Nacelle structure for an electric aircraft

Abstract

The application provides a nacelle structure of an electric aircraft, comprising: upper and lower skins riveted with frames, beams and reinforcing members in the nacelle structure; a tilt-rotor connecting joint connected with a tilt mechanism connecting frame, a tilt-rotor motor and a tilt mechanism; a tilt mechanism connecting frame used for fixing the tilt-rotor connecting joint and riveted on the upper and lower skins; a controller mounting assembly connected by a controller front partition frame, a controller rear partition frame, a controller left short beam and a controller right short beam and used for mounting a controller; a nacelle wing connecting frame used for connecting with a wing, wherein the wing connecting frame comprises a front wing connecting frame and a rear wing connecting frame; and a speed reducer connecting frame riveted with the upper and lower skins and located at the tail of the nacelle structure and connected with a speed reducer, wherein the speed reducer connecting frame is designed with eight bolt connecting holes.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircrafts, and relates to a nacelle structure of an electric aircraft. BACKGROUND

[0002] An electric vertical take-off and landing (EVTO) aircraft is a new type of aircraft, which is different from a traditional aircraft. First, in order to reduce air pollution and noise pollution, the power system of the electric vertical take-off and landing aircraft directly converts electric energy into mechanical energy to provide power for flight. Generally, a battery carried by the aircraft provides electric energy for a motor, and a propeller installed on a rotor shaft of the motor is driven to rotate together, so that the propeller generates thrust and lift. In order to realize the convenience of vertical take-off of a helicopter and the high-speed flight capability of a fixed-wing aircraft, and to realize conversion between the two modes, a tilting mechanism is used as a method.

[0003] After checking the nacelle structure in the past, it is found that the design is complex, and generally, a metal beam and a reinforcing rib are designed inside for longitudinal bearing, which are used to fix a bearing control mechanism, a tilting rotor and a speed reducer. The bending moment load is mainly transmitted by the metal longitudinal beam. As a result, a large amount of metal structure is used, which is heavy and complex to assemble, and the effect is not ideal. SUMMARY

[0004] The purpose of the application is to provide a nacelle structure of an electric aircraft, six frame structures are designed, and a control mechanism, a tilting rotor and a speed reducer are reasonably arranged. The frames are connected by a skin and transmit force, so that the traditional longitudinal bearing metal beam can be cancelled, and a large amount of composite material is used to save a large amount of weight under the requirements of strength and stiffness. The tilting mechanism and the speed reducer can be detached from the structure, which is convenient for daily maintenance.

[0005] The application provides a nacelle structure of an electric aircraft, which comprises six frames, beams, upper and lower skins.

[0006] The upper and lower skins are connected with the six frames and beams by riveting to form a nacelle structure cylinder. The six frames are a tilting mechanism connecting frame, a controller front partition frame, a controller rear partition frame, a front wing connecting frame, a rear wing connecting frame and a speed reducer connecting frame from front to back.

[0007] An oval hole is arranged on the tilting mechanism connecting frame. The tilting mechanism is arranged in the nacelle structure cylinder through the oval hole. A tilting rotor connecting joint is arranged on the tilting mechanism connecting frame. A tilting rotor motor is rotatably connected to the tilting rotor connecting joint. A tilting rotor is arranged on the tilting rotor motor. The tilting mechanism is connected with the tilting rotor motor to drive the tilting rotor motor to rotate.

[0008] Wire holes are further arranged on the tilting mechanism connecting frame and the controller front partition frame.

[0009] The controller front partition frame and the controller rear partition frame are further connected with a controller right short beam and a controller left short beam, forming a controller mounting assembly for mounting the controller, and the cable of the controller passes through the wire hole and is connected with the tilting mechanism and the tilting rotor motor;

[0010] The front wing connecting frame and the rear wing connecting frame are used for connecting with the wings of the electric aircraft;

[0011] The reducer connecting frame is used for mounting the reducer;

[0012] The upper skin and the lower skin are composite laminates;

[0013] The tilting mechanism connecting frame is a whole stiffened shell structure, and the peripheral flange is riveted with the upper skin and the lower skin.

[0014] Optionally, the upper skin and the lower skin are both provided with a controller ventilation hole;

[0015] The upper skin is provided with a wire hole at the wing connecting position.

