Fuselage structure and aircraft with same

Abstract

The utility model discloses a fuselage structure and an aircraft with the fuselage structure, the fuselage structure comprises a fuselage, the fuselage comprises a first part and a second part, the first part is connected to the upper side of the second part, the first part defines a battery compartment, and the second part defines a passenger compartment; the vehicle arm connector is connected with the first part and the second part; and one end of the vehicle arm is connected with the vehicle arm connector, and the other end of the vehicle arm is used for installing a rotor wing assembly. According to the fuselage structure disclosed by the utility model, the first part, the second part and the arms are respectively connected through the arm joints, on one hand, the driving force of the rotor wing assembly can be directly transmitted to the battery compartment and the passenger compartment through the arms, and a force transmission path on the fuselage structure is relatively simple, so that an aircraft is easier to control; on the other hand, the connection reliability of the first part and the second part can be improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a fuselage structure and an aircraft having the same. Background Art

[0002] With the development of battery technology, some aircraft have begun to use batteries as power sources. Batteries are often heavy. In related technologies, the force transmission path between the arms, batteries, and the passenger compartment of the fuselage is relatively complex, making it difficult to control the aircraft during operation. Utility Model Content

[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a fuselage structure, the force transmission path on which is simpler.

[0004] The utility model also provides an aircraft with the fuselage structure.

[0005] The fuselage structure according to the first aspect of the utility model includes: a fuselage, wherein the fuselage includes a first part and a second part, the first part is connected to the upper side of the second part, the first part defines a battery compartment, and the second part defines a passenger compartment; an arm joint, wherein the arm joint is connected to both the first part and the second part; and an arm, wherein one end of the arm is connected to the arm joint, and the other end of the arm is used for mounting a rotor assembly.

[0006] According to the fuselage structure of the first aspect of the utility model, the first part, the second part and the arm are respectively connected through the arm joint. On the one hand, the driving force of the rotor assembly can be directly transmitted to the battery compartment and the passenger compartment through the arm. The force transmission path on the fuselage structure is relatively simple, making the aircraft easier to control. On the other hand, the reliability of the connection between the first part and the second part can be improved.

[0007] According to some embodiments of the utility model, the arm joint includes: a base plate, a first side plate and a second side plate, the base plate is a horizontal plate, the first side plate extends in the up and down directions, one end of the base plate is connected to the lower end of the first side plate, and the second side plate is connected between the other end of the base plate and the upper end of the first side plate, wherein the base plate is connected to the second part, the first side plate is connected to the first part, and the second side plate is connected to the arm.

[0008] According to some embodiments of the utility model, a plurality of mounting parts are provided on the second side panel, and the plurality of mounting parts are arranged at intervals in the horizontal direction and the vertical direction. A plurality of connecting parts are provided at one end of the arm, and the plurality of connecting parts correspond to and are connected to the mounting parts one by one.

[0009] According to some embodiments of the utility model, the mounting portion includes an ear piece, the ear piece includes a first ear piece and a second ear piece arranged at an interval up and down, a first mounting hole is formed on the first ear piece, and a second mounting hole is formed on the second ear piece; the connecting portion includes a connecting plate, a connecting hole is formed on the connecting plate, the connecting plate extends between the first ear piece and the second ear piece, and the arm is connected to the arm joint by fasteners that pass through the first mounting hole, the connecting hole and the second mounting hole in sequence.

[0010] According to some embodiments of the utility model, a first mounting plate is provided on the second side panel, and the first ear pieces of the plurality of ear pieces arranged side by side in the horizontal direction are all arranged on the first mounting plate; and / or, a second mounting plate is provided on the second side panel, and the second ear pieces of the plurality of ear pieces arranged side by side in the horizontal direction are all arranged on the second mounting plate.

[0011] According to some embodiments of the present utility model, a wire passing hole is formed on the arm joint, a wire passing channel extending along the length direction of the arm is formed in the arm, and the wire passing hole is communicated with the wire passing channel.

[0012] According to some embodiments of the present invention, a plurality of material reduction grooves are formed on the arm joint.

