Single-body type hovercar attitude adjusting device and single-body type hovercar

Abstract

The utility model discloses a single-body type flying car attitude adjusting device and a single-body type flying car, and the single-body type flying car attitude adjusting device is connected between an integrated power device and a chassis frame and is used for driving the integrated power device to switch between a first position and a second position. The single-body type aerocar attitude adjusting device comprises a conversion steering engine and a lifting frame steering shaft composite body, the lifting frame steering shaft composite body is connected with the integrated power device and a driving part of the conversion steering engine, and the driving part can drive the lifting frame steering shaft composite body to rotate around a first axis so as to adjust the position of the integrated power device. Therefore, the single-body type hovercar attitude adjusting device can drive the integrated power device to rotate around the first axis so as to switch the position of the integrated power device, so that the working modes of the single-body type hovercar are switched, the switching action is simple, and the switching efficiency of the working modes of the single-body type hovercar is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of flying cars, in particular to a single-body flying car attitude adjustment device and a single-body flying car. Background Art

[0002] The flying car has both ground walking function and flying function.

[0003] In the related art, a flying car needs to switch the working mode of the flying car through multiple switching devices, which makes the switching action cumbersome, inconvenient to operate, and has low switching efficiency. Utility Model Content

[0004] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a single-body flying car attitude adjustment device, which has a simple structure and switching action, and is conducive to improving the efficiency of switching the working mode of the single-body flying car.

[0005] A single-body flying car attitude adjustment device is connected between an integrated power device and a chassis frame in driving the single-body flying car, and is used to drive the integrated power device to switch between a first position suitable for driving the single-body flying car to fly and a second position suitable for driving the single-body flying car to walk on the ground. The single-body flying car attitude adjustment device includes: a conversion steering gear, which is arranged on the chassis frame; a landing gear steering shaft complex, which is connected to the integrated power device, and the landing gear steering shaft complex is connected to a driving part of the conversion steering gear, and the driving part can drive the landing gear steering shaft complex to rotate around a first axis to adjust the position of the integrated power device.

[0006] According to the unibody flying car attitude adjustment device of the utility model, by arranging a conversion steering gear on the chassis frame, and making the take-off and landing gear steering shaft complex connected to the conversion steering gear and the integrated power device respectively, the conversion steering gear can drive the integrated power device to rotate around the first axis through the take-off and landing gear steering shaft complex, so that the integrated power device can be switched between the first position and the second position, thereby switching the working mode of the unibody flying car, and the switching action is simple, which is conducive to improving the switching efficiency of the working mode of the unibody flying car, and the structure of the unibody flying car attitude adjustment device is simple, which is conducive to simplifying the structure of the unibody flying car and reducing the production and assembly cost of the unibody flying car.

[0007] According to some embodiments of the present utility model, the landing gear steering shaft complex includes: a main body portion, the main body portion being power-connected to the conversion servo; a connecting rod, one end of the connecting rod being connected to the main body portion, and the connecting rod extending along a first direction; a connecting seat, the connecting seat being connected to the other end of the connecting rod, and the connecting seat being used for connecting to the integrated power device; wherein, the first direction is arranged parallel to the first axis.

[0008] According to some embodiments of the present utility model, the connecting seat is provided with an integrated power installation hole, the integrated power installation hole penetrating through the connecting seat along a second direction and being used for installing the integrated power device; wherein, the second direction is arranged perpendicular to the first direction.

[0009] According to some embodiments of the present utility model, the connecting seat is provided with a landing shaft installation hole, the landing shaft installation hole penetrating through the connecting seat along the first direction and being used for connecting to the chassis frame, so as to rotatably connect the connecting seat to the chassis frame around the first axis.

[0010] According to some embodiments of the present utility model, the landing gear steering shaft complex further includes an auxiliary shaft connecting seat, the auxiliary shaft connecting seat being arranged in the middle of the connecting rod and having a landing gear auxiliary shaft hole with a central axis collinear with the first axis, and the auxiliary shaft connecting seat being rotatably connected to the chassis frame around the first axis.

[0011] According to some embodiments of the present utility model, the landing gear steering shaft complex is provided with two groups of the connecting rods and the connecting seats, and the two groups of the connecting rods and the connecting seats are respectively arranged on both sides of the main body portion in the first direction.

[0012] According to some embodiments of the present utility model, the single-body flying vehicle attitude adjustment device further includes a servo landing gear, the servo landing gear being power-connected to the driving portion and connected to the landing gear steering shaft complex to drive the landing gear steering shaft complex to rotate around the first axis.

