Folding rotor aircraft

Abstract

The utility model discloses a folding rotor aircraft which comprises an aircraft body and a plurality of aircraft arms, a folding assembly is arranged between the aircraft arms and the aircraft body, and the folding assembly comprises a first mounting seat, a second mounting seat and a driving part; the first mounting seat and the second mounting seat are oppositely arranged on the fuselage at an interval, the first mounting seat is rotationally connected with the arm, the fixed end of the driving part is rotationally connected with the second mounting seat, the driving end of the driving part is rotationally connected with the arm, and the first mounting seat is connected to the end face of the arm to form a first rotating point; the driving end of the driving piece is connected to the side wall of the vehicle arm to form a second rotating point, the fixed end of the driving piece is connected to the second mounting base to form a third rotating point, and the vehicle arm rotates to be close to or away from the horizontal central axis of the vehicle body through the first rotating point, the second rotating point and the third rotating point. The connecting stability of the vehicle arms and the vehicle body is enhanced, the vehicle arms can bear rotor wing structures with large weight, and the vehicle arms can be folded, retracted and released more stably.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft, and in particular relates to a folding rotor aircraft. Background Art

[0002] Electric vertical take-off and landing aircraft (eVTOL) currently have a variety of configurations, mainly including multi-rotor configuration, composite wing configuration and vector propulsion configuration. In order to achieve a compact structure and minimize the space occupied by the aircraft, the multi-rotor configuration aircraft has a rotatable and foldable structure for the aircraft's arms, which can adjust its posture during flight.

[0003] Existing aircraft drive their arms by means of a worm gear combination. The turbine is set on a rotating shaft. The rotating shaft serves as a connecting structure between the arm and the fuselage and needs to withstand a large force to support the expansion and contraction of the arm relative to the fuselage. For an aircraft with a four-axis eight-propeller configuration, the arm and the fuselage are connected only by a rotating shaft, which is prone to damage and affects the rotational stability of the arm. Utility Model Content

[0004] The purpose of the utility model is to solve the above technical problems and provide a folding rotorcraft, so as to enhance the connection stability between the arm and the fuselage, the arm can bear a heavier weight rotor structure, and the arm can be folded and retracted more smoothly. In order to achieve the above purpose, the technical solution of the utility model is as follows:

[0005] A folding rotor aircraft comprises a fuselage, a plurality of arms arranged on the fuselage, and at least one auxiliary rotor assembly arranged on the arms, a folding assembly is arranged between the arms and the fuselage, and the folding assembly comprises a first mounting seat, a second mounting seat, and a driving member; the first mounting seat and the second mounting seat are arranged on the fuselage at a relative interval, the first mounting seat is rotatably connected to the arm, the fixed end of the driving member is rotatably connected to the second mounting seat, the driving end of the driving member is rotatably connected to the arm, the first mounting seat is connected to the end face of the arm to form a first rotating point, the driving end of the driving member is connected to the side wall of the arm to form a second rotating point, and the fixed end of the driving member is connected to the second mounting seat to form a third rotating point. The arm is rotated close to or away from the horizontal center axis of the fuselage through the first rotating point, the second rotating point and the third rotating point.

[0006] Specifically, a plurality of arms arranged in groups are respectively provided on both sides of the fuselage, one group of arms is provided on both sides of the front part of the fuselage, and another group of arms is provided on both sides of the rear part of the fuselage, and each group of arms is symmetrically arranged along the horizontal central axis of the fuselage.

[0007] Specifically, the installation height of the folding assembly located at the front of the fuselage is lower than the installation height of the folding assembly located at the rear of the fuselage.

[0008] Specifically, the arm located at the front of the fuselage rotates toward or away from the rear of the fuselage, and the arm located at the rear of the fuselage rotates toward or away from the front of the fuselage.

[0009] Specifically, the first mounting seat includes a seat body and a mounting platform arranged on the seat body; the first mounting seat is connected to the fuselage, and a mounting groove is arranged at an end of the mounting platform.

[0010] Specifically, a connecting tube which fits snugly therewith is disposed at the end of the machine arm, a first connecting portion is disposed on the end surface of the connecting tube, and a second connecting portion is disposed on the side wall of the connecting tube.

