A composite wing system and air mobile

Abstract

The application discloses a composite wing system and a flying car, and solves the technical problem of a complex folding mechanism of a flying car in the prior art. The composite wing system is used for an aircraft, and comprises a wing assembly and a rotor assembly. The wing assembly comprises a wing folding mechanism and two wings. The wing comprises a wing surface and a four-bar linkage mechanism. The wing folding mechanism is in force transmission connection with the four-bar linkage mechanism. The rotor assembly comprises an arm and a blade assembly. The arm is rotationally installed on one connecting rod of the four-bar linkage mechanism and is arranged at an angle with the connecting rod. The two wings are driven by the wing folding mechanism to be parallel or perpendicular to the aircraft. One connecting rod of the four-bar linkage mechanism is driven by the wing folding mechanism to be parallel or perpendicular to the wing. The wing folding mechanism can drive the two wings to be parallel or perpendicular to the aircraft. One set of wing folding structures can realize the folding of the wings and the arm, so that the mass of the aircraft is reduced.

Description

Technical Field

[0001] This application belongs to the field of flying car technology, specifically relating to a compound wing system and a flying car. Background Technology

[0002] With the increasing number of cars in cities, road congestion has become increasingly serious. To alleviate traffic congestion, urban multi-level transportation systems have been constructed. These systems include air transportation in addition to existing road, rail, and waterway transportation. Flying cars, as an important component of urban air transportation, have broad application prospects. However, flying cars, equipped with large components such as wings and rotors, need to be folded to travel on open roads. These folding mechanisms are generally complex, increasing both the overall weight of the vehicle and the probability of mechanical component malfunctions. Summary of the Invention

[0003] To address the complex technical problems of current flying car folding mechanisms, this application provides a compound wing system and a flying car.

[0004] In a first aspect of this application, a compound wing system for an aircraft is provided, comprising:

[0005] The wing assembly includes a wing folding mechanism and two wings rotatably connected to the aircraft. The wings include wing surfaces and a four-bar linkage disposed within the wing surface cavity. The wing folding mechanism is connected to the four-bar linkage for force transmission.

[0006] The rotor assembly includes an arm parallel to the aircraft and two sets of blade assemblies respectively mounted at both ends of the arm. The arm is rotatably mounted on one of the links of the four-bar linkage and is set at an angle to the link.

[0007] The two wings are rotated to be parallel or perpendicular to the aircraft under the drive of the wing folding mechanism, and one of the links of the four-bar linkage is rotated to be parallel or perpendicular to the wing under the drive of the wing folding mechanism.

[0008] Furthermore, the four-bar linkage includes a first link, a second link, and a third link; the arm is rotatably mounted on the third link, the first link is parallel to the second link, and the third link is angularly positioned relative to both the first and second links.

[0009] Furthermore, the wing folding mechanism includes a wing drive component and a wing transmission assembly driven by the wing drive component;

[0010] The active output end of the wing drive assembly is coaxially connected to the first link or the second link of one of the four-bar linkages, and the driven output end of the wing drive assembly is coaxially connected to the first link or the second link of the other four-bar linkage.

[0011] Furthermore, the wing drive assembly includes:

[0012] The drive gear is coaxially mounted on the output end of the wing drive component and coaxially connected to the first link or the second link in one of the four-bar linkages.

[0013] The steering gear meshes with the drive gear;

[0014] The driven gear is connected to the steering gear via a first transmission member and is coaxially connected to the first or second link of another four-bar linkage.

[0015] Furthermore, the wing has one or more ribs, and each rib has two parallel grooves, wherein the first link passes through one of the grooves and the second link passes through the other groove;

[0016] One of the first and second links in the same four-bar linkage passes through the slide groove and is fixedly connected to the corresponding rib, while the other is slidably connected to the corresponding slide groove.

[0017] Furthermore, the blade assembly includes:

[0018] The first blade is equipped with a first drive shaft;

[0019] The second blade is provided with a second drive shaft. The second blade and the first blade are staggered in the height direction, and the second blade and the first blade are connected for force transmission.

[0020] The rotor motor has its output end connected to the first drive shaft or the second drive shaft for force transmission.

[0021] Furthermore, both the first blade and the second blade are provided with a meshing disc extending circumferentially. The meshing disc of the first blade meshes with the meshing disc of the second blade to enable the second blade to be connected to the first blade for force transmission.

[0022] Furthermore, the blade assembly also includes:

[0023] The lifting force transmission component acts on the first blade or the second blade;

[0024] A transmission sleeve is connected to the four-bar linkage for force transmission; the second transmission shaft passes through the transmission sleeve.

[0025] An adsorption component has a first end acting on the transmission sleeve and a second end acting on the first blade or the second blade, so that the first blade or the second blade adsorbs or separates from the transmission sleeve.

[0026] The first or second blade moves axially under the drive of the lifting force transmission component to separate the second blade from the first blade; the first or second blade is adsorbed by the transmission sleeve under the action of the adsorption component, and the transmission sleeve rotates under the drive of the four-bar linkage to drive the first and second blades to rotate relative to each other until their horizontal projections at least partially overlap.

[0027] Furthermore, the lifting force transmission component is a lead screw, which has a through hole, and the second transmission shaft has a threaded through hole. The second transmission shaft is located on the lead screw and meshes with the lead screw.

[0028] The first drive shaft passes through the through hole and the threaded through hole, and is connected to the output end of the rotor motor for force transmission; wherein, the drive sleeve is attracted to the second drive shaft under the action of the adsorption assembly, the drive sleeve rotates under the drive of the four-bar linkage, so that the second drive shaft rotates, and the second drive shaft drives the second blade to move axially under the threaded engagement of the lead screw.

[0029] Further, the adsorption component includes:

[0030] Elastic components;

[0031] The friction element includes two friction plates, which are connected to the inner wall of the transmission sleeve via the elastic element.

[0032] An electromagnet is provided at the end of the friction plate to bring the two friction plates closer or further apart, thereby clamping or releasing the second drive shaft.

[0033] In a second aspect of this application, a flying car is provided, comprising:

[0034] The vehicle body has steps.

