Aircraft

Abstract

The invention provides an aircraft which comprises a fuselage, a buffer, a connecting mechanism and an undercarriage, and a cylinder body of the buffer is assembled on the fuselage; the connecting mechanism is hinged to the machine body and a movable rod of the buffer; the landing gear is foldably connected to the connecting mechanism. Thus, when the undercarriage vibrates, the undercarriage can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, and then the movable rod is driven to slide in the cylinder body, so that the effects of energy absorption and vibration reduction are achieved through the buffer. Besides, compared with the technical scheme that the buffer is synchronously folded along with the undercarriage in the related technology, the aircraft provided by the embodiment of the invention does not need to consider the influence of the weight of the buffer on the folding of the undercarriage, the weight of the folding part is reduced, the folding space does not need to be reserved for the buffer after the undercarriage is folded, and the folding efficiency is improved. And the size of the aircraft can be reduced.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft. Background Art

[0002] The landing gear structure of an aircraft is usually configured as a folding structure, and a buffer structure is usually provided in the landing gear structure to reduce vibration and absorb energy.

[0003] The traditional landing gear structure takes up a large space when folded, which is difficult to meet the needs of users. Summary of the invention

[0004] The purpose of this application is to propose an aircraft to improve at least one of the above technical problems. This application achieves the above purpose through the following technical solutions.

[0005] An embodiment of the present application provides an aircraft, including a fuselage, a buffer, a connecting mechanism and a landing gear, wherein a cylinder of the buffer is assembled on the fuselage; the connecting mechanism is hinged to the fuselage and a movable rod of the buffer; and the landing gear is foldably connected to the connecting mechanism.

[0006] In some embodiments, the cylinder is embedded in the fuselage.

[0007] In some embodiments, the fuselage includes a load-bearing beam, which is at least partially located at the bottom of the fuselage. The load-bearing beam is provided with a mounting groove, and the cylinder body is embedded in the mounting groove.

[0008] In some embodiments, the sliding direction of the movable rod in the cylinder is parallel to the direction from the bottom of the fuselage to the top of the fuselage.

[0009] In some embodiments, the connecting mechanism includes a rocker arm and a connecting arm, the rocker arm is hinged to the fuselage and the connecting arm, one end of the connecting arm away from the rocker arm is hinged to the movable rod, and the landing gear is foldably connected to the rocker arm.

[0010] In some embodiments, the aircraft further includes a first telescopic driving member, which is connected to the connecting mechanism or the fuselage, and is used to drive the landing gear to fold.

[0011] In some embodiments, the rocker arm has a first installation space and a second installation space separated from each other, the connecting arm is at least partially located in the first installation space, and the first telescopic drive member is connected to the connecting mechanism and is located in the second installation space.

[0012] In some embodiments, the rocker arm includes a connecting portion, a first arm body, a second arm body and a third arm body, the first arm body, the second arm body and the third arm body are all connected to the connecting portion and are arranged side by side in sequence, the first arm body, the second arm body and the third arm body are coaxially hinged to the fuselage at one end away from the connecting portion, and the landing gear is hinged to the connecting portion; the first installation space is located between the first arm body and the second arm body, the connecting arm is hinged to the first arm body and the second arm body, and the second installation space is located between the second arm body and the third arm body.

[0013] In some embodiments, the landing gear has a first end and a second end relative to each other, and the first end is rotatably connected to the connecting mechanism; the landing gear has a storage position and a supporting position, when the landing gear is in the storage position, the second end is close to the fuselage, and when the landing gear is in the supporting position, the second end is away from the fuselage, and the landing gear supports the fuselage.

[0014] In some embodiments, the aircraft also includes a locking piece, the landing gear has a first locking hole, and the connecting mechanism has a second locking hole; when the landing gear is in the supporting position, the locking piece is inserted into the first locking hole and the second locking hole; when the landing gear rotates from the supporting position to the storage position, the locking piece disengages from the first locking hole and the second locking hole.

[0015] In some embodiments, the aircraft also includes a second telescopic drive member, which is connected to the connecting mechanism, and the second telescopic drive member is used to drive the locking member to extend and retract so that the locking member is inserted into the first locking hole and the second locking hole, or is disengaged from the first locking hole and the second locking hole.

[0016] In some embodiments, the landing gear includes a support arm and a grounding member, wherein the support arm is foldably connected to the connecting mechanism, the grounding member is connected to an end of the support arm away from the connecting mechanism, and the grounding member is one of a slide plate and a roller.