[0011] Specifically, the first connection portion is hinged to the installation groove, the second connection portion is hinged to the driving end of the driving member, and the end of the second mounting seat is hinged to the fixed end of the driving member.

[0012] Specifically, the rotor assembly includes a mounting tube and a branch portion connecting two sides of the mounting tube.

[0013] Specifically, the mounting tube is fitted with the machine arm, and the branches on both sides of the mounting tube are symmetrically arranged along the axis of the mounting tube.

[0014] Specifically, the rotor assembly also includes a rotor drive device and a rotor arranged on the branch portion, and the rotor drive device provides a rotational driving force for the rotor.

[0015] Compared with the prior art, the folding rotor aircraft of the utility model has the following beneficial effects:

[0016] The fuselage is connected to the arm through a folding assembly, and the folding assembly includes a first mounting seat, a second mounting seat, and a driving member. The first mounting seat and the second mounting seat provide a stable support basis for the arm and the driving member. The first mounting seat and the second mounting seat are arranged at an interval. The driving end of the driving member is connected to the arm, and the fixed end of the driving member is connected to the second mounting seat. A stable connection space is formed among the first mounting seat, the second mounting seat, the driving member, and the arm, thereby improving the connection strength of each component. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of a folded state of a folding rotorcraft provided in an embodiment of the present application;

[0018] Figure 2 A schematic top view of a folding rotorcraft provided in an embodiment of the present application;

[0019] Figure 3 A schematic diagram of the unfolded state of the folding rotor aircraft provided in an embodiment of the present application;

[0020] Figure 4 A schematic diagram of the front end of a folding rotorcraft provided in an embodiment of the present application;

[0021] Figure 5 An enlarged schematic diagram of a folding assembly provided in an embodiment of the present application;

[0022] Figure 6 An enlarged schematic diagram of the rotor assembly provided in an embodiment of the present application.

[0023] Reference numerals:

[0024] Body 1, arm 11, connecting tube 12, first connecting part 13, second connecting part 14;

[0025] Rotor assembly 2, mounting tube 21, branch portion 22, rotor drive device 23, rotor 24;

[0026] Folding assembly 3, first mounting seat 31, second mounting seat 32, driving member 33, seat body 34, mounting platform 35, mounting groove 36;

[0027] The first rotation point 4 , the second rotation point 41 , and the third rotation point 42 . DETAILED DESCRIPTION

[0028] In order to make the technical solutions and advantages in the embodiments of the present application more clearly understood, the exemplary embodiments of the present application are further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than an exhaustive list of all the embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0029] Embodiment 1

[0030] The present embodiment provides a folding rotorcraft, comprising a fuselage 1, a plurality of arms 11 disposed on the fuselage 1, and at least one auxiliary rotor assembly 2 disposed at the end of the arm 11. A folding assembly 3 is disposed between the arm 11 and the fuselage 1, and the folding and unfolding actions of the arm 11 relative to the fuselage 1 are realized by the folding assembly 3. The end of the arm 11 needs to bear the weight of the rotor assembly 2. Therefore, during the folding and unfolding action of the arm 11, the folding assembly 3 needs to have a certain connection strength to maintain the stability of the folding action of the arm 11.

[0031] The aircraft in this embodiment is a four-axis eight-propeller configuration, including four arms 11 and eight rotors 24. Specifically, each arm 11 has two rotors 24 at the end. Compared with a traditional rotor assembly 2, the arm 11 needs to bear a greater weight.

[0032] Figure 1 A schematic diagram of a folded state of a folding rotorcraft provided in an embodiment of the present application; Figure 2 A schematic top view of a folding rotorcraft provided in an embodiment of the present application; Figure 3 A schematic diagram of the unfolded state of the folding rotor aircraft provided in an embodiment of the present application; Figure 4 A schematic diagram of the front end of a folding rotorcraft provided in an embodiment of the present application; Figure 5 This is an enlarged schematic diagram of the folding assembly provided in an embodiment of the present application.

