Lightweight fuselage skeleton of eVTOL aircraft
By designing an optimized lightweight fuselage skeleton of eVTOL aircraft, the problem of limited application of carbon fiber composite materials in the prior art is solved, and the effect of reducing aircraft weight, improving endurance and payload is achieved, while reducing R&D and manufacturing costs.
Patent Information
- Application Number
- CN202422028111.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-20
- Publication Date
- 2025-05-16
- Estimated Expiration
- 2034-08-20
AI Technical Summary
During the research and development process of the eVTOL aircraft, due to the complex shape of carbon fiber composite materials, high mold costs, many connectors, and long manufacturing cycles, the R&D cycles are long and the cost is high.
Design a lightweight body skeleton, adopting structures such as rectangular bottom main frame, top frame, ring frame, column and tail frame. By optimizing the skeleton design and material selection, simplifying the structure, reducing material use, and improving manufacturing efficiency.
It has achieved the reduction of the overall weight of the aircraft, increased range, increased payload, and reduced R&D and manufacturing costs.
Smart Images
Figure CN222876261U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to an aircraft fuselage frame, and more specifically, to a lightweight fuselage frame for an eVTOL aircraft. Background Technology
[0002] eVTOL aircraft have special requirements for airframe strength and weight, so a typical eVTOL airframe is made of carbon fiber composite materials, using a combination of plate shell structure and hollow tube structure. However, during the verification phase of the overall design and layout of eVTOL products, the application of carbon fiber composite materials is limited by factors such as complex shapes, high mold costs, numerous connectors, and long manufacturing cycles, resulting in a long development cycle and high development costs. Utility Model Content
[0003] This invention addresses the aforementioned deficiencies in the prior art by providing a lightweight fuselage frame for an eVTOL aircraft.
[0004] The technical solution adopted by this utility model to solve its technical problem is: to construct a lightweight fuselage frame for an eVTOL aircraft, the fuselage frame including a rectangular bottom main frame, a first head column fixed to a first side of the head of the main frame, a second head column fixed to a second side of the head of the main frame, a first ring frame fixed to the middle of the main frame, a first tail column fixed to a first side of the tail of the main frame, a second tail column fixed to a second side of the tail of the main frame, a rectangular top frame fixed between the top of the first tail column and the second tail column and the top of the first ring frame, and a tail frame fixedly connected to the main frame and the top frame and extending outward from the tail of the main frame and the top frame.
[0005] A first nose fixing post is provided between the first annular frame and the top of the first head column, which is fixedly connected to the first annular frame and the top of the first head column and extends outward to the main frame head. A second nose fixing post is provided between the first annular frame and the top of the second head column, which is fixedly connected to the first annular frame and the top of the second head column and extends outward to the main frame head. A hinge seat for installing the cockpit door is fixed in the middle of the second head column.
[0006] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the main frame includes a first crossbeam, a second crossbeam arranged parallel to the first crossbeam, a third crossbeam arranged parallel to the first crossbeam, a first longitudinal beam fixed to the first side of the first crossbeam and the first side of the second crossbeam, a second longitudinal beam fixed to the second side of the first crossbeam and the second side of the second crossbeam, a third longitudinal beam fixed to the first side of the second crossbeam and the first side of the third crossbeam, and a fourth longitudinal beam fixed to the second side of the second crossbeam and the second side of the third crossbeam.
[0007] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the main frame also includes a first main diagonal brace that is fixedly connected to the middle of the first crossbeam and the first side of the third crossbeam, and a second main diagonal brace that is fixedly connected to the middle of the first crossbeam and the second side of the third crossbeam. Both the first main diagonal brace and the second main diagonal brace pass through the second crossbeam.
