aircraft

Abstract

The application provides an aircraft, comprising a fuselage, a bumper, a connecting mechanism and a landing gear, the cylinder body of the bumper is assembled to the fuselage; the connecting mechanism is hinged to the movable rod of the bumper and the fuselage; and the landing gear is foldably connected to the connecting mechanism. In this way, when the landing gear vibrates, the landing gear can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, and then drive the movable rod to slide in the cylinder body to achieve the effect of energy absorption and vibration reduction through the bumper. In addition, compared with the technical solution in the prior art that the bumper is synchronously folded with the landing gear, the aircraft provided by the embodiment of the application does not need to consider the influence of the weight of the bumper on the folding of the landing gear, the weight of the folding part is reduced, and no folding space needs to be reserved for the bumper after the landing gear is folded, which helps to reduce the volume of the aircraft.

Description

TECHNICAL FIELD

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

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

[0003] The conventional landing gear structure occupies a large space when folded, which is difficult to meet the needs of users. SUMMARY

[0004] The present application aims to provide an aircraft to improve at least one of the above technical problems. The present application achieves the above-mentioned purpose through the following technical solutions.

[0005] The present application provides an aircraft, comprising a fuselage, a buffer, a connecting mechanism, and a landing gear, the cylinder body of the buffer is assembled to the fuselage; the connecting mechanism is hinged to the movable rod of the buffer and the fuselage; the landing gear is foldably connected to the connecting mechanism.

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

[0007] In some embodiments, the fuselage comprises a load-bearing beam, the load-bearing beam 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 body is parallel to the direction from the bottom of the fuselage to the top of the fuselage.

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

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

[0011] In some embodiments, the rocker arm has a first mounting space and a second mounting space spaced apart, the connecting arm is at least partially located in the first mounting space, and the first telescopic driving member is connected to the connecting mechanism and located in the second mounting space.

[0012] In some embodiments, the rocker arm comprises 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 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 mounting 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 mounting space is located between the second arm body and the third arm body.

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

[0014] In some embodiments, 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 support position, the locking member is inserted into the first locking hole and the second locking hole; when the landing gear rotates from the support position to the storage position, the locking member is separated from the first locking hole and the second locking hole.

[0015] In some embodiments, the aircraft further comprises a second telescopic driving member, the second telescopic driving member is connected to the connecting mechanism, and the second telescopic driving member is used to drive the locking member to telescope so as to insert the locking member into the first locking hole and the second locking hole or separate the locking member from the first locking hole and the second locking hole.

[0016] In some embodiments, the landing gear comprises a support arm and a ground member, the support arm is foldably connected to the connecting mechanism, the ground member is connected to one end of the support arm away from the connecting mechanism, and the ground member is one of a sliding plate and a roller.

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

[0018] In the aircraft provided by the embodiments of the present application, the cylinder body of the buffer is assembled to 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 generates vibration after contacting the ground, the landing gear can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, and then drive the movable rod to slide in the cylinder body 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 is folded synchronously with the landing gear, in the aircraft provided by the embodiments of the present application, the cylinder body of the buffer is assembled to the fuselage, so that the influence of the weight of the buffer on the folding of the landing gear does not need to be considered, the weight of the folding part is reduced, and after the landing gear is folded, no folding space needs to be reserved for the buffer, which helps to reduce the volume of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the description of the embodiments. Obviously, the drawings described in the following only are some of the embodiments of the present application, and all other drawings obtained by those skilled in the art without creative effort based on the embodiments in the present application shall fall within the scope of the present application.

[0020] Figure 1 A structural schematic diagram of an aircraft provided by the embodiments of the present application is shown.

[0021] Figure 2 A partially exploded structural schematic diagram of the aircraft of Figure 1 is shown.

[0022] Figure 3 A partially exploded structural schematic diagram of the aircraft of Figure 2 is shown.

[0023] Figure 4 A structural schematic diagram of the aircraft of Figure 1 is shown.

[0024] Figure 5 A structural schematic diagram of the aircraft of Figure 1 is shown, with the landing gear in a stowed position.

[0025] Figure 6 A structural schematic diagram of the aircraft of Figure 1 is shown, with the landing gear in a support position. DETAILED DESCRIPTION

[0026] The embodiments of the present application will be described in detail below, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only, and are used to explain the present application, and cannot be understood as a limitation of the present application.