[0013] According to some embodiments of the present utility model, the servo landing gear includes: a first rotating arm and a second rotating arm, the first rotating arm and the second rotating arm being oppositely arranged in the first direction, and the first rotating arm and the second rotating arm being respectively power-connected to two driving portions on both sides of the conversion servo in the first direction; a fixing plate, the fixing plate being connected between the first rotating arm and the second rotating arm, and the fixing plate being arranged at an interval from the conversion servo and being used for connecting to the main body portion.

[0014] According to some embodiments of the present utility model, the main body portion includes: a first connecting plate, which is provided on a side of the first rotating arm away from the conversion servo in a first direction and is connected to the first rotating arm; a second connecting plate, which is disposed opposite to the first connecting plate in the first direction, and the second connecting plate is provided on a side of the second rotating arm away from the conversion servo in the first direction and is connected to the second rotating arm; a third connecting plate, which is connected between the first connecting plate and the second connecting plate and is used for fixedly connecting with the fixing plate.

[0015] According to some embodiments of the present utility model, the single-piece flying vehicle attitude adjustment device further includes a servo fixing bracket, which is provided on the chassis frame and is used for installing and fixing the conversion servo.

[0016] According to some embodiments of the present utility model, the servo fixing bracket structure includes: a first fixing wall and a second fixing wall, which are disposed opposite to each other and are respectively connected to two sides of the conversion servo; a connecting wall, which is connected between the first fixing wall and the second fixing wall and is used for fixedly connecting with the chassis frame.

[0017] Another object of the present utility model is to propose a single-piece flying vehicle.

[0018] A single-piece flying vehicle includes the above-mentioned single-piece flying vehicle attitude adjustment device.

[0019] The single-piece flying vehicle has the same advantages as the above-mentioned single-piece flying vehicle attitude adjustment device, which will not be elaborated here one by one.

[0020] The additional aspects and advantages of the present utility model will be partially given in the following description, partially will become obvious from the following description, or will be understood through the practice of the present utility model. Description of the Drawings

[0021] The above and / or additional aspects and advantages of the present utility model will become obvious and easy to understand from the description of the embodiments in conjunction with the following drawings, where:

[0022] Figure 1 is a schematic structural diagram of the single-piece flying vehicle according to the embodiment of the present utility model in the ground walking mode;

[0023] Figure 2 is a schematic structural diagram of the single-piece flying vehicle according to the embodiment of the present utility model in the flying mode;

[0024] Figure 3 is a schematic structural diagram of the single-piece flying vehicle attitude adjustment device according to the embodiment of the present utility modelFigure 1 ;

[0025] Figure 4 Structural schematic of the monolithic flying car attitude adjustment device according to the embodiment of the present utility model Figure 2 。

[0026] Reference numerals:

[0027] Monolithic flying car 100,

[0028] Chassis frame 10, main take-off and landing shaft main rotation axis 11, auxiliary take-off and landing frame auxiliary rotation axis 12,

[0029] Integrated power device 20, wheel assembly 21,

[0030] Power component 22, ducted motor 221, fan blade 222, ducted wall 223,

[0031] Connecting shaft assembly 23,

[0032] Monolithic flying car attitude adjustment device 30, conversion servo 31, driving part 311, output shaft 3111, servo disc 3112,

[0033] Take-off and landing frame steering shaft complex 32,

[0034] Main body part 321, first connecting plate 3211, second connecting plate 3212, third connecting plate 3213,

[0035] Connecting rod 322,

[0036] Connecting seat 323, integrated power installation hole 3231, take-off and landing shaft installation hole 3232,

[0037] Auxiliary rotation axis connecting seat 324, take-off and landing frame auxiliary rotation axis hole 3241,

[0038] Servo take-off and landing frame 33, first rotating arm 331, second rotating arm 332,

[0039] Servo fixing frame 34, first fixing wall 341, second fixing wall 342, connecting wall 343, fixing hole 3431, servo installation hole 344,

[0040] Steering servo 40. Detailed implementation manners

[0041] The embodiments of the present utility model will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions from beginning to end. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present utility model and should not be construed as a limitation to the present utility model.

[0042] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by terms such as "center", "axial direction", "radial direction", "circumferential direction", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present utility model, unless otherwise specified, the meaning of "a plurality" is two or more.

[0043] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0044] Next, reference is made to Figures 1 - 4 Describe a monolithic flying car attitude adjustment device 30 and a monolithic flying car 100 according to an embodiment of the present utility model.

[0045] In combination with Figures 1 to 3 , for the monolithic flying car attitude adjustment device 30 according to the present utility model, the monolithic flying car attitude adjustment device 30 is connected between an integrated power device 20 and a chassis frame 10 in the monolithic flying car 100, and is used to drive the integrated power device 20 to switch between a first position suitable for driving the monolithic flying car 100 to fly and a second position suitable for driving the monolithic flying car 100 to travel on the ground.