[0035] The aforementioned compound wing system is located at the stepped portion.

[0036] According to one or more embodiments of this application, a compound wing system and a flying car are provided. The compound wing system is used for an aircraft. The wing assembly includes a wing folding mechanism and two wings rotatably connected to the aircraft. Each wing includes a wing surface and a four-bar linkage disposed within the wing surface cavity. The wing folding mechanism is force-transmittingly connected to the four-bar linkage. The rotor assembly includes an arm parallel to the aircraft and two sets of blade assemblies respectively mounted at both ends of the arm. The arm is rotatably mounted on one link of the four-bar linkage and is angled to the link. The two wings rotate to be parallel or perpendicular to the aircraft under the drive of the wing folding mechanism, and one link of the four-bar linkage also rotates to be parallel or perpendicular to the wings under the drive of the wing folding mechanism. The wing folding mechanism can drive the two wings to rotate to be parallel or perpendicular to the aircraft, and the arm and wings share the wing folding mechanism. The arm is aligned to be parallel or perpendicular to the wings via the wing folding mechanism. Through a set of wing folding structures, the folding of the wings and arms can be achieved, thereby reducing the mass of the aircraft. Attached Figure Description

[0037] Figure 1 A structural schematic diagram of the aircraft in the deployed state of this application is shown.

[0038] Figure 2 It shows Figure 1 A schematic diagram of the aircraft in its folded state.

[0039] Figure 3 It shows Figure 1 A structural diagram of the aircraft during the folding process.

[0040] Figure 4 It shows Figure 1 An exploded view of the wing folding mechanism in the wing.

[0041] Figure 5 It shows Figure 1 A schematic diagram of the wing folding mechanism in an aircraft wing.

[0042] Figure 6 It shows Figure 1 A schematic diagram of a four-bar linkage in the wing-spread state.

[0043] Figure 7 It shows Figure 1 A schematic diagram of the structure with the wings deployed.

[0044] Figure 8 It shows Figure 1 A schematic diagram of a four-bar linkage in the folded state of an aircraft wing.

[0045] Figure 9 It shows Figure 1 A schematic diagram of the structure of the wing in its folded state.

[0046] Figure 10 It shows Figure 1 A schematic diagram of the propeller assembly structure.

[0047] Figure 11 It shows Figure 1 A schematic diagram of the transmission sleeve structure.

[0048] Figure 12 It shows Figure 1 A schematic diagram of the propeller assembly in its deployed state.

[0049] Figure 13 It shows Figure 1 A schematic diagram of the propeller assembly in its folded state.

[0050] Figure 14 A schematic diagram of the rib structure of this application is shown.

[0051] Explanation of reference numerals in the attached drawings: 100-Compound wing system, 110-Wing assembly, 111-Wing folding mechanism, 112-Wing, 1121-Wing surface, 1122-First wing, 1123-Second wing, 113-Four-bar linkage, 1131-First link, 1132-Second link, 1133-Third link, 114-Wing drive component, 115-Wing transmission assembly, 1151-Drive gear, 1152-Steering gear, 1153-Driven gear, 1154-First transmission component, 1155-Drive shaft, 1156-Steering shaft, 1157-Driven shaft, 1158-Left bushing, 1159-Right bushing, 116- Wing rib, 1161-First wing rib groove, 1162-Second wing rib groove, 117-First connecting rod shaft, 118-Second connecting rod shaft, 119-Wing groove, 120-Rotor assembly, 121-Arm, 122-Blade assembly, 123-First blade, 1231-First drive shaft, 124-Second blade, 1241-Second drive shaft, 125-Rotor motor, 126-Meshing disc, 127-Lifting force transmission component, 128-Transmission sleeve, 129-Adsorption assembly, 1291-Elastic component, 1292-Friction pad, 1293-Electromagnet, 130-Second transmission component, 131-Bearing, 200-Body, 210-Wheel. Detailed Implementation

[0052] To enable those skilled in the art to more clearly understand this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0053] Please see Figure 1 To be continued Figure 14 According to a first aspect of this application, a compound wing system 100 is provided for an aircraft. The compound wing system includes a wing assembly 110 and a rotor assembly 120. The wing assembly 110 includes a wing folding mechanism 111 and two wings 112. Both wings 112 are rotatably connected to the aircraft. When folding of the wings 112 is required, the wing folding mechanism 111 folds the wings 112. The two wings 112 are symmetrically arranged on the aircraft. The lift can be evenly distributed on both sides, allowing the aircraft to maintain balance during flight. The wing 112 includes a wing surface 1121 and a four-bar linkage 113. The cross-section of the wing 112 is airfoil-shaped, with the upper surface of the wing 112's cross-section convex and the lower surface relatively horizontal. To facilitate the installation of the four-bar linkage 113 with the wing 112, an inner cavity is provided inside the wing surface 1121, and the four-bar linkage 113 is located within the inner cavity. The wing folding mechanism 111 is connected to the four-bar linkage 113 for force transmission. Through the force transmission connection between the wing folding mechanism 111 and the four-bar linkage 113, the wing 112 can be rotated to be parallel to the aircraft, i.e., the wing 112 is folded onto the aircraft, allowing for flight mode; alternatively, the wing 112 can be rotated to be perpendicular to the aircraft, i.e., the wing 112 is unfolded onto the aircraft, allowing for flight mode.

[0054] like Figure 1 , Figure 2 and Figure 6 As shown, the rotor assembly 120 includes an arm 121 and a blade assembly 122. The arm 121 is parallel to the aircraft. The blade assembly 122 has two sets, which are respectively installed at both ends of the arm 121. The arm 121 is rotatably mounted on one of the links of the four-bar linkage 113 and is set at an angle to the link. In order to ensure that the blade assembly 122 is installed at both ends of the arm 121 and to ensure the symmetry of the blade assembly 122, the center of the arm 121 is rotatably mounted on one of the links of the four-bar linkage 113.

