Four-shaft eight-propeller rotor wing folding mechanism for hovercar

Abstract

The invention provides a four-shaft eight-propeller rotor wing folding mechanism suitable for a hovercar. The four-axis eight-propeller rotor wing structure is characterized in that the four-axis eight-propeller rotor wing structure comprises foldable supporting arms and march-up blades, the blades and the supporting arms are sequentially folded step by step through control driving, a limiting structure is designed to assist a control system in precise folding, and finally environment-friendly folding of the large-size four-axis eight-propeller rotor wing structure is achieved. Through the design of a paddle protection layer and the design of a mechanism protection device, multi-protection and storage of the rotor wing folding mechanism in a parking state on the ground are realized step by step. Based on the method, precise and efficient small folding and comprehensive protection design of the four-axis eight-propeller rotor wing mechanism can be achieved, and the problems that a traditional hovercar rotor wing mechanism is large in occupied area and low in safety are effectively solved. The four-axis eight-propeller rotor wing folding mechanism has the advantages of being easy, convenient and rapid to operate, ingenious in folding design, high in folding efficiency and precision, comprehensive in protection and the like, and can be widely applied to design of the four-axis eight-propeller rotor wing folding mechanism of the hovercar.

Description

Technical Field

[0001] The present invention belongs to the technical field of rotorcraft design, and specifically relates to the efficient folding and protection of the rotors of a four-rotor flying car, and in particular to a four-axis eight-blade rotor folding mechanism suitable for a flying car. Background Art

[0002] Flying cars offer a new mode of transportation for modern and future transportation, combining both aerial and ground travel, effectively alleviating traffic congestion. Flying cars primarily rely on multi-rotor mechanisms for aerial flight. Vertical takeoff and landing (VTOL) require large, high-speed propellers to generate lift. Therefore, a refined rotor design is crucial for the safety, reliability, and overall space efficiency of a flying car. Current flying cars often utilize a quad-rotor mechanism, including propellers, drive motors, and support rods. Due to the high takeoff weight of manned flying cars, multiple large propeller blades are required to generate lift. These large propeller blades and support rods make them larger than the vehicle's body when deployed, resulting in inefficient space utilization. The propeller blades are easily damaged by bumps and knocks, severely impacting the safety and reliability of a flying car. Therefore, a sophisticated and efficient rotor design is crucial, ensuring efficient folding and protection.

[0003] Most existing flying car rotor mechanisms feature a support rod and propeller connected by a rotating shaft, with the blades being an integrated design. Neither the support rod nor the blades are foldable. A few designs allow the support rod to rotate and fold around a center point. However, due to the large size of the propeller blades and support rods, existing folding methods still make the rotor mechanism larger than the circumferential dimensions of the vehicle body when the flying car is parked on the ground, posing significant challenges in securing storage space. Furthermore, existing foldable rotor mechanisms rely entirely on a control system. A malfunction in this control system can directly impact the accuracy of the mechanism's folding, or even render it impossible to fold. Flying car blades are made of composite materials, which have poor impact resistance and are significantly affected by the environment. If a collision or rain or snow occurs while the flying car is parked, the mechanical properties of the blades can be significantly reduced, seriously impacting the safety and reliability of the flying car. Summary of the Invention

[0004] The present invention proposes a four-axis, eight-propeller rotor folding mechanism suitable for a flying car, which includes a foldable support rod, foldable blades, a drive motor, and a protective storage box. Through the two-level control folding design proposed in the invention, the four-axis, eight-propeller, four-rotor structure can be folded in a secondary embracing manner. The final size of the folding mechanism is smaller than the vehicle body structure, effectively reducing the space occupied when parked on the ground. At the same time, the folding mechanism is cleverly designed with a limit slider to assist the control system or manual adjustment for accurate folding. Finally, the folding mechanism is also designed with a double-layer protective device, which not only realizes the independent protection of the blades, but also reasonably designs and arranges the protective storage box structure to realize the protection and storage of the entire rotor folding mechanism. The invention not only realizes a compact design of the mechanism, thereby improving the space utilization rate of the flying car, but also realizes multiple protections of the mechanism, thereby improving the safety and reliability of the flying car.