[0046] Exemplarily, in combination with Figure 1 and Figure 2 , the integrated power device 20 includes a wheel assembly 21 and a power assembly 22. The power assembly 22 includes a ducted motor 221, a fan blade 222, and a duct wall 223. The wheel assembly 21 is sleeved on the duct wall 223. The ducted motor 221 can drive the fan blade 222 and the wheel assembly 21 to rotate, so that the integrated power device 20 can output ground travel power and flight power.

[0047] Specifically, as shown in Figure 2As shown, when the integrated power unit 20 is in the first position, the central axis of the integrated power unit 20 is perpendicular to the ground, the wheel assembly 21 is separated from the ground, the fan blade 222 faces the ground, and the ducted motor 221 can drive the fan blade 222 to rotate to form an air flow to push the single-piece flying vehicle 100 to fly. That is, when the integrated power unit 20 is in the first position, the single-piece flying vehicle 100 is in the flight mode, and the single-piece flying vehicle 100 can achieve the flight mode.

[0048] As Figure 1 shown, when the integrated power unit 20 is in the second position, the central axis of the integrated power unit 20 is parallel to the ground, the wheel assembly 21 is in contact with the ground, the ducted motor 221 can drive the wheel assembly 21 to rotate relative to the duct wall 223, and the wheel assembly 21 can roll on the ground to realize the ground walking mode of the single-piece flying vehicle 100.

[0049] The integrated power unit 20 is connected to the chassis frame 10 through the single-piece flying vehicle attitude adjustment device 30, and the single-piece flying vehicle attitude adjustment device 30 can rotate relative to the chassis frame 10, thereby driving the integrated power unit 20 to rotate relative to the chassis frame 10 to realize adjusting the position of the integrated power unit 20 through the single-piece flying vehicle attitude adjustment device 30, so as to switch the working mode of the single-piece flying vehicle 100.

[0050] Combined with Figure 1 、 Figure 2 and Figure 4 , the single-piece flying vehicle attitude adjustment device 30 includes: a conversion servo 31, the conversion servo 31 is arranged on the chassis frame 10; a landing gear steering shaft complex 32, the landing gear steering shaft complex 32 is connected to the integrated power unit 20, and the landing gear steering shaft complex 32 is connected to the driving part 311 of the conversion servo 31, and the driving part 311 can drive the landing gear steering shaft complex 32 to rotate around the first axis to adjust the position of the integrated power unit 20.

[0051] Specifically, the conversion servo 31 is installed on the chassis frame 10, and the conversion servo 31 is drivingly connected to the landing gear steering shaft complex 32. The conversion servo 31 can drive the landing gear steering shaft complex 32 to rotate about the first axis. The landing gear steering shaft complex 32 is connected to the integrated power unit 20, and the landing gear steering shaft complex 32 can drive the integrated power unit 20 to rotate about the first axis. The first axis is perpendicular to the central axis of the integrated power unit 20, so that the integrated power unit 20 can be switched between the first position and the second position, thereby enabling the single-body flying vehicle 100 to switch between the flight mode and the ground walking mode. There is no need to set up additional switching components, which is beneficial to simplifying the switching action when the single-body flying vehicle 100 switches modes and improving the efficiency of the single-body flying vehicle 100 when switching working modes.

[0052] According to the single-body flying vehicle attitude adjustment device 30 of the present utility model, by arranging the conversion servo 31 on the chassis frame 10 and connecting the landing gear steering shaft complex 32 to the conversion servo 31 and the integrated power unit 20 respectively, the conversion servo 31 can drive the integrated power unit 20 to rotate about the first axis through the landing gear steering shaft complex 32, so that the integrated power unit 20 can be switched between the first position and the second position, thereby switching the working mode of the single-body flying vehicle 100. And the switching action is simple, which is beneficial to improving the switching efficiency of the working mode of the single-body flying vehicle 100. Moreover, the structure of the single-body flying vehicle attitude adjustment device 30 is simple, which is beneficial to simplifying the structure of the single-body flying vehicle 100 and reducing the production and assembly cost of the single-body flying vehicle 100.

[0053] Combined with Figure 1 and Figure 3 , in some embodiments of the present utility model, the landing gear steering shaft complex 32 includes: a main body portion 321, the main body portion 321 is power-connected to the conversion servo 31; a connecting rod 322, one end of the connecting rod 322 is connected to the main body portion 321, and the connecting rod 322 extends along the first direction; a connecting seat 323, the connecting seat 323 is connected to the other end of the connecting rod 322, and the connecting seat 323 is used for connecting to the integrated power unit 20; wherein, the first direction is parallel to the first axis.