[0017] In some embodiments, the grounding member is detachably connected to the support arm.

[0018] In the aircraft provided in the embodiment of the present application, the cylinder of the buffer is assembled on the fuselage, the connecting mechanism is hinged to the fuselage and the movable rod of the buffer, and the landing gear is foldably connected to the connecting mechanism. In this way, when the aircraft lands, the landing gear vibrates after contacting the ground, and the landing gear can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, thereby driving the movable rod to slide in the cylinder, so as to achieve the effect of energy absorption and vibration reduction through the buffer. In addition, compared with the technical solution in the related art that the buffer folds synchronously with the landing gear, in the aircraft provided in the embodiment of the present application, the cylinder of the buffer is assembled on the fuselage, so there is no need to consider the influence of the weight of the buffer on the folding of the landing gear, which reduces the weight of the folded part, and there is no need to reserve folding space for the buffer after the landing gear is folded, which helps to reduce the volume of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the implementation modes of the present application, the drawings required for use in the description of the implementation modes will be briefly introduced below. Obviously, the drawings described below are only some implementation modes of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 A schematic diagram of the structure of an aircraft provided in an embodiment of the present application is shown.

[0021] Figure 2 Shows Figure 1 Schematic diagram of the partially exploded structure of the aircraft.

[0022] Figure 3 Shows Figure 2 Schematic diagram of the partially exploded structure of the aircraft.

[0023] Figure 4 Shows Figure 1 Schematic diagram of the structure of the aircraft part.

[0024] Figure 5 Shows Figure 1 Schematic diagram of part of the structure of the aircraft when the landing gear is in the stowed position.

[0025] Figure 6 Shows Figure 1 Schematic diagram of part of the structure of the aircraft when the landing gear is in the supporting position. DETAILED DESCRIPTION

[0026] The embodiments of the present application 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 only used to explain the present application, and cannot be understood as limiting the present application.

[0027] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the implementation mode of the present application will be clearly and completely described below in conjunction with the drawings in the implementation mode of the present application. Obviously, the described implementation mode is only a part of the implementation mode of the present application, not all the implementation modes. Based on the implementation mode in the present application, all other implementation modes obtained by those skilled in the art without making creative work are within the scope of protection of the present application.

[0028] See also Figure 1 to Figure 2 An embodiment of the present application provides an aircraft 10, which may be a flying car, an airplane, a drone or other flying equipment.

[0029] The aircraft 10 includes a fuselage 11 , a buffer 13 , a connecting mechanism 15 and a landing gear 17 .

[0030] The cylinder 131 of the buffer 13 is mounted on the fuselage 11, the connecting mechanism 15 is hinged to the fuselage 11 and the movable rod 133 of the buffer 13, and the landing gear 17 is foldably connected to the connecting mechanism 15. In this way, when the landing gear 17 vibrates, for example, when the aircraft 10 lands, the landing gear 17 vibrates after contacting the ground, and the landing gear 17 can transmit the vibration to the connecting mechanism 15 to drive the connecting mechanism 15 to rotate relative to the fuselage 11, thereby driving the movable rod 133 to slide in the cylinder 131, so as to achieve the effect of energy absorption and vibration reduction through the buffer 13. In addition, compared with the technical solution in the related art that the buffer folds synchronously with the landing gear 17, in the aircraft 10 provided by the embodiment of the present application, the cylinder 131 of the buffer 13 is mounted on the fuselage 11, so that there is no need to consider the influence of the weight of the buffer 13 on the folding of the landing gear 17, which reduces the weight of the folded part, and there is no need to reserve a folding space for the buffer 13 after the landing gear 17 is folded, which helps to reduce the volume of the aircraft 10.

[0031] Among them, the cylinder body 131 of the buffer 13 is assembled on the fuselage 11, which may mean that the cylinder body 131 of the buffer 13 is assembled inside the fuselage 11, or that the cylinder body 131 of the buffer 13 is assembled outside the fuselage 11, or that the cylinder body 131 of the buffer 13 is partially assembled inside the fuselage 11.

[0032] In some embodiments, the aircraft 10 may include a plurality of landing structures, each of which may include a buffer 13, a connecting mechanism 15, and a landing gear 17 to more stably support the fuselage 11. The term "plurality" may refer to 3 or more than 3, for example, a plurality of landing structures may refer to 3 landing structures, 4 landing structures, 5 landing structures, or other numbers of landing structures.