[0055] like Figures 5 to 9As shown, in some embodiments, the four-bar linkage 113 includes a first link 1131, a second link 1132, and a third link 1133; the arm 121 is rotatably mounted on the third link 1133; the wing folding mechanism 111 is connected to the first link 1131 or the second link 1132 for force transmission; and the third link 1133 is angularly positioned with both the first link 1131 and the second link 1132. For example, when the wing folding mechanism 111 is connected to the second link 1132 for force transmission, the first link 1131 is rotatably connected to the third link 1133, and the second link 1132 is rotatably connected to the third link 1133. When the two wings 112 need to change from the folded state to the unfolded state, the second link 1132 rotates under the action of the wing folding mechanism 111, and drives the wings 112 to rotate through the four-bar linkage, thus completing the change of a set of wings 112 from the folded state to the unfolded state. At this time, the rotation of the second link 1132 drives the third link 1133 to rotate to a state parallel to the wings 112.

[0056] like Figure 7 As shown, in some embodiments, a wing groove 119 is provided on the wing surface 1121. Under the action of the wing folding mechanism 111, the connection between the third link 1133 and the second link 1132 moves along the wing groove 119, thereby ensuring that when the wing 112 rotates to a state parallel to the aircraft, after the second link 1132 rotates and moves along the wing groove 119, the third link 1133 rotates to a state parallel to the wing 112. At this time, the arm 121 is perpendicular to the third link 1133, and the arm 121 is in the unfolded state. Specifically, the wing groove 119 is arc-shaped, and the central angle corresponding to the arc is 90 degrees.

[0057] When the two wings 112 change from the unfolded state to the folded state, the second link 1132 rotates under the action of the wing folding mechanism 111. The rotation of the second link 1132 drives the third link 1133 to rotate to a state perpendicular to the wings 112. Regardless of whether the wings 112 are unfolded or folded, the arm 121 is parallel to the aircraft.

[0058] Thus, the two wings 112 rotate to be parallel or perpendicular to the aircraft under the drive of the wing folding mechanism 111, and one of the links of the four-bar linkage 113 rotates to be parallel or perpendicular to the wings 112 under the drive of the wing folding mechanism 111. The wing folding mechanism 111 can drive the two wings 112 to rotate to be parallel to the aircraft, realizing the folding action of the wings 112. And through the combined action of the wing folding mechanism 111 and the four-bar linkage 113, the third link 1133, which is rotatably connected to the arm 121, is driven to be perpendicular to the wings 112. At this time, the arm 121 is parallel to the wings 112. That is, the folding of the wings 112 and the arm 121 is realized through the combined action of the wing folding mechanism 111 and the four-bar linkage 113.

[0059] In addition, the wing folding mechanism 111 can drive the two wings 112 to rotate to be perpendicular to the aircraft, thereby realizing the unfolding of the wings 112; through the combined action of the wing folding mechanism 111 and the four-bar linkage 113, the third linkage 1133, which is rotatably connected to the arm 121, is driven to be parallel to the wings 112, at which point the arm 121 is perpendicular, that is, the unfolding of the wings 112 and the arm 121 is realized through the combined action of the wing folding mechanism 111 and the four-bar linkage 113.

[0060] like Figures 6 to 9 As shown, in some embodiments, the first link 1131 is rotatably connected to the third link 1133, and the second link 1132 is also rotatably connected to the third link 1133. To ensure that the arm 121 is rotatably connected to the third link 1133, the end of the third link 1133 that is rotatably connected to the first link 1131 and the second link 1132 includes two pivots, respectively designated as the first link pivot 117 and the second link pivot 118. The line connecting the first link pivot 117 and the second link pivot 118 forms the third link 1133. The center of the arm 121 is rotatably mounted on the third link 1133. During the folding or unfolding of the wing 112, the second link 1132, which is connected to the wing folding mechanism 111 for force transmission, rotates. At this time, the second link pivot 118, which is rotatably connected to the second link 1132, moves along the wing slide groove 119.

[0061] like Figure 4 and Figure 5 As shown, in some embodiments, the wing folding mechanism 111 includes a wing drive member 114 and a wing transmission assembly 115 driven by the wing drive member 114; the active output end of the wing transmission assembly 115 is coaxially connected to the first link 1131 or the second link 1132 in one of the four-bar linkages 113, and the driven output end of the wing transmission assembly 115 is coaxially connected to the first link 1131 or the second link 1132 of another four-bar linkage 113. For example, the two wings 112 are the first wing 1122 and the second wing 1123. The first wing 1122 is provided with a four-bar linkage 113, and the second wing 1123 is also provided with a four-bar linkage 113. The second link 1132 of the four-bar linkage 113 of the first wing 1122 is coaxially connected to the active output end of the wing transmission assembly 115. The second link 1132 of the four-bar linkage 113 of the second wing 1123 is coaxially connected to the driven output end of the wing transmission assembly 115. The second link 1132 is slidably connected to the wing 112, and the first link 1131 is fixedly connected to the wing 112.

[0062] Therefore, when the two wings 112 need to change from a folded state to an unfolded state, the wing drive component 114 drives the wing transmission assembly 115. The active output end of the wing transmission assembly 115 drives the second link 1132 of the first wing 1122 to rotate in the forward direction. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the first wing 1122 to unfold. The driven output end of the wing transmission assembly 115 drives the second link 1132 of the second wing 1123 to rotate in the forward direction. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the second wing 1123 to unfold.

[0063] Furthermore, when the two wings 112 need to change from an unfolded state to a folded state, the wing drive component 114 drives the wing transmission assembly 115. The active output end of the wing transmission assembly 115 drives the second link 1132 of the first wing 1122 to rotate in the opposite direction. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the first wing 1122 to fold. The driven output end of the wing transmission assembly 115 drives the second link 1132 of the second wing 1123 to rotate in the opposite direction. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the second wing 1123 to fold.

[0064] like Figure 5 As shown, in some embodiments, the wing drive component 114 is a folding drive motor. The output end of the folding drive motor is connected to the wing transmission assembly 115. The active output end of the wing transmission assembly 115 is coaxially connected to the second link 1132 of one of the four-bar linkages 113, and the driven output end of the wing transmission assembly 115 is coaxially connected to the first link 1131 of the other four-bar linkage 113. That is, the folding and unfolding of the wing 112 and the arm 121 can be achieved by a single motor drive, effectively reducing the weight of the aircraft.

