Aircraft assembly, aircraft assembly and automobile

Abstract

The utility model provides an aircraft assembly, an aircraft assembly and an automobile. The aircraft assembly comprises a fixed arm, a folding arm and a rotating blade, the first end of the fixed arm is used for being mounted on a to-be-flied structure; the first end of the folding arm is rotatably mounted at the second end of the fixed arm around a first axial direction; the rotating blade is rotatably installed at the second end of the folding arm in the second axial direction, and the second axial direction is perpendicular to the folding arm. According to the aircraft assembly, the overall structure is simple, the applicability is good, a to-be-flying structure does not need to be greatly changed subversively, parts of the aircraft assembly are universal parts, and the cost of the aircraft assembly is effectively reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft components, in particular to an aircraft component, an aircraft assembly and a car. Background Art

[0002] At present, aircraft components are used in many flight structures, but the existing aircraft components are complex in structure and poor in applicability, and need to make subversive modifications to the flight structure. For example, when adding aircraft components to cars, the most valuable passenger space of the car is sacrificed. In order to meet the layout of the aircraft, the original conventional 5-seater car can only provide 2 or only 1 person for the arrangement of aircraft components, thus losing the meaning of the car as a convenient passenger. In addition, in order to arrange the complex aircraft components, the exterior shape makes a greater compromise, resulting in a bloated car and low internal space utilization. Utility Model Content

[0003] The utility model provides an aircraft component, an aircraft assembly and a car, so as to solve the problems that the existing aircraft components have complex structures, poor applicability and need to make subversive modifications to the flight structure.

[0004] An aircraft assembly includes a fixed arm, a folding arm, and a rotating blade;

[0005] The first end of the fixed arm is used to be mounted on the structure to be flown;

[0006] The first end of the folding arm is rotatably mounted on the second end of the fixed arm around a first axial direction;

[0007] The rotating blade is rotatably mounted on the second end of the folding arm about a second axial direction, and the second axial direction is perpendicular to the folding arm.

[0008] Preferably, the aircraft assembly further comprises an adapter assembly, and the adapter assembly comprises an adapter shaft and an adapter sleeve that cooperate with each other;

[0009] The adapter sleeve is arranged at the second end of the fixed arm, and the adapter shaft is arranged at the first end of the folding arm;

[0010] Alternatively, the adapter sleeve is arranged at the first end of the folding arm, and the adapter shaft is arranged at the second end of the fixed arm.

[0011] Preferably, the adapter sleeve comprises two oppositely arranged snap rings;

[0012] The two clamping rings are arranged on the second end of the fixed arm along the first axial direction, and the adapter shaft arranged on the first end of the folding arm passes through the two clamping rings;

[0013] Alternatively, the two clamping rings are arranged on the first end of the folding arm along the first axial direction, and the adapter shaft arranged on the second end of the fixed arm passes through the two clamping rings.

[0014] Preferably, the folding arm comprises a supporting body and a fulcrum extending from a second end of the supporting body in a direction perpendicular to the supporting body;

[0015] The first end of the support body is rotatably mounted on the second end of the fixed arm about a first axial direction;

[0016] The rotary blade is rotatably mounted on the support shaft around a second axial direction.

[0017] Preferably, the number of the rotating blades is at least two, and at least two of the rotating blades are rotatably mounted on the support shaft in sequence.

[0018] An aircraft assembly comprises the aircraft component and a control component; the control component is respectively connected to the folding arm and the rotating blade of the aircraft component and is used for controlling the rotation of the folding arm and the rotating blade.

[0019] Preferably, when the folding arm is perpendicular to the fixed arm and the rotating blade is arranged overlapping with the folding arm, the aircraft assembly is in a folded state;

[0020] When the folding arm and the fixed arm are in the same straight line direction and the rotating blade is arranged above or below the second end of the folding arm, the aircraft assembly is in an unfolded state.

[0021] A car comprises a car body and the above-mentioned aircraft assembly; the car body is the structure to be flown.

[0022] Preferably, the number of the aircraft assemblies is four, the automobile body comprises four wheels, and a receiving groove opening outward is provided at the center of the wheel hub of each wheel;

[0023] The automobile comprises four aircraft assemblies, and the first end of the fixing arm in each of the aircraft assemblies is installed in the accommodating groove.

[0024] Preferably, when the folding arms in the aircraft assembly remain parallel to the side surfaces in the front-rear direction of the vehicle body, the aircraft assembly is in a folded state;

[0025] When the folding arm in the aircraft assembly is perpendicular to the front and rear sides of the vehicle body, the aircraft assembly is in an unfolded state.