[0027] In order to make the person skilled in the art better understand the present application, the technical solutions in the embodiments of the present application will be described clearly and completely below by referring to the drawings in the embodiments of the present application. Obviously, the described embodiments only are some of the embodiments of the present application, and are not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort shall fall within the scope of the present application.

[0028] Please refer to Figures 1 to 2 , the embodiments of the present application provide an aircraft 10, which can be a flying car, an airplane, a drone or other flying equipment.

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

[0030] The cylinder 131 of the bumper 13 is assembled to the fuselage 11, the connecting mechanism 15 is hinged to the movable rod 133 of the bumper 13 and the fuselage 11, and the landing gear 17 is foldably connected to the connecting mechanism 15. Thus, when the landing gear 17 vibrates, for example, when the aircraft 10 lands, the landing gear 17 generates vibration 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 to achieve the energy absorption and vibration reduction effect through the bumper 13. In addition, compared with the technical solution in the related art that the bumper is folded synchronously with the landing gear 17, in the aircraft 10 provided by the embodiment of the present application, the cylinder 131 of the bumper 13 is assembled to the fuselage 11, so that the influence of the weight of the bumper 13 on the folding of the landing gear 17 is not considered, the weight of the folding part is reduced, and no folding space needs to be reserved for the bumper 13 after the landing gear 17 is folded, which helps to reduce the volume of the aircraft 10.

[0031] Here, the cylinder 131 of the bumper 13 assembled to the fuselage 11 can mean that the cylinder 131 of the bumper 13 is assembled inside the fuselage 11, or that the cylinder 131 of the bumper 13 is assembled outside the fuselage 11, or that part of the cylinder 131 of the bumper 13 is assembled inside the fuselage 11.

[0032] In some embodiments, the aircraft 10 can comprise a plurality of landing structures, each of which can comprise a bumper 13, a connecting mechanism 15, and a landing gear 17 to more stably support the fuselage 11. Here, the term "plurality" can mean 3 or more, for example, the plurality of landing structures can mean 3 landing structures, 4 landing structures, 5 landing structures, or other numbers of landing structures.

[0033] In some embodiments, the fuselage 11 can comprise a load-bearing beam 111, which can mean a fuselage frame of the fuselage 11, or the number of load-bearing beams 111 can be a plurality, and the plurality of load-bearing beams 111 are connected to form a fuselage frame. The fuselage frame can act to support and assemble other structures of the aircraft 10. The load-bearing beam 111 can be made of metal to enhance the structural strength of the fuselage frame.

[0034] In some embodiments, the load-bearing 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] Please refer to Figures 2 to 4In some embodiments, the buffer 13 can be selected from various types of buffers, for example, the buffer 13 can be an oil-gas buffer, the specific structure of which can refer to the prior art and will not be described herein.

[0036] In some other embodiments, the buffer 13 can also adopt other buffering devices, means or equipment.

[0037] In some embodiments, the shape of the cylinder 131 can be selected or designed according to requirements, for example, the cylinder 131 can be substantially cylindrical, so as to reduce the volume of the cylinder 131 and facilitate assembly.

[0038] In some embodiments, the cylinder 131 can be embedded in the fuselage 11, so as to make full use of the space in the fuselage 11 and be more aesthetically pleasing. For example, the cylinder 131 can be located in the fuselage 11 and connected to the load-bearing beam 111.

[0039] In some embodiments, the load-bearing beam 111 can be provided with a mounting groove 1111, and the cylinder 131 can be embedded in the mounting groove 1111, so as to make full use of the space in the load-bearing beam 111 without occupying the space of other positions in the cabin of the aircraft 10.

[0040] In some embodiments, the mounting groove 1111 can be located on the side surface of the fuselage 11. When the buffer 13 is installed, the cylinder 131 of the buffer 13 can be press-fitted in the mounting groove 1111. The cylinder 131 can include a cylinder body 1311 and a fixing portion 1313, the movable rod 133 can be slidably arranged in the cylinder body 1311, and the fixing portion 1313 can be protruded from the outer surface of the cylinder body 1311, the cylinder 131 can 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 can be connected through a fixing member, which can be a bolt, a screw, a rivet or other fixing structure.