[0016] Optionally, the tilting rotor connecting joint is a two-piece triangular connecting joint;

[0017] The oval hole in the middle of the tilting mechanism connecting frame is provided with bolt holes on both sides for connecting the tilting rotor connecting joint;

[0018] The triangular connecting joint is provided with a rotating shaft hole at the top corner for rotating connection with the tilting rotor motor, and the bottom profile is trapezoidal and matched with the outer shape of the tilting mechanism connecting frame; the triangular connecting joint is provided with an inclined rib connecting the top corner and the bottom surface, and the width of the bottom of the inclined rib is greater than the width of the top;

[0019] Two bolt holes are arranged on both sides of the inclined rib.

[0020] Optionally, each triangular connecting joint is single-ear connected with the tilting rotor motor.

[0021] Optionally, the controller left short beam and the controller right short beam are riveted above the controller front partition frame and the controller rear partition frame and are riveted with the upper and lower skins;

[0022] The controller left short beam is provided with a controller.

[0023] Optionally, the top of the front wing connecting frame and the rear wing connecting frame is provided with a single-ear joint connected with the double-ear joint of the wing.

[0024] Optionally, eight bolt holes matched with the reducer are designed on the circumference of the reducer connecting frame.

[0025] Optionally, the reducer connecting frame is designed with a limiting boss at the bolt hole on the inner side, for limiting the rotation of the connecting bolt.

[0026] Advantages of the present application:

[0027] The present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame. The present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame. The present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0029] Figure 2 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0030] Figure 3 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0031] Figure 4 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0032] Figure 5 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0033] Figure 6 The nacelle structure of the present application provides a nacelle structure of an electric aircraft, which is a long tubular structure composed of upper and lower composite skins, a tilt-rotor connecting joint, a wing connecting frame and a reducer connecting frame.

[0034] 1-tilt mechanism fairing; 2-lower skin; 3-upper skin; 4-wing-body blending trailing edge fairing; 5-reducer fairing; 6-rear rotor; 7-duct; 8-front rotor; 9-tilt-rotor connecting joint; 10-tilt mechanism connecting frame;

[0035] 11.1-controller front bulkhead; 11.2-controller right short beam; 11.3-controller left short beam; 11.4-controller rear bulkhead; 12-front wing connecting frame; 13-rear wing connecting frame; 14-reducer connecting frame; 15-self-made bolt; 16-tilt-rotor motor; 17-tilt mechanism; 18-wing. DETAILED DESCRIPTION

[0036] Please refer to Figures 1-6The key of the application is to provide a nacelle with a composite material skin as a main load-bearing structure, wherein the upper and lower skins are both composite material laminated structures, the weight of the nacelle is greatly reduced compared with the nacelle with a metal frame beam as a main load-bearing structure, and the composite material skin structure is easier to maintain and process than the metal skin structure, the composite material skin is divided into upper and lower skin blocks, and is easier to process and assemble with the internal structure.

[0037] The tilting mechanism connecting frame is a key component for connecting the electric tilting rotor, and is a whole stiffened panel structure; the cable of the controller passes through the wire passing hole and the elliptical hole on the frame, and the electric tilting mechanism is arranged inside the nacelle barrel through the elliptical hole;

[0038] The controller front partition frame and the controller rear partition frame are support components of the controller installation assembly, and are provided with large elliptical holes in the middle part for passing through the controller cable; the elliptical holes are provided with reinforcing ribs on both sides for connecting with the left and right short beams of the controller;

[0039] The front wing connecting frame and the rear wing connecting frame are mainly used for connecting with the joints on the wings, and are provided with single ear joints on the left and right sides of the upper part of the frame; the middle part can pass through the cable from the wing;

[0040] The reducer connecting frame is mainly used for connecting with the reducer through the bolt holes on the web plate, the web plate is relatively thick, reinforcing ribs are arranged on both sides of the bolt holes, and the web plate is provided with two cable holes for passing through the cable from the inside of the nacelle to the reducer.

[0041] The tilting mechanism fairing 1 is installed on the tilting mechanism connecting frame; the wing-body blending trailing edge fairing 4 is installed at the middle part of the upper skin 3 and the lower skin 2; the guide cone 7 is installed at the controller of the upper and lower skins; and the reducer fairing 5 is installed on the reducer connecting frame.

[0042] The application provides a nacelle structure of an electric aircraft, which comprises:

[0043] The upper and lower skins are connected with the frames and beams in the nacelle through riveting to form a nacelle structure barrel;

[0044] The tilting mechanism connecting frame is riveted with the upper and lower skins, and a tilting rotor connecting joint is installed thereon; the tilting mechanism connecting frame is designed with an elliptical hole and a wire passing hole.

[0045] The tilting rotor connecting joint is connected with the tilting mechanism connecting frame, and is used for installing a tilting rotor motor; the tilting rotor connecting joint comprises two parts; and the tilting rotor motor is provided with a front rotor 8.