[0054] Specifically, the rotation center of the driving portion 311 of the conversion servo 31 is parallel and collinear with the first axis. The conversion servo 31 can drive the main body portion 321 to rotate about the first axis. The connecting rod 322 extends along a direction parallel to the first axis, and one end of the connecting rod 322 is connected to the main body portion 321. The connecting seat 323 is connected to the end of the connecting rod 322 far from the main body portion 321, and the connecting seat 323 is used for connecting to the integrated power unit 20.

[0055] When the conversion servo 31 works, the conversion servo 31 can drive the main body 321 to rotate around the first axis. The main body 321 drives the connecting rod 322 to rotate around the first axis, and the connecting rod 322 drives the connecting seat 323 to rotate around the first axis. Since the connecting seat 323 is connected to the integrated power device 20, the connecting seat 323 can drive the integrated power device 20 to rotate around the first axis, so as to switch the position of the integrated power device 20, thereby switching the working mode of the single-body flying vehicle 100.

[0056] Combined with Figure 1 、 Figure 3 and Figure 4 In some embodiments of the present invention, the connecting seat 323 is provided with an integrated power installation hole 3231. The integrated power installation hole 3231 penetrates through the connecting seat 323 along the second direction and is used for installing the integrated power device 20; wherein, the second direction is perpendicular to the first direction.

[0057] It should be noted that both the "first direction" and the "second direction" are directions defined based on the landing gear steering shaft complex 32. For a specific direction illustration, reference can be made to Figure 3 as shown.

[0058] Specifically, the integrated power installation hole 3231 is penetrated through the connecting seat 323, and the axial direction of the integrated power installation hole 3231 is perpendicular to the first direction (which can also be understood as the first axis). The integrated power device 20 is provided with a connecting shaft assembly 23. The central axis of the connecting shaft assembly 23 is perpendicular to the central axis of the integrated power device 20, and the central axis of the connecting shaft assembly 23 is parallel to the second direction. The connecting shaft assembly 23 passes through the integrated power installation hole 3231 and is connected to the connecting seat 323. When the conversion servo 31 drives the connecting seat 323 to rotate around the first axis through the main body 321 and the connecting rod 322, the connecting seat 323 can drive the connecting shaft assembly 23 to rotate around the first axis, so that the integrated power device 20 can rotate around the first axis, so as to adjust the position of the integrated power device 20, so that the integrated power device 20 can rotate around the first axis to a position where the central axis of the integrated power device 20 is parallel or perpendicular to the ground, thereby switching the working mode of the single-body flying vehicle 100.

[0059] Combined with Figure 1 and Figure 3 In some embodiments of the present invention, the connecting seat 323 is provided with a landing shaft installation hole 3232. The landing shaft installation hole 3232 penetrates through the connecting seat 323 along the first direction and is used for connecting with the chassis frame 10, so as to rotatably connect the connecting seat 323 to the chassis frame 10 around the first axis.

[0060] Specifically, a main takeoff and landing shaft rotating shaft 11 is provided on the chassis frame 10. The central axis of the main takeoff and landing shaft rotating shaft 11 is parallel and collinear with the first axis. The connecting seat 323 is rotatably connected to the main takeoff and landing shaft rotating shaft 11 through the takeoff and landing shaft mounting hole 3232, so that the connecting seat 323 can be rotatably connected to the chassis frame 10 around the first axis, which is beneficial to improving the connection reliability between the takeoff and landing frame steering shaft complex 32 and the chassis frame 10, and is also beneficial to improving the stability when the takeoff and landing frame steering shaft complex 32 rotates relative to the chassis frame 10.

[0061] It should be noted that the takeoff and landing shaft mounting hole 3232 and the integrated power mounting hole 3231 are arranged at intervals to avoid interference between the main takeoff and landing shaft rotating shaft 11 and the connecting shaft assembly 23, and facilitate the installation of the main takeoff and landing shaft rotating shaft 11 and the connecting shaft assembly 23.

[0062] Combined Figure 1 with Figure 3 , in some embodiments of the present invention, the takeoff and landing frame steering shaft complex 32 further includes an auxiliary rotating shaft connecting seat 324. The auxiliary rotating shaft connecting seat 324 is arranged in the middle of the connecting rod 322, and is formed with a takeoff and landing frame auxiliary rotating shaft hole 3241 whose central axis is collinear with the first axis, and the auxiliary rotating shaft connecting seat 324 is rotatably connected to the chassis frame 10 around the first axis.

[0063] Specifically, in the extending direction of the connecting rod 322, the auxiliary rotating shaft connecting seat 324 is arranged between the connecting seat 323 and the main body portion 321, and is located in the middle of the connecting rod 322. The auxiliary rotating shaft connecting seat 324 extends from the connecting rod 322 in a direction perpendicular to the first axis and towards the chassis frame 10, and one end of the auxiliary rotating shaft connecting seat 324 away from the connecting rod 322 is formed with a takeoff and landing frame auxiliary rotating shaft hole 3241. The central axis of the takeoff and landing frame auxiliary rotating shaft hole 3241 is parallel and collinear with the first axis.