[0005] The present invention primarily addresses the problem that existing flying cars require a large rotor mechanism when parked on the ground, resulting in low ground space utilization and blades susceptible to damage, compromising safety. To address this issue, the present invention proposes a four-axis, eight-propeller rotor folding mechanism suitable for flying cars. The mechanism comprises key components, including support rods, propeller blades, a drive motor, and a protective storage box. A control system determines when the rotor mechanism folds after the flying car is parked on the ground. Controlled drive gradually folds the propeller blades and the support structure, and a limited slider design determines the folding position, ultimately achieving environmentally friendly and precise folding of the rotor mechanism on top of the vehicle body. The support rod, designed in the present invention, accommodates the drive motor, providing protection for the drive motor. The rotor mechanism is multi-faceted and contained, thanks to a rubber coating on the leading edge of the blades, a dedicated blade guard on the support rod, and a protective storage box on the mechanism.

[0006] Its main contents include:

[0007] Secondary folding mechanism design based on flight control:

[0008] Different from the design and folding form of the rotor mechanism of current flying cars, the present invention designs a two-stage folding mechanism based on flight control suitable for flying cars. Through the action of the flight control module and the mechanical transmission structure, the four-axis eight-propeller rotor folding mechanism is driven to achieve a two-stage folding with step-by-step coupling, which effectively solves the problem of large space occupation and low space utilization of the existing flying car rotor mechanism during the parking stage. Figure 1 .

[0009] According to one aspect of the present application, a four-axis eight-propeller rotor folding mechanism for a flying car is provided, which comprises a flight control module 1, a rear support rod 2, a support rod drive motor 3, a front support rod 4, a blade drive motor 5, and connecting joints 6 and 7.

[0010] Among them, there are 4 rear support rods 2, 4 front support rods 4, 4 blade drive motors 5, 8 connecting joints 6, and 16 blades of the 7-blade.

[0011] The rear support rod 2 is made of carbon fiber material, which is lightweight and meets high support performance, connecting the flight control module 1 and the front support rod 4;

[0012] The root of the rear support rod 2 near the flight control module 1 is a solid structure to ensure the stiffness of the support, and the rest is a hollow symmetric groove structure, providing sufficient space for the rotatable and foldable mechanism and the hidden placement of the support rod drive motor 3;

[0013] The support rod drive motor 3 is a bus servo, integrating a drive motor, a reduction gear set, and an actuator for receiving control signals;

[0014] The output end of the support rod drive motor 3 is connected to the rear support rod 2 through a rotating shaft, mainly controlling and driving the rotation of the front support rod 4;

[0015] The front support rod 4 is a rotating arm, an H-shaped round rod structure, including two short rods 4-2, 4-3 and a long rod 4-1; one of the short rods is connected to the rear support rod 2 and also connected to the output end of the support rod drive motor; the other short rod is connected to the connecting joint 6 and also connected to the output end of the blade drive motor 5; the structure is shown in Figure 2 。

[0016] The front support rod 4 is made of carbon fiber material, and the design can meet the effect of weight reduction while ensuring the load-bearing strength of the structure;

[0017] The blade drive motor 5 is a bus servo, integrating a drive motor, a reduction gear set, and an actuator for receiving control signals;

[0018] The output end of the blade drive motor 5 is connected to a short rod on one side of the front support rod 4 through a rotating shaft and is bolted at the middle position of the short rod, controlling and driving the rotation of the 7-blade;

[0019] The 7-blade is a split design, and each blade is connected to the lug of the connecting joint 6 through a blade connecting shaft and can rotate 90 degrees around the blade connecting shaft.

[0020] The 7-blade is made of carbon fiber composite material, and its rotation driven by the motor provides lift and thrust for the flying car.

[0021] The center of the connecting joint 6 has a center hole 6-1, and a short rod on one side of the front support rod 4 is connected to the connecting joint 6 through the center hole 6-1, and the connecting joint 6 can rotate 360 degrees around the short rod on one side of the front support rod 4;

[0022] The connecting joint 6 is provided with two lugs 6-2 and 6-3. The lugs have central holes with a pore diameter of Φ20mm, and are connected to the 7 blades through the blade connecting shafts 6-4 and 6-5.

