A fuselage box structure of a Mars multi-rotor aircraft

Abstract

The present invention provides a fuselage box structure for a Mars multi-rotor aircraft. The present invention relates to the field of rotor-type Mars aircraft, specifically a fuselage and internal layout structure of a Mars multi-rotor aircraft, including an outer shell, a heat insulation shell and other internal structures. The outer shell is wrapped outside the heat insulation shell, a solar panel connecting frame is installed at the center of the top, and other internal structures are installed inside the heat insulation shell. The present invention provides a structural solution for the aircraft box, which can protect the electronic control components and batteries of the aircraft in the Mars environment.

Description

Technical Field

[0001] The present invention belongs to the technical field of rotor-type Mars aircraft, and particularly relates to a fuselage box structure of a multi-rotor Mars aircraft. Background Art

[0002] Mars exploration is of great significance for expanding the living space of mankind and exploring the origin of life. At present, the main Mars exploration method is Mars rover exploration.

[0003] In view of the fact that the current Mars rovers do not yet have functions such as large-scale visual detection, three-dimensional map construction of unknown terrains in the landing area, and autonomous path planning, by utilizing the local detection ability of Mars aircraft, areas that are difficult for Mars rovers to reach can be observed at fixed points, thereby improving the efficiency of Mars exploration missions.

[0004] Due to the harsh environment on the Mars surface, the fuselages of existing rotor aircraft cannot be used on the Mars surface. Summary of the Invention

[0005] The purpose of the present invention is to solve the problem that the fuselages of existing rotor aircraft cannot be used on the Mars surface, and a fuselage box structure of a multi-rotor Mars aircraft is proposed.

[0006] The present invention is realized through the following technical solutions. The present invention proposes a fuselage box structure of a multi-rotor Mars aircraft, and the fuselage box structure includes three layers: an outer shell, a heat insulation shell, and internal devices; the outer shell is used to prevent dust on the Mars surface from entering the inside of the box and affecting the operation of the electronic control system and other internal devices, and provides installation interfaces for solar cell glass sheets, rotor arm rods, and aircraft wheel legs; the heat insulation shell is used to prevent heat exchange between the Mars surface environment and the inside of the box and provide a suitable working temperature for the electronic control system and other internal devices; the internal devices provide power and control signals for the aircraft.

[0007] Further, the outer shell includes: main outer shell side plates 1, inclined outer shell side plates 2, solar panel connection brackets 11, outer shell top plates 12, outer shell bottom plates 16, bottom reinforcement plates 17, and 135° angle members 18;

[0008] There are 4 main outer shell side plates 1 and 4 inclined outer shell side plates 2, which are arranged at intervals. Two 135° angle members 18 are installed at the top and bottom between adjacent main outer shell side plates 1 and inclined outer shell side plates 2, and are bolted to each other; a reserved hole is provided at the center of the top of the main outer shell side plate 1 for installing the rotor arm rod; the outer shell top plate 12 and the outer shell bottom plate 16 are respectively installed at the top and bottom and are bolted to the 135° angle members 18; the solar panel connection bracket 11 is installed at the center position on the outside of the outer shell top plate 12 and is bolted to the outer shell top plate 12 for installing the solar cell glass sheet; the bottom reinforcement plate 17 is installed on the outside of the outer shell bottom plate 16 and is bolted to the internal three-sided angle member 9.

[0009] Furthermore, the heat insulation shell includes: heat insulation side plates 3, a battery bottom plate 6, and a heat insulation top plate 13;

[0010] There are 4 heat insulation side plates 3, arranged at intervals of an internal partition 10 from each other; the heat insulation side plates 3 are clamped between the rotor arm fixing angle members 19 and the main side plate 1 of the outer shell; the battery bottom plate 6 is clamped between the triangular corner members 9 and the bottom plate 16 of the outer shell, and is clamped tightly with the triangular corner members 9 through transition fit; the heat insulation top plate 13 is clamped between the triangular corner members 9 and the top plate 16 of the outer shell, and is clamped tightly with the triangular corner members 9 through transition fit.