[0065] like Figure 5As shown, in order to ensure that the active output end and the driven output end of the wing drive assembly 115 can transmit force to the four-bar linkage 113 of the two wings 112, in some embodiments, the wing drive assembly 115 includes a drive gear 1151, a steering gear 1152 and a driven gear 1153. The drive gear 1151 is coaxially mounted on the output end of the wing drive member 114 and is coaxially connected to the first link 1131 or the second link 1132 in one of the four-bar linkages 113. The steering gear 1152 meshes with the drive gear 1151. The driven gear 1153 is connected to the steering gear 1152 through the first transmission member 1154 and is coaxially connected to the first link 1131 or the second link 1132 of the other four-bar linkage 113. For example, the two wings 112 are the first wing 1122 and the second wing 1123. The first wing 1122 is equipped with a four-bar linkage 113, and the second wing 1123 is also equipped with a four-bar linkage 113. The second link 1132 of the four-bar linkage 113 of the first wing 1122 is coaxially connected to the drive gear 1151, and the second link 1132 of the four-bar linkage 113 of the second wing 1123 is coaxially connected to the driven gear 1153. The driven gear 1153 and the steering gear 1152 are connected by a first transmission member 1154.

[0066] Therefore, when the two wings 112 need to change from a folded state to an unfolded state, the wing drive component 114 drives the drive gear 1151 to rotate, the drive gear 1151 drives the second link 1132 of the first wing 1122 to rotate, the second link 1132 drives the third link 1133 to rotate, the third link 1133 drives the first link 1131 to rotate, the first link 1131 rotates and drives the wing 112 to rotate, thereby causing the first wing 1122 to unfold. The drive gear 1151 drives the steering gear 1152 to rotate, the steering gear 1152 drives the driven gear 1153 to rotate through the first transmission component 1154, the driven gear 1153 rotates and drives the second link 1132 of the second wing 1123 to rotate, the second link 1132 drives the third link 1133 to rotate, the third link 1133 drives the first link 1131 to rotate, the first link 1131 rotates and drives the wing 112 to rotate, thereby causing the second wing 1123 to unfold.

[0067] When the two wings 112 need to change from the deployed state to the folded state, the wing drive component 114 drives the drive gear 1151 to rotate. The drive gear 1151 drives the second link 1132 of the first wing 1122 to rotate. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the first wing 1122 to fold. The drive gear 1151 drives the steering gear 1152 to rotate. The steering gear 1152 drives the driven gear 1153 to rotate through the first transmission component 1154. The rotation of the driven gear 1153 drives the second link 1132 of the second wing 1123 to rotate. The second link 1132 drives the third link 1133 to rotate. The third link 1133 drives the first link 1131 to rotate. The rotation of the first link 1131 drives the wing 112 to rotate, thereby causing the second wing 1123 to fold.

[0068] like Figure 4 and Figure 5 As shown, in some embodiments, the wing drive component 114 is a folding drive motor. The output end of the folding drive motor is provided with a drive shaft 1155, which is fixed to the output end of the folding drive motor. The folding drive motor can drive the drive shaft 1155 to rotate. A flat key can be provided on the drive shaft 1155, which then engages with the drive gear 1151. The folding drive motor can drive the drive shaft 1155 and the drive gear to rotate at the same angular velocity. A left shaft sleeve 1158 is also fitted on the top of the drive shaft 1155. The drive shaft 1155 is connected to one of the four-bar linkages 1. The second link 1132 of 13 is fixedly connected. The left bushing 1158 fitted on the top of the drive shaft 1155 can separate the drive gear 1151 and the second link 1132. The top of the passive shaft 1157 is fitted with a right bushing 1159. The passive shaft 1157 is fixedly connected to the second link 1132 of another four-bar linkage 113. The right bushing 1159 fitted on the top of the passive shaft 1157 can separate the passive shaft 1157 and the second link 1132. The folding drive motor can drive the drive shaft 1155 and the second link 1132 to rotate at the same angular velocity.

[0069] like Figure 4 and Figure 5 As shown, in some other embodiments, the steering gear 1152 is provided with a steering shaft 1156, the driven gear 1153 is provided with a driven shaft 1157, and the driven shaft 1157 is provided with a flat key. The driven gear 1153 and the driven shaft 1157 cooperate with each other through the flat key. The folding drive motor rotates, driving the drive shaft 1155, the drive gear 1151, and the second connecting rod 1132 of the first wing 1122 to rotate together.

[0070] like Figure 4 and Figure 5 As shown, in some embodiments, a drive belt is fitted around the lower part of the steering gear 1152, and a driven gear 1153 is fitted around the other end of the drive belt. Specifically, the steering shaft 1156 and the driven shaft 1157 are connected by a drive belt. The steering gear 1152 meshes externally with the drive gear 1151 and rotates in the opposite direction to the folding drive motor at the same angular velocity. To ensure that the angular velocities of the steering gear 1152 and the driven gear 1153 are consistent, the radii of the lower parts of both the steering gear 1152 and the driven gear 1153 that contact the drive belt are the same. The driven gear 1153 transmits power to the second link 1132 of the second wing 1123 through the driven shaft 1157, thereby driving the rotation of the second wing 1123.

[0071] Therefore, the above mechanism enables a single motor to drive the second link 1132 of the first wing 1122 and the second link 1132 of the second wing 1123 to rotate in opposite directions at the same angular velocity. This allows the first wing 1122 and the second wing 1123 to fold and unfold.

[0072] like Figures 6 to 9 and attached Figure 14 As shown, in order to ensure that the arm 121 can remain parallel to the aircraft when the wing 112 is folded, in some embodiments, the wing 112 is provided with one or more ribs 116, and the rib 116 is provided with two parallel sliding grooves, wherein the first link 1131 passes through one of the rib sliding grooves, and the second link 1132 passes through the other rib sliding groove; one of the first link 1131 and the second link 1132 located in the same four-bar linkage 113 is fixedly connected to the corresponding rib 116, and the other is slidably connected to the corresponding rib sliding groove.