[0013] According to some embodiments of the present invention, the fuselage structure further includes: a covering member, the covering member covers the outer side of the fuselage, and a portion of the arm joint is arranged between the covering member and the fuselage.

[0014] According to some embodiments of the utility model, a suspension member is further provided on the arm joint, and the suspension member is used to suspend the fuselage structure.

[0015] An aircraft according to a second aspect of the utility model comprises: the fuselage structure according to the first aspect of the utility model.

[0016] According to the aircraft of the second aspect of the present invention, by providing the fuselage structure according to the first aspect of the present invention, the maneuverability of the aircraft can be improved and the design difficulty of the aircraft can be reduced.

[0017] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a fuselage structure according to an embodiment of the utility model;

[0019] Figure 2 yes Figure 1A cross-sectional view in the AA direction shown in FIG.

[0020] Figure 3 yes Figure 1 A schematic diagram of the first part and the upper part of the second part shown in ;

[0021] Figure 4 yes Figure 1 A schematic diagram of the arm, arm joints and suspension shown in FIG.

[0022] Figure 5 yes Figure 4 Schematic diagram of the arm joint shown in .

[0023] Reference numerals:

[0024] 100. Fuselage structure;

[0025] 10. Fuselage; 11. First part; 111. Battery compartment; 12. Second part; 121. Passenger compartment;

[0026] 20. Arm joint; 21. Bottom plate; 211. Second rivet hole; 22. First side plate; 221. First rivet hole; 23. Second side plate; 231. Ear piece; 2311. First ear piece; 23111. First mounting hole; 2312. Second ear piece; 232. First mounting plate; 2321. Suspension hole; 233. Second mounting plate; 24. Wire hole; 25. Material reduction groove; 26. Reinforcement rib;

[0027] 30. Machine arm; 31. Connecting plate; 32. Fastener;

[0028] 40. Covering parts;

[0029] 50. Suspension parts. DETAILED DESCRIPTION

[0030] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0031] Reference below Figure 1-Figure 5 A fuselage structure 100 according to an embodiment of the first aspect of the present invention is described.

[0032] like Figure 1-Figure 3 As shown, the fuselage structure 100 according to the embodiment of the first aspect of the utility model includes: a fuselage 10, an arm joint 20 and an arm 30.

[0033] Specifically, the fuselage 10 includes a first part 11 and a second part 12, the first part 11 is connected to the upper side of the second part 12, the first part 11 defines a battery compartment 111, the second part 12 defines a passenger compartment 121, the arm joint 20 is connected to both the first part 11 and the second part 12, one end of the arm 30 is connected to the arm joint 20, and the other end of the arm 30 is used to install the rotor assembly.

[0034] The battery compartment 111 is used to arrange the battery pack of the aircraft, the passengers or pilots sit in the passenger compartment 121, and the rotor assembly includes a drive motor and a rotor.

[0035] During the operation of the aircraft, the driving motor drives the rotor to rotate to provide driving force, and the driving force generated by the rotor is transmitted to the first part 11 and the second part 12 through the arm 30 and the arm joint 20, thereby driving the fuselage 10 to move.

[0036] It is understandable that during the operation of the aircraft, the weight of the battery compartment 111 and the battery pack in the battery compartment 111, and the weight of the passenger compartment 121 and the passengers in the passenger compartment 121 account for a large proportion of the aircraft. When adjusting the flight state of the aircraft, the force acting on the first part 11 and the second part 12 can make the aircraft state easier to adjust.

[0037] In this embodiment, the arm 30 is respectively connected to the first part 11 and the second part 12 through the arm joint 20, and the driving force can be directly transmitted from the arm 30 to the first part 11 and the second part 12. In this way, the driving force acting on the first part 11 and the second part 12 can make the driving state of the aircraft easier to change. At the same time, the driving force transmission between the arm 30 and the first part 11 and the second part 12 is relatively direct, and the force transmission path from the arm 30 to the fuselage 10 is relatively simple. When the aircraft adjusts its flight state, the change in the state of the fuselage 10 is more correlated with the change in the driving force of the rotor assembly, thereby making the aircraft easier to control.