[0026] The aircraft assembly provided by the embodiment of the utility model includes a fixed arm, a folding arm and a rotating blade; the first end of the fixed arm is mounted on the structure to be flown, and then the first end of the folding arm is rotatably mounted on the second end of the fixed arm around the first axial direction, and finally the rotating blade is rotatably mounted on the second end of the folding arm around the second axial direction. In this example, when the aircraft assembly is not in use, the folding arm is controlled to rotate so that the folding arm and the fixed arm are perpendicular to each other, the folding arm is in a folded state, and the rotating blade is overlapped with the folding arm, and the rotating blade is in a folded state. At this time, the aircraft assembly is in a folded state; when the aircraft assembly is in use, the folding arm is controlled to rotate so that the folding arm and the fixed arm are kept in the same straight line direction, and the folding arm is in an unfolded state; the rotating blade is controlled to rotate so that the rotating blade is evenly distributed above or below the second end of the folding arm with the second axial direction as a reference, and the rotating blade is in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the rotating blade is controlled to rotate continuously, so that the flight with the structure to be flown can be realized. The second axial direction is perpendicular to the folding arm, and such a setting can ensure that the rotating blade can rotate around the second end of the folding arm while avoiding interference between the rotating blade and the folding arm. The aircraft assembly in this example has a simple overall structure and good applicability. There is no need to make major disruptive changes to the flight structure, and the parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments of the utility model will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0028] Figure 1 This is an exploded view of an aircraft assembly in an embodiment of the utility model.

[0029] Figure 2 It is a schematic diagram of a folding arm in a folded state in one embodiment of the utility model;

[0030] Figure 3 It is a schematic diagram of a vehicle door in a normal opening state with the folding arm in an embodiment of the utility model;

[0031] Figure 4 It is a schematic diagram of a folding arm in an expanded state in one embodiment of the utility model;

[0032] Figure 5 It is a schematic diagram of the rotary blades in an expanded state in one embodiment of the utility model.

[0033] Among them, 1. fixed arm; 2. folding arm; 21. supporting body; 22. support shaft; 3. rotating blade; 4. adapter assembly; 41. adapter shaft; 42. adapter sleeve; 5. automobile body. DETAILED DESCRIPTION

[0034] In order to make the technical problems, technical solutions and beneficial effects solved by the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0035] In the description of the present invention, it should be understood that the terms "longitudinal", "radial", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention 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, and therefore cannot be understood as a limitation on the present invention. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0036] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" 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 or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0037] The utility model embodiment provides an aircraft component, referring to Figure 1-5 The aircraft assembly includes a fixed arm 1, a folding arm 2 and a rotating blade 3; the first end of the fixed arm 1 is used to be installed on the structure to be flown; the first end of the folding arm 2 is rotatably installed on the second end of the fixed arm 1 around a first axial direction; the rotating blade 3 is rotatably installed on the second end of the folding arm 2 around a second axial direction, and the second axial direction is perpendicular to the folding arm 2.

[0038] The first axial direction and the second axial direction are two axial directions perpendicular to each other, and the axial direction here can be understood as the axis direction of the rotating structure. For example, the first axial direction is the front-to-back direction of the car, and the second axial direction is the up-down direction of the car.

[0039] As an example, the aircraft assembly includes a fixed arm 1, a folding arm 2 and a rotating blade 3; the first end of the fixed arm 1 is mounted on the structure to be flown, and then the first end of the folding arm 2 is rotatably mounted on the second end of the fixed arm 1 around the first axial direction, and finally the rotating blade 3 is rotatably mounted on the second end of the folding arm 2 around the second axial direction. In this example, when the aircraft assembly is not in use, the folding arm 2 is controlled to rotate so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, the folding arm 2 is in a folded state, and the rotating blade 3 is overlapped with the folding arm 2, and the rotating blade 3 is in a folded state. At this time, the aircraft assembly is in a folded state; when the aircraft assembly is in use, the folding arm 2 is controlled to rotate so that the folding arm 2 and the fixed arm 1 are kept in the same straight line direction, and the folding arm 2 is in an unfolded state; the rotating blade 3 is controlled to rotate so that the rotating blade 3 is evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blade 3 is in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the rotating blade 3 is controlled to rotate continuously, so that the flight with the structure to be flown can be realized. The second axial direction is perpendicular to the folding arm 2, and such a setting can ensure that the rotating blade 3 can rotate around the second end of the folding arm 2 while avoiding interference between the rotating blade 3 and the folding arm 2. The overall structure of the aircraft assembly in this example is simple and has good applicability. There is no need to make a subversive major change to the flight structure, and the parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly.

