Butt joint guiding device of split type composite wing hovercar

Abstract

The invention discloses a butt joint guiding device of a split type composite wing hovercar, which comprises a shell of a circular truncated cone type structure, and the lower bottom surface of the shell is connected with the bottom of a flying body; the locking devices are symmetrically arranged in the shell in a sliding mode, and the locking devices can selectively retract into or penetrate out of the two sides of the shell; one end of the second butt joint mechanism is connected with the passenger compartment, and a containing cavity is formed in the second butt joint mechanism; wherein the shell is matched with the containing cavity, and the locking device and the second butt joint mechanism can be selectively clamped or separated. The system has the advantages that accurate and rapid butt joint between the flight unit and the passenger compartment can be achieved, rapid switching between the flight mode and the driving mode of the hovercar is achieved, and the butt joint precision and reliability are high.

Description

Technical Field

[0001] The present invention relates to the technical field of electric manned aircraft, and more specifically to a docking guide device for a split composite-wing flying car. Background Art

[0002] At present, urban roads are crowded, daily commuting time is long, and cargo transportation is inconvenient, which has become a common problem in cities. The advent of split composite wing flying cars can alleviate this problem. Split composite wing flying cars have two modes: flight mode and driving mode. The flight mode consists of a flight unit and a passenger compartment, and the driving mode consists of a passenger compartment and a wire-controlled chassis. The two modes can realize air flight and ground driving. The two modes can be switched freely through the docking guide device.

[0003] Most of the existing docking mechanisms are traditional hook slots, rod slots, pin slots, and lock core slots. Even if the flying body and the passenger cabin are stationary, they cannot achieve fast and high-precision positioning docking due to airflow and natural wind disturbances. They have certain limitations in terms of high reliability, high redundancy, light weight, and low space occupation. In addition, the docking is hard contact and is difficult to adapt to multiple rapid docking. Therefore, there is an urgent need for a docking guide device for a split flying car with high flexibility, high redundancy, high precision, and strong comprehensive performance. Summary of the invention

[0004] The purpose of the present invention is to design and develop a docking guide device for a split-type composite-wing flying car, which reduces hard contact through a truncated cone-shaped shell and, through mutual matching with a second docking mechanism, relieves descending pressure and improves docking stability and accuracy.

[0005] The technical solution provided by the present invention is: A docking guide device for a split composite wing flying car, comprising: A shell having a truncated cone structure, wherein the lower bottom surface of the shell is connected to the bottom of the flying body; A locking device, which is symmetrically and slidably arranged in the housing, and the locking device can be selectively received in or passed through two sides of the housing; A second docking mechanism, one end of which is connected to the passenger compartment, and a receiving cavity is provided inside the second docking mechanism; The shell and the accommodating cavity match each other, and the locking device and the second docking mechanism can be selectively engaged or separated.

[0006] Preferably, it also includes: A seeker, which is detachably arranged on the upper bottom surface of the shell and is used to seal the shell; The shell is a hollow structure, and two through holes are symmetrically arranged in the circumferential direction of the shell.

[0007] Preferably, the locking device comprises: Two locking finger supports are symmetrically arranged in the housing and are hollow structures; Two guide rails, which are respectively arranged inside the two locking finger supports; Wherein, the two locking finger supports are respectively arranged corresponding to the two through holes.

[0008] Preferably, the locking device further comprises: Two motor seats are symmetrically arranged between the two locking finger supports, and the two motor seats are respectively connected to the adjacent locking finger supports; Two servo motors are respectively fixed on the outsides of the two motor seats, and the power output ends of the two servo motors penetrate into the two motor seats.

[0009] Preferably, the locking device further comprises: Two active bevel gears, which are respectively fixed to the power output ends of the two servo motors; Two ball screws, one end of which is rotatably supported on two motor seats; Two driven bevel gears are respectively fixed to one end of the two ball screws, and the two driven bevel gears are respectively meshed with the two driving bevel gears; Two locking fingers, which are slidably disposed in the two locking finger supports, and the two locking fingers can be selectively moved closer to or farther from each other, and both locking fingers are provided with a central through hole; Two lead screw nuts, which respectively cooperate with the two ball screws, and the two lead screw nuts are respectively fixed on the two locking fingers; The other ends of the two ball screws are rotatably arranged in the central through hole, and the two locking fingers can be selectively passed through the two through holes respectively.