[0033] In some embodiments, the fuselage 11 may include a load-bearing beam 111, which may refer to a fuselage frame of the fuselage 11, or there may be multiple load-bearing beams 111, which are connected to form a fuselage frame. The fuselage frame may be used to support and assemble other structures of the aircraft 10. The load-bearing beam 111 may be made of metal to enhance the structural strength of the fuselage frame.

[0034] In some embodiments, the load beam 111 is at least partially located at the bottom of the fuselage 11 to better support and assemble other structures of the aircraft 10 .

[0035] See also Figures 2 to 4In some embodiments, the buffer 13 may have multiple options. For example, the buffer 13 may be an oil-gas buffer. The specific structure thereof may refer to the prior art and will not be described in detail.

[0036] In some other implementations, the buffer 13 may also adopt other buffering devices, components or equipment.

[0037] In some embodiments, the shape of the cylinder 131 can be selected or designed according to needs. For example, the cylinder 131 can be roughly columnar, such as cylindrical, to reduce the volume of the cylinder 131 and make it easier to assemble.

[0038] In some embodiments, the cylinder 131 may be embedded in the fuselage 11 , so that the space in the fuselage 11 can be fully utilized and the appearance is more beautiful. For example, the cylinder 131 may be located in the fuselage 11 and connected to the load-bearing beam 111 .

[0039] In some embodiments, the load beam 111 may be provided with a mounting groove 1111 , and the cylinder 131 may be embedded in the mounting groove 1111 , so that the space in the load beam 111 can be fully utilized without occupying space in other locations in the cabin of the aircraft 10 .

[0040] In some embodiments, the mounting groove 1111 may be located on the side of the fuselage 11. When the buffer 13 is installed, the cylinder 131 of the buffer 13 may be press-fitted into the mounting groove 1111. The cylinder 131 may include a cylinder body 1311 and a fixing portion 1313. The movable rod 133 may be slidably disposed in the cylinder body 1311. The fixing portion 1313 may be protruding from the outer surface of the cylinder body 1311. The cylinder 131 may be fixedly connected to the load-bearing beam 111 through the fixing portion 1313. For example, the fixing portion 1313 and the load-bearing beam 111 may be connected by a fixing member, and the fixing member may be a bolt, a screw, a rivet or other fixing structure.

[0041] There may be a plurality of fixing parts 1313, and the fixing parts 1313 may be distributed at intervals on the outer surface of the cylinder body 1311. For example, the top of the cylinder body 1311 away from the movable rod 133 may be provided with a fixing part 1313, and the left and right sides of the outer peripheral surface of the cylinder body 131 may be provided with a fixing part 1313. Correspondingly, the shape of the mounting groove 1111 may be adapted to the shape of the cylinder body 131, so that the cylinder body 1311 and the fixing part 1313 may be embedded in the mounting groove 1111. The shape of the bearing beam 111 may also be adapted to the shape of the cylinder body 131. For example, at least a part of the structure of the bearing beam 111 is roughly columnar, and a boss 1113 may be convexly provided on the surface of the bearing beam 111, and the mounting groove 1111 is partially provided in the boss 1113, so as to facilitate the installation of the fixing part 1313 of the cylinder body 131, which helps the cylinder body 131 to be more firmly and stably embedded in the mounting groove.

[0042] In addition, since the top and side (for example, the left side, the right side, etc.) of the outer peripheral surface of the cylinder body 131 are provided with a fixing portion 1313, when the movable rod 133 slides relative to the cylinder body 1311 to absorb energy and reduce vibration, the cylinder body 131 will not deviate toward the side direction or loosen toward the top direction, which helps to improve the stability of the cylinder body 131 assembled on the fuselage 11 and improve the reliability of the energy absorption and vibration reduction of the buffer 13.

[0043] In some embodiments, the buffer 13 may be exposed from the body 11 , and the buffer 13 may also be shielded by other structures to achieve different visual effects.

[0044] Taking the buffer 13 being blocked as an example, the aircraft 10 may further include a skin, which may be wrapped around the outer surface of the fuselage 11 to block the buffer 13 .