[0008] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, a first auxiliary brace is fixed between the first side of the first crossbeam and the first end of the first main brace; a second auxiliary brace is fixed between the second side of the first crossbeam and the first end of the second main brace; a third auxiliary brace is fixed between the middle of the second crossbeam and the middle of the first main brace; a fourth auxiliary brace is fixed between the middle of the second crossbeam and the middle of the second main brace; a fifth auxiliary brace is fixed between the middle of the third crossbeam and the second end of the first main brace; and a sixth auxiliary brace is fixed between the middle of the third crossbeam and the second end of the second main brace.
[0009] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the top frame includes a fourth crossbeam, a fifth crossbeam arranged parallel to the fourth crossbeam, a fifth longitudinal beam fixed to the first side of the fourth crossbeam and the first side of the fifth crossbeam, a sixth longitudinal beam fixed to the second side of the fourth crossbeam and the second side of the fifth crossbeam, a first connecting beam fixed to the first side of the fourth crossbeam and the first side of the fifth crossbeam and located inside the fifth longitudinal beam, a second connecting beam fixed to the second side of the fourth crossbeam and the second side of the fifth crossbeam and located inside the sixth longitudinal beam, a first wing mounting bar fixed to the first end of the first connecting beam and the first end of the second connecting beam, and a second wing mounting bar fixed to the second end of the first connecting beam and the second end of the second connecting beam.
[0010] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, a first oblique reinforcing column is fixed between the middle of the fourth crossbeam and the middle of the first connecting beam, a second oblique reinforcing column is fixed between the middle of the fourth crossbeam and the middle of the second connecting beam, a third oblique reinforcing column is fixed between the middle of the fifth crossbeam and the middle of the first connecting beam, and a fourth oblique reinforcing column is fixed between the middle of the fifth crossbeam and the middle of the second connecting beam.
[0011] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the fourth crossbeam is fixedly connected to the first ring frame through at least two first connecting columns, and the fifth crossbeam is fixedly connected to the tail frame through at least two second connecting columns.
[0012] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the tail frame includes a sixth crossbeam, a first inclined beam extending obliquely upward from the first side of the tail of the main frame, a second inclined beam extending obliquely upward from the second side of the tail of the main frame, a first tail frame column fixed between the first side of the sixth crossbeam and the tail of the first inclined beam, and a second tail frame column fixed between the second side of the sixth crossbeam and the tail of the second inclined beam.
[0013] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, the tail frame also includes a seventh crossbeam fixed in the middle of the first tail frame column and the middle of the second tail frame column. A fifth oblique reinforcing column is fixed between the middle of the sixth crossbeam and the first end of the seventh crossbeam, and a sixth oblique reinforcing column is fixed between the middle of the sixth crossbeam and the second end of the seventh crossbeam.
[0014] In the lightweight fuselage frame of the eVTOL aircraft described in this utility model, a first luggage compartment door mounting bar for installing a luggage compartment door is fixed at the tail of the first inclined beam, and a second luggage compartment door mounting bar for installing a luggage compartment door is fixed at the tail of the second inclined beam.
[0015] The lightweight fuselage frame of the eVTOL aircraft of this invention has the following beneficial effects: When using the lightweight fuselage frame of the eVTOL aircraft of this invention, by setting a bottom main frame and a top frame, using the bottom main frame and top frame as the main frame, and then supplementing it with a first ring frame, a first nose column, a second nose column, a first tail column, a second tail column, a tail frame, etc., the fuselage frame is designed as a cage-shaped fuselage frame made of hollow square and rectangular tubes. By optimizing the frame design and simplifying the frame structure, while ensuring the safety of the frame's stress strength, the use of materials is reduced, achieving the effect of reducing the frame weight, thereby reducing the overall weight of the aircraft, increasing the range, and increasing the payload. Seamless square tube metal material is used, and the frame is manufactured through welding. Installation positions are reserved for system components such as wings, fuselage tail end, cockpit door hinges, floor, landing gear, etc. The simplified fuselage frame design also provides the largest possible area for the design of the windshield and side windows, allowing the pilot / passengers to obtain a better observation / viewing field of vision. Attached Figure Description
[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments. In the accompanying drawings:
[0017] Figure 1 This is a structural schematic diagram of the lightweight fuselage frame of the eVTOL aircraft of this utility model. Detailed Implementation
[0018] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in further detail below with reference to the accompanying drawings.