[0010] Preferably, the second docking mechanism comprises: The upper connecting plate is a ring-shaped structure; The lower connecting plate is an annular structure, and the lower connecting plate and the upper connecting plate are symmetrically spaced apart.

[0011] Preferably, the second docking mechanism further includes: Two supporting devices are symmetrically arranged between the upper connecting plate and the lower connecting plate, and both supporting devices are provided with locking grooves; Two buffer devices are symmetrically arranged between the upper connecting plate and the lower connecting plate, and the two buffer devices are arranged at intervals between the two supporting devices; Two universal balls, which are respectively fixed on opposite sides of the two buffer devices; Wherein, a receiving cavity is formed between the upper connecting plate, the lower connecting plate, the two supporting devices and the two buffer devices, and the two locking fingers can selectively pass through the two locking grooves.

[0012] Preferably, the inner diameter of the upper connecting plate is the same as the diameter of the lower bottom surface of the shell, and the inner diameter of the lower connecting plate is larger than the diameter of the guide head.

[0013] Preferably, it also includes: a first pressure sensor, disposed on the seeker head, for monitoring the contact pressure between the shell and the passenger compartment; a second pressure sensor, disposed in the locking groove, for monitoring the contact pressure between the locking finger and the locking groove; a laser distance measuring sensor, which is detachably disposed in the housing and is used to monitor the relative distance between the flying object and the passenger cabin; a gyroscope, which is detachably disposed in the housing and is used to monitor the angular deviation during the docking process between the flying object and the crew cabin; A controller connected to the first pressure sensor, the second pressure sensor, the laser ranging sensor and the gyroscope, and used for receiving and processing data; Wherein, a laser hole is arranged on the seeker at a position relative to the laser ranging sensor.

[0014] Preferably, the shell is made of carbon fiber composite material.

[0015] The beneficial effects of the present invention are: The present invention designs and develops a docking guide device for a split-type composite-wing flying car, which adopts a truncated cone-shaped shell and a universal ball to achieve soft contact to achieve docking. Under the premise of meeting the reliability of the device, it can realize multiple high-precision docking and separation functions, and solves the problems of low redundancy, complex structure, and large mass of the current docking device. Through the monitoring of multiple sensors, more accurate docking position and attitude control can be achieved. Compared with the existing docking that only relies on mechanical mechanisms and simple guide surfaces, the docking accuracy can be significantly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The figure is a schematic diagram of the assembly structure of the docking guide device of the split-type composite-wing flying car of the present invention.

[0017] Figure 2 It is a structural schematic diagram of the first docking mechanism of the present invention.

[0018] Figure 3 It is a schematic diagram of the half-section structure of the first docking mechanism of the present invention.

[0019] Figure 4 It is a schematic structural diagram of the locking device of the present invention.

[0020] Figure 5 It is a schematic cross-sectional structural diagram of the locking device of the present invention.

[0021] Figure 6 It is a schematic diagram of the explosion structure of the first docking mechanism of the present invention.

[0022] Figure 7 It is a structural schematic diagram of the second docking mechanism of the present invention.

[0023] Figure 8 It is a schematic diagram of the exploded structure of the second docking mechanism of the present invention. DETAILED DESCRIPTION

[0024] The present invention is further described in detail below so that those skilled in the art can implement it according to the description.

[0025] like Figure 1 As shown, the present invention provides a docking guide device for a split composite wing flying car, comprising: A first docking mechanism 100 and a second docking mechanism 200; like Figure 2~Figure 6 As shown, the first docking mechanism 100 includes a shell 101 and a locking device. The shell 101 is a truncated cone structure, and the lower bottom surface of the shell 101 is connected to the bottom of the flying body 300. The locking device is symmetrically and slidably arranged in the shell 101, and can be selectively retracted into or out of the two sides of the shell 101, so as to realize extension and retraction in the horizontal direction relative to the shell 101.