[0064] Furthermore, a takeoff and landing frame auxiliary rotating shaft 12 is provided on the chassis frame 10. The central axis of the takeoff and landing frame auxiliary rotating shaft 12 is parallel and collinear with the first axis, and the takeoff and landing frame auxiliary rotating shaft 12 is arranged in the takeoff and landing frame auxiliary rotating shaft hole 3241, so that the auxiliary rotating shaft connecting seat 324 can be rotatably connected to the chassis frame 10 around the first axis to assist the rotation of the takeoff and landing frame steering shaft complex 32 relative to the chassis frame 10, which is beneficial to improving the rigidity of the rotational connection between the takeoff and landing frame steering shaft complex 32 and the chassis frame 10, and is also beneficial to preventing the takeoff and landing frame steering shaft complex 32 from twisting due to the excessive distance between the main body portion 321 and the connecting seat 323.

[0065] Combined Figures 1 to 4, in some embodiments of the present utility model, the landing gear steering shaft complex 32 is provided with two sets of connecting rods 322 and connecting seats 323, and the two sets of connecting rods 322 and connecting seats 323 are respectively arranged on both sides of the main body portion 321 in the first direction.

[0066] Specifically, one connecting rod 322 is respectively arranged on both sides of the main body portion 321 in the first direction. The connecting rod 322 extends away from the main body portion 321 in the first direction, and a connecting seat 323 is arranged at the end of each connecting rod 322 away from the main body portion 321. Each connecting seat 323 is used to connect an integrated power device 20. Thus, by enabling the landing gear steering shaft complex 32 to be respectively connected to the two integrated power devices 20, when the conversion servo 31 drives the landing gear steering shaft complex 32 to rotate around the first axis, the landing gear steering shaft complex 32 can simultaneously drive the two integrated power devices 20 to rotate around the first axis, which is beneficial to further simplify the structure of the single - body flying vehicle attitude adjustment device 30, and is also beneficial to simplify the switching action when the single - body flying vehicle attitude adjustment device 30 drives the integrated power device 20 to switch positions, improving the convenience of switching the position of the integrated power device 20.

[0067] Combined with Figure 3 and Figure 4 , in some embodiments of the present utility model, the single - body flying vehicle attitude adjustment device 30 further includes a servo landing gear 33. The servo landing gear 33 is power - connected to the driving portion 311 and is connected to the landing gear steering shaft complex 32 to drive the landing gear steering shaft complex 32 to rotate around the first axis.

[0068] Specifically, a servo disk 3112 is arranged on the output shaft 3111 of the conversion servo 31. The servo disk 3112 and the output shaft 3111 of the conversion servo 31 together constitute the driving portion 311. The servo landing gear 33 is power - connected to the driving portion 311. Specifically, the servo landing gear 33 is connected to the side of the servo disk 3112 away from the conversion servo 31 in the first direction. When the conversion servo 31 outputs power, the servo disk 3112 rotates around the first axis, and the servo disk 3112 can drive the servo landing gear 33 to rotate around the first axis. The servo landing gear 33 is connected to the landing gear steering shaft complex 32, and the servo landing gear 33 can drive the landing gear steering shaft complex 32 to rotate around the first axis, thereby realizing that the conversion servo 31 drives the landing gear steering shaft complex 32 to rotate around the first axis through the servo landing gear 33.

[0069] Among them, since the central axis of the integrated power unit 20 is perpendicular to the ground when in the first position and parallel to the ground when in the second position, the rotation angle of the integrated power unit 20 is 90°. The rotation angle of the output shaft 3111 of the conversion servo 31 is preferably 90°, which is beneficial to improving the accuracy of the integrated power unit 20 switching positions. In addition, by providing servo discs 3112 on both sides of the conversion servo 31, it is beneficial to ensure that the landing gear steering shaft complex 32 is evenly stressed.

[0070] Combined with Figure 3 and Figure 4 , in some embodiments of the present invention, the servo landing gear 33 includes: a first rotating arm 331 and a second rotating arm 332. The first rotating arm 331 and the second rotating arm 332 are oppositely arranged in a first direction, and the first rotating arm 331 and the second rotating arm 332 are respectively power-connected to two driving parts 311 on both sides of the conversion servo 31 in the first direction; a fixing plate (not shown), the fixing plate is connected between the first rotating arm 331 and the second rotating arm 332, and the fixing plate is arranged at an interval from the conversion servo 31 and is used for connecting with the main body part 321.