[0011] Furthermore, the internal device includes: an electronic control board 4, a battery lower partition 5, batteries 7, 90° angle members 8, triangular corner members 9, internal partitions 10, a battery top plate 14, a battery upper partition 15, and rotor arm fixing angle members 19;

[0012] There are 4 internal partitions 10, which are respectively vertically arranged at the inner center of the main side plate 1 of the outer shell; each internal partition 10 is bolt - connected to the main side plate 1 of the outer shell through 2 triangular corner members 9 at the upper and lower parts; two rotor arm fixing angle members 19 are symmetrically installed on both sides of the middle position of one side of the internal partition 10 close to the main side plate 1 of the outer shell, and the internal partition 10 is thread - connected to the rotor arm fixing angle members 19; two triangular corner members 9 are symmetrically installed at the upper and lower ends of the side of the internal partition 10 far from the main side plate 1 of the outer shell, for clamping the heat insulation top plate 13 and the battery bottom plate 6; there are 4 electronic control boards 4, installed between adjacent rotor arm fixing angle members 19, and connected by bolts; the battery lower partition 5 is bolt - connected to the internal partition 10 through 8 90° angle members 8, and the 4 top corners of the battery lower partition 5 are embedded into the internal partition 10 through card slots; the battery upper partition 15 is bolt - connected to the internal partition 10 through 8 90° angle members 8, and the 4 top corners of the battery upper partition 15 are embedded into the internal partition 10 through card slots; the 4 top corners of the battery top plate 14 are embedded into the internal partition 10; there are 15 batteries 7, installed in the corresponding slot holes of the battery upper partition 15, the battery lower partition 5, and the battery bottom plate 6.

[0013] The beneficial effects of the present invention are as follows:

[0014] 1. The structure design of the present invention is scientific and reasonable. Each layer of the shell and other internal structures are connected by various angle members. Each layer of the shell adopts a lightweight design, reducing the body weight of the aircraft and improving the load - carrying capacity of the aircraft. Various angle members are made of carbon fiber materials, which can ensure strength while reducing the body weight of the aircraft, and further improve the load - carrying capacity of the aircraft.

[0015] 2. The present invention takes into account the external structures of aircraft of different sizes, reserves modular interfaces for solar cell glass sheets, rotor arms, and aircraft wheel legs, and can adapt to various mission requirements. Description of the Drawings

[0016] Figure 1 This is the axonometric view of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention.

[0017] Figure 2 This is the front view of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention.

[0018] Figure 3 This is the bottom view of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention.

[0019] Figure 4 This is the sectional view along the A-A axis of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention.

[0020] Figure 5 This is the sectional view along the B-B axis of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention.

[0021] Figure 6 This is the sectional view along the C-C axis of the three-dimensional structure of the fuselage box structure of the Mars multi-rotor aircraft according to the present invention. Detailed implementation manners

[0022] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0023] As Figures 1 to 6 shown, the present invention provides a fuselage box structure of a Mars multi-rotor aircraft. The fuselage box structure includes three layers: an outer shell, a heat insulation shell, and internal devices. The outer shell is used to prevent dust on the Mars surface from entering the inside of the box and affecting the operation of the electronic control system and other internal devices, and provides installation interfaces for solar cell glass slides, rotor arm rods, and aircraft wheel legs. The heat insulation shell is used to prevent heat exchange between the Mars surface environment and the inside of the box and provide a suitable working temperature for the electronic control system and other internal devices. The internal devices provide power and control signals for the aircraft.

[0024] The outer shell includes: main side plates 1 of the outer shell, inclined side plates 2 of the outer shell, solar cell panel connectors 11, top plates 12 of the outer shell, bottom plates 16 of the outer shell, bottom reinforcement plates 17, and 135° angle members 18;

[0025] There are 4 main side plates 1 of the outer shell and 4 inclined side plates 2 of the outer shell, which are arranged at intervals of each other. Two 135° angle members 18 are installed at the top and bottom between adjacent main side plates 1 of the outer shell and inclined side plates 2 of the outer shell, and they are bolted to each other; a reserved hole position is provided at the center of the top of the main side plate 1 of the outer shell for installing the rotor arm rod; the top plate 12 of the outer shell and the bottom plate 16 of the outer shell are respectively installed at the top and bottom, and are bolted to the 135° angle member 18; the solar panel connecting frame 11 is installed at the center position outside the top plate 12 of the outer shell and is bolted to the top plate 12 of the outer shell for installing the solar cell glass sheet; the bottom reinforcement plate 17 is installed outside the bottom plate 16 of the outer shell and is bolted to the internal triangular corner member 9.

[0026] The heat insulation shell includes: heat insulation side plates 3, a battery bottom plate 6 and a heat insulation top plate 13;

[0027] There are 4 heat insulation side plates 3, which are arranged at intervals of internal partition plates 10; the heat insulation side plates 3 are clamped between the rotor arm rod fixing angle members 19 and the main side plates 1 of the outer shell; the battery bottom plate 6 is clamped between the triangular corner member 9 and the bottom plate 16 of the outer shell and is clamped tightly with the triangular corner member 9 through transitional fit; the heat insulation top plate 13 is clamped between the triangular corner member 9 and the top plate 16 of the outer shell and is clamped tightly with the triangular corner member 9 through transitional fit.