[0073] In order to ensure that the shape of the wing surface 1121 does not deform, in some embodiments, the outer edge of the wing rib 116 is fixedly connected to the wing surface 1121.

[0074] In some embodiments, the two wings 112 are a first wing 1122 and a second wing 1123, respectively. A four-bar linkage 113 is provided in both the first and second wings 1122 and 1123. The second link 1132 of the four-bar linkage 113 in the first wing 1122 is coaxially connected to the active output end of the wing transmission assembly 115. The second link 1132 of the four-bar linkage 113 in the second wing 1123 is coaxially connected to the driven output end of the wing transmission assembly 115 and is connected to the first link 1131. The slide groove is designated as the first wing rib slide groove 1161. To ensure that the rotation of the first connecting rod 1131 drives the rotation of the wing 112, thereby realizing the folding and unfolding of the wing 112, the first connecting rod 1131 is fixedly connected to the first wing rib slide groove 1161. The slide groove connected to the second connecting rod 1132 is designated as the second wing rib slide groove 1162. To ensure that the second connecting rod 1132 rotates and moves around the wing slide groove 119, the second connecting rod 1132 is slidably connected to the second wing rib slide groove 1162. The second wing rib slide groove 1162 can restrict the movement of the second connecting rod 1132. At this time, the first connecting rod 1131, the second connecting rod 1132, the third connecting rod 1133, and the wing rib 116 form a four-bar linkage 113.

[0075] Therefore, when the two wings 112 need to change from a folded state to an unfolded state, the wing drive component 114 drives the drive gear 1151 to rotate, and the drive shaft 1155 drives the second link 1132 of the first wing 1122 to rotate. When the second link 1132 rotates 90°, it drives the third link 1133 to rotate 90°, which in turn drives the first link 1131 to rotate 90°. The rotation of the first link 1131 then drives the wing 112 to rotate 90°, thus completing the unfolding of the first wing 1122. During the deployment of the first wing 1122, the rotation of the second link 1132 drives the third link 1133 to rotate until it is parallel to the wing 112. At this time, the second link 1132 slides along the second wing rib groove 1162, and the connection between the second link 1132 and the third link 1133 slides along the wing groove 119, so that the third link 1133 rotates to a state parallel to the wing 112. The third link 1133 is perpendicular to the arm 121. At this time, the arm 121 is perpendicular to the wing 112, and the rotor assembly 120 is also in the deployed state.

[0076] During the deployment of the first wing 1122, the drive gear 1151 drives the steering gear 1152 to rotate. The steering gear 1152 drives the driven gear 1153 to rotate through the first transmission component 1154. The rotation of the driven gear 1153 drives the second link 1132 of the second wing 1123 to rotate. The rotation of the second link 1132 drives the wing 112 to rotate. When the second link 1132 rotates 90°, it drives the third link 1133 to rotate 90°. The third link 1133 drives the first link 1131 to rotate 90°. The rotation of the first link 1131 drives the wing 112 to rotate 90°, thus completing the deployment of the second wing 1123. During the deployment of the second wing 1123, the rotation of the second link 1132 causes the third link 1133 to rotate until it is parallel to the wing 112. At this time, the second link 1132 slides along the second wing rib groove 1162, and the connection between the second link 1132 and the third link 1133 slides along the wing groove 119, so that the third link 1133 rotates to a state parallel to the wing 112. The arm 121 is perpendicular to the third link 1133 and perpendicular to the wing 112. At this time, the rotor assembly 120 is also in the deployed state. During the deployment of the first wing 1122 and the second wing 1123, the arm 121 remains parallel to the aircraft. When the third link 1133 rotates to a state parallel to the wing 112, the arm 121 is perpendicular to the wing 112. At this time, the rotor assembly 120 is also in the deployed state.

[0077] When the two wings 112 need to change from the unfolded state to the folded state, the wing drive component 114 drives the drive gear 1151 to rotate. The drive gear 1151 drives the second link 1132 of the first wing 1122 to rotate. When the second link 1132 rotates 90° in the opposite direction, the second link 1132 drives the third link 1133 to rotate 90°. The third link 1133 drives the first link 1131 to rotate 90°. The rotation of the first link 1131 drives the wing 112 to rotate 90° in the opposite direction, thus completing the folding of the first wing 1122. During the folding process of the first wing 1122, the second link 1132 rotates, causing the third link 1133 to rotate to be perpendicular to the wing 112. At this time, the second link 1132 slides along the second wing rib groove 1162, and the connection between the second link 1132 and the third link 1133 slides along the wing groove 119, so that the third link 1133 rotates to be perpendicular to the wing 112. The arm 121 is perpendicular to the third link 1133. At this time, the arm 121 is parallel to the wing 112, and the rotor assembly 120 is also in a folded state.

[0078] During the folding process of the first wing 1122, the drive gear 1151 drives the steering gear 1152 to rotate. The steering gear 1152 drives the driven gear 1153 to rotate via the transmission belt. The rotation of the driven gear 1153 drives the second link 1132 of the second wing 1123 to rotate. The rotation of the second link 1132 drives the wing 112 to rotate. When the second link 1132 rotates 90° in the opposite direction, it drives the third link 1133 to rotate 90°. The third link 1133 drives the first link 1131 to rotate 90°. The rotation of the first link 1131 drives the wing 112 to rotate in the opposite direction. The second wing 1123 is folded by rotating 90°. During the folding process, the second link 1132 rotates, causing the third link 1133 to rotate perpendicular to the wing 112. At this time, the second link 1132 slides along the second wing rib groove 1162, and the connection between the second link 1132 and the third link 1133 slides along the wing groove 119, so that the third link 1133 rotates to a position perpendicular to the wing 112. The arm 121 is perpendicular to the third link 1133, and at this time, the arm 121 is parallel to the wing 112, and the rotor assembly 120 is also folded. During the folding process of the first wing 1122 and the second wing 1123, the arm 121 remains parallel to the aircraft. When the third link 1133 rotates to a position perpendicular to the wing 112, the arm 121 is parallel to the wing 112, and the rotor assembly 120 is also folded.