[0033] like Figure 1-Figure 5 As shown, this embodiment provides an aircraft, wherein a folding assembly 3 is arranged between the arm 11 and the fuselage 1, and the folding assembly 3 includes a first mounting seat 31, a second mounting seat 32, and a driving member 33; the first mounting seat 31 and the second mounting seat 32 are relatively spaced and arranged on the fuselage 1, the first mounting seat 31 is rotatably connected to the arm 11, the fixed end of the driving member 33 is rotatably connected to the second mounting seat 32, the driving end of the driving member 33 is rotatably connected to the arm 11, the first mounting seat 31 is connected to the end surface of the arm 11 to form a first rotation point 4, the driving end of the driving member 33 is connected to the side wall of the arm 11 to form a second rotation point 41, the fixed end of the driving member 33 is connected to the second mounting seat 32 to form a third rotation point 42, and the arm 11 can rotate close to or away from the horizontal center axis of the fuselage 1 through the first rotation point 4, the second rotation point 41 and the third rotation point 42.

[0034] The fuselage 1 provided in this embodiment is provided with a plurality of arms 11 arranged in groups on both sides. One group of arms 11 is provided on both sides of the front part of the fuselage 1, and another group of arms 11 is provided on both sides of the rear part of the fuselage 1. Each group of arms 11 is symmetrically arranged on both sides along the horizontal central axis of the fuselage 1 to maintain the flight stability of the aircraft.

[0035] The installation height of the folding assembly 3 at the front of the fuselage 1 is lower than the installation height of the folding assembly 3 at the rear of the fuselage 1; when the arm 11 needs to be folded, the arm 11 at the front of the fuselage 1 rotates toward or away from the rear of the fuselage 1, and the arm 11 at the rear of the fuselage 1 rotates toward or away from the front of the fuselage 1. After folding, the arm 11 at the front of the fuselage 1 and the arm 11 at the rear of the fuselage 1 are in a spaced and misaligned space, and no interference problem occurs.

[0036] When the arm 11 is folded, the projection of the arm 11 located at the front of the fuselage 1 and the projection of the arm 11 located at the rear of the fuselage 1 cross and overlap, and the distance between the two folding components 3 located on the same side of the fuselage 1 is greater than the distance between the rotation centers of the two rotor components 2 located on the same side of the fuselage 1. The arms 11 on both sides of the fuselage 1 can be folded close to the fuselage 1 to the maximum extent, reducing the space volume after the arms 11 are folded; avoid the distance between the rotor components 2 at the front and rear of the fuselage 1 being too small, resulting in a large space being occupied after the arms 11 are folded, and avoid the distance between the rotor components 2 at the front and rear of the fuselage 1 being too large, resulting in the rotor components 2 extending far out of the front and rear space of the fuselage 1, which also affects the space after the arms 11 are folded, and affects the distance of the arms 11 close to the horizontal center axis of the fuselage 1.

[0037] In this embodiment, the fuselage 1 is connected to the arm 11 through a folding assembly 3. The folding assembly 3 includes a first mounting seat 31, a second mounting seat 32, and a driving member 33. The first mounting seat 31 and the second mounting seat 32 provide a stable support base for the arm 11 and the driving member 33. The first mounting seat 31 and the second mounting seat 32 are arranged at an interval. The driving end of the driving member 33 is connected to the arm 11, and the fixed end of the driving member 33 is connected to the second mounting seat 32. A stable connection space is formed among the first mounting seat 31, the second mounting seat 32, the driving member 33, and the arm 11, thereby improving the connection strength of each component; the driving member 33 can control the rotation angle of the arm 11 through its own driving stroke. The driving end of the driving member 33 is connected to the side wall of the arm 11, and the first mounting seat 31 is connected to the end face of the arm 11. When the arm 11 is unfolded, the second rotation point 41 where the driving end of the driving member 33 is connected to the arm 11 is located in the space between the first mounting seat 31 and the second mounting seat 32. When the arm 11 is folded, the second rotation point 41 where the driving end of the driving member 33 is connected to the arm 11 is located in the space outside the first mounting seat 31 and the second mounting seat 32. The folding process of the arm 11 is to rotate closer to or away from the central axis of the fuselage 1, thereby reducing the load-bearing force of the driving member 33, making its driving action more stable, the force more uniform, and the folding process of the arm 11 smoother.