[0028] The internal device includes: an electronic control board 4, a battery lower partition plate 5, a battery 7, a 90° angle member 8, a triangular corner member 9, an internal partition plate 10, a battery top plate 14, a battery upper partition plate 15 and a rotor arm rod fixing angle member 19;

[0029] There are 4 internal partition plates 10, which are respectively vertically arranged at the center of the inner side of the main side plate 1 of the outer shell; each internal partition plate 10 is bolted to the main side plate 1 of the outer shell through 2 triangular corner members 9 at the upper and lower parts; two rotor arm rod fixing angle members 19 are symmetrically installed on both sides at the middle position of one side of the internal partition plate 10 close to the main side plate 1 of the outer shell, and the internal partition plate 10 is threadedly connected to the rotor arm rod fixing angle member 19; two triangular corner members 9 are symmetrically installed at the upper and lower ends of the side of the internal partition plate 10 far from the main side plate 1 of the outer shell for clamping the heat insulation top plate 13 and the battery bottom plate 6; there are 4 electronic control boards 4, which are installed between adjacent two rotor arm rod fixing angle members 19 and are bolted; the battery lower partition plate 5 is bolted to the internal partition plate 10 through 8 90° angle members 8, and the 4 top corners of the battery lower partition plate 5 are embedded in the internal partition plate 10 through card slots; the battery upper partition plate 15 is bolted to the internal partition plate 10 through 8 90° angle members 8, and the 4 top corners of the battery upper partition plate 15 are embedded in the internal partition plate 10 through card slots; the 4 top corners of the battery top plate 14 are embedded in the internal partition plate 10; there are 15 batteries 7, which are installed in the corresponding slot holes of the battery upper partition plate 15, the battery lower partition plate 5 and the battery bottom plate 6.

[0030] Embodiment

[0031] As Figures 1 to 6As shown in the figure, the present invention is implemented in the following specific manner:

[0032] The present invention provides a fuselage and internal layout structure for a Mars multi-rotor aircraft, including: outer shell main side plates 1, outer shell inclined side plates 2, heat insulation side plates 3, electronic control boards 4, battery lower partitions 5, battery bottom plates 6, batteries 7, 90° angle parts 8, three-sided angle parts 9, internal partitions 10, solar panel connection brackets 11, outer shell top plates 12, heat insulation top plates 13, battery top plates 14, battery upper partitions 15, outer shell bottom plates 16, bottom reinforcement plates 17, 135° angle parts 18, and rotor arm fixing angle parts 19.

[0033] There are 4 internal partitions 10. At the four corners of each side of each internal partition 10, a total of 6 three-sided angle parts 9 are connected by bolts, and the three-sided angle parts 9 are not installed at the top corners above the card slots. At the card slot positions on each side of each internal partition 10, a total of 4 90° angle parts 8 are connected by bolts. At the small hole positions on the outer sides of each internal partition 10, 2 rotor arm fixing angle parts 19 are installed by bolt connection.

[0034] The battery upper partition 15 and the battery lower partition 5 are respectively snapped into the card slots of the 4 internal partitions 10, and are locked with the 90° angle parts 8 near the card slots through bolt connection to form a partition combination.

[0035] A total of 16 three-sided angle parts 9 at the lower part of the partition combination are embedded into the corresponding slot holes of the battery bottom plate 6.

[0036] 15 batteries 7 are inserted into the corresponding hole positions of the partition combination, and the bottoms are embedded into the corresponding slot holes of the battery bottom plate 6.

[0037] The 4 electronic control boards 4 are respectively installed on the adjacent rotor arm fixing angle parts 19 in the partition combination and are connected by bolts.

[0038] The 4 heat insulation side plates 3 are respectively snapped between the angle parts on both sides of the electronic control board 4, and then the hole positions of the 4 outer shell main side plates 1 are aligned with the hole positions of the three-sided angle parts 9 in the partition combination and are connected by bolts. One set of rotor arms can be installed on the outside of each outer shell main side plate 1.

[0039] The upper and lower ends of two adjacent outer shell main side plates 1 are connected by bolts through 135° angle parts 18.

[0040] The hole positions of the 4 outer shell inclined side plates 2 are aligned with the hole positions of 4 groups of upper and lower 135° angle parts 18 and are connected by bolts.

[0041] The battery top plate 14 is covered above the battery 7, and then 8 three-sided angle parts 9 are installed on the spare hole positions of the internal partition 10 and are connected by bolts.

[0042] The hole of the heat insulation top plate 13 is aligned with the 16 three-sided angle parts 9 above the partition combination and is embedded.