[0071] Specifically, the first rotating arm 331 and the second rotating arm 332 are opposite and spaced apart in the direction of extension of the first axis. Driving parts 311 are respectively arranged on both sides of the conversion servo 31 in the first direction. The first rotating arm 331 and the second rotating arm 332 are respectively connected to the two driving parts 311, so that the conversion servo 31 can drive the first rotating arm 331 and the second rotating arm 332 to rotate around the first axis at the same time.

[0072] Furthermore, the fixing plate is connected between the first rotating arm 331 and the second rotating arm 332, and both the first rotating arm 331 and the second rotating arm 332 extend away from the conversion servo 31 in a direction perpendicular to the first axis, that is, the servo landing gear 33 is configured as a U-shaped frame, so that the fixing plate is arranged at an interval from the conversion servo 31. During the process of the conversion servo 31 driving the servo landing gear 33 to rotate, the fixing plate and the conversion servo 31 can avoid each other to prevent interference between the servo landing gear 33 and the conversion servo 31 during the rotation of the servo landing gear 33, ensuring the rotation stroke of the servo landing gear 33, and thus being beneficial to ensuring the rotation stroke of the landing gear steering shaft complex 32.

[0073] Combined with Figure 3 and Figure 4, in some embodiments of the present utility model, the main body portion 321 includes: a first connecting plate 3211, the first connecting plate 3211 is provided on the side of the first rotating arm 331 away from the conversion servo 31 in the first direction and is connected to the first rotating arm 331; a second connecting plate 3212, the second connecting plate 3212 and the first connecting plate 3211 are oppositely arranged in the first direction, and the second connecting plate 3212 is provided on the side of the second rotating arm 332 away from the conversion servo 31 in the first direction and is connected to the second rotating arm 332; a third connecting plate 3213, the third connecting plate 3213 is connected between the first connecting plate 3211 and the second connecting plate 3212 and is used for fixedly connecting with the fixing plate.

[0074] Specifically, the main body portion 321 is configured as a U-shaped frame. Among them, the first connecting plate 3211 is connected to the side of the first rotating arm 331 away from the conversion servo 31, the second connecting plate 3212 is connected to the side of the second rotating arm 332 away from the conversion servo 31, and the third connecting plate 3213 is connected to the side of the fixing plate away from the conversion servo 31, so as to increase the connection area between the main body portion 321 and the servo landing gear 33, thereby improving the connection reliability between the main body portion 321 and the servo landing gear 33, which is beneficial to improving the driving effect of the conversion servo 31 on the landing gear steering shaft complex 32.

[0075] Furthermore, the two connecting rods 322 on both sides of the main body portion 321 are respectively connected to the first connecting plate 3211 and the second connecting plate 3212. In the direction perpendicular to the first axis, the connecting rod 322 connected to the first connecting plate 3211 is connected to the end of the first connecting plate 3211 away from the conversion servo 31, and the connecting rod 322 connected to the second connecting plate 3212 is connected to the end of the second connecting plate 3212 away from the conversion servo 31, and the connecting rod 322 is parallel and spaced from the first axis, which is beneficial to increasing the rotational force arm of the connecting rod 322 relative to the conversion servo 31, so as to facilitate the conversion servo 31 to drive the connecting rod 322 to rotate around the first axis.

[0076] Among them, hole structures are formed on both the third connecting plate 3213 and the fixing plate and penetrate in the direction perpendicular to the first axis. A connecting member (such as a screw, etc.) can pass through the hole structure to connect the third connecting plate 3213 with the fixing plate, so as to facilitate the positioning and installation of the servo landing gear 33 and the main body portion 321.

[0077] Combined Figure 1 、 Figure 3 and Figure 4 , in some embodiments of the present utility model, the single-body flying vehicle attitude adjustment device 30 further includes a servo fixing frame 34, and the servo fixing frame 34 is provided on the chassis frame 10 and is used for installing and fixing the conversion servo 31.

[0078] Specifically, the conversion servo 31 is installed on the servo fixing bracket 34, and the conversion servo 31 can be connected to the chassis frame 10 through the servo fixing bracket 34, so as to facilitate the positioning and installation of the conversion servo 31.

[0079] Optionally, the servo fixing bracket 34 can be integrally formed with the chassis frame 10, or the servo fixing bracket 34 can be separately provided and connected to the chassis frame 10. The specific arrangement of the servo fixing bracket 34 and the chassis frame 10 can be determined according to actual processing and production, and will not be specifically limited herein.

[0080] Combined with Figure 1 、 Figure 3 and Figure 4 In some embodiments of the present utility model, the servo fixing bracket 34 includes: a first fixing wall 341 and a second fixing wall 342, the first fixing wall 341 and the second fixing wall 342 are oppositely arranged and are respectively connected to both sides of the conversion servo 31; a connecting wall 343, the connecting wall 343 is connected between the first fixing wall 341 and the second fixing wall 342 and is used for fixedly connecting with the chassis frame 10.