[0045] In some embodiments, the sliding direction of the movable rod 133 in the cylinder 131 can be parallel to the direction from the bottom of the fuselage 11 to the top of the fuselage 11 (vertical direction). It can be understood that when the movable rod of the buffer of the related art slides obliquely, the cylinder and the movable rod need to be arranged obliquely, resulting in the movable rod and the cylinder occupying a large space. When the movable rod 133 of the buffer 13 of the embodiment of the present application slides vertically, the cylinder 131 can be arranged in the vertical direction, and the sliding direction of the movable rod 133 is roughly parallel to the vertical direction, which helps to reduce the space occupied by the movable rod 133 and the cylinder 131, thereby reducing the volume of the aircraft 10.

[0046] In some embodiments, the connection mechanism 15 may be a connecting rod mechanism, so that the movable rod 133 can slide more smoothly in the cylinder body 131 along the vertical direction.

[0047] Specifically, in some embodiments, the connection mechanism 15 may include a rocker arm 151 and a connecting arm 153, the rocker arm 151 may be hinged to the fuselage 11 and the connecting arm 153, and one end of the connecting arm 153 away from the rocker arm 151 is hinged to the movable rod 133, so that the rocker arm 151 can rotate relative to the fuselage 11 to drive the connecting arm 153 to rotate synchronously. While the connecting arm 153 rotates synchronously with the rocker arm 151, the connecting arm 153 also rotates relative to the rocker arm 151 to push the movable rod 133 to slide smoothly in the cylinder body 131, which helps to avoid interference between the movable rod 133 and the cylinder body 131.

[0048] The landing gear 17 is foldably connected to the rocker arm 151. The vibration generated when the landing gear 17 contacts the ground can be transmitted to the rocker arm 151, driving the rocker arm 151 to rotate relative to the fuselage 11. The connecting arm 153 rotates synchronously with the rocker arm 151. At the same time, the connecting arm 153 can rotate between the rocker arm 151 and the movable rod 133 to drive the movable rod 133 to slide in the cylinder body 131.

[0049] In some embodiments, one end of the rocker arm 151 may be hinged to the fuselage 11, the other end of the rocker arm 151 may be hinged to the landing gear 17, and the connecting arm 153 may be hinged between the two ends of the rocker arm 151. In this way, the buffer 13 is helped to achieve a better energy absorption and vibration reduction effect.

[0050] In some embodiments, the rocker arm 151 may have a first installation space 1511 and a second installation space 1513 separated therefrom. The first installation space 1511 and the second installation space 1513 may be used to assemble other structural parts to fully utilize the internal space of the rocker arm 151 , thereby helping to reduce the size of the aircraft 10 .

[0051] In some embodiments, the rocker arm 151 may include a connecting portion 1515, a first arm body 1516, a second arm body 1517, and a third arm body 1518. The first arm body 1516, the second arm body 1517, and the third arm body 1518 are all connected to the connecting portion 1515, and the first arm body 1516, the second arm body 1517, and the third arm body 1518 are sequentially arranged side by side. The ends of the first arm body 1516, the second arm body 1517, and the third arm body 1518 that are away from the connecting portion 1515 are coaxially hinged to the fuselage 11, and the landing gear 17 is hinged to the connecting portion 1515, which helps to simplify the structure of the rocker arm 151, thereby reducing the difficulty of processing or assembling the rocker arm 151.

[0052] Among them, the first arm 1516, the second arm 1517 and the third arm 1518 are coaxially hinged to the fuselage 11 at one end away from the connecting portion 1515, which means that the first arm 1516 has a first end away from the connecting portion 1515, the second arm 1517 has a second end away from the connecting portion 1515, and the third arm 1518 has a third end away from the connecting portion 1515, and the first end, the second end and the third end are coaxially hinged to the fuselage 11.

[0053] The vibration generated when the landing gear 17 contacts the ground can be transmitted to the connecting part 1515, the first arm 1516, the second arm 1517 and the third arm 1518, so as to drive the first arm 1516, the second arm 1517 and the third arm 1518 to rotate coaxially, thereby driving the connecting arm 153 to rotate, so as to drive the movable rod 133 to slide in the cylinder body 131.

[0054] In some embodiments, the first installation space 1511 can be located between the first arm 1516 and the second arm 1517 , the connecting arm 153 can be hinged to the first arm 1516 and the second arm 1517 , and the second installation space 1513 can be located between the second arm 1517 and the third arm 1518 .

[0055] In some embodiments, the connecting portion 1515, the first arm body 1516, the second arm body 1517 and the third arm body 1518 can be formed as an integral body, or the connecting portion 1515, the first arm body 1516, the second arm body 1517 and the third arm body 1518 can also be separate structures, and the connecting portion 1515, the first arm body 1516, the second arm body 1517 and the third arm body 1518 are assembled to form the rocker arm 151.