[0079] In some embodiments, the arms 121 on the first wing 1122 are connected to each other via two arm 121 pivots, allowing relative rotation between the two arm 121 pivots and the arms 121. Power is input through the second link 1132 to drive the four-bar linkage 113 to rotate.

[0080] like Figures 10 to 13 As shown, in some embodiments, the blade assembly 122 includes a first blade 123, a second blade 124, and a rotor motor 125. The first blade 123 is provided with a first drive shaft 1231; the second blade 124 is provided with a second drive shaft 1241. The second blade 124 and the first blade 123 are staggered in the height direction, and the second blade 124 is connected to the first blade 123 for force transmission. The output end of the rotor motor 125 is connected to the first drive shaft 1231 or the second drive shaft 1241 for force transmission.

[0081] Therefore, when the first blade 123 and the second blade 124 are combined into one unit, the rotor motor 125 can drive the first drive shaft 1231 or the second drive shaft 1241 to rotate, thereby driving the first blade 123 and the second blade 124 to rotate as a whole.

[0082] In some embodiments, both the first blade 123 and the second blade 124 are provided with a circumferentially extending engagement disk 126. The engagement disk 126 of the first blade 123 engages with the engagement disk 126 of the second blade 124 to enable the second blade 124 to be connected to the first blade 123 for force transmission. When the first blade 123 and the second blade 124 are integrated, the first blade 123 and the second blade 124 engage through the engagement disk 126, thereby achieving circumferential limiting.

[0083] like Figure 10 As shown, in some embodiments, the blade assembly 122 further includes a lifting force transmission component 127, a transmission sleeve 128, and an adsorption component 129. The lifting force transmission component 127 acts on the first blade 123 or the second blade 124; the transmission sleeve 128 is connected to the four-bar linkage 113 for force transmission; the second transmission shaft 1241 passes through the transmission sleeve 128; the adsorption component 129 has a first end acting on the transmission sleeve 128 and a second end acting on the first blade 123 or the second blade 124, so that the first blade 123 or the second blade 124 is engaged with the first blade 123 or the second blade 124. The transmission sleeve 128 adsorbs or separates; wherein, the first blade 123 or the second blade 124 moves axially under the drive of the lifting force transmission component 127, so that the second blade 124 separates from the first blade 123; the first blade 123 or the second blade 124 is adsorbed by the transmission sleeve 128 under the action of the adsorption component 129, and the transmission sleeve 128 rotates the four-bar linkage 113 under the drive of the four-bar linkage 113, so as to drive the first blade 123 and the second blade 124 to rotate relative to each other until the horizontal projections at least partially overlap.

[0084] like Figure 10 As shown, in some embodiments, when the first blade 123 is located above and the second blade 124 is located below the first blade 123, the second blade 124 moves axially under the drive of the lifting force transmission member 127. When the first blade 123 and the second blade 124 separate, the second blade 124 moves axially away from the first blade 123 under the drive of the lifting force transmission member 127, thereby causing the first blade 123 and the second blade 124 to separate.

[0085] like Figure 10As shown, in order to achieve the first blade 123 and the second blade 124 being located on the same side, in some embodiments, the second blade 124 is adsorbed by the adsorption component 129 and the transmission sleeve 128, that is, the second blade 124 and the transmission sleeve 128 are integrated under the action of the adsorption component 129. The transmission sleeve 128 is connected to the four-bar linkage 113 for force transmission. Under the action of the four-bar linkage 113, the transmission sleeve 128 rotates, thereby driving the second blade 124 to rotate, so that the first blade 123 and the second blade 124 rotate relative to each other until the first blade 123 and the second blade 124 are located on the same side, that is, the horizontal projections of the first blade 123 and the second blade 124 completely overlap.

[0086] like Figure 10 As shown, in order to realize the axial movement of the first blade 123 under the drive of the lifting force transmission component 127, in some embodiments, the lifting force transmission component 127 is a lead screw with a through hole, and the second drive shaft 1241 has a threaded through hole. The second drive shaft 1241 is located on the lead screw and meshes with the lead screw; the first drive shaft 1231 passes through the threaded through hole and the through hole and is connected to the output end of the rotor motor 125 for force transmission; wherein, the transmission sleeve 128 is attracted to the second drive shaft 1241 under the action of the adsorption component 129, and the transmission sleeve 128 rotates under the drive of the four-bar linkage 113 mechanism to make the second drive shaft rotate, and the second drive shaft 1241 drives the second blade 124 to move axially under the threaded engagement of the lead screw.

[0087] like Figure 10 As shown, in some embodiments, the lead screw is fixed to the arm 121, and the second drive shaft 1241 meshes with the lead screw. During the rotation of the drive sleeve 128, the drive sleeve 128 drives the second drive shaft 1241 to rotate. Under the action of the threaded engagement with the lead screw, the second drive shaft 1241 moves up and down along the axial direction, thereby realizing the lifting and lowering of the second blade 124.

[0088] like Figure 10 and Figure 11 As shown, in order to achieve the adsorption of the transmission sleeve 128 and the first blade 123, in some embodiments, the adsorption assembly 129 includes an elastic element 1291, a friction element and an electromagnet 1293. The friction element includes two friction plates 1292, which are connected to the inner wall of the transmission sleeve 128 through the elastic element 1291. The electromagnet 1293 is disposed at the end of the friction plates 1292 so that the two friction plates 1292 move closer or further away from each other, thereby clamping or releasing the second transmission shaft 1241.

[0089] like Figure 10 and Figure 11As shown, in some embodiments, the friction plate 1292 is U-shaped, and two U-shaped friction plates 1292 are arranged opposite to each other in the transmission sleeve 128. Each end of the two U-shaped plates is provided with an electromagnet 1293. The two adjacent electromagnets 1293 are opposite in direction. When the electromagnet 1293 is energized, the two adjacent electromagnets attract each other in opposite directions. The elastic element 1291 stretches and drives the friction plate 1292 to move towards the side closer to the second transmission shaft 1241. At this time, the second blade 124 is attracted together with the transmission sleeve 128. When the electromagnet 1293 is de-energized, the two adjacent electromagnets 1293 do not generate interaction force. Under the action of the elastic element 1291, the elastic element 1291 resets and drives the friction plate 1292 to move away from the second transmission shaft 1241. At this time, the second blade 124 separates from the transmission sleeve 128.