[0026] In this embodiment, the shell 101 includes an integrally arranged side surface and a lower bottom surface, that is, the shell 101 is a hollow structure, and two through holes are symmetrically arranged in the circumferential direction of the shell 101. A guide head 103 is connected to the upper bottom surface of the shell 101 through internal and external threads, which is used to seal the shell 101 while guiding the first docking mechanism 100 and the second docking mechanism 200 to achieve docking.

[0027] The locking device includes a power device, a transmission device and a locking assembly. The power device includes two motor seats 120 and two servo motors 121. The transmission device includes two active bevel gears 131, two ball screws 133, two screw nuts 134 and two driven bevel gears 132. The locking assembly includes two locking finger supports 110 and two locking fingers 111. The structures of the two motor seats 120 and the two locking finger supports 110 are exactly the same. The two motor seats 120 are bolted together with the lower bottom surface of the housing 101 through the bottom seat holes, and the two motor seats 120 are in contact with each other. Both motor seats 120 are hollow structures, and the two The side of the motor seats 120 away from each other is an open structure, and the two sides of the two motor seats 120 are connected to each other through side seat holes, respectively. The two locking finger supports 110 are bolted together with the lower bottom surface of the shell 101 through the bottom seat holes, and the two locking finger supports 110 are hollow structures, that is, the interiors of the two locking finger supports 110 are connected to the interiors of the two motor seats 120 in a one-to-one correspondence, and the two locking finger supports 110 and the two motor seats 120 are arranged in a straight line, and the side of the two locking finger supports 110 away from each other is an inclined structure parallel to the waist of the shell 101, and the two locking finger supports 110 are relative to the two Through holes are provided; locking fingers 111 are slidably provided in the two locking finger supports 110, and the two locking fingers 111 can be selectively moved closer to or farther away from each other, and both locking fingers 111 are provided with a central through hole; one end of the two ball screws 133 is rotated by a deep groove ball bearing embedded in the side wall of the motor seat 120, and the axial displacement is fixedly limited by the stepped optical axis part of the ball screw 133, and the other end is rotatably provided in the central through hole by a single-row angular contact bearing, and two screw nuts 134 are respectively matched with the two ball screws 133, and the two screw nuts 134 are respectively integrated with the two locking fingers; the The two servo motors 121 are respectively vertically arranged on the outside of the two motor seats 120, and the power output ends of the two servo motors 121 penetrate into the two motor seats 120, and the two driving bevel gears 131 are respectively connected to the motor shafts of the servo motors 121 by screws, and the driven bevel gear 132 is fixed to the optical axis part at one end of the ball screw by screws, and the driven bevel gear 132 and the driving bevel gear 131 are meshed with each other, so that the servo motor 121 drives the driving bevel gear 131 to rotate, and then the driven bevel gear 132 drives the ball screw 133 to rotate, and the horizontal extension and retraction of the locking finger 111 is realized by the rotation of the ball screw 133.

[0028] In this embodiment, a guide rail 112 is provided inside the locking finger support 110 , and a guide rail groove is provided at the bottom of the locking finger 111 , so as to realize smooth horizontal extension and retraction of the locking finger 111 .

[0029] When the two locking fingers 111 are away from each other, they can pass through two through holes, that is, pass through the housing 101, so as to cooperate with the second docking mechanism 200 to achieve docking.

[0030] like Figure 7 , Figure 8 As shown, the second docking mechanism 200 is embedded in the top of the passenger cabin 400, which can realize seamless docking between the flying body 300 and the passenger cabin 400, reducing wind resistance in the flight mode, and the second docking mechanism 200 includes an upper connecting plate 201, a lower connecting plate 202, two supporting devices 210 and two buffer devices 220, the upper connecting plate 201 and the lower connecting plate 202 are both annular structures, and the lower connecting plate 202 and the upper connecting plate 201 are symmetrically spaced to form the outer contour skeleton of the second docking mechanism 200, the two supporting devices 210 are symmetrically arranged between the upper connecting plate 201 and the lower connecting plate 202, and the two supporting devices 210 are both provided with locking grooves 211, and the locking grooves 220 are arranged at the same time. The size of 11 is the same as that of the locking finger 111, and the two locking fingers 111 can be optionally passed through two locking grooves 211; the two buffer devices 220 are symmetrically arranged between the upper connecting plate 201 and the lower connecting plate 202, and the two buffer devices 220 are arranged at intervals between the two supporting devices 210; universal balls 221 are arranged on opposite sides of the two buffer devices 220 through internal and external threads, and when the shell 101 descends and docks with the second docking mechanism 200, the shell 101 contacts the universal balls 221 to achieve the functions of buffering pressure and guiding docking; wherein, a accommodating cavity is formed between the upper connecting plate 201, the lower connecting plate 202, the two supporting devices 210 and the two buffer devices 220.