[0043] The upper part of the fuselage box structure is covered with the outer shell top plate 12, and the lower part is covered with the outer shell bottom plate 16, which are respectively connected to the internal three-sided corner parts 9 by bolts.

[0044] The solar panel connecting frame 11 is installed at the center of the outside of the outer shell top plate 12 by bolt connection. One solar panel glass sheet can be installed on the solar panel connecting frame 11.

[0045] The bottom reinforcement plate 17 is connected to the outside of the outer shell bottom plate 16 by bolt connection. Four groups of aircraft wheel legs can be installed on the bottom reinforcement plate 17.

[0046] The above has introduced in detail a fuselage box structure of a Mars multi-rotor aircraft proposed by the present invention. Specific examples are used in this article to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A fuselage box structure of a Mars multi-rotor aircraft, characterized in that: The fuselage box structure includes three layers: an outer shell, a heat insulation shell, and internal devices; the outer shell is used to prevent dust on the Martian surface from entering the interior of the box, affecting the operation of the electronic control system and other internal devices, and provides mounting interfaces for solar cell glass sheets, rotor arm rods, and aircraft wheel legs; the heat insulation shell is used to prevent heat exchange between the Martian surface environment and the interior of the box, providing a suitable working temperature for the electronic control system and other internal devices; The internal devices provide power and control signals for the aircraft; The outer shell includes: outer shell main side plates (1), outer shell inclined side plates (2), solar panel connecting frames (11), outer shell top plates (12), outer shell bottom plates (16), bottom reinforcement plates (17), and 135° angle members (18); There are 4 outer shell main side plates (1) and 4 outer shell inclined side plates (2), arranged at intervals from each other. Two 135° angle members (18) are installed at the top and bottom between adjacent outer shell main side plates (1) and outer shell inclined side plates (2), and are bolted to each other; a reserved hole position is provided at the center of the top of the outer shell main side plate (1) for installing the rotor arm rod; the outer shell top plate (12) and the outer shell bottom plate (16) are respectively installed at the top and bottom, and are bolted to the 135° angle member (18); the solar panel connecting frame (11) is installed at the center position outside the outer shell top plate (12) and is bolted to the outer shell top plate (12) for installing the solar cell glass sheet; the bottom reinforcement plate (17) is installed outside the outer shell bottom plate (16) and is bolted to the internal trihedral angle member (9); The heat insulation shell includes: heat insulation side plates (3), battery bottom plates (6), and heat insulation top plates (13); There are 4 heat insulation side plates (3), arranged at intervals with internal partition plates (10) between them; the heat insulation side plates (3) are clamped between the rotor arm rod fixing angle members (19) and the outer shell main side plates (1); the battery bottom plates (6) are clamped between the trihedral angle members (9) and the outer shell bottom plates (16), and are clamped tightly with the trihedral angle members (9) through transitional fit; the heat insulation top plates (13) are clamped between the trihedral angle members (9) and the outer shell top plates (16), and are clamped tightly with the trihedral angle members (9) through transitional fit.

2. The fuselage box structure according to claim 1, wherein The internal devices include: electronic control boards (4), battery lower partition plates (5), batteries (7), 90° angle members (8), trihedral angle members (9), internal partition plates (10), battery top plates (14), battery upper partition plates (15), and rotor arm rod fixing angle members (19); There are 4 internal partitions (10), which are respectively vertically arranged at the center inside the main side plate (1) of the outer shell; each internal partition (10) is bolted to the main side plate (1) of the outer shell through 2 three-sided corner pieces (9) at the upper and lower positions; on both sides of the middle position of one side of the internal partition (10) close to the main side plate (1) of the outer shell, 2 rotor arm fixing corner pieces (19) are symmetrically installed, and the internal partition (10) is threadedly connected to the rotor arm fixing corner pieces (19); at the upper and lower ends of one side of the internal partition (10) far from the main side plate (1) of the outer shell, 2 three-sided corner pieces (9) are symmetrically installed on each side, which are used to clamp the heat insulation top plate (13) and the battery bottom plate (6); there are 4 electronic control boards (4), which are installed between adjacent rotor arm fixing corner pieces (19) and are bolted; the battery lower partition (5) is bolted to the internal partition (10) through 8 90° angle pieces (8), and the 4 top corners of the battery lower partition (5) are embedded in the internal partition (10) through card slots; the battery upper partition (15) is bolted to the internal partition (10) through 8 90° angle pieces (8), and the 4 top corners of the battery upper partition (15) are embedded in the internal partition (10) through card slots; the 4 top corners of the battery top plate (14) are embedded in the internal partition (10); there are 15 batteries (7), which are installed in the corresponding slot holes of the battery upper partition (15), the battery lower partition (5) and the battery bottom plate (6).

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