[0019] like Figure 1 As shown, in the first embodiment of the lightweight fuselage frame of the eVTOL aircraft of this utility model, the fuselage frame 10 includes a rectangular bottom main frame 11, a first head column 12 fixed to a first side of the head of the main frame 11, a second head column 13 fixed to a second side of the head of the main frame 11, a first ring frame 14 fixed to the middle of the main frame 11, a first tail column 15 fixed to a first side of the tail of the main frame 11, a second tail column 16 fixed to a second side of the tail of the main frame 11, a rectangular top frame 17 fixed between the top of the first tail column 15 and the second tail column 16 and the top of the first ring frame 14, and a tail frame 18 fixedly connected to the main frame 11 and the top frame 17 and extending outward from the tail of the main frame 11 and the top frame 17.
[0020] A first nose fixing post 19 is provided between the top of the first ring frame 14 and the top of the first head column 12, and extends outward from the head of the main frame 11. A second nose fixing post 20 is provided between the top of the first ring frame 14 and the top of the second head column 13, and extends outward from the head of the main frame 11. A hinge seat 21 for installing the cockpit door is fixed in the middle of the second head column 13.
[0021] When using the lightweight fuselage frame of this eVTOL aircraft, a bottom main frame 11 and a top frame 17 are set up, with the bottom main frame 11 and the top frame 17 serving as the main frame. Then, supplemented by structures such as the first ring frame 14, the first nose column 12, the second nose column 13, the first tail column 15, the second tail column 16, and the tail frame 18, the fuselage frame 10 is designed as a cage-like fuselage frame 10 made of hollow square and rectangular tubes. By optimizing the frame design and simplifying the frame structure, while ensuring the frame's structural strength, material usage is reduced, achieving the effect of reducing the frame's weight, thereby reducing the overall weight of the aircraft, increasing range, and increasing payload. Seamless square tube metal material is used, and the frame is manufactured through welding. Installation positions are reserved for system components such as the wings, fuselage tail end, cockpit door hinges, floor, and landing gear. The simplified fuselage frame 10 design also provides the largest possible area for the design of the windshield and side windows, allowing pilots / passengers to obtain better observation / viewing visibility.
[0022] Preferably, the main frame 11, first head column 12, second head column 13, first ring frame 14, first tail column 15, second tail column 16, top frame 17, tail frame 18, first head fixing column 19, and second head fixing column 20 in this application are all made of seamless hollow square and rectangular metal tubes, and the above structures are fixedly connected to each other by welding. The fuselage frame is made of seamless hollow square and rectangular metal tubes, which can meet the static load requirement of more than 8 tons. The cross-section of each structural component adopts the minimum cross-sectional area, and the overlap angle between each independent structure is the optimal load-bearing angle calculated, forming a very low frame weight / load-bearing ratio, that is, the lightest weight, the maximum load-bearing value, and the structural components themselves are relatively easy to process and have low manufacturing costs.
[0023] Specifically, the main frame 11 includes a first crossbeam 22, a second crossbeam 23 arranged parallel to the first crossbeam 22, a third crossbeam 24 arranged parallel to the first crossbeam 22, a first longitudinal beam 25 fixed to the first side of the first crossbeam 22 and the first side of the second crossbeam 23, a second longitudinal beam 26 fixed to the second side of the first crossbeam 22 and the second side of the second crossbeam 23, a third longitudinal beam 27 fixed to the first side of the second crossbeam 23 and the first side of the third crossbeam 24, and a fourth longitudinal beam 28 fixed to the second side of the second crossbeam 23 and the second side of the third crossbeam 24.