[0038] Embodiment 2

[0039] This embodiment optimizes the folding rotorcraft on the basis of the above embodiment, and in particular provides a specific implementation method of a fuselage:

[0040] The fuselage 1 may be an ellipsoid, a fusiform, or a cone. In the present embodiment, the fuselage 1 is roughly a fusiform.

[0041] Figure 2 A schematic top view of a folding rotorcraft provided in an embodiment of the present application; Figure 4 A schematic diagram of the front end of a folding rotor aircraft provided in an embodiment of the present application.

[0042] like Figure 2 , Figure 4 As shown, the front end of the fuselage 1 is a pointed tip, and the rear end of the fuselage 1 is a flat end. The top of the fuselage 1 is an arc-shaped surface, and the bottom of the fuselage 1 extends to both sides of the central axis to form V-shaped surfaces. The external structure of the fuselage 1 effectively reduces the wind resistance during flight. At the same time, after the arms 11 are folded, the rotor assembly 2 is close to the front and rear of the fuselage 1. The shuttle-shaped fuselage 1 structure can provide a certain folding avoidance space for the rotor assembly 2, further reducing the space volume after the arms 11 are folded.

[0043] Embodiment 3

[0044] This embodiment optimizes the folding rotorcraft on the basis of the above embodiment, and in particular provides a specific implementation method of a folding component:

[0045] Figure 1 A schematic diagram of a folded state of a folding rotorcraft provided in an embodiment of the present application; Figure 5 This is an enlarged schematic diagram of the folding assembly provided in an embodiment of the present application.

[0046] like Figure 1 , Figure 5 As shown, the folding assembly 3 includes a first mounting seat 31, a second mounting seat 32, and a driving member 33; the first mounting seat 31 includes a seat body 34 and a mounting platform 35 arranged on the seat body 34; the seat body 34 and the fuselage 1 can be connected by snapping, screwing, welding, or integrally formed. In this embodiment, the seat body 34 and the fuselage 1 are integrally formed.

[0047] The mounting platform 35 is a substantially pyramidal structure, and a mounting groove 36 is provided at the end of the mounting platform 35. The structures of the first mounting seat 31 and the second mounting seat 32 are substantially the same, and will not be described in detail herein.

[0048] The end of the machine arm 11 is provided with a connecting tube 12 that fits therewith, the end surface of the connecting tube 12 is provided with a first connecting portion 13, and the side wall of the connecting tube 12 is provided with a second connecting portion 14. The first connecting portion 13 is hingedly arranged with the mounting groove 36, and the second connecting portion 14 is hingedly arranged with the driving end of the driving member 33. The end of the second mounting seat 32 is hingedly arranged with the fixed end of the driving member 33.

[0049] In this embodiment, the driving member 33 is an electric push rod. The connecting tube 12 cooperates with the first mounting seat 31 through the first connecting part 13 and cooperates with the driving end of the driving member 33 through the second connecting part 14 to realize the rotation operation of the connecting tube 12. The assembly structure is simple and it is easy to achieve a smooth lateral adjustment posture.

[0050] The connecting tube 12 and the machine arm 11 can be connected by welding or screwing. In this embodiment, the connecting tube 12 and the machine arm 11 are fixed by welding.

[0051] Embodiment 4

[0052] This embodiment optimizes the folding rotorcraft on the basis of the above embodiment, and in particular provides a specific implementation method of an arm:

[0053] Figure 1 A schematic diagram of a folded state of a folding rotorcraft provided in an embodiment of the present application; Figure 6 An enlarged schematic diagram of the rotor assembly provided in an embodiment of the present application.

[0054] like Figure 1 , Figure 6 As shown, a connecting tube 12 is provided at one end of the arm 11, and a rotor assembly 2 is provided at the other end of the arm 11; the rotor assembly 2 includes a mounting tube 21 and a branch portion 22 connecting the two sides of the mounting tube 21; the mounting tube 21 is fitted with the arm 11, and the mounting tube 21 and the arm 11 can be connected by welding or screwing. In this embodiment, the mounting tube 21 and the arm 11 are fixed by welding.