[0090] like Figure 10 and Figure 11 As shown, in order to avoid the first blade 123 and the second blade 124 from rotating together and affecting each other, in some embodiments, the second drive shaft 1241 is provided with a bearing 131 near the threaded through hole of the first blade 123. After the first drive shaft 1231 passes through the threaded through hole, the bearing 131 can support the meshing disk 126 of the first blade 123 and play a supporting role. At the same time, it can also prevent the mutual influence between the meshing disk 126 of the first blade 123 and the meshing disk 126 of the second blade 124.

[0091] like Figure 10 and Figure 11 As shown, in order to achieve the force transmission connection between the transmission sleeve 128 and the four-bar linkage 113, in some embodiments, the transmission sleeve 128 is connected to the four-bar linkage 113 through a second transmission member 130. Specifically, the transmission sleeve 128 is connected to the shaft on the third link 1133 through the second transmission member 130, and the second transmission member 130 can be a transmission belt.

[0092] like Figure 10 and Figure 11 As shown, in order to ensure that when the wing 112 rotates 90° under the action of the four-bar linkage 113, the second blade 124 rotates 180° under the action of the four-bar linkage 113, in some embodiments, the radius of the transmission sleeve 128 is half of the outer diameter of the shaft sleeved on the transmission belt, that is, when the shaft rotates 180°, the transmission sleeve 128 rotates 90°.

[0093] like Figure 10 and Figure 11As shown, in order to ensure that the rotor motor 125 drives the first blade 123 and / or the second blade 124 to rotate, in some embodiments, the rotor motor 125 is mounted on the arm 121. The output end of the rotor motor 125 is coaxially connected to the first drive shaft 1231. The rotor motor 125 can drive the first drive shaft 1231 to rotate, and at the same time drive the first blade 123 to rotate. When the first blade 123 and the second blade 124 are engaged and limited to form a single unit by the meshing disc 126, the rotor motor 125 drives the first blade 123 and the second blade 124 to rotate together.

[0094] Therefore, when the wing 112 unfolds, as the four-bar linkage 113 rotates, the shaft connected to the third linkage 1133 rotates, and the rotation of the shaft drives the transmission sleeve 128 connected to the second transmission component 130 to rotate, thereby realizing the unfolding of the arm 121. Specifically, when the rotor motor 125 is energized, the second blade 124 rotates to a state parallel to the arm 121. At this time, the rotor motor 125 is de-energized, causing the first blade 123 and the second blade 124 to stop rotating. When the electromagnet 1293 is energized, the friction plate 1292 is stretched by the elastic element 1291 under the opposite attraction of the electromagnets, causing the friction plate 1292 to move towards the side closer to the second drive shaft 1241. At this time, the transmission sleeve 128 is tightly attached to the second drive shaft 1241 of the second blade 124 to form an integral unit. The rotating shaft connected to the third connecting rod 1133 rotates, and the rotation of the rotating shaft drives the transmission sleeve 128 connected to the second transmission component 130 to rotate. Since the outer diameter of the rotating shaft sleeved on the second transmission component 130 is twice the outer diameter of the transmission sleeve 128, when the rotating shaft rotates 90°, the transmission sleeve 128 rotates 180°. At this time, as the transmission sleeve 128 rotates, the second transmission shaft 1241 rotates and moves upward under the action of the threaded engagement until the meshing disk 126 of the first blade 123 engages with the meshing disk 126 of the second blade 124. Meanwhile, the second transmission shaft of the second blade 124 disengages from the lead screw.

[0095] like Figure 10 and Figure 11As shown, after the first blade 123 and the second blade 124 are deployed, the electromagnet 1293 is de-energized and exerts no force. Under the action of the elastic element 1291, the friction plate 1292 moves away from the second drive shaft 1241. At this time, the transmission sleeve 128 separates from the second drive shaft 1241 of the second blade 124, that is, the transmission sleeve 128 and the second blade 124 are decoupled. The rotor motor 125 drives the first blade 123 and the second blade 124 to rotate together. Since the first blade 123 and the second blade 124 generate lift, the meshing disk 126 of the second blade 124 will stick tightly to the meshing disk 126 of the first blade 123, creating a self-locking effect. Furthermore, the upward rotation direction of the second drive shaft 1241 is opposite to the rotation direction of the second blade 124. The torque generated by the resistance of the rotation of the second blade 124 is in the same direction as the upward movement of the second drive shaft 1241. Even if the meshing disc 126 of the second drive shaft 1241 becomes loose, it will automatically lock due to the resistance. It has a double self-locking effect.

[0096] like Figure 10 and Figure 11 As shown, in some other embodiments, when the wing 112 is folded, as the four-bar linkage 113 rotates, the shaft connected to the third linkage 1133 rotates, and the rotation of the shaft drives the transmission sleeve 128 connected to the second transmission member 130 to rotate, thereby realizing the folding of the arm 121. Specifically, when the rotor motor 125 is energized, the second blade 124 rotates to a state parallel to the arm 121. At this time, the rotor motor 125 is de-energized, causing the first blade 123 and the second blade 124 to stop rotating. When the electromagnet 1293 is energized, the friction plate 1292 is stretched by the elastic element 1291 under the opposite attraction of the electromagnets, causing the friction plate 1292 to move towards the side closer to the second drive shaft 1241. At this time, the transmission sleeve 128 is tightly attached to the second drive shaft 1241 of the second blade 124 to form an integral unit. The rotating shaft connected to the third connecting rod 1133 rotates, and the rotation of the rotating shaft drives the transmission sleeve 128 connected to the second transmission component 130 to rotate. Since the outer diameter of the rotating shaft sleeved on the second transmission component 130 is twice the outer diameter of the transmission sleeve 128, when the rotating shaft rotates 90°, the transmission sleeve 128 rotates 180°. At this time, as the transmission sleeve 128 rotates, the second transmission shaft 1241 rotates and moves downward under the action of the threaded engagement until the meshing disk 126 of the first blade 123 separates from the meshing disk 126 of the second blade 124. At this time, the folding of the first blade 123 and the second blade 124 is completed.