[0038] It should be noted that the aircraft can be manually controlled by the pilot, or the aircraft's auxiliary driving system can be controlled together with the pilot.

[0039] In addition, the arm joint 20 can be connected to the first part 11 and the second part 12, thereby improving the reliability of the connection between the first part 11 and the second part 12. The number of parts used when the arm 30 is connected to the fuselage 10 is relatively small, which can reduce the difficulty of assembly, improve assembly efficiency, and reduce production costs.

[0040] According to the fuselage structure 100 of the first aspect of the utility model, the first part 11, the second part 12 and the arm 30 are respectively connected through the arm joint 20. On the one hand, the force transmission path on the fuselage structure 100 can be simplified to make the aircraft easier to control. On the other hand, the reliability of the connection between the first part 11 and the second part 12 can be improved.

[0041] In some embodiments of the present invention, Figure 2 , Figure 3 and Figure 5 As shown, the arm joint 20 includes: a base plate 21, a first side plate 22 and a second side plate 23, the base plate 21 is a horizontal plate, the first side plate 22 extends in the up and down direction, one end of the base plate 21 is connected to the lower end of the first side plate 22, and the second side plate 23 is connected between the other end of the base plate 21 and the upper end of the first side plate 22, wherein the base plate 21 is connected to the second part 12, the first side plate 22 is connected to the first part 11, and the second side plate 23 is connected to the arm 30.

[0042] That is, on the horizontal projection plane, the outer contour of the first part 11 is located inside the outer contour of the second part 12, and the arm joint 20 is connected between the upper surface of the second part 12 and the outer wall of the first part 11 in the horizontal direction. The bottom plate 21, the first side plate 22, and the second side plate 23 of the arm joint 20 can form a triangular prism with two ends open. During the assembly process, the first side plate 22 and the bottom plate 21 can provide positioning and limiting for the arm joint 20, so that the arm joint 20 can be quickly placed in place, thereby improving the assembly efficiency. After the assembly is completed, the triangular prism structure has higher strength and a more stable structure, which can improve the reliability of the connection between the arm 30 and the first part 11 and the second part 12 and the stability of the fuselage structure 100.

[0043] In some embodiments of the present invention, Figure 5 As shown, the first side plate 22 is provided with a first rivet hole 221, and the first side plate 22 is riveted to the first part 11 through the first rivet hole 221. The bottom plate 21 is provided with a second rivet hole 211, and the bottom plate 21 is riveted to the second part 12 through the second rivet hole 211. The riveted connection has high strength and high fatigue resistance, thereby improving the reliability of the connection between the bottom plate 21 and the second part 12, and the first side plate 22 and the first part 11.

[0044] In some embodiments of the utility model, a plurality of mounting parts are provided on the second side panel 23. For example, the mounting parts may be two, three, four or six, and the plurality of mounting parts are arranged at intervals in the horizontal direction and the up and down directions. A plurality of connecting parts are provided at one end of the arm 30, and the plurality of connecting parts correspond to and are connected to the mounting parts one by one.

[0045] In this way, during the connection between the machine arm 30 and the second side plate 23 , each set of connecting parts and mounting parts can cooperate to provide positioning, thereby improving the assembly accuracy of the machine arm 30 and the second side plate 23 .

[0046] After the arm 30 is connected to the second side panel 23, multiple groups of connecting parts and mounting parts can share the force between the arm 30 and the second side panel 23 at different positions, thereby improving the stability of the connection between the arm 30 and the second side panel 23, and when the connection of one group of connecting parts and mounting parts fails, the remaining connecting parts and mounting parts can still maintain the connection between the arm 30 and the second side panel 23, thereby improving the reliability of the connection between the arm 30 and the second side panel 23.

[0047] In some embodiments of the present invention, Figure 2 , Figure 4 and Figure 5 As shown, the mounting portion includes an ear piece 231, and the ear piece 231 includes a first ear piece 2311 and a second ear piece 2312 arranged at an interval up and down. The first ear piece 2311 is formed with a first mounting hole 23111, and the second ear piece 2312 is formed with a second mounting hole. The connecting portion includes a connecting plate 31, and the connecting plate 31 is formed with a connecting hole. The connecting plate 31 extends between the first ear piece 2311 and the second ear piece 2312. The arm 30 is connected to the arm joint 20 by a fastener 32 that passes through the first mounting hole 23111, the connecting hole, and the second mounting hole in sequence.