[0023] One connecting joint is connected to each of the upper and lower symmetric positions of the front support rod 4 to realize the function of four axes and eight blades; the structure is shown in Figure 3 .

[0024] The connecting joint 6 is made of stainless steel, with strong mechanical properties and corrosion resistance.

[0025] The flight control module includes a comprehensive sensor and a control mechanism, which realizes the precise control of the attitude of the flight module, as well as the interactive feedback of the safety information of the ground alignment state and the folding mechanism of the flying car. The module material is carbon fiber composite material, which is light in weight and provides good support and protection for the flight control mechanism.

[0026] The four-axis eight-blade rotor folding mechanism for a flying car further includes a limit design based on a two-stage folding mechanism.

[0027] Traditional flying car rotor folding mechanisms rely on the control system to determine the folding position, which requires extremely high precision of the control system. However, when the accuracy of the control system is insufficient or the control system fails, the folding position of the mechanism cannot be guaranteed, so the high-efficiency and high-precision folding cannot be achieved, which will further affect the overall folding effect of the mechanism.

[0028] This patent proposes a limit design based on a two-stage folding mechanism. Through the design of mechanical modules, it helps each stage of the folding mechanism to easily find the position, reducing the difficulty of the control system. The four-axis eight-blade folding mechanism applicable to a flying car described in the patent has two-stage folding. The limit design structure of the first-stage blade folding is shown in Figure 4 , and the limit design structure of the second-stage support rod folding is shown in Figure 5 .

[0029] It includes the first-stage blade folding limit, specifically: a chute 6-6 and a limiting block 6-7 are provided on the inner surface 6-11 of the inner shaft of the lug of the connecting joint 6. The chute 6-6 is located at the center position inside the lug. One side of the chute 6-6 is open, and the other side is provided with a limiting block 6-7. The limiting block 6-7 is connected to the connecting joint 6 by bolts. The chute 6-6 and the limiting block 6-7 jointly limit the movement trajectory and position of the 7 blades in the unfolded state;

[0030] A rubber pad 6-8 is pasted in the chute 6-6 to play a buffering role;

[0031] In the connecting joint 6, the opposite side of the opening side of the chute 6-6 is the inner wall surface 6-10. A rubber pad 6-9 is provided at the middle of the edge where the inner wall surface 6-10 intersects with the inner shaft surface 6-11 to play a buffering role.

[0032] Including the folding limit of the secondary support rod, specifically: there is an arc-shaped groove 4-6 on the surface at the end of the rear support rod 2, and the trajectory of the arc-shaped groove 4-6 is the trajectory of the folding movement of the front support rod 4; a shoulder 4-7 is provided on the short rod connecting the front support rod 4 and the rear support rod 2, and the clearance fit between the shoulder 4-7 and the arc-shaped groove 4-6 limits the unfolded and folded positions of the support rod respectively;

[0033] When the 7 blades are unfolded, the surface where the shoulder 4-7 is in contact with the arc-shaped groove 4-6 is the contact A surface 4-8;

[0034] When the 7 blades are retracted, the surface where the shoulder 4-7 is in contact with the arc-shaped groove 4-6 is the contact B surface 4-9;

[0035] The shoulder 4-7 is integrally manufactured with the short rod connecting the front support rod 4 and the rear support rod 2.

[0036] The four-axis eight-blade rotor folding mechanism for a flying car further includes a multiple protection design for the rotor folding mechanism during the ground parking stage.

[0037] The rotor blades of a flying car are usually made of composite materials, and their impact resistance is poor. When the flying car is in the ground parking state, the traditional rotor mechanism directly exposes the blades outside the body of the flying car. The blades are damaged by hard objects such as sand and gravel, and are exposed to special weather such as rain and snow for a long time. The mechanical properties of the blades are highly sensitive to the environment. Their mechanical properties seriously degenerate in the case of invisible damage, seriously threatening the safety and reliability of the flying car.