[0081] Specifically, a fixing hole 3431 is provided on the connecting wall 343, the fixing hole 3431 penetrates through the connecting wall 343, and a threaded connector (such as a screw, a bolt, etc.) can pass through the fixing hole 3431 and fix the fixing wall on the chassis frame 10. The connecting wall 343 is respectively connected with the first fixing wall 341 and the second fixing wall 342 on both sides in the first direction. The first fixing wall 341 and the second fixing wall 342 are perpendicular to the connecting wall 343. The conversion servo 31 is arranged between the first fixing wall 341 and the second fixing wall 342. Servo mounting holes 344 are respectively formed on the first fixing wall 341 and the second fixing wall 342, and a threaded member (such as a screw, a bolt, etc.) can pass through the servo mounting holes 344 and connect the conversion servo 31 with the first fixing wall 341 and the second fixing wall 342.

[0082] Thus, the threaded connection between the servo fixing bracket 34 and the chassis frame 10 is realized, which is beneficial to improving the assembly convenience of the servo fixing bracket 34 and the chassis. At the same time, the threaded connection between the servo fixing bracket 34 and the conversion servo 31 improves the assembly convenience of the conversion servo 31 and the servo fixing bracket 34.

[0083] It should be noted that the first fixing wall 341 and the second fixing wall 342 are respectively arranged in a staggered manner with the two driving parts 311 of the conversion servo 31 to prevent the first fixing wall 341 and the second fixing wall 342 from interfering with the rotation of the driving parts 311.

[0084] The single - body flying vehicle 100 according to the present utility model includes the above - mentioned single - body flying vehicle attitude adjustment device 30.

[0085] Since the monolithic flying vehicle 100 is provided with the above-mentioned monolithic flying vehicle attitude adjustment device 30, by arranging a conversion servo 31 on the chassis frame 10 and connecting the landing gear steering shaft complex 32 to the conversion servo 31 and the integrated power device 20 respectively, the conversion servo 31 can drive the integrated power device 20 to rotate around the first axis through the landing gear steering shaft complex 32, so that the integrated power device 20 can be switched between the first position and the second position, thereby switching the working mode of the monolithic flying vehicle 100. And the switching action is simple, which is beneficial to improving the switching efficiency of the working mode of the monolithic flying vehicle 100. Moreover, the structure of the monolithic flying vehicle attitude adjustment device 30 is simple, which is beneficial to simplifying the structure of the monolithic flying vehicle 100 and reducing the production and assembly cost of the monolithic flying vehicle 100.

[0086] Referring to Figure 1 , in some embodiments of the present invention, the monolithic flying vehicle 100 further includes a steering servo 40, and the steering servo 40 is arranged at one end of the connecting shaft assembly 23 away from the integrated power device 20. The steering servo 40 can drive the connecting shaft assembly 23 to drive the integrated power device 20 to rotate around the second axis, and the second axis is the central axis of the connecting shaft assembly 23.

[0087] Specifically, the output end of the steering servo 40 is connected to one end of the connecting shaft assembly 23 away from the integrated power device 20, and the second axis is collinearly arranged with the rotation central axis of the output end of the steering servo 40. When the monolithic flying vehicle 100 is in the ground walking mode, the wheel assembly 21 is in contact with the ground, and the wheel assembly 21 can roll on the ground. The steering servo 40 can drive the connecting shaft assembly 23 to rotate around the second axis in the integrated power installation hole 3231, and the connecting shaft assembly 23 drives the integrated power device 20 to rotate around the second axis to adjust the included angle between the central axis of the integrated power device 20 and the second axis, so as to realize adjusting the steering angle of the integrated power device 20 on the ground, and further realize adjusting the steering angle of the monolithic flying vehicle 100 in the ground walking mode.

[0088] In the description of this specification, the description of reference terms such as "one embodiment", "some embodiments", "schematic embodiments", "examples", "specific examples", or "some examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions 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 a suitable manner in any one or more embodiments or examples.

[0089] Although embodiments of the present utility model have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present utility model. The scope of the present utility model is defined by the claims and their equivalents.

Claims

1. A single-body flying car attitude adjustment device, characterized in that: The single-body flying car attitude adjustment device is connected between an integrated power device (20) and a chassis frame (10) in driving the single-body flying car, and is used to drive the integrated power device (20) to switch between a first position suitable for driving the single-body flying car to fly and a second position suitable for driving the single-body flying car to walk on the ground. The single-body flying car attitude adjustment device comprises: A conversion steering gear (31), wherein the conversion steering gear (31) is arranged on the chassis frame (10); A landing gear steering shaft complex (32), wherein the landing gear steering shaft complex (32) is connected to the integrated power device (20), and the landing gear steering shaft complex (32) is connected to a driving unit (311) of the conversion steering gear (31), and the driving unit (311) can drive the landing gear steering shaft complex (32) to rotate around a first axis to adjust the position of the integrated power device (20).