[0056] In some embodiments, the shapes and structures of the first arm 1516, the second arm 1517, and the third arm 1518 may be the same, which helps to further reduce the difficulty of processing or reduce the manufacturing cost.

[0057] In some other embodiments, the shapes of the first arm 1516 , the second arm 1517 , and the third arm 1518 may also be different.

[0058] In some embodiments, the landing gear 17 can be manually operated to achieve folding or unfolding, or the landing gear 17 can be driven by a driving member to achieve folding or unfolding.

[0059] Taking the example of a driving member driving the landing gear 17 to fold or unfold, in some embodiments, the aircraft 10 may also include a first telescopic driving member, which may be connected to the connecting mechanism 15 or the fuselage 11. The first telescopic driving member may be used to drive the landing gear 17 to fold, thereby eliminating the need for manual operation and improving convenience.

[0060] Specifically, the telescopic rod or cylinder of the first telescopic driving member can be connected to the landing gear 17, and when the telescopic rod of the first telescopic driving member is extended and retracted relative to the cylinder, the landing gear 17 can be driven to rotate relative to the connecting mechanism 15, so as to unfold or fold the landing gear 17. Alternatively, the telescopic rod or cylinder of the first telescopic driving member can also be connected to the landing gear 17 through other structures, for example, the telescopic rod or cylinder of the first telescopic driving member is connected to the landing gear 17 through a connecting rod structure, and when the telescopic rod of the first telescopic driving member is extended and retracted relative to the cylinder, the connecting rod structure can be driven to move, and when the connecting rod structure moves, the landing gear 17 can be driven to unfold or fold, which helps to reduce the interference between the telescopic rod or cylinder of the first telescopic driving member and other structural members.

[0061] In some embodiments, the connecting arm 153 can be at least partially located in the first installation space 1511, and the first telescopic drive component can be connected to the connecting mechanism 15 and located in the second installation space 1513, so that the connecting arm 153 and the first telescopic drive component are respectively located in different spaces, which can reduce the motion interference between the connecting arm 153 and the first telescopic drive component, and also help to make more effective use of the space in the rocker arm 151, thereby further reducing the size of the aircraft 10.

[0062] In some embodiments, the landing gear 17 may have a first end and a second end opposite to each other, the first end being rotatably connected to the connecting mechanism 15, and the first end being rotated relative to the connecting mechanism 15 to drive the landing gear 17 to fold or unfold. For example, the first end may be hinged to the connecting portion 1515.

[0063] As an example, the first end may have a first hinge portion 1711 and a second hinge portion 1713 that are oppositely and spaced apart. The first hinge portion 1711 and the second hinge portion 1713 may both be hinged to the connecting portion 1515 and rotate coaxially, thereby enhancing the hinge strength of the landing gear 17 and the connecting mechanism 15.

[0064] In some embodiments, the landing gear 17 may have a stowed position and a support position. When the landing gear 17 is in the stowed position (ie, when the landing gear 17 is folded, such as Figure 5 As shown in FIG. 1 ), the second end can be close to the fuselage 11 to store the landing gear 17. For example, after the aircraft 10 takes off, the landing gear 17 can be rotated to the storage position (i.e., when the landing gear 17 is deployed, as shown in FIG. 1 ). Figure 6 As shown), or when the aircraft 10 is a small unmanned aerial vehicle, the landing gear 17 can be rotated to the storage position to facilitate the storage of the aircraft 10.

[0065] When the landing gear 17 is in the supporting position, the second end can be away from the fuselage 11, and the landing gear 17 supports the fuselage 11, so that when the aircraft 10 lands, the landing gear 17 can support the fuselage 11.

[0066] In some embodiments, the landing gear 17 may be located on the side of the fuselage 11 when in the stowed position, and the landing gear 17 may also be located on the bottom of the fuselage 11 when in the stowed position.

[0067] In some embodiments, when the landing gear 17 is in the stowed position, the landing gear 17 may be located outside the fuselage 11 or may be stowed inside the fuselage 11 .

[0068] In some embodiments, the aircraft 10 may further include a locking member, the landing gear 17 may have a first locking hole, and the connecting mechanism 15 may have a second locking hole.