[0041] In some embodiments, the number of the fixing portions 1313 can be multiple, and the multiple fixing portions 1313 can 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 can be provided with a fixing portion 1313, and the left and right sides of the outer circumferential surface of the cylinder 131 can be provided with fixing portions 1313. Correspondingly, the shape of the mounting groove 1111 can be adapted to the shape of the cylinder 131, so that the cylinder body 1311 and the fixing portion 1313 can be embedded in the mounting groove 1111. The shape of the load-bearing beam 111 can also be adapted to the shape of the cylinder 131, for example, at least a part of the structure of the load-bearing beam 111 can be substantially cylindrical, the surface of the load-bearing beam 111 can be protruded with a boss 1113, and the mounting groove 1111 can be partially arranged in the boss 1113, so as to facilitate the installation of the fixing portion 1313 of the cylinder 131 and help the cylinder 131 to be more firmly and stably embedded in the mounting groove.

[0042] In addition, since the top and side (e.g. left side, right side, etc.) of the outer circumferential surface of the cylinder body 131 are provided with the fixing portion 1313, the cylinder body 131 will not be offset to the side or loosened to the top during the energy absorption and vibration reduction process of the sliding of the movable rod 133 relative to the cylinder body 1311, 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 bumper 13.

[0043] In some embodiments, the bumper 13 can be exposed to the fuselage 11, and the bumper 13 can be shielded by other structures to achieve different visual effects.

[0044] Taking the bumper 13 being shielded as an example, the aircraft 10 can further include a skin, which can be wrapped on the outer surface of the fuselage 11 to shield the bumper 13.

[0045] In some embodiments, the sliding direction of the movable rod 133 in the cylinder body 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 related art bumper is inclined to slide, the cylinder and the movable rod need to be inclined to arrange, which causes the movable rod and the cylinder to occupy a larger space. However, when the movable rod 133 of the bumper 13 of the present application embodiment slides vertically, the cylinder body 131 can be arranged along the vertical direction, and the sliding direction of the movable rod 133 is substantially parallel to the vertical direction, which helps to reduce the space occupied by the movable rod 133 and the cylinder body 131, so as to reduce the volume of the aircraft 10.

[0046] In some embodiments, the connecting mechanism 15 can 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 connecting mechanism 15 can include a rocker arm 151 and a connecting arm 153, the rocker arm 151 can be hinged to the fuselage 11 and the connecting arm 153, and the 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 the interference between the movable rod 133 and the cylinder body 131.

[0048] The landing gear 17 is foldably connected to the rocker arm 151. 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 can rotate synchronously with the rocker arm 151, and the connecting arm 153 can rotate between the rocker arm 151 and the movable rod 133, driving the movable rod 133 to slide in the cylinder 131.

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

[0050] In some embodiments, the rocker arm 151 can have spaced first mounting space 1511 and second mounting space 1513. The first mounting space 1511 and the second mounting space 1513 can be used to assemble other structural members, so as to make full use of the internal space of the rocker arm 151, and help to reduce the size of the aircraft 10.

[0051] In some embodiments, the rocker arm 151 can 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 connected to the connecting portion 1515, and are arranged side by side in sequence. The first arm body 1516, the second arm body 1517, and the third arm body 1518 are coaxially hinged to the fuselage 11 at one end away from the connecting portion 1515, and the landing gear 17 is hinged to the connecting portion 1515. This helps to make the structure of the rocker arm 151 simpler, thereby reducing the processing or assembly difficulty of the rocker arm 151.

[0052] In some embodiments, the first arm body 1516, the second arm body 1517, and the third arm body 1518 are coaxially hinged to the fuselage 11 at one end away from the connecting portion 1515. That is, the first arm body 1516 has a first end portion away from the connecting portion 1515, the second arm body 1517 has a second end portion away from the connecting portion 1515, and the third arm body 1518 has a third end portion away from the connecting portion 1515. The first end portion, the second end portion, and the third end portion are coaxially hinged to the fuselage 11.

[0053] Vibration generated when the landing gear 17 contacts the ground can be transmitted to the connecting portion 1515, the first arm body 1516, the second arm body 1517, and the third arm body 1518, driving the first arm body 1516, the second arm body 1517, and the third arm body 1518 to rotate coaxially, and further driving the connecting arm 153 to rotate, and driving the movable rod 133 to slide in the cylinder 131.

[0054] In some embodiments, the first mounting space 1511 can be located between the first arm body 1516 and the second arm body 1517, the connecting arm 153 can be hinged to the first arm body 1516 and the second arm body 1517, and the second mounting space 1513 can be located between the second arm body 1517 and the third arm body 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 integrally formed, or the connecting portion 1515, the first arm body 1516, the second arm body 1517 and the third arm body 1518 can 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 first arm body 1516, the second arm body 1517 and the third arm body 1518 can have the same shape structure, which can further reduce the processing difficulty or the manufacturing cost.