2. The single-body flying car attitude adjustment device according to claim 1, characterized in that: The landing gear steering shaft complex (32) comprises: A main body (321), the main body (321) being dynamically connected to the conversion steering engine (31); A connecting rod (322), one end of which is connected to the main body (321), and the connecting rod (322) extends along a first direction; A connecting seat (323), the connecting seat (323) being connected to the other end of the connecting rod (322), and the connecting seat (323) being used to be connected to the integrated power device (20); Wherein, the first direction is arranged parallel to the first axis.

3. The single-body flying car attitude adjustment device according to claim 2, characterized in that: The connecting seat (323) is provided with an integrated power installation hole (3231), the integrated power installation hole (3231) penetrates the connecting seat (323) along the second direction, and is used for installing the integrated power device (20); Wherein, the second direction is arranged perpendicular to the first direction.

4. The single-body flying car attitude adjustment device according to claim 2, characterized in that: The connecting seat (323) is provided with a lifting and lowering shaft mounting hole (3232), and the lifting and lowering shaft mounting hole (3232) is arranged to pass through the connecting seat (323) along the first direction and is used to be connected to the chassis frame (10) so as to rotatably connect the connecting seat (323) to the chassis frame (10) around the first axis.

5. The single-body flying car attitude adjustment device according to claim 2, characterized in that: The landing gear steering shaft complex (32) also includes an auxiliary shaft-winding connection seat (324), which is arranged in the middle of the connecting rod (322) and forms a landing gear auxiliary shaft-winding hole (3241) whose central axis is arranged colinearly with the first axis, and the auxiliary shaft-winding connection seat (324) is rotatably connected to the chassis frame (10) around the first axis.

6. The single-body flying car attitude adjustment device according to any one of claims 2 to 5, characterized in that: The landing gear steering shaft complex (32) is provided with two groups of connecting rods (322) and connecting seats (323), and the two groups of connecting rods (322) and connecting seats (323) are respectively arranged on both sides of the main body (321) in the first direction.

7. The single-body flying car attitude adjustment device according to claim 2, characterized in that: It also includes a steering gear landing gear (33), wherein the steering gear landing gear (33) is connected to the driving unit (311) by power, and is connected to the landing gear steering shaft complex (32) to drive the landing gear steering shaft complex (32) to rotate around the first axis.

8. The single-body flying car attitude adjustment device according to claim 7, characterized in that: The steering gear landing gear (33) comprises: A first rotating arm (331) and a second rotating arm (332), wherein the first rotating arm (331) and the second rotating arm (332) are arranged opposite to each other in the first direction, and the first rotating arm (331) and the second rotating arm (332) are respectively connected to two driving parts (311) on both sides of the conversion steering gear (31) in the first direction by power; A fixing plate is connected between the first rotating arm (331) and the second rotating arm (332), and the fixing plate is arranged at intervals from the conversion steering gear (31) and is used to be connected to the main body (321).

9. The single-body flying car attitude adjustment device according to claim 8, characterized in that: The main body (321) comprises: a first connecting plate (3211), the first connecting plate (3211) being arranged on a side of the first rotating arm (331) away from the conversion steering gear (31) in a first direction, and being connected to the first rotating arm (331); a second connecting plate (3212), the second connecting plate (3212) and the first connecting plate (3211) being arranged opposite to each other in the first direction, and the second connecting plate (3212) being arranged on a side of the second rotating arm (332) away from the conversion steering gear (31) in the first direction, and being connected to the second rotating arm (332); A third connecting plate (3213), the third connecting plate (3213) is connected between the first connecting plate (3211) and the second connecting plate (3212), and is used to be fixedly connected to the fixing plate.

10. The single-body flying car attitude adjustment device according to claim 1, characterized in that: It also includes a steering gear fixing frame (34), which is arranged on the chassis frame (10) and is used to install and fix the conversion steering gear (31).

11. The single-body flying car attitude adjustment device according to claim 10, characterized in that: The steering gear fixing frame (34) comprises: A first fixed wall (341) and a second fixed wall (342), wherein the first fixed wall (341) and the second fixed wall (342) are arranged opposite to each other and are respectively connected to two sides of the conversion steering gear (31); A connecting wall (343), the connecting wall (343) is connected between the first fixed wall (341) and the second fixed wall (342), and is used for being fixedly connected to the chassis frame (10).

12. A single-body flying car, characterized in that: It comprises a single-body flying car attitude adjustment device according to any one of claims 1-11.

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