[0031] In this embodiment, the inner diameter of the upper connecting plate 201 is the same as the diameter of the lower bottom surface of the shell 101 , and the inner diameter of the lower connecting plate 202 is slightly larger than the diameter of the guide head 103 , so as to facilitate accommodating the first docking mechanism 100 .

[0032] In this embodiment, two extension plates 102 are symmetrically arranged on the lower bottom surface of the shell 101 near the side surface, and the shell 101 is bolted to the bottom of the flying body 300 through the two extension plates 102 .

[0033] A pressure sensor is disposed inside the seeker head 103 , and during the descent and docking process of the shell 101 , the contact pressure between the seeker head 103 and the passenger compartment 400 can be monitored in real time to determine whether the seeker head 103 has been lowered into place, thereby forming a closed-loop feedback control.

[0034] A pressure sensor is disposed inside the locking groove 211 . During the extension and retraction process of the locking finger 111 , the plane pressure inside the locking finger 111 and the locking groove 211 can be monitored in real time to determine whether the locking is performed, thereby forming a closed-loop feedback control.

[0035] A laser ranging sensor 141 and a gyroscope 142 are arranged inside the shell 101. The laser ranging sensor 141 is connected to the threaded hole on the lower bottom surface of the shell 101 through the bottom external threaded shaft, and a through laser hole is arranged on the guide head 103 at a position relative to the laser ranging sensor 141 to facilitate the ranging of the laser ranging sensor 141. During the docking process, the laser ranging sensor 141 can accurately measure the relative distance between the flying body 300 and the passenger cabin 400, facilitate the attitude control of the flying body 300, and improve the docking accuracy and smoothness; the gyroscope 142 is bolted to the lower bottom surface of the shell 101 through the bottom threaded base, and can monitor the angle deviation during the docking process in real time, achieve more accurate docking position and attitude control, and improve docking accuracy.

[0036] In this embodiment, the gyroscope 142 is a high-precision gyroscope.

[0037] The laser distance measuring sensor 141 and the gyroscope 142 are respectively arranged on both sides of the locking device.

[0038] The first docking mechanism 100 adopts a 60-degree frustoconical shell. Due to its hyperbolic geometric shape, the stress distribution at the junction of the cone and the groove can be smooth, and the universal ball 221 is installed on the second docking mechanism 200 to achieve flexible and smooth docking.

[0039] In this embodiment, the housing 101 is made of carbon fiber composite material, which greatly reduces the weight of the docking mechanism while ensuring structural strength and rigidity.

[0040] A docking guide device for a split-type composite-wing flying car designed and developed by the present invention can achieve rapid and accurate docking of a flying body and a passenger cabin, with high reliability and redundancy. The first docking mechanism uses a truncated cone-shaped shell to reduce hard contact, and descends smoothly at a 60-degree angle along the supporting device. A universal ball is arranged on the buffer device to relieve the descending pressure, and the overall space occupied is small. The first docking mechanism can also be used as a support frame to facilitate idle parking of the flying body. Through the monitoring of multiple sensors, more accurate docking position and attitude control can be achieved. Compared with the existing docking that only relies on mechanical mechanisms and simple guide surfaces, the docking accuracy can be significantly improved.

[0041] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and the implementation modes. They can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily implemented. Therefore, without departing from the general concept defined by the claims and the scope of equivalents, the present invention is not limited to the specific details and the embodiments shown and described herein.