[0057] In other embodiments, the first arm body 1516, the second arm body 1517 and the third arm body 1518 can also have different shapes.

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

[0059] For example, the landing gear 17 is driven by the driving member to be folded or unfolded, in some embodiments, the aircraft 10 can further include a first telescopic driving member, which can be connected to the connecting mechanism 15 or the fuselage 11, and the first telescopic driving member can be used to drive the landing gear 17 to be folded, so as to improve the convenience without manual operation.

[0060] Specifically, the telescopic rod or cylinder of the first telescopic driving member can be connected to the landing gear 17, and the telescopic rod of the first telescopic driving member can drive the landing gear 17 to rotate relative to the connecting mechanism 15 when the telescopic rod of the first telescopic driving member is telescoped relative to the cylinder, 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 the telescopic rod of the first telescopic driving member can drive the connecting rod structure to move when the telescopic rod of the first telescopic driving member is telescoped relative to the cylinder, and the connecting rod structure can drive the landing gear 17 to unfold or fold when the connecting rod structure moves, which can help 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 mounting space 1511, the first telescopic driving member can be connected to the connecting mechanism 15 and located in the second mounting space 1513, so that the connecting arm 153 and the first telescopic driving member are located in different spaces respectively, which can reduce the motion interference of the connecting arm 153 and the first telescopic driving member, and also helps to make full use of the space in the rocker arm 151, and further reduces the size of the aircraft 10.

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

[0063] As an example, the first end can have opposite and spaced first and second hinge portions 1711 and 1713, both of which can be hinged to the connecting portion 1515 and coaxially rotate, so as to enhance the hinge strength of the landing gear 17 and the connecting mechanism 15.

[0064] In some embodiments, the landing gear 17 can have a stowed position and a supporting position, when the landing gear 17 is in the stowed position (i.e. when the landing gear 17 is folded, as shown in Figure 5 For example, when the aircraft 10 takes off, the landing gear 17 can be rotated to the stowed position (i.e. when the landing gear 17 is unfolded, as shown in Figure 6 For example, when the aircraft 10 takes off, the landing gear 17 can be rotated to the stowed position (i.e. when the landing gear 17 is unfolded, as shown in

[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 can support 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 in the stowed position can be located on the side of the fuselage 11, and the landing gear 17 in the stowed position can also be located on the bottom of the fuselage 11.

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

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

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

[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 holes and the second locking holes, so that the landing gear 17 can rotate to the storage position relative to the rocker arm 151.

[0071] In some embodiments, the number of the first locking holes can be one or multiple, for example, the number of the first locking holes can be two, and the two first locking holes can be respectively arranged at the first hinge part 1711 and the second hinge part 1713. It can be understood that the number of the second locking holes can be the same as the number of the first locking holes, and one-to-one correspondence, and each set of the first locking holes and the second locking holes can correspond to one locking member.

[0072] In some embodiments, the locking member can 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 holes and the second locking holes, and the locking member can also be driven by the driving member to be inserted into or disengaged from the first locking holes and the second locking holes.

[0074] For example, the second telescopic driving member can be connected to the connecting mechanism 15, for example, the second telescopic driving member can be connected to the connecting part 1515 of the rocker arm 151.

[0075] The second telescopic driving member can be used to drive the locking member to move, so that the locking member is inserted into the first locking holes and the second locking holes, or the locking member is disengaged from the first locking holes and the second locking holes. When the landing gear 17 is in the supporting position, the second telescopic driving member can drive the locking member to be inserted into the first locking holes and the second locking holes 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 driving member can drive the locking member to be disengaged from the first locking holes and the second locking holes, 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 driving member, so that the second telescopic driving member can drive the locking member to move, or the second telescopic driving member can also include the locking member, and the locking member can be used as a telescopic rod of the second telescopic driving member.

[0077] Please refer to Figure 1 and Figure 3 In some embodiments, the landing gear 17 can include a support arm 171 and a ground engaging member 173, the support arm 171 is foldably connected to the connecting mechanism 15, for example, the support arm 171 can be hinged to the connecting portion 1515 of the rocker arm 151, and the first hinge portion 1711 and the second hinge portion 1713 can be arranged at one end of the support arm 171 away from the ground engaging member 173.