[0024] Furthermore, the main frame 11 also includes a first main diagonal brace 29 that is fixedly connected to the middle of the first crossbeam 22 and the first side of the third crossbeam 24, and a second main diagonal brace 30 that is fixedly connected to the middle of the first crossbeam 22 and the second side of the third crossbeam 24. Both the first main diagonal brace 29 and the second main diagonal brace 30 pass through the second crossbeam 23.
[0025] By setting the first main diagonal brace 29 and the second main diagonal brace 30, the overall structural strength of the main frame 11 is increased.
[0026] Furthermore, a first auxiliary diagonal brace 31 is fixed between the first side of the first crossbeam 22 and the first end of the first main diagonal brace 29; a second auxiliary diagonal brace 32 is fixed between the second side of the first crossbeam 22 and the first end of the second main diagonal brace 30; a third auxiliary diagonal brace 33 is fixed between the middle of the second crossbeam 23 and the middle of the first main diagonal brace 29; a fourth auxiliary diagonal brace 34 is fixed between the middle of the second crossbeam 23 and the middle of the second main diagonal brace 30; a fifth auxiliary diagonal brace 35 is fixed between the middle of the third crossbeam 24 and the second end of the first main diagonal brace 29; and a sixth auxiliary diagonal brace 36 is fixed between the middle of the third crossbeam 24 and the second end of the second main diagonal brace 30.
[0027] By setting the first secondary diagonal brace 31, the second secondary diagonal brace 32, the third secondary diagonal brace 33, the fourth secondary diagonal brace 34, the fifth secondary diagonal brace 35, and the sixth secondary diagonal brace 36, the overall structural strength of the main frame 11 is further increased. This ensures that the various connecting structures of the main frame 11 are fixedly connected to form a whole.
[0028] Specifically, the top frame 17 includes a fourth crossbeam 37, a fifth crossbeam 38 arranged parallel to the fourth crossbeam 37, a fifth longitudinal beam 39 fixed to the first side of the fourth crossbeam 37 and the first side of the fifth crossbeam 38, a sixth longitudinal beam 40 fixed to the second side of the fourth crossbeam 37 and the second side of the fifth crossbeam 38, a first connecting beam 41 fixed to the first side of the fourth crossbeam 37 and the first side of the fifth crossbeam 38 and located inside the fifth longitudinal beam 39, a second connecting beam 42 fixed to the second side of the fourth crossbeam 37 and the second side of the fifth crossbeam 38 and located inside the sixth longitudinal beam 40, a first wing mounting bar 43 fixed to the first end of the first connecting beam 41 and the first end of the second connecting beam 42, and a second wing mounting bar 44 fixed to the second end of the first connecting beam 41 and the second end of the second connecting beam 42.
[0029] Furthermore, a first diagonal reinforcing column 45 is fixed between the middle of the fourth crossbeam 37 and the middle of the first connecting beam 41, a second diagonal reinforcing column is fixed between the middle of the fourth crossbeam 37 and the middle of the second connecting beam 42, a third diagonal reinforcing column 46 is fixed between the middle of the fifth crossbeam 38 and the middle of the first connecting beam 41, and a fourth diagonal reinforcing column is fixed between the middle of the fifth crossbeam 38 and the middle of the second connecting beam 42.
[0030] By setting the first oblique reinforcing column 45, the second oblique reinforcing column, the third oblique reinforcing column 46, and the fourth oblique reinforcing column, the overall strength of the top frame 17 is increased. Preferably, the first wing mounting bar 43 and the second wing mounting bar 44 are fixedly welded to the first oblique reinforcing column 45, the second oblique reinforcing column, the third oblique reinforcing column 46, and the fourth oblique reinforcing column.
[0031] Furthermore, the fourth crossbeam 37 is fixedly connected to the first ring frame 14 by at least two first connecting columns 47, and the fifth crossbeam 38 is fixedly connected to the tail frame 18 by at least two second connecting columns 48.