[0038] This patent first proposes to adopt a multiple protection design for the rotor folding mechanism. The protection and storage of the four-axis eight-blade rotor folding mechanism are realized through the special treatment of the blades, the design of the folding position, and the design of the protection device. See the blade structure in Figure 6 , see the blade folding position in Figure 7 , see the protection device of the rotor folding mechanism in Figure 8 .

[0039] The 7 blades are composed of two layers. The inner layer is a solid carbon fiber composite material 7-1, and the outer layer is an elastic buffer material 7-2 evenly sprayed on the carbon fiber composite material 7-1, which can reduce the vibration of the blades and protect against the impact of small sand and gravel at the same time.

[0040] After the first-stage folding, the 7 blades are retracted into the rotor folding mechanism, without leakage in the width and thickness directions. Looking from above, the rear support rod 2 is designed in an "X" shape on the roof of the car, which has the effect of evenly distributing the load and providing rigid support. At the same time, the 7 blades are stored in the "X" structure, which plays a role in protecting the 7 blades and preventing foreign objects from directly colliding with the 7 blades.

[0041] The rotor folding mechanism protective device is designed at the top of the rear support rod 2 and is realized by connecting rings 8, 9, 10, 11 and protective cloths 18, 19. Four connecting rings are designed on the rear support rod 2, and the connecting rings are welded to the top of the rear support rod 2. Each piece of protective cloth is designed with a pair of hooks 12, 13, 14, 15, which cooperate with the connecting rings to realize the connection and separation of the protective cloth and the rotor folding mechanism. The protective cloth is closed with elastic bands 16, 17, which can be fitted with the end of the rear support rod to form a protective cover after being pulled open. The protective cloth is made of hydrophobic and rainproof fabric, which can better protect the blades and mechanisms from the influence of special weather. The two protective covers are detachable.

[0042] The advantages of this application are:

[0043] This invention proposes a rotor folding mechanism suitable for flying cars. It achieves precise, two-stage, circumferential folding and protection of the rotor mechanism for flying cars. This allows the folded mechanism to occupy a smaller circumferential footprint than the vehicle body, while also improving the precision of controlled or manual folding. Furthermore, it provides better protection for the blades and folding mechanism during ground parking. This method effectively achieves precise folding and protection of the rotor mechanism, improving space utilization and flight safety, and is suitable for rotor mechanism designs for ground-parked flying cars in future transportation applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 A four-axis eight-propeller two-stage folding mechanism structure based on flight control is proposed.

[0045] Figure 2 This is the front support rod structure diagram.

[0046] Figure 3 Connection joint structure diagram.

[0047] Figure 4 Structural diagram of the limit design for the folding of the first-stage propeller blades.

[0048] Figure 5 Structural diagram of the limit design for the folding of the secondary support rod.

[0049] Figure 6 Blade structure diagram.

[0050] Figure 7 Diagram of the propeller blade folding position.

[0051] Figure 8 Diagram of the rotor folding mechanism protective device.

[0052] Figure 9 Diagram of the rotor folding mechanism in the deployed state.

[0053] Figure 10 Diagram of the first-stage folding state of the rotor folding mechanism.

[0054] Figure 11 Schematic diagrams of the blade in the deployed state and the folded state.

[0055] Figure 12 Diagram of the secondary folded state of the rotor folding mechanism.

[0056] Note: Among them Figure 1 1 is the flight control module; 2 is the rear support rod; 3 is the support rod drive motor; 4 is the front support rod; 5 is the blade drive motor; 6 is the connecting joint; 7 is the blade.

[0057] Figure 2 In 4, 4-1 is the long rod; 4-2 and 4-3 are the short rods.

[0058] Figure 3 In 6, 6-1 is the central hole; 6-2 and 6-3 are the lugs; 6-4 and 6-5 are the blade connecting shafts.

[0059] Figure 4 In 6, 6-6 is the chute; 6-7 is the limit block; 6-8 is the rubber pad; 6-9 is the rubber pad; 6-10 is the inner wall surface; 6-11 is the inner surface of the shaft.