[0040] For example, the structure to be flown is a car, and the first end of the fixed arm 1 of the aircraft assembly is installed on the car. When the car is driving, the folding arm 2 is controlled to rotate so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, and the folding arm 2 is in a folded state; and the rotating blades 3 are overlapped with the folding arm 2, and the rotating blades 3 are in a folded state. At this time, the aircraft assembly is in a folded state and does not affect the normal driving of the car. When encountering traffic congestion and the car cannot drive normally, the car can find a safe position, control the folding arm 2 to rotate, and keep the folding arm 2 and the fixed arm 1 in the same straight line direction, and the folding arm 2 is in an unfolded state; control the rotating blades 3 to rotate, so that the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blades 3 are in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the rotating blades 3 are controlled to rotate continuously, so that flying with the car can be realized.

[0041] The aircraft assembly in this embodiment has a reasonable structural arrangement, which is not only simple in structure and has good applicability, but also does not require excessive modifications to the existing exterior shape of the car; the parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly; and when in a folded state, it does not need to be hidden in the car body, does not need to occupy the limited car body space, and can meet the normal internal passenger space of the car.

[0042] In one embodiment, referring to Figure 1 The aircraft assembly also includes an adapter assembly 4, which includes an adapter shaft 41 and an adapter sleeve 42 that cooperate with each other; the adapter sleeve 42 is arranged at the second end of the fixed arm 1, and the adapter shaft 41 is arranged at the first end of the folding arm 2; or, the adapter sleeve 42 is arranged at the first end of the folding arm 2, and the adapter shaft 41 is arranged at the second end of the fixed arm 1.

[0043] As an example, the aircraft assembly also includes an adapter assembly 4, which includes an adapter shaft 41 and an adapter sleeve 42 that cooperate with each other; the adapter assembly 4 is used to rotatably mount the first end of the folding arm 2 on the second end of the fixed arm 1, and there are two schemes for setting the adapter assembly 4. The first scheme: the adapter sleeve 42 is set at the second end of the fixed arm 1, the adapter shaft 41 is set at the first end of the folding arm 2, and the adapter shaft 41 is installed in the adapter sleeve 42, which can drive the folding arm 2 to rotate around the adapter shaft 41, so as to achieve a mutually perpendicular state with the fixed arm 1 or keep it on the same straight line, so as to switch the working state of the aircraft assembly.

[0044] The second solution is to set the adapter sleeve 42 at the first end of the folding arm 2 and the adapter shaft 41 at the second end of the fixed arm 1 , which can also achieve the above functions and will not be described in detail.

[0045] In one embodiment, referring to Figure 1 The adapter sleeve 42 includes two oppositely arranged snap rings; the two snap rings are arranged at the second end of the fixed arm 1 along the first axial direction, and the adapter shaft 41 arranged on the first end of the folding arm 2 passes through the two snap rings;

[0046] Alternatively, two clamping rings are arranged on the first end of the folding arm 2 along the first axial direction, and the adapter shaft 41 arranged on the second end of the fixed arm 1 passes through the two clamping rings.

[0047] As an example, the adapter sleeve 42 includes two oppositely arranged snap rings; the two snap rings can be arranged on both sides of the second end of the fixed arm 1 along the first axial direction, and the adapter shaft 41 arranged on the first end of the folding arm 2 is passed through the two snap rings. This arrangement facilitates the installation and disassembly of the adapter shaft 41 and the adapter sleeve 42, so as to install and disassemble the folding arm 2.

[0048] Alternatively, two clamping rings are arranged on both sides of the first end of the folding arm 2 along the first axial direction, and the adapter shaft 41 arranged on the second end of the fixed arm 1 passes through the two clamping rings, which can also achieve the above function.

[0049] In one embodiment, referring to Figure 1The folding arm 2 includes a supporting body 21 and a support shaft 22 extending from the second end of the supporting body 21 in a direction perpendicular to the supporting body 21; the first end of the supporting body 21 is rotatably mounted on the second end of the fixed arm 1 around a first axial direction; the rotating blade 3 is rotatably mounted on the support shaft 22 around a second axial direction.

