] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the protection scope of the present invention.

[0026] This invention provides an adjustable support structure for a distributed electric ducted fan. An embodiment of this invention is a distributed electric ducted fan containing six ducted fans, such as... Figure 6 As shown, six ducted fans are evenly distributed on the upper part of the aircraft and fixed to the aircraft beam by a support structure.

[0027] like Figures 1-5 As shown, the adjustable support structure of the distributed electric ducted fan of the present invention includes a cylinder 1, a bearing 2, a bearing bolt 3, a screw 4, a left-end pin 5, a left-end rotating block 6, a bolt 7, a fan 8, a right-end rotating block 9, a right-end pin 10, a motor support seat 11, a motor 12, and a side plate 13. The lower end of the cylinder 1 is fixed to the aircraft crossbeam; the outer ring of the bearing 2 is positioned with the center bolt hole at the upper end of the cylinder 1 by bearing bolts 3; the inner thread of the bearing 2 meshes with the outer thread of the screw 4; the upper end of the screw 4 is connected to the lower end of the left end rotating block 6 by the left end pin 5; the upper end of the left end rotating block 6 is positioned with the center bolt hole near the air intake end of the fan 8 by bolts; the right end rotating block 9 is positioned with the center bolt hole away from the air intake end of the fan 8 by bolts 7; the lower end of the right end rotating block 9 is connected to the motor support base 11 by the right end pin 10; the motor 12 is horizontally fixed to the upper right end of the motor support base 11 by bolts 7; the lower end of the motor support base 11 is fixed to the aircraft crossbeam by bolts; the upper ends of the two side plates 13 are respectively fixed to both ends of the motor support base 11 by bolts; the lower ends of the two side plates 13 are fixed to the aircraft crossbeam.

[0028] The adjustment process of the fan 8 is as follows: the inner ring of the bearing 2 is rotated. Since the inner ring of the bearing 2 is connected to the outer ring of the bearing 2 through 8 balls, it can ensure that the inner ring of the bearing 2 rotates without sliding up and down; the inner thread of the inner ring of the bearing 2 meshes with the outer thread of the screw 4, and the rotation of the inner ring of the bearing 2 drives the screw 4 to slide up and down; the sliding of the screw 4 drives the left end pin 5 and the left end rotating block 6 to slide up and down; since the right end pin 10 is fixed longitudinally, the left end rotating block 6 and the right end rotating block 9 rotate relative to the left end pin 5 and the right end pin 10 respectively, thereby realizing the pitch adjustment of the fan 8.

[0029] The internal thread of bearing 2 and the external thread of screw 4 are both left-hand threads with a pitch of 1mm. When the inner ring of bearing 2 rotates clockwise one revolution, screw 4 moves upward by 1mm. Simultaneously, the centers of mass of the left-end pin 5 and the right-end pin 10 are on the same horizontal line. Therefore, assuming the distance between the centers of mass of the left-end pin 5 and the right-end pin 10 is y, and the inner ring of bearing 2 rotates clockwise x revolutions, the clockwise rotation angle α of fan 8 is: Similarly, the counterclockwise rotation angle of fan 8 can be obtained.

[0030] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An adjustable support structure for a distributed electric ducted fan, characterized in that: The system includes a cylinder (1), a bearing (2), a bearing bolt (3), a screw (4), a left-end pin (5), a left-end rotating block (6), a bolt (7), a fan (8), a right-end rotating block (9), a right-end pin (10), a motor support (11), a motor (12), and a side plate (13). The lower end of the cylinder (1) is fixed to the aircraft beam. The outer ring of the bearing (2) is positioned with the upper center bolt hole of the cylinder (1) by the bearing bolt (3). The inner thread of the bearing (2) meshes with the outer thread of the screw (4). The upper end of the screw (4) is connected to the lower end of the left-end rotating block (6) by the left-end pin (5). The upper end of the rotating block (6) is positioned with the fan (8) near the center bolt hole of the air intake end by bolts; the upper end of the right rotating block (9) is positioned with the fan (8) away from the center bolt hole of the air intake end by bolts (7); the lower end of the right rotating block (9) is connected to the motor support base (11) by the right pin (10); the motor (12) is horizontally fixed to the upper end of the motor support base (11) by bolts; the lower end of the motor support base (11) is fixed to the aircraft beam by bolts; the upper ends of the two side plates (13) are respectively fixed to the two ends of the motor support base (11) by bolts; the lower ends of the two side plates (13) are fixed to the aircraft beam. The upper ends of the two side plates (13) are positioned with the central threaded hole of the motor support seat (11) by bolts. The two side plates (13) and the aircraft crossbeam form two triangles to increase the stability of the support structure. Two symmetrical triangular weight-reducing grooves are opened in the middle of the side plates (13). The adjustable support structure of the distributed electric ducted fan can adjust the pitch of the fan. The inner ring of the bearing (2) is connected to the outer ring of the bearing (2) through 8 balls, ensuring that the inner ring of the bearing (2) rotates without sliding up and down. The inner thread of the inner ring of the bearing (2) meshes with the outer thread of the screw (4). The rotation of the inner ring of the bearing (2) drives the screw (4) to slide up and down. The sliding of the screw (4) drives the left end pin (5) and the left end rotating block (6) to slide. The left end rotating block (6) and the right end rotating block (9) rotate relative to the left end pin (5) and the right end pin (10), thereby realizing the adjustable pitch of the fan.

2. The adjustable support structure for a distributed electric ducted fan according to claim 1, characterized in that: An electric motor (12) is placed at the upper right end of the motor support (11). The motor support (11) is a structure combining an I-beam and a triangle.

3. The adjustable support structure for a distributed electric ducted fan according to claim 1, characterized in that: The internal thread of the bearing (2) and the external thread of the screw (4) are both left-hand threads with a pitch of 1 mm. When the inner ring of the bearing (2) rotates clockwise one revolution, the screw (4) moves upward by 1 mm. At the same time, the centroids of the left-end pin (5) and the right-end pin (10) are on the same horizontal line. Assuming the distance between the centroids of the left-end pin (5) and the right-end pin (10) is... The inner ring of bearing (2) rotates clockwise. The fan (8) is rotated clockwise to adjust its pitch angle. for: Similarly, the counterclockwise pitch adjustment angle of the fan (8) is obtained.

4. The adjustable support structure for a distributed electric ducted fan according to claim 1, characterized in that: The right-end rotating block (9) and the motor support base (11) have rounded rectangular slots as channels for the external wiring of the motor (12) to be introduced into the fan (8).

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