[0060] Figure 5 In 4, 4-4 is the schematic diagram of the support rod connection position; 4-5 is the partial enlarged schematic diagram of the limit design; 4-6 is the arc-shaped groove; 4-7 is the shoulder; 4-8 is the contact surface A; 4-9 is the contact surface B.

[0061] Figure 6 In 7, 7-1 is the carbon fiber composite material; 7-2 is the elastic buffer material.

[0062] Figure 7 In 0, 01 is the top view after folding; 02 is the side view after folding.

[0063] Figure 8 In 8-11 are the connecting rings; 12-15 are the hooks; 16-17 are the elastic bands; 18-19 are the protective fabrics. Detailed implementation manners

[0064] The following describes the present application in detail with reference to the embodiments, but the present application is not limited to these embodiments.

[0065] Embodiment 1

[0066] A rotor folding mechanism applicable to a flying car in the deployed state (flight state) is as Figure 9 shown. Its primary folded state is as Figure 10 shown. The secondary folded state (parking state) is as Figure 11 shown.

[0067] Taking the folding process of a four-axis eight-blade rotor mechanism adapted to a blade with a length of 770 mm, a root width of 96 mm, and a thickness of 28 mm as an example, when the flying car is in a flying state, the support rod and the blade are in an unfolded state. In the top-down view, the length of the mechanism is 5212 mm and the width is 2800 mm.

[0068] First, the flight control mechanism is fixed inside the module. The module is a circular hollow structure with a radius of 350 mm, a height of 340 mm, and a shell thickness of 10 mm. After the flight control module recognizes the alignment of the aircraft and the vehicle chassis, it gives instructions to the blade drive motor.

[0069] Then, eight blade drive motors simultaneously drive the connecting joint to rotate clockwise by 90 degrees, and the lugs of the connecting joint change from the direction along the support rod to the direction perpendicular to the support rod.

[0070] Next, eight blade drive motors simultaneously drive each blade to rotate clockwise by 90 degrees around the rotation axis, and all the blades become along the direction from the front support rod to the center of the mechanism. At this time, the first-stage folding of the rotor folding mechanism is achieved.

[0071] The support rod is designed in two parts: the rear support rod and the front support rod. The rear support rod is a fixed rod with dimensions of 770 mm × 200 mm × 340 mm. The front support rod is a folding rod composed of two short rods and one long rod. The short rod is a cylindrical structure with a diameter of 60 mm and a length of 380 mm. The long rod is a cylindrical structure with a diameter of 60 mm and a length of 1095 mm.

[0072] Finally, the output shafts of four support rod drive motors rotate simultaneously to drive the front support rod to rotate clockwise by 90 degrees in sequence, and then reach the inward folding position of the rotor. The blade structure rotates into the groove of the rear support rod. The groove size is 555 mm × 200 mm × 260 mm, which can completely accommodate the blade size. The second-stage folding of the rotor folding mechanism is achieved.

[0073] After the four-axis eight-blade rotor folding mechanism completes the secondary folding, in the top-down view, the length of the mechanism is 1500 mm and the width is 1500 mm. The floor area of the folded mechanism is about 154% of the floor area of the unfolded mechanism. It can greatly improve the space utilization rate.

[0074] The limit design of the above rotor folding mechanism applicable to a flying car based on a two-stage folding mechanism is as follows:

[0075] Taking the unfolding and folding processes of a four-axis eight-blade rotor mechanism adapted to a blade with a length of 770 mm, a root width of 96 mm, and a thickness of 28 mm as an example, the details are as follows:

[0076] (1) A chute is designed at the inner center position of the connecting joint lug. The width of the chute is 5 mm, the length is 115 mm, and the depth is 5 mm. A limiting block is connected inside the chute. The size of the limiting block is 5 mm × 10 mm × 3 mm, and the materials are fiberglass and rubber pad. The fiberglass is 2 mm thick and the rubber pad is 1 mm thick, which plays a buffering role. The limiting block is the final position of the blade root. When the blade rotates and unfolds driven by the driving motor, when the blade root touches the limiting block, the blade has unfolded along the axial direction of the connecting lug.