[0050] As an example, the folding arm 2 includes a supporting body 21 and a support shaft 22. During installation, the first end of the supporting body 21 is rotatably mounted on the second end of the fixed arm 1 around a first axial direction. The support shaft 22 extends from the second end of the supporting body 21 in a direction perpendicular to the supporting body 21. The rotating blade 3 is rotatably mounted on the support shaft 22 around a second axial direction. This can prevent the rotating blade 3 from interfering with the folding arm 2 while ensuring that the rotating blade 3 can rotate around the second end of the folding arm 2.

[0051] In one embodiment, referring to Figure 1 and Figure 5 The number of the rotating blades 3 is at least two, and at least two rotating blades 3 are rotatably mounted on the support shaft 22 in sequence.

[0052] As an example, the number of the rotating blades 3 is at least two, and at least two rotating blades 3 are rotatably mounted on the support shaft 22 in sequence. This arrangement can ensure that the rotating blades 3 generate balanced power to enable the aircraft assembly to fly.

[0053] The utility model embodiment provides an aircraft assembly, referring to Figure 1-5 , including an aircraft component and a control component; the control component is respectively connected to the folding arm 2 and the rotating blade 3 of the aircraft component, and is used to control the rotation of the folding arm 2 and the rotating blade 3.

[0054] As an example, the aircraft assembly includes an aircraft component and a control component, and the aircraft component includes a fixed arm 1, a folding arm 2 and a rotating blade 3; the first end of the fixed arm 1 is mounted on the structure to be flown, and then the first end of the folding arm 2 is rotatably mounted on the second end of the fixed arm 1 around a first axial direction, and finally the rotating blade 3 is rotatably mounted on the second end of the folding arm 2 around a second axial direction, and the control component is respectively connected to the folding arm 2 and the rotating blade 3, and is used to control the rotation of the folding arm 2 and the rotating blade 3. Specifically, the control component includes a first motor, a second motor and a controller, and the first motor is set at the first end of the fixed arm 1 and connected to the second end of the folding arm 2, and the first motor is controlled to work by the controller, thereby driving the folding arm 2 to rotate; the second motor is set at the second end of the folding arm 2 and connected to the rotating blade 3, and the second motor is controlled to work by the controller, thereby driving the rotating blade 3 to rotate. When the aircraft assembly is not in use, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, and the folding arm 2 is in a folded state; and the rotating blades 3 are overlapped with the folding arm 2, and the rotating blades 3 are in a folded state. At this time, the aircraft assembly is in a folded state. When the aircraft assembly is in use, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are kept in the same straight line direction, and the folding arm 2 is in an unfolded state; the control component controls the rotating blades 3 to rotate, so that the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blades 3 are in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the control component controls the rotating blades 3 to rotate continuously, so that the flight with the structure to be flown can be realized. The second axial direction is perpendicular to the folding arm 2. Such a setting can ensure that the rotating blades 3 can rotate around the second end of the folding arm 2 while avoiding interference between the rotating blades 3 and the folding arm 2. The aircraft assembly in this example has a simple structure and good applicability. There is no need to make a subversive major change to the structure to be flown, and the parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly.

[0055] For example, the structure to be flown is a car, and the first end of the fixed arm 1 of the aircraft assembly is installed on the car. When the car is driving, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, and the folding arm 2 is in a folded state; and the rotating blades 3 are overlapped with the folding arm 2, and the rotating blades 3 are in a folded state. At this time, the aircraft assembly is in a folded state and does not affect the normal driving of the car. When encountering traffic congestion and the car cannot drive normally, the car can find a safe position, and the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are kept in the same straight line direction, and the folding arm 2 is in an unfolded state; the control component controls the rotating blades 3 to rotate, so that the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blades 3 are in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the control component controls the rotating blades 3 to rotate continuously, so that flying with the car can be realized.

[0056] The aircraft assembly in this embodiment has a reasonable structural arrangement, which is not only simple in structure and has good applicability, but also does not require excessive modifications to the existing exterior shape of the car; the parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly; and when in a folded state, it does not need to be hidden in the car body, does not need to occupy the limited car body space, and can meet the normal internal passenger space of the car.

[0057] In one embodiment, referring to Figure 2 and Figure 4 When the folding arm 2 is perpendicular to the fixed arm 1 and the rotating blade 3 overlaps with the folding arm 2, the aircraft assembly is in a folded state; when the folding arm 2 and the fixed arm 1 are in the same straight line direction and the rotating blade 3 is arranged above or below the second end of the folding arm 2, the aircraft assembly is in an unfolded state.