[0069] When the landing gear 17 is in the supporting position, the first locking hole can be opposite to the second locking hole, and the locking piece can be inserted into the first locking hole and the second locking hole to fix the relative position of the landing gear 17 and the rocker arm 151, so that the landing gear 17 can be locked in the supporting position, so that the landing gear 17 can support the fuselage 11 more stably, which helps to avoid the landing gear 17 from rotating in the supporting position and improves the stability of the landing gear 17 support.

[0070] When the landing gear 17 rotates from the supporting position to the storage position, the locking member can be disengaged from the first locking hole and the second locking hole, so that the landing gear 17 can rotate relative to the rocker arm 151 to the storage position.

[0071] In some embodiments, the number of the first locking holes may be one or more, for example, the number of the first locking holes may be two, and the two first locking holes may be respectively provided at the first hinge portion 1711 and the second hinge portion 1713. It can be understood that the number of the second locking holes may be the same as the number of the first locking holes, and they correspond one to one, and each group of the first locking holes and the second locking holes may correspond to a locking member.

[0072] In some embodiments, the locking member may be a locking pin.

[0073] In some embodiments, the locking member can be manually operated to be inserted into or disengaged from the first locking hole and the second locking hole, and the locking member can also be driven by a driving member to be inserted into or disengaged from the first locking hole and the second locking hole.

[0074] Taking the example of a driving member driving the locking member to insert into or disengage from the first locking hole and the second locking hole, in some embodiments, the aircraft 10 may also include a second telescopic driving member, and the second telescopic driving member may be connected to the connecting mechanism 15, for example, the second telescopic driving member may be connected to the connecting portion 1515 of the rocker arm 151.

[0075] The second telescopic drive member can be used to drive the locking member to move so that the locking member is inserted into the first locking hole and the second locking hole, or the locking member is disengaged from the first locking hole and the second locking hole. When the landing gear 17 is in the supporting position, the second telescopic drive member can drive the locking member to be inserted into the first locking hole and the second locking hole to fix the landing gear 17 and the rocker arm 151, so that the landing gear 17 can be locked in the supporting position; when the landing gear 17 rotates from the supporting position to the storage position, the second telescopic drive member can drive the locking member to disengage from the first locking hole and the second locking hole, so that the landing gear 17 can rotate to the storage position.

[0076] It can be understood that the locking member can be connected to the telescopic end of the second telescopic drive member, so that the second telescopic drive member can drive the locking member to move, or the second telescopic drive member can also include a locking member, and the locking member can serve as the telescopic rod of the second telescopic drive member.

[0077] See also Figure 1 and Figure 3 In some embodiments, the landing gear 17 may include a support arm 171 and a grounding piece 173. The support arm 171 may be foldably connected to the connecting mechanism 15. For example, the support arm 171 may be hinged to the connecting portion 1515 of the rocker arm 151. The first hinge portion 1711 and the second hinge portion 1713 may both be disposed at one end of the support arm 171 away from the grounding piece 173.

[0078] The grounding member 173 can be connected to one end of the support arm 171 away from the connecting mechanism 15 . The grounding member 173 can be one of a skateboard and a roller. In this way, the aircraft 10 can have a variety of structural forms, thereby expanding the application range of the aircraft 10 .

[0079] In some embodiments, the grounding member 173 is detachably connected to the support arm 171 , so that the grounding member 173 can be easily replaced, which is helpful for subsequent maintenance and replacement.

[0080] In the aircraft 10 provided in the embodiment of the present application, the cylinder 131 of the buffer 13 is assembled to the fuselage 11, the connecting mechanism 15 is hinged to the fuselage 11 and the movable rod 133 of the buffer 13, and the landing gear 17 is foldably connected to the connecting mechanism 15. In this way, when the landing gear 17 vibrates, for example, when the aircraft 10 lands, the landing gear 17 vibrates after contacting the ground, and the landing gear 17 can transmit the vibration to the connecting mechanism 15, so as to drive the connecting mechanism 15 to rotate relative to the fuselage 11, and then drive the movable rod 133 to slide in the cylinder 131, so as to achieve the effect of energy absorption and vibration reduction through the buffer 13. In addition, compared with the technical solution in the related art that the buffer folds synchronously with the landing gear 17, in the aircraft 10 provided in the embodiment of the present application, the cylinder 131 of the buffer 13 is assembled on the fuselage 11, so there is no need to consider the impact of the weight of the buffer 13 on the folding of the landing gear 17, thereby reducing the weight of the folded part, and there is no need to reserve folding space for the buffer 13 after the landing gear 17 is folded, which helps to reduce the volume of the aircraft 10.