[0077] (2) An arc groove is designed on the inner wall of the connecting lug. A rubber pad is pasted in the groove to play a buffering role, and the arc groove can limit the position of the blade after folding. The height of the arc groove is 5 mm and the thickness of the rubber pad is 1 mm. The rubber pad is the final position of the blade root when folding. When the blade is driven by the rotating shaft of the driving motor to fold, when the blade root touches the rubber pad, the blade has been retracted into the inner side of the connecting lug.

[0078] (3) An arc groove is designed on the surface of the end position of the rear support rod. The depth of the groove is 5 mm, and the arc track is the track where the front support rod can move. A shoulder is designed on the short rod connecting the front support rod and the rear support rod. The protruding height of the shoulder is 3 mm, and the shoulder is 1 mm away from the mating surface of the groove. When the front support rod rotates and unfolds driven by the driving motor, when the shoulder A side on the short rod of the front support rod contacts the groove A side at the end position of the rear support rod, that is, the front support rod completes the unfolding; when the front support rod rotates and folds driven by the driving motor, when the shoulder B side on the short rod of the front support rod contacts the groove B side at the end position of the rear support rod, that is, the front support rod completes the folding.

[0079] The multiple protection designs of the rotor folding mechanism during the ground parking stage of the rotor folding mechanism applicable to flying cars are as follows:

[0080] Taking the folding of the four-axis and eight-blade rotor mechanism as an example, the application steps of the multiple protection proposed in this patent are as follows:

[0081] First, an elastic buffer material is evenly sprayed on the outer layer during the manufacture of the blade. The elastic buffer material is a rubber material with a thickness of 1 mm.

[0082] Secondly, the "X" shape design of the rear support rod leaves a relatively large triangular space between adjacent support rods. The size is a base length of 1500 mm and a height of 420 mm. When the rotor mechanism undergoes secondary folding, the blades are completely retracted into the triangular space, and the entire folding mechanism forms a square closed chamber, realizing lateral storage protection of the blades in the width direction of the mechanism. In the side view direction, the height of the rotor folding mechanism is greater than the total thickness of the double-layer blades, realizing longitudinal protection of the blades in the thickness direction of the mechanism.

[0083] Finally, after the rotor folding mechanism completes the secondary folding, the protective cloth can be taken out from the flying car. The protective cloth is 2 mm thick and is made of a hydrophobic and rainproof fabric. Hang the hooks on the protective cloth on the connecting rings at the top of the rear support rods respectively. Then pull open the elastic band of the protective cloth and fit it over the ends of the rear support rods, thus forming a protective cover like a shower cap. Even in special weather such as rain and snow, it is possible to protect the blades and the rotor mechanism.

[0084] The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can make several deformations or substitutions, which should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A four-axis and eight-blade rotor folding mechanism for a flying car, characterized in that it consists of a flight control module (1), rear support rods (2), support rod drive motors (3), front support rods (4), blade drive motors (5), connection joints (6), and blades (7); Among them, there are 4 rear support rods (2), 4 front support rods (4), 4 blade drive motors (5), 8 connection joints (6), and 16 blades (7).

2. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 1, characterized in that the rear support rod (2) is made of carbon fiber material, which is lightweight and meets high support performance, connecting the flight control module (1) and the front support rod (4); the root of the rear support rod (2) near the flight control module (1) is a solid structure to ensure the stiffness of the support, and the rest is a hollow and symmetric groove structure, providing sufficient space for the rotatable folding mechanism and the hidden placement of the support rod drive motor (3); the support rod drive motor (3) is a bus servo, integrating a drive motor, a reduction gear set, and an actuator for receiving control signals; the output end of the support rod drive motor (3) is connected to the rear support rod (2) through a rotating shaft, mainly controlling and driving the rotation of the front support rod (4); the front support rod (4) is a rotating arm, an H-shaped round rod structure, including two short rods (4-2), (4-3) and a long rod (4-1); one short rod is connected to the rear support rod (2) and is also connected to the output end of the support rod drive motor; the other short rod is connected to the connection joint (6) and is also connected to the output end of the blade drive motor (5); the front support rod (4) is made of carbon fiber material, and the design can meet the effect of weight reduction while ensuring the load-bearing strength of the structure; the blade drive motor (5) is a bus servo, integrating a drive motor, a reduction gear set, and an actuator for receiving control signals; the output end of the blade drive motor (5) is connected to the short rod on one side of the front support rod (4) through a rotating shaft and is bolted in the middle position of the short rod, controlling and driving the rotation of the blade (7); the blade (7) is of a split design, and each blade is connected to the lug of the connection joint (6) through a blade connection shaft and can rotate 90 degrees around the blade connection shaft; the blade (7) is made of carbon fiber composite material, and its rotation driven by the motor provides lift and thrust for the flying car.

3. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 2, characterized in that the connection joint (6) has a central hole (6-1), and one short rod of the front support rod (4) is connected to the connection joint through the central hole (6-1), and the connection joint (6) can rotate 360 degrees around one short rod of the front support rod (4); the connection joint (6) is provided with two lugs (6-2), (6-3), the lugs have central holes, and the hole diameter is Φ20mm, which cooperate with the blade connection shafts (6-4), (6-5) to connect the blade (7); one front support rod (4) is connected to one connection joint at the upper and lower symmetric positions respectively to achieve the function of four axes and eight blades; The connecting joint (6) is made of stainless steel, with strong mechanical properties and corrosion resistance.

4. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 1, wherein the flight control module includes an integrated sensor and a control mechanism to achieve precise control of the attitude of the flight module, as well as the interactive feedback of the ground alignment state of the flying car and the safety information of the folding mechanism.

5. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 1, wherein it includes a primary blade folding limit, specifically: a chute (6-6) and a limiting block (6-7) are provided on the inner surface of the inner shaft of the lug of the connecting joint (6) (6-11). The chute (6-6) is located at the center position inside the lug. One side of the chute (6-6) is open, and the other side is provided with a limiting block (6-7). The limiting block (6-7) is bolted to the connecting joint (6). The chute (6-6) and the limiting block (6-7) jointly limit the movement trajectory and position of the blade (7) in the deployed state; a rubber pad (6-8) is pasted in the chute (6-6) to play a buffering role; in the connecting joint (6), the opposite side of the opening side of the chute (6-6) is the inner wall surface (6-10). A rubber pad (6-9) is provided in the middle of the edge where the inner wall surface (6-10) intersects the inner shaft surface (6-11) to play a buffering role.

6. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 1, wherein it includes a secondary support rod folding limit, specifically: an arc-shaped groove (4-6) is provided on the surface at the end of the rear support rod (2). The trajectory of the arc-shaped groove (4-6) is the trajectory of the folding movement of the front support rod (4); a shoulder (4-7) is provided on the short rod connecting the front support rod (4) and the rear support rod (2). The shoulder (4-7) and the arc-shaped groove (4-6) are in clearance fit to respectively limit the positions of the support rod in the deployed and folded states; when the blade (7) is deployed, the surface where the shoulder (4-7) is in contact with the arc-shaped groove (4-6) is the contact surface A (4-8); when the blade (7) is retracted, the surface where the shoulder (4-7) is in contact with the arc-shaped groove (4-6) is the contact surface B (4-9); the shoulder (4-7) is integrally manufactured with the short rod connecting the front support rod (4) and the rear support rod (2).

7. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 2, wherein the blade (7) is composed of two layers. The inner layer is a solid carbon fiber composite material (7-1), and the outer layer is an elastic buffer material (7-2) uniformly sprayed on the carbon fiber composite material (7-1), which can reduce the vibration of the blade and protect against the impact of small sand and gravel at the same time.

8. The four-axis and eight-blade rotor folding mechanism for a flying car according to claim 1, wherein After the first-stage folding, the blade (7) is retracted inside the rotor folding mechanism without any external leakage in terms of width and thickness. In the top view direction, the rear support rod (2) is designed in an "X" shape on the roof, achieving the effects of uniform load distribution and rigid support. At the same time, the blade (7) is accommodated in the "X" structure, providing protection for the blade (7) to prevent foreign objects from directly colliding with the blade (7).

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