[0097] like Figure 10 and Figure 11As shown, after the first blade 123 and the second blade 124 are folded, the electromagnet 1293 is de-energized and has no force. Under the action of the elastic element 1291, the friction plate 1292 is reset and moves away from the second drive shaft 1241. At this time, the transmission sleeve 128 is separated from the second drive shaft 1241 of the second blade 124, that is, the transmission sleeve 128 and the second blade 124 are decoupled.

[0098] The second aspect of this application, as Figure 1 To be continued Figure 3 A flying car is provided, including a body 200 and the aforementioned compound wing system 100. The body 200 is equipped with wheels 210 connected to it. The body 200 has a stepped portion, and the compound wing system 100 is disposed on the stepped portion, so that the upper surface of the compound wing system 100 is flush with the upper surface of the vehicle's front. This flying car employs the aforementioned compound wing system 100. The specific structure of the compound wing system 100 is as described in the above embodiments. Since the compound wing system 100 adopts all the technical solutions of all the above embodiments, it possesses at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be elaborated further here.

[0099] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0100] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0101] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0102] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined with "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0103] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. A compound wing system for an aircraft, characterized by, The application relates to a foldable aircraft, which comprises a wing assembly, a rotor assembly and a fuselage. The wing assembly comprises a wing folding mechanism and two wings rotatably connected to the aircraft, the wing comprises a wing surface and a four-bar linkage mechanism arranged in the inner cavity of the wing surface, the wing folding mechanism is in force transmission connection with the four-bar linkage mechanism, the four-bar linkage mechanism comprises a first connecting rod, a second connecting rod and a third connecting rod, the first connecting rod is parallel to the second connecting rod, and the third connecting rod is arranged at an angle with respect to the first connecting rod and the second connecting rod, the wing folding mechanism comprises a wing driving member and a wing transmission assembly driven by the wing driving member, the main output end of the wing transmission assembly is coaxially connected to the first connecting rod or the second connecting rod in one of the four-bar linkage mechanisms, and the driven output end of the wing transmission assembly is coaxially connected to the first connecting rod or the second connecting rod in the other four-bar linkage mechanism, the wing is provided with more than one wing rib, the wing rib is provided with two parallel sliding grooves, the first connecting rod penetrates through one of the sliding grooves, and the second connecting rod penetrates through the other sliding groove, one of the first connecting rod and the second connecting rod in the same four-bar linkage mechanism penetrates through the sliding groove and is fixedly connected to the corresponding wing rib, and the other one is in sliding connection with the corresponding sliding groove. The rotor assembly comprises a machine arm parallel to the aircraft and two groups of blade assemblies respectively arranged at the two ends of the machine arm, the machine arm is rotatably arranged on the third connecting rod and is arranged at an angle with respect to the third connecting rod. The two wings are rotated to be parallel or perpendicular to the aircraft under the drive of the wing folding mechanism, and one of the connecting rods in the four-bar linkage mechanism is rotated to be parallel or perpendicular to the wing under the drive of the wing folding mechanism.

2. The compound wing system of claim 1, wherein, The wing transmission assembly comprises a driving gear coaxially arranged on the output end of the wing driving member and coaxially connected to the first connecting rod or the second connecting rod in one of the four-bar linkage mechanisms, a steering gear in mesh with the driving gear, and a passive gear in transmission connection with the first connecting rod or the second connecting rod in the other four-bar linkage mechanism through a first transmission member. The blade assembly comprises a first blade provided with a first transmission shaft, a second blade provided with a second transmission shaft, the second blade is arranged at an angle with respect to the first blade in the height direction and is in force transmission connection with the first blade, and a rotor motor with an output end in force transmission connection with the first transmission shaft or the second transmission shaft. The first blade and the second blade are both provided with engagement discs extending in the circumferential direction, the engagement disc of the first blade is in mesh with the engagement disc of the second blade, so that the second blade is in force transmission connection with the first blade. The blade assembly further comprises a lifting transmission member acting on the first blade or the second blade, a transmission sleeve in force transmission connection with the four-bar linkage mechanism, the second transmission shaft penetrates through the transmission sleeve, and an adsorption assembly with a first end acting on the transmission sleeve and a second end acting on the first blade or the second blade, so that the first blade or the second blade is adsorbed or separated from the transmission sleeve.

3. The compound wing system of claim 1 or 2, wherein, ​ ​ ​ ​ 4. The compound wing system of claim 3, wherein, ​ 5. The compound wing system of claim 4, wherein, ​ ​ ​ ​ The first paddle or the second paddle is driven by the lifting force transmission member to move axially to separate the second paddle from the first paddle; the first paddle or the second paddle is adsorbed to the transmission sleeve by the adsorption assembly, and the transmission sleeve is driven by the four-bar linkage mechanism to rotate to drive the first paddle and the second paddle to rotate to a state of at least partially overlapping in horizontal projection.

6. The compound wing system of claim 5, wherein, The lifting force transmission member is a lead screw, the lead screw is provided with a through hole, the second transmission shaft is provided with a threaded hole, and the second transmission shaft is arranged on the lead screw and engaged with the lead screw; The first transmission shaft is arranged in the through hole and the threaded hole and is connected in force transmission with the output end of the rotor motor; the transmission sleeve is adsorbed to the second transmission shaft by the adsorption assembly, the transmission sleeve is driven by the four-bar linkage mechanism to rotate to drive the second transmission shaft to rotate, and the second transmission shaft is driven by the threaded cooperation of the lead screw to drive the second paddle to move axially.

7. The compound wing system of claim 6, wherein, The adsorption assembly comprises: an elastic member; a friction member comprising two friction plates, the friction plates being connected to the inner wall of the transmission sleeve by the elastic member; an electromagnet arranged at the end of the friction plate to make the two friction plates approach or move away from each other to clamp or release the second transmission shaft.

8. A flying car characterized by, It comprises: a vehicle body provided with a stepped portion; the composite wing system according to any one of claims 1-7 is arranged on the stepped portion.

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