[0081] In this application, unless otherwise clearly specified or limited, the terms "installation", "connection" 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; it can be a direct connection, or it can be indirectly connected through an intermediate medium, it can be internal communication between two elements, it can be only surface contact, or it can be connected through surface contact through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0082] In addition, the terms "first", "second", etc. are only used to distinguish descriptions and cannot be understood as specific or special structures. The descriptions of the terms "some embodiments", "other embodiments", etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiments or examples are included in at least one embodiment or example of the present application. In the present application, 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 can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0083] The above implementation modes are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned implementation modes, a person skilled in the art should understand that the technical solutions described in the aforementioned implementation modes can still be modified, or some of the technical features can be replaced by equivalents. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various implementation modes of the present application, and should all be included in the protection scope of the present application.

Claims

1. An aircraft, characterized in that: include: body; A buffer, a cylinder of which is mounted on the fuselage; A connecting mechanism, the connecting mechanism being hinged to the body and the movable rod of the buffer; as well as A landing gear is foldably connected to the connecting mechanism.

2. The aircraft according to claim 1, characterized in that The cylinder body is embedded in the fuselage.

3. The aircraft according to claim 2, characterized in that: The fuselage comprises a load-bearing beam, wherein at least a part of the load-bearing beam is located at the bottom of the fuselage, and the load-bearing beam is provided with a mounting groove, and the cylinder body is embedded in the mounting groove.

4. The aircraft according to claim 1, characterized in that: The sliding direction of the movable rod in the cylinder is parallel to the direction from the bottom of the fuselage to the top of the fuselage.

5. The aircraft according to claim 1, characterized in that: The connecting mechanism comprises a rocker arm and a connecting arm, the rocker arm is hinged to the fuselage and the connecting arm, one end of the connecting arm away from the rocker arm is hinged to the movable rod, and the landing gear is foldably connected to the rocker arm.

6. The aircraft according to claim 5, characterized in that The aircraft further comprises a first telescopic driving member, which is connected to the connecting mechanism or the fuselage, and is used for driving the landing gear to fold.

7. The aircraft according to claim 6, characterized in that The rocker arm has a first installation space and a second installation space separated from each other, the connecting arm is at least partially located in the first installation space, and the first telescopic driving member is connected to the connecting mechanism and is located in the second installation space.

8. The aircraft according to claim 7, characterized in that The rocker arm comprises a connecting portion, a first arm body, a second arm body and a third arm body, wherein the first arm body, the second arm body and the third arm body are all connected to the connecting portion and are arranged side by side in sequence, and ends of the first arm body, the second arm body and the third arm body away from the connecting portion are coaxially hinged to the fuselage, and the landing gear is hinged to the connecting portion; The first installation space is located between the first arm body and the second arm body, the connecting arm is hinged to the first arm body and the second arm body, and the second installation space is located between the second arm body and the third arm body.

9. The aircraft according to claim 1, characterized in that: The landing gear has a first end and a second end opposite to each other, the first end is rotatably connected to the connecting mechanism; the landing gear has a storage position and a supporting position, when the landing gear is in the storage position, the second end is close to the fuselage, and when the landing gear is in the supporting position, the second end is away from the fuselage, and the landing gear supports the fuselage.

10. The aircraft according to claim 9, characterized in that The aircraft further comprises a locking member, the landing gear has a first locking hole, and the connecting mechanism has a second locking hole; When the landing gear is in the supporting position, the locking member is inserted into the first locking hole and the second locking hole; when the landing gear rotates from the supporting position to the storage position, the locking member is disengaged from the first locking hole and the second locking hole.

11. The aircraft according to claim 10, characterized in that The aircraft also includes a second telescopic driving member, which is connected to the connecting mechanism and is used to drive the locking member to be telescopic so that the locking member is inserted into the first locking hole and the second locking hole, or is disengaged from the first locking hole and the second locking hole.

12. The aircraft according to claim 1, characterized in that: The landing gear comprises a support arm and a grounding piece, wherein the support arm is foldably connected to the connecting mechanism, the grounding piece is connected to one end of the support arm away from the connecting mechanism, and the grounding piece is one of a slide plate and a roller.

13. The aircraft according to claim 12, characterized in that The grounding member is detachably connected to the supporting arm.

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