[0046] The controller installation assembly is used for installing a controller, and is riveted on the upper and lower skins;

[0047] Nacelle wing connecting frame, for connecting with the wing;

[0048] Reduction gear connecting frame, located at the tail position of the nacelle structure, for installing the reduction gear.

[0049] Preferably, the upper and lower skins include:

[0050] Upper skin, nacelle cylinder upper load-bearing member, with wire passage holes and radiator vent holes designed thereon;

[0051] Lower skin, nacelle cylinder lower load-bearing member, riveted with the upper skin to form the nacelle cylinder structure, with radiator vent holes designed thereon.

[0052] Preferably, the tilt-rotor connecting joint includes:

[0053] First triangular connecting joint, connected with the first double-ear joint of the tilt-rotor motor, designed as a shell plus inclined rib structure;

[0054] Second triangular connecting joint, connected with the second double-ear joint of the tilt-rotor motor, designed as a shell plus inclined rib structure.

[0055] Preferably, the tilt mechanism connecting frame:

[0056] Connected with the tilt-rotor connecting joint, flange riveted with the upper and lower skins, with an elliptical hole for passing through the tilt mechanism designed on the tilt mechanism connecting frame;

[0057] Preferably, the controller installation assembly includes:

[0058] Controller front partition frame 11.1, with a middle elliptical hole;

[0059] The controller front partition frame is riveted with the controller left short beam and the controller right short beam, and the flange is riveted with the upper and lower skins;

[0060] Controller rear partition frame 11.4, with a middle elliptical hole;

[0061] The controller rear partition frame is riveted with the controller left short beam and the controller right short beam, and the flange is riveted with the upper and lower skins;

[0062] Controller left short beam 11.3, one end riveted with the controller front partition frame and the other end riveted with the controller rear partition frame, riveted with the upper and lower skins respectively, with a connecting hole and a supporting plate nut for installing the controller on the controller left short beam;

[0063] Controller right short beam 11.2, one end riveted with the controller front partition frame and the other end riveted with the controller rear partition frame, riveted with the upper and lower skins respectively;

[0064] Preferably, the nacelle wing connecting frame comprises:

[0065] The front wing connecting frame is riveted with the upper and lower skins, and is connected with the front wing double ear joint through the left and right single ear joints.

[0066] The rear wing connecting frame is riveted with the upper and lower skins, and is connected with the rear wing double ear joint through the left and right single ear joints.

[0067] Preferably, the reducer connecting frame comprises:

[0068] The reducer connecting frame is installed at the tail end of the nacelle structure, is riveted with the upper and lower skins, and is connected with the reducer through eight bolt holes.

[0069] Preferably, the reducer connecting bolt comprises:

[0070] The eight reducer connecting bolts are provided with special boss planes on the bolt heads, and are used in cooperation with the boss planes at the bolt holes of the reducer.

[0071] The connecting frame of the designed tilting mechanism is provided with an elliptical hole, so that the tilting mechanism can be conveniently taken out and meet the daily maintenance needs.

[0072] The designed tilting rotor connecting joint is designed in a split manner, is easy to process, and can be disassembled and maintained on the connecting frame.

[0073] The designed controller mounting assembly can mount the controller in the nacelle structure, so that the controller does not need to be installed at other places of the fuselage, thereby reducing the length of the line, saving weight, and the upper and lower skins of the nacelle are provided with heat dissipation holes, so that the radiator can dissipate heat conveniently.

[0074] The designed reducer connecting frame is riveted with the upper and lower skins, is provided with eight bolt holes, and is fixed with the reducer on the reducer connecting frame through self-made bolts.

[0075] The application is arranged on four aircrafts in a left-right symmetrical manner.

[0076] Please refer to Figure 1 、 Figure 2 , the nacelle is provided with a tilting rotor at the front part, the motor of the tilting rotor can rotate around the tilting rotor connecting joint 9, the rear part is provided with a reducer connecting frame 14 connected with the rear rotor 6, the front wing connecting frame 12 is connected with the front wing double ear joint, and the rear wing connecting frame 13 is connected with the rear wing double ear joint.

[0077] Please refer to Figure 3 、Figure 4 The tilt-rotor connecting joint 9 is installed on the tilt-mechanism connecting frame 10, and the tilt-rotor connecting joint is bolted on the tilt-mechanism connecting frame 10 respectively, facilitating disassembly and maintenance; the tilt-mechanism connecting frame 10 is designed with six fairing mounting lugs, facilitating disassembly of the fairing; the tilt-rotor motor 16 rotates around the tilt-rotor connecting joint 9, the tilt-mechanism 17 is connected with the tilt-rotor motor at one end and connected with the tilt-rotor connecting joint 9 at the other end, and the tilt-mechanism 17 can be taken out through the tilt-mechanism connecting frame 10.