[0078] The ground engaging member 173 can be connected to one end of the support arm 171 away from the connecting mechanism 15, and the ground engaging member 173 can be one of a slide plate and a roller, so that the aircraft 10 can have various structural forms, thereby expanding the application range of the aircraft 10.

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

[0080] In the aircraft 10 provided by the embodiments of the present application, the cylinder body 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. Therefore, 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 body 131, so that the energy absorption and vibration reduction effect can be achieved through the buffer 13. In addition, compared with the technical solution in the prior art in which the buffer is folded synchronously with the landing gear 17, in the aircraft 10 provided by the embodiments of the present application, the cylinder body 131 of the buffer 13 is assembled to the fuselage 11, so that the influence of the weight of the buffer 13 on the folding of the landing gear 17 is not considered, the weight of the folding part is reduced, and no folding space needs to be reserved 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 "mounting", "connecting" and the like should be interpreted broadly. For example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection; it can be direct connection, or indirect connection through intermediate medium, or internal communication of two elements, or only surface contact, or surface contact connection through intermediate medium. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0082] In addition, the terms "first", "second" and the like are only used to distinguish descriptions, and cannot be understood as specific or special structures. The description of the terms "some embodiments", "other embodiments" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiments or examples are contained in at least one embodiment or example of the application. In this application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in this application and the features of different embodiments or examples without contradiction.

[0083] The above embodiments are only used to illustrate the technical solutions of the application, not to limit them; although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the application, and should be included in the protection scope of the application.

Claims

1. An aircraft, characterized in that The aircraft comprises: a fuselage; a buffer, a cylinder of the buffer is assembled to the fuselage, a sliding direction of a movable rod of the buffer in the cylinder is parallel to a direction from a bottom of the fuselage to a top of the fuselage; a connecting mechanism, the connecting mechanism comprises a rocker and a connecting arm, the rocker is hinged to the fuselage and the connecting arm, an end of the connecting arm away from the rocker is hinged to the movable rod, the rocker can rotate relative to the fuselage to drive the connecting arm to rotate synchronously, when the connecting arm rotates synchronously with the rocker, the connecting arm rotates relative to the rocker to push the movable rod to slide in the cylinder; and a landing gear, the landing gear is foldably connected to the rocker.

2. The aircraft of claim 1, wherein, The cylinder is embedded in the fuselage.

3. The aircraft of claim 2, wherein, The fuselage comprises a load-bearing beam, the load-bearing beam is at least partially located at the bottom of the fuselage, the load-bearing beam is provided with a mounting groove, and the cylinder is embedded in the mounting groove.

4. The aircraft of claim 1, wherein, The aircraft further comprises a first telescopic driving member, the first telescopic driving member is connected to the connecting mechanism or the fuselage, and the first telescopic driving member is used to drive the landing gear to fold.

5. The aircraft of claim 4, wherein, The rocker has spaced first and second mounting spaces, the connecting arm is at least partially located in the first mounting space, the first telescopic driving member is connected to the connecting mechanism and located in the second mounting space.

6. The aircraft of claim 5, wherein, The rocker comprises a connecting portion, first, second and third arm bodies, the first, second and third arm bodies are connected to the connecting portion and arranged side by side in sequence, coaxially hinged ends of the first, second and third arm bodies away from the connecting portion are hinged to the fuselage, and the landing gear is hinged to the connecting portion. The first mounting space is located between the first and second arm bodies, the connecting arm is hinged to the first and second arm bodies, and the second mounting space is located between the second and third arm bodies.

7. The aircraft of claim 1, wherein, The landing gear has opposite first and second ends, 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, when the landing gear is in the supporting position, the second end is away from the fuselage, and the landing gear supports the fuselage.

8. The aircraft of claim 7, wherein, 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 and second locking holes, and when the landing gear rotates from the supporting position to the storage position, the locking member is separated from the first and second locking holes.

9. The aircraft of claim 8, wherein, The aircraft further comprises a second telescopic driving member, the second telescopic driving member is connected to the connecting mechanism, and the second telescopic driving member is used to drive the locking member to telescope so that the locking member is inserted into the first and second locking holes or separated from the first and second locking holes.

10. The aircraft of claim 1, wherein, The landing gear includes a support arm foldably connected to the connecting mechanism, and a ground-engaging member connected to an end of the support arm away from the connecting mechanism, the ground-engaging member being one of a skid plate and a roller.

11. The aircraft of claim 10, wherein, The ground-engaging member is detachably connected to the support arm.

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