[0055] The branches 22 on both sides of the mounting tube 21 are symmetrically arranged along the axis of the mounting tube 21, and the branches 22 are located in the upper space and the lower space of the arm 11. The rotor assembly 2 also includes a rotor drive device 23 and a rotor 24 arranged on the branch portion 22. The rotor drive device 23 provides a rotational driving force for the rotor 24, and the rotor drive device 23 can be a motor.

[0056] A rotor assembly 2 is provided at the end of the arm 11. In this embodiment, each rotor assembly 2 includes two rotors 24, which provide a larger flight driving force for the aircraft, but also increase the load of the arm 11. The arm 11 is connected to the fuselage 1 through a folding assembly 3, which provides a stable supporting force for the arm 11 and reduces the risk of damage to the arm 11.

[0057] In the description of the present application, 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" 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 application 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 application.

[0058] 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 this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0059] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" 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 can communicate with each other; 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 this application can be understood according to specific circumstances.

[0060] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0061] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A folding rotorcraft, comprising a fuselage, a plurality of arms disposed on the fuselage, and at least one rotor assembly disposed on the arms, characterized in that: A folding assembly is arranged between the arm and the fuselage, and the folding assembly includes a first mounting seat, a second mounting seat, and a driving member; the first mounting seat and the second mounting seat are arranged on the fuselage with relative intervals, the first mounting seat is rotatably connected to the arm, the fixed end of the driving member is rotatably connected to the second mounting seat, the driving end of the driving member is rotatably connected to the arm, the first mounting seat is connected to the end surface of the arm to form a first rotation point, the driving end of the driving member is connected to the side wall of the arm to form a second rotation point, and the fixed end of the driving member is connected to the second mounting seat to form a third rotation point. The arm can rotate close to or away from the horizontal central axis of the fuselage through the first rotation point, the second rotation point and the third rotation point.

2. The folding rotor aircraft according to claim 1, characterized in that: A plurality of arms arranged in groups are respectively arranged on both sides of the fuselage, one group of arms is arranged on both sides of the front part of the fuselage, and another group of arms is arranged on both sides of the rear part of the fuselage. Each group of arms is symmetrically arranged along the horizontal central axis of the fuselage.

3. The folding rotor aircraft according to claim 1, characterized in that: The installation position height of the folding assembly located at the front of the fuselage is lower than the installation position height of the folding assembly located at the rear of the fuselage.

4. The folding rotor aircraft according to claim 1, characterized in that: The arm located at the front of the fuselage rotates toward or away from the rear of the fuselage, and the arm located at the rear of the fuselage rotates toward or away from the front of the fuselage.

5. The folding rotor aircraft according to claim 1, characterized in that: The first mounting seat comprises a seat body and a mounting platform arranged on the seat body; the first mounting seat is connected to the fuselage, and a mounting groove is arranged at the end of the mounting platform.

6. The folding rotor aircraft according to claim 5, characterized in that: The end of the machine arm is provided with a connecting tube which fits therewith, the end surface of the connecting tube is provided with a first connecting portion, and the side wall of the connecting tube is provided with a second connecting portion.

7. The folding rotor aircraft according to claim 6, characterized in that: The first connection portion is hinged to the installation groove, the second connection portion is hinged to the driving end of the driving member, and the end of the second mounting seat is hinged to the fixed end of the driving member.

8. The folding rotor aircraft according to claim 1, characterized in that: The rotor assembly includes a mounting tube and a branch portion connecting two sides of the mounting tube.

9. The folding rotor aircraft according to claim 8, characterized in that: The installation tube is fitted with the machine arm, and the branches on both sides of the installation tube are symmetrically arranged along the axis of the installation tube.

10. The folding rotor aircraft according to claim 8, characterized in that: The rotor assembly also includes a rotor drive device and a rotor arranged on the branch portion, and the rotor drive device provides a rotational driving force for the rotor.

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