[0048] In this way, the force distribution between the connecting part and the mounting part can be made more uniform, thereby further improving the reliability and stability of the connection between the arm 30 and the second side panel 23. During the product design process, the size of the first ear piece 2311 and the second ear piece 2312, the spacing between the first ear piece 2311 and the second ear piece 2312, the size of the connecting plate 31, the size of the first mounting hole 23111 and the second mounting hole, or the size of the connecting hole can be adjusted to meet more product design needs.

[0049] Preferably, the fastener 32 is a fastening bolt, which has high connection strength and is easy to operate, and can ensure that the connection strength between the connecting plate 31 and the ear piece 231 meets the use requirements and improves production efficiency.

[0050] In some embodiments of the present invention, Figure 2 and Figure 5 As shown, a first mounting plate 232 is provided on the second side panel 23, and the first ear pieces 2311 of a plurality of ear pieces 231 arranged side by side in the horizontal direction are all provided on the first mounting plate 232, so that the first mounting plate 232 can provide support between the first ear pieces 2311, thereby improving the connection strength between the first ear pieces 2311 and the second side panel 23.

[0051] In some embodiments of the present invention, Figure 2 and Figure 5 As shown, a second mounting plate 233 is provided on the second side panel 23, and the second ear pieces 2312 of a plurality of ear pieces 231 arranged side by side in the horizontal direction are all provided on the second mounting plate 233, so that the second mounting plate 233 can provide support between the second ear pieces 2312, thereby improving the connection strength between the second ear pieces 2312 and the second side panel 23.

[0052] In some embodiments of the present invention, Figure 2 , Figure 4 and Figure 5 As shown, a reinforcing rib 26 is further provided on the arm joint 20, the first ear piece 2311 is provided above the second ear piece 2312, and the reinforcing rib 26 is connected between the second side plate 23 and the first ear piece 2311, thereby further improving the connection strength between the first ear piece 2311 and the second side plate 23.

[0053] In some embodiments of the present invention, Figure 5 As shown, a wire hole 24 is formed on the arm joint 20, and a wire passage extending along the length direction of the arm 30 is formed in the arm 30, and the wire hole 24 is connected with the wire passage. It can be understood that the rotor assembly needs to be connected to the components in the fuselage 10 through the wire harness, and the wire hole 24 and the wire passage can provide an escape space for the wire harness during the assembly process, so that the wire harness can be connected between the rotor assembly and the components in the fuselage 10, and the arm 30 can provide protection for the wire harness.

[0054] In some embodiments of the present invention, Figure 5 As shown, a plurality of material reduction grooves 25 are formed on the arm joint 20. For example, the number of the material reduction grooves 25 may be two, three, ten or twelve. By providing the material reduction grooves 25, the weight of the arm joint 20 may be reduced. On the premise that the strength of the arm joint 20 meets the use requirements, the production cost may be reduced, and it is conducive to realizing the lightweight design of the aircraft.

[0055] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the fuselage structure 100 further includes: a covering member 40, the covering member 40 covers the outside of the fuselage 10, and a portion of the arm joint 20 is disposed between the covering member 40 and the fuselage 10. By providing the covering member 40, the covering member 40 can provide protection for the fuselage 10 and the arm joint 20, reduce the probability of damage to the fuselage 10 and the arm joint 20 caused by the external environment, and reduce the corrosion of the fuselage 10 and the arm joint 20 by the external environment.

[0056] Preferably, the bottom plate 21, the first side plate 22 and the second side plate 23 are arranged between the covering member 40 and the fuselage 10, and the covering member 40 and the second side plate 23 of the arm joint 20 are bonded and connected by structural adhesive.