[0032] Specifically, the tail frame 18 includes a sixth crossbeam 49, a first inclined beam 50 extending obliquely upward from the first side of the tail of the main frame 11, a second inclined beam 51 extending obliquely upward from the second side of the tail of the main frame 11, a first tail frame column 52 fixed between the first side of the sixth crossbeam 49 and the tail of the first inclined beam 50, and a second tail frame column 53 fixed between the second side of the sixth crossbeam 49 and the tail of the second inclined beam 51.
[0033] The tail frame 18 also includes a seventh crossbeam 54 fixed in the middle of the first tail frame column 52 and the middle of the second tail frame column 53. A fifth diagonal reinforcing column is fixed between the middle of the sixth crossbeam 49 and the first end of the seventh crossbeam 54. A sixth diagonal reinforcing column 55 is fixed between the middle of the sixth crossbeam 49 and the second end of the seventh crossbeam 54.
[0034] The overall structural strength of the tail frame 18 is enhanced by setting the seventh crossbeam 54, the fifth diagonal reinforcing column and the sixth diagonal reinforcing column 55.
[0035] Furthermore, the tail of the first inclined beam 50 is fixed with a first luggage compartment door mounting bar for installing the luggage compartment door, and the tail of the second inclined beam 51 is fixed with a second luggage compartment door mounting bar 56 for installing the luggage compartment door.
[0036] The first end of the first luggage compartment door mounting bar and the second luggage compartment door mounting bar 56 are fixedly welded to the outer side of the tail frame 18, and the second end of the first luggage compartment door mounting bar and the second luggage compartment door mounting bar 56 extends outward and upward. The first luggage compartment door mounting bar and the second luggage compartment door mounting bar 56 are used to install the luggage compartment door.
[0037] Furthermore, in this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," "stacked," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0038] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the description and drawings of this utility model, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.
Claims
1. A lightweight fuselage frame for an eVTOL aircraft, characterized in that: The fuselage frame includes a rectangular bottom main frame, a first head column fixedly arranged on a first side of the head of the main frame, a second head column fixedly arranged on a second side of the head of the main frame, a first annular frame fixedly arranged in the middle of the main frame, a first tail column fixedly arranged on a first side of the tail of the main frame, a second tail column fixedly arranged on a second side of the tail of the main frame, a rectangular top frame fixedly arranged between the tops of the first tail column and the second tail column and the top of the first annular frame, and a tail frame fixedly connected to the main frame and the top frame and extending outward from the tail of the main frame and the top frame; A first nose fixing column is provided between the first annular frame and the top of the first head column, which is fixedly connected to the first annular frame and the top of the first head column and extends to the outside of the head of the main frame; a second nose fixing column is provided between the first annular frame and the top of the second head column, which is fixedly connected to the first annular frame and the top of the second head column and extends to the outside of the head of the main frame; a hinged seat for installing a cockpit door is fixedly provided in the middle of the second head column.
2. The lightweight fuselage frame of an eVTOL aircraft according to claim 1, characterized in that: The main frame includes a first crossbeam, a second crossbeam arranged parallel to the first crossbeam, a third crossbeam arranged parallel to the first crossbeam, a first longitudinal beam fixed on the first side of the first crossbeam and the first side of the second crossbeam, a second longitudinal beam fixed on the second side of the first crossbeam and the second side of the second crossbeam, a third longitudinal beam fixed on the first side of the second crossbeam and the first side of the third crossbeam, and a fourth longitudinal beam fixed on the second side of the second crossbeam and the second side of the third crossbeam.
3. The lightweight fuselage frame of the eVTOL aircraft according to claim 2, characterized in that: The main frame also includes a first main diagonal brace fixedly connected to the middle of the first beam and the first side of the third beam, and a second main diagonal brace fixedly connected to the middle of the first beam and the second side of the third beam, and both the first main diagonal brace and the second main diagonal brace pass through the second beam.