[0078] Please refer to Figure 5 The reducer is installed on the reducer connecting frame 14 through the self-made bolt 15, and the reducer connecting frame 14 and the self-made bolt 15 are designed with a boss surface limiting rotation of the bolt.

[0079] Please refer to Figure 6 The installation position of the nacelle structure on the wing 18 of the electric aircraft.

[0080] The application can transmit the load transmitted by the rotor in the helicopter mode, the transition state and the fixed-wing mode, can provide an installation interface for the electric propulsion system, and can transmit the lifting force and the pulling force to the wing, the front part provides an installation interface for the tilt-rotor, the rear part provides an installation interface for the coaxial rotor system, and the middle part is connected with the wing.

[0081] The key of the application is to make the nacelle structure simple, to use a composite skin as a main load-bearing structure, to use metal pieces to connect key parts, to make the weight smaller, to connect the front and rear frames in a manner facilitating disassembly of the motor and the reducer, and to facilitate maintenance.

Claims

1. A nacelle structure for an electric aircraft, characterized in that, include: Six frames, beams, upper and lower skins; The upper and lower skins are connected to six frames and beams by riveting to form the nacelle structure. The six frames, from front to back, are the tilting mechanism connecting frame, the controller front bulkhead, the controller rear bulkhead, the front wing connecting frame, the rear wing connecting frame, and the gearbox connecting frame. The tilting mechanism connecting frame is provided with an elliptical hole; the tilting mechanism is installed in the nacelle structure cylinder through the elliptical hole, the tilting rotor connecting joint is installed on the tilting mechanism connecting frame, the tilting rotor motor is rotatably connected to the tilting rotor connecting joint, and the tilting rotor motor is provided with a tilting rotor; the tilting mechanism is connected to the tilting rotor motor to drive the tilting rotor motor to rotate. The tilting mechanism connecting frame and the controller front partition are also provided with wire holes; The controller's front and rear frames are connected by a right short beam and a left short beam, forming a controller mounting assembly for mounting the controller. The controller's cables pass through the cable holes and connect to the tilting mechanism and the tilting rotor motor. The front wing connecting frame and the rear wing connecting frame are used to connect with the wings of the electric aircraft; Gearbox connecting frame, used for mounting the gearbox; The upper and lower skins are composite laminates; The tilting mechanism connecting frame is a reinforced shell structure, with peripheral flanges riveted to the upper and lower skins.

2. The nacelle structure of the electric aircraft according to claim 1, characterized in that, Both the upper and lower skins are equipped with controller ventilation holes; There are wire holes at the connection point between the upper skin and the wing.

3. The nacelle structure of the electric aircraft according to claim 1, characterized in that, The tilt rotor connection joint consists of two identical triangular connectors. Bolt holes are provided on both sides of the elliptical hole in the middle of the tilting mechanism connecting frame for connecting the tilting rotor connecting joint; The apex of the triangular connector is provided with a rotating axial hole for the tilt rotor motor to rotate and connect. The bottom contour is trapezoidal, matching the shape of the tilt mechanism connection frame. The triangular connector is provided with a diagonal rib to connect the apex and the bottom. The bottom width of the diagonal rib is greater than the top width. Two bolt holes are provided on each side of the diagonal reinforcement.

4. The nacelle structure of the electric aircraft according to claim 3, characterized in that, Each triangular connector is connected to the tilt rotor motor via a single or double lug.

5. The nacelle structure of the electric aircraft according to claim 1, characterized in that, The left and right short beams of the controller are riveted to the top of the front and rear partitions of the controller, and are also riveted to the upper and lower skins. The controller is installed on the left short beam.

6. The nacelle structure of the electric aircraft according to claim 1, characterized in that, Both sides of the front wing connecting frame and the rear wing connecting frame are provided with single-ear connectors at the top, which are connected to the double-ear connectors of the wing.

7. The nacelle structure of the electric aircraft according to claim 1, characterized in that, The reducer connection frame has eight bolt holes around its circumference that are compatible with the reducer.

8. The nacelle structure of the electric aircraft according to claim 7, characterized in that, The bolt holes on the inner side of the reducer connecting frame are designed with limiting bosses to restrict the rotation of the connecting bolts.

Images