[0058] As an example, when the aircraft assembly is not in use, the folding arm 2 is perpendicular to the fixed arm 1, the rotating blades 3 are arranged overlapping the folding arm 2, and the aircraft assembly is in a folded state. When the aircraft assembly is in use, the folding arm 2 and the fixed arm 1 are in the same straight line direction, the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, the aircraft assembly is in an unfolded state, and the rotating blades 3 are controlled to rotate continuously, so that the structure to be flown can be flown.

[0059] The utility model embodiment provides a car, referring to Figure 1-5 , including a car body 5 and an aircraft assembly; the car body 5 is a structure to be flown.

[0060] As an example, a car includes a car body 5 and an aircraft assembly; the aircraft assembly includes an aircraft component and a control component, and the aircraft component includes a fixed arm 1, a folding arm 2, and a rotating blade 3; the first end of the fixed arm 1 is mounted on the car body 5, and then the first end of the folding arm 2 is rotatably mounted on the second end of the fixed arm 1 around a first axial direction, and finally the rotating blade 3 is rotatably mounted on the second end of the folding arm 2 around a second axial direction, and the control component is respectively connected to the folding arm 2 and the rotating blade 3, and is used to control the rotation of the folding arm 2 and the rotating blade 3. Specifically, the control component includes a first motor, a second motor, and a controller, and the first motor is set at the first end of the fixed arm 1 and connected to the second end of the folding arm 2, and the first motor is controlled to work by the controller, thereby driving the folding arm 2 to rotate; the second motor is set at the second end of the folding arm 2 and connected to the rotating blade 3, and the second motor is controlled to work by the controller, thereby driving the rotating blade 3 to rotate. When the aircraft assembly is not in use, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, and the folding arm 2 is in a folded state; and the rotating blades 3 are overlapped with the folding arm 2, and the rotating blades 3 are in a folded state. At this time, the aircraft assembly is in a folded state. When the aircraft assembly is in use, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are kept in the same straight line direction, and the folding arm 2 is in an unfolded state; the control component controls the rotating blades 3 to rotate, so that the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blades 3 are in an unfolded state. At this time, the aircraft assembly is in an unfolded state, and the control component controls the rotating blades 3 to rotate continuously, so that the vehicle body 5 can be flown. The second axial direction is perpendicular to the folding arm 2, and such a setting can ensure that the rotating blades 3 can rotate around the second end of the folding arm 2 while avoiding interference between the rotating blades 3 and the folding arm 2.

[0061] The aircraft assembly in this embodiment has a reasonable structural arrangement, and is not only simple in structure and has good applicability, but also does not require excessive modifications to the existing exterior shape of the car. The parts of the aircraft assembly are universal parts, which effectively reduces the cost of the aircraft assembly. Moreover, when in a folded state, it does not need to be hidden in the car body and does not need to occupy the limited car body space, and can meet the normal internal passenger space of the car. At the same time, the folded aircraft assembly does not affect the normal opening and closing of the front and rear doors.

[0062] In one embodiment, referring to Figure 2-5 The automobile body 5 includes four wheels; a receiving groove with an opening facing outward is provided at the center of the wheel hub of each wheel; the number of the aircraft assemblies is four, and the first end of the fixed arm 1 in each aircraft assembly is installed in the receiving groove.

[0063] As an example, the automobile body 5 includes four wheels; a receiving groove with an opening facing outward is provided at the center of the wheel hub of each wheel; the number of aircraft assemblies is four, and the first end of the fixed arm 1 in each aircraft assembly is installed in the receiving groove, which can ensure that the aircraft assembly will not rotate with the rotation of the wheel.

[0064] When the car is driving, the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are perpendicular to each other, and the folding arm 2 is in a folded state; and the rotating blades 3 are overlapped with the folding arm 2, and the rotating blades 3 are in a folded state. At this time, the aircraft component is in a folded state, which does not affect the normal driving of the car. When encountering traffic congestion and the car cannot drive normally, the car can find a safe position, and the control component controls the folding arm 2 to rotate, so that the folding arm 2 and the fixed arm 1 are kept in the same straight line direction, and the folding arm 2 is in an unfolded state; the control component controls the rotating blades 3 to rotate, so that the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction, and the rotating blades 3 are in an unfolded state. At this time, the aircraft component is in an unfolded state, and the control component controls the rotating blades 3 to rotate continuously, so that flying with the car can be realized.