[0057] In some embodiments of the present invention, Figure 1 , Figure 4 and Figure 5 As shown, a suspension member 50 is also provided on the arm joint 20, and the suspension member 50 is used to suspend the fuselage structure 100. By providing the suspension member 50, when the fuselage structure 100 needs to be suspended, the suspension member 50 can realize the connection between the fuselage 10 and the external suspension device, thereby facilitating the suspension of the fuselage structure 100.

[0058] Among them, preferably, a suspension hole 2321 is formed on the first mounting plate 232, and the suspension component 50 is connected to the first mounting plate 232 by fastening bolts and cooperating with the suspension hole 2321. Thus, the connection strength between the suspension component 50 and the fuselage structure 100 can be made higher, and the suspension hole 2321 does not damage the fuselage 10.

[0059] The aircraft according to the embodiment of the second aspect of the utility model comprises: the fuselage structure 100 according to the embodiment of the first aspect of the utility model.

[0060] According to the aircraft of the second aspect of the present invention, by setting the fuselage structure 100 according to the first aspect of the present invention, the force transmission path on the fuselage structure 100 is relatively simple, which can improve the controllability of the aircraft and reduce the design difficulty of the aircraft.

[0061] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0062] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0063] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0064] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0065] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A fuselage structure, characterized in that: include: A fuselage, the fuselage comprising a first portion and a second portion, the first portion being connected to an upper side of the second portion, the first portion defining a battery compartment, and the second portion defining a passenger compartment; an arm joint, the arm joint being connected to both the first part and the second part; A machine arm, one end of which is connected to the machine arm joint, and the other end of which is used for mounting the rotor assembly.

2. The fuselage structure according to claim 1, characterized in that: The arm joint comprises: a bottom plate, a first side plate and a second side plate, wherein the bottom plate is a horizontal plate, the first side plate extends in the up-down direction, one end of the bottom plate is connected to the lower end of the first side plate, and the second side plate is connected between the other end of the bottom plate and the upper end of the first side plate. Wherein, the bottom plate is connected to the second part, the first side plate is connected to the first part, and the second side plate is connected to the machine arm.

3. The fuselage structure according to claim 2, characterized in that: The second side plate is provided with a plurality of mounting portions, and the plurality of mounting portions are arranged at intervals in the horizontal direction and in the vertical direction. One end of the machine arm is provided with a plurality of connecting parts, and the plurality of connecting parts correspond to and are connected with the mounting part one by one.

4. The fuselage structure according to claim 3, characterized in that: The mounting portion includes an ear piece, and the ear piece includes a first ear piece and a second ear piece which are arranged in an upper and lower interval, a first mounting hole is formed on the first ear piece, and a second mounting hole is formed on the second ear piece; The connecting portion includes a connecting plate, a connecting hole is formed on the connecting plate, the connecting plate extends between the first ear piece and the second ear piece, and the arm is connected to the arm joint by a fastener that passes through the first mounting hole, the connecting hole and the second mounting hole in sequence.

5. The fuselage structure according to claim 4, characterized in that: A first mounting plate is provided on the second side plate, and the first ear pieces of the plurality of ear pieces arranged side by side in the horizontal direction are all provided on the first mounting plate; and / or, A second mounting plate is disposed on the second side plate, and the second ear pieces of the plurality of ear pieces arranged side by side in a horizontal direction are all disposed on the second mounting plate.

6. The fuselage structure according to any one of claims 1 to 5, characterized in that: A wire passing hole is formed on the arm joint, a wire passing channel extending along the length direction of the arm is formed in the arm, and the wire passing hole is communicated with the wire passing channel.

7. The fuselage structure according to any one of claims 1 to 5, characterized in that: A plurality of material reduction grooves are formed on the arm joint.

8. The fuselage structure according to any one of claims 1 to 5, characterized in that: The fuselage structure further includes a covering member, which covers the outer side of the fuselage, and a portion of the arm joint is arranged between the covering member and the fuselage.

9. The fuselage structure according to any one of claims 1 to 5, characterized in that: A suspension member is also provided on the arm joint, and the suspension member is used to suspend the fuselage structure.

10. An aircraft, characterized in that: include: The fuselage structure according to any one of claims 1 to 9.

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