Claims

1. A docking guide device for a split composite wing flying car, characterized in that: include: A shell having a truncated cone structure, wherein the lower bottom surface of the shell is connected to the bottom of the flying body; A locking device, which is symmetrically and slidably arranged in the housing, and the locking device can be selectively received in or passed through two sides of the housing; A second docking mechanism, one end of which is connected to the passenger compartment, and a receiving cavity is provided inside the second docking mechanism; The shell and the accommodating cavity match each other, and the locking device and the second docking mechanism can be selectively engaged or separated.

2. The docking guide device for a split composite wing flying car according to claim 1, characterized in that: Also includes: A seeker, which is detachably arranged on the upper bottom surface of the shell and is used to seal the shell; The shell is a hollow structure, and two through holes are symmetrically arranged in the circumferential direction of the shell.

3. The docking guide device for the split composite wing flying car according to claim 2, characterized in that: The locking device comprises: Two locking finger supports are symmetrically arranged in the housing and are hollow structures; Two guide rails, which are respectively arranged inside the two locking finger supports; Wherein, the two locking finger supports are respectively arranged corresponding to the two through holes.

4. The docking guide device for the split composite wing flying car according to claim 3, characterized in that: The locking device also includes: Two motor seats are symmetrically arranged between the two locking finger supports, and the two motor seats are respectively connected to the adjacent locking finger supports; Two servo motors are respectively fixed on the outsides of the two motor seats, and the power output ends of the two servo motors penetrate into the two motor seats.

5. The docking guide device for the split composite wing flying car according to claim 4, characterized in that: The locking device also includes: Two active bevel gears, which are respectively fixed to the power output ends of the two servo motors; Two ball screws, one end of which is rotatably supported on two motor seats; Two driven bevel gears are respectively fixed to one end of the two ball screws, and the two driven bevel gears are respectively meshed with the two driving bevel gears; Two locking fingers, which are slidably disposed in the two locking finger supports, and the two locking fingers can be selectively moved closer to or farther from each other, and both locking fingers are provided with a central through hole; Two lead screw nuts, which respectively cooperate with the two ball screws, and the two lead screw nuts are respectively fixed on the two locking fingers; The other ends of the two ball screws are rotatably arranged in the central through hole, and the two locking fingers can be selectively passed through the two through holes respectively.

6. The docking guide device for the split composite wing flying car according to claim 5, characterized in that: The second docking mechanism comprises: The upper connecting plate is a ring-shaped structure; The lower connecting plate is an annular structure, and the lower connecting plate and the upper connecting plate are symmetrically spaced apart.

7. The docking guide device for the split composite wing flying car according to claim 6, characterized in that: The second docking mechanism also includes: Two supporting devices are symmetrically arranged between the upper connecting plate and the lower connecting plate, and both supporting devices are provided with locking grooves; Two buffer devices are symmetrically arranged between the upper connecting plate and the lower connecting plate, and the two buffer devices are arranged at intervals between the two supporting devices; Two universal balls, which are respectively fixed on opposite sides of the two buffer devices; Wherein, a receiving cavity is formed between the upper connecting plate, the lower connecting plate, the two supporting devices and the two buffer devices, and the two locking fingers can selectively pass through the two locking grooves.

8. The docking guide device for the split composite wing flying car according to claim 7, characterized in that: The inner diameter of the upper connecting plate is the same as the diameter of the lower bottom surface of the shell, and the inner diameter of the lower connecting plate is larger than the diameter of the guide head.

9. The docking guide device for a split composite wing flying car as claimed in claim 8, characterized in that: Also includes: a first pressure sensor, disposed on the seeker head, for monitoring the contact pressure between the shell and the passenger compartment; a second pressure sensor, disposed in the locking groove, for monitoring the contact pressure between the locking finger and the locking groove; a laser distance measuring sensor, which is detachably disposed in the housing and is used to monitor the relative distance between the flying object and the passenger cabin; a gyroscope, which is detachably disposed in the housing and is used to monitor the angular deviation during the docking process between the flying object and the crew cabin; A controller connected to the first pressure sensor, the second pressure sensor, the laser ranging sensor and the gyroscope, and used for receiving and processing data; Wherein, a laser hole is arranged on the seeker at a position relative to the laser ranging sensor.

10. The docking guide device for the split composite wing flying car according to claim 9, characterized in that: The shell is made of carbon fiber composite material.

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