[0065] In one embodiment, referring to Figure 2-5 When the folding arm 2 in the aircraft assembly is parallel to the side of the front and rear direction of the automobile body 5, the aircraft assembly is in a folded state; when the folding arm 2 in the aircraft assembly is perpendicular to the side of the front and rear direction of the automobile body 5, the aircraft assembly is in an unfolded state.

[0066] As an example, when the aircraft assembly is not in use, the folding arm 2 is perpendicular to the fixed arm 1, the rotating blades 3 are arranged overlapping the folding arm 2, and when the folding arm 2 in the aircraft assembly is parallel to the side of the front and rear direction of the automobile body 5, the aircraft assembly is in a folded state. When the aircraft assembly is in use, the folding arm 2 and the fixed arm 1 are in the same straight line direction, and the rotating blades 3 are evenly distributed above or below the second end of the folding arm 2 based on the second axial direction. When the folding arm 2 in the aircraft assembly is perpendicular to the side of the front and rear direction of the automobile body 5, the aircraft assembly is in an unfolded state, and the rotating blades 3 are controlled to rotate continuously, so that the structure to be flown can be flown.

[0067] The embodiments described above are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. An aircraft component, characterized in that: It includes a fixed arm, a folding arm and a rotating blade; The first end of the fixed arm is used to be mounted on the structure to be flown; The first end of the folding arm is rotatably mounted on the second end of the fixed arm around a first axial direction; The rotating blade is rotatably mounted on the second end of the folding arm about a second axial direction, and the second axial direction is perpendicular to the folding arm.

2. The aircraft assembly according to claim 1, characterized in that The aircraft assembly further comprises an adapter assembly, wherein the adapter assembly comprises an adapter shaft and an adapter sleeve that cooperate with each other; The adapter sleeve is arranged at the second end of the fixed arm, and the adapter shaft is arranged at the first end of the folding arm; Alternatively, the adapter sleeve is arranged at the first end of the folding arm, and the adapter shaft is arranged at the second end of the fixed arm.

3. The aircraft assembly according to claim 2, characterized in that: The adapter sleeve includes two clamping rings arranged opposite to each other; The two clamping rings are arranged on the second end of the fixed arm along the first axial direction, and the adapter shaft arranged on the first end of the folding arm passes through the two clamping rings; Alternatively, the two clamping rings are arranged on the first end of the folding arm along the first axial direction, and the adapter shaft arranged on the second end of the fixed arm passes through the two clamping rings.

4. The aircraft assembly according to claim 1, characterized in that: The folding arm comprises a supporting body and a fulcrum extending from a second end of the supporting body in a direction perpendicular to the supporting body; The first end of the support body is rotatably mounted on the second end of the fixed arm about a first axial direction; The rotary blade is rotatably mounted on the support shaft around a second axial direction.

5. The aircraft assembly according to claim 4, characterized in that The number of the rotating blades is at least two, and at least two of the rotating blades are rotatably mounted on the support shaft in sequence.

6. An aircraft assembly, characterized in that: It comprises the aircraft component and control component according to any one of claims 1 to 5; the control component is respectively connected to the folding arm and the rotating blade of the aircraft component, and is used to control the rotation of the folding arm and the rotating blade.

7. The aircraft assembly according to claim 6, characterized in that: When the folding arm is perpendicular to the fixed arm and the rotating blade is arranged overlapping with the folding arm, the aircraft assembly is in a folded state; When the folding arm and the fixed arm are in the same straight line direction and the rotating blade is arranged above or below the second end of the folding arm, the aircraft assembly is in an unfolded state.

8. A car, characterized in that: It comprises a car body and the aircraft assembly as described in any one of claims 6-7; the car body is the structure to be flown.

9. The automobile according to claim 8, characterized in that: The number of the aircraft assemblies is four, the vehicle body includes four wheels, and a receiving groove with an opening facing outward is provided at the center of the wheel hub of each wheel; The automobile comprises four aircraft assemblies, and the first end of the fixing arm in each of the aircraft assemblies is installed in the accommodating groove.

10. The automobile according to claim 9, characterized in that: When the folding arms in the aircraft assembly remain parallel to the side surfaces in the front-rear direction of the vehicle body, the aircraft assembly is in a folded state; When the folding arms in the aircraft assembly are perpendicular to the side surfaces in the front-rear direction of the automobile body, the aircraft assembly is in an unfolded state.

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