4. The lightweight fuselage frame of the eVTOL aircraft according to claim 3, characterized in that: A first secondary diagonal brace is fixedly provided between the first side of the first crossbeam and the first end of the first main diagonal brace, a second secondary diagonal brace is fixedly provided between the second side of the first crossbeam and the first end of the second main diagonal brace, a third secondary diagonal brace is fixedly provided between the middle part of the second crossbeam and the middle part of the first main diagonal brace, a fourth secondary diagonal brace is fixedly provided between the middle part of the second crossbeam and the middle part of the second main diagonal brace, a fifth secondary diagonal brace is fixedly provided between the middle part of the third crossbeam and the second end of the first main diagonal brace, and a sixth secondary diagonal brace is fixedly provided between the middle part of the third crossbeam and the second end of the second main diagonal brace.
5. The lightweight fuselage frame of an eVTOL aircraft according to claim 1, characterized in that: The top frame includes a fourth cross beam, a fifth cross beam arranged parallel to the fourth cross beam, a fifth longitudinal beam fixedly arranged on a first side of the fourth cross beam and a first side of the fifth cross beam, a sixth longitudinal beam fixedly arranged on a second side of the fourth cross beam and a second side of the fifth cross beam, a first connecting beam fixedly arranged on a first side of the fourth cross beam and a first side of the fifth cross beam and located on an inner side of the fifth longitudinal beam, a second connecting beam fixedly arranged on a second side of the fourth cross beam and a second side of the fifth cross beam and located on an inner side of the sixth longitudinal beam, a first wing mounting bar fixedly arranged on a first end of the first connecting beam and a first end of the second connecting beam, and a second wing mounting bar fixedly arranged on a second end of the first connecting beam and a second end of the second connecting beam.
6. The lightweight fuselage frame of the eVTOL aircraft according to claim 5, characterized in that: A first oblique reinforcement column is fixedly provided between the middle portion of the fourth cross beam and the middle portion of the first connecting beam, a second oblique reinforcement column is fixedly provided between the middle portion of the fourth cross beam and the middle portion of the second connecting beam, a third oblique reinforcement column is fixedly provided between the middle portion of the fifth cross beam and the middle portion of the first connecting beam, and a fourth oblique reinforcement column is fixedly provided between the middle portion of the fifth cross beam and the middle portion of the second connecting beam.
7. The lightweight fuselage frame of an eVTOL aircraft according to claim 6, characterized in that: The fourth cross beam is fixedly connected to the first annular frame through at least two first connecting columns, and the fifth cross beam is fixedly connected to the tail frame through at least two second connecting columns.
8. The lightweight fuselage frame of an eVTOL aircraft according to claim 1, characterized in that: The tail frame includes a sixth cross beam, a first oblique beam extending obliquely upward from the first side of the tail of the main frame, a second oblique beam extending obliquely upward from the second side of the tail of the main frame, a first tail frame column fixed between the first side of the sixth cross beam and the tail of the first oblique beam, and a second tail frame column fixed between the second side of the sixth cross beam and the tail of the second oblique beam.
9. The lightweight fuselage frame of an eVTOL aircraft according to claim 8, characterized in that: The tail frame also includes a seventh cross beam fixedly arranged at the middle of the first tail frame column and the middle of the second tail frame column, a fifth oblique reinforcement column fixedly arranged between the middle of the sixth cross beam and the first end of the seventh cross beam, and a sixth oblique reinforcement column fixedly arranged between the middle of the sixth cross beam and the second end of the seventh cross beam.
10. The lightweight fuselage frame of an eVTOL aircraft according to claim 9, characterized in that: A first luggage compartment door mounting bar for mounting a luggage compartment door is fixedly disposed at the tail portion of the first oblique beam, and a second luggage compartment door mounting bar for mounting a luggage compartment door is fixedly disposed at the tail portion of the second oblique beam.