Separating coupling mechanism, land vehicle and traffic device

Abstract

This application discloses a separation and connection mechanism, a land vehicle, and transportation equipment, relating to the field of flying car technology. The separation and connection mechanism is located on the body of the land vehicle and is used to connect or separate from an aircraft. The aircraft is equipped with a connection mechanism and a motion guide. The separation and connection mechanism includes a support assembly and a guide structure. The support assembly has an opening that gradually widens outwards to guide the connection mechanism to move towards the center of the opening. The aircraft can sway horizontally towards the support assembly as the connection mechanism moves, thereby correcting the aircraft's direction of movement. The guide structure guides the motion guide to move along its length, ensuring that the aircraft's movement within the vehicle body is along the length of the guide structure. This helps to straighten the aircraft and reduce the likelihood of it colliding with the vehicle body or sustaining damage.

Description

Technical Field

[0001] This application relates to the field of flying car technology, and in particular to a separation and connection mechanism, a land vehicle, and transportation equipment. Background Technology

[0002] Flying cars have always been a key research area, and with the development of pure electric vertical takeoff and landing aircraft, flying cars have ushered in a new research boom. Flying cars possess both flying and land-based functions, and they come in many forms. One form of flying car decouples the land and flight scenarios. It consists of two parts: a land-based body (also known as a land vehicle) and an aircraft. The land-based body can drive on the road like a car, while the aircraft flies in the sky when needed. At the same time, the land-based body can also be combined with the aircraft to form a complete flying car.

[0003] In the existing technology, during the process of the aircraft being pulled into the vehicle body, the aircraft has a large positional deviation in the horizontal direction, and the aircraft is also tilted and moved inside the vehicle body. This often leads to situations where the aircraft collides with the vehicle body and is damaged. Utility Model Content

[0004] The main purpose of this application is to propose a separation and connection mechanism, a land vehicle, and a transportation device, which aims to solve the problem in the prior art that the aircraft has a large positional deviation in the horizontal direction and the aircraft also moves at an angle within the vehicle body, which often leads to the aircraft colliding with the vehicle body and the aircraft being damaged.

[0005] To achieve the above objectives, the separation and connection mechanism proposed in this application is located on the body of a land vehicle and is used to connect or separate from the aircraft. The aircraft is equipped with a connection mechanism and a motion guide. The separation and connection mechanism includes:

[0006] A bracket assembly, mounted on the body of a land vehicle, has an opening that gradually widens outwards, and a guide portion for guiding the connecting mechanism to move towards the center of the opening; and

[0007] The guide structure is used to guide the motion guide to move along the length of the guide structure. The aircraft moves horizontally along the length of the guide structure as the motion guide moves.

[0008] This application also proposes a land vehicle including a disengagement mechanism.

[0009] This application also proposes a transportation device, including aircraft and land vehicles.

[0010] This application also proposes a transportation device, including an aircraft and a separation and connection mechanism.

[0011] The technical solution of this application employs an opening in the support assembly, with the opening gradually widening outwards to guide the connecting mechanism to move towards the center of the opening. The aircraft can sway horizontally toward the support assembly as the connecting mechanism moves, thereby correcting the aircraft's direction of movement. Furthermore, a guide structure is provided to guide the motion guide to move along the length of the guide structure, ensuring that the aircraft's movement within the vehicle body is along the length of the guide structure. This allows the aircraft to be aligned, reducing the likelihood of the aircraft colliding with the vehicle body or sustaining damage. Attached Figure Description

[0012] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0013] Figure 1 A schematic diagram of the structure of an embodiment of the transportation equipment provided in this application;

[0014] Figure 2 A bottom view of an embodiment of the transportation equipment provided in this application;

[0015] Figure 3 A top view of an embodiment of the transportation equipment provided in this application;

[0016] Figure 4 A schematic diagram of the structure of a support assembly in a separation and connection mechanism provided in this application;

[0017] Figure 5 A schematic diagram of the structure of the connecting mechanism when it is not engaged in the separation and connection mechanism in one embodiment of the separation and connection mechanism provided in this application;

[0018] Figure 6 A schematic diagram of the structure of the connecting mechanism when it enters the separating and connecting mechanism in one embodiment of the separating and connecting mechanism provided in this application;

[0019] Figure 7 A schematic diagram of the structure of the connecting mechanism when it enters the opening in one embodiment of the separation and connection mechanism and the connecting mechanism provided in this application;

[0020] Figure 8 A rear view of a support assembly in an embodiment of the separation and connection mechanism provided in this application;

[0021] Figure 9A three-dimensional structural schematic diagram of an embodiment of the connection mechanism for an aircraft in the transportation equipment provided in this application;

[0022] Figure 10 A top view of a motion guide component touching an inlet trough section in one embodiment of the transportation equipment provided in this application;

[0023] Figure 11 A top view of a motion guide component in an embodiment of the transportation equipment provided in this application as it moves in the guide channel section;

[0024] Figure 12 A top view of a motion guide member in one embodiment of the transportation equipment provided in this application as it enters the chute section from the guide section;

[0025] Figure 13 A front view of a motion guide member touching an inlet groove section in one embodiment of the transportation equipment provided in this application;

[0026] Figure 14 A front view of a motion guide member in one embodiment of the transportation equipment provided in this application as it enters the chute section from the guide section;

[0027] Figure 15 A three-dimensional structural diagram of the motion guide component touching the guide groove section in another embodiment of the transportation equipment provided in this application;

[0028] Figure 16 A top view of the motion guide component touching the guide groove section in another embodiment of the transportation equipment provided in this application;

[0029] Figure 17 A three-dimensional structural diagram of the motion guide member in another embodiment of the transportation equipment provided in this application as it enters the chute section from the guide section.

[0030] Explanation of icon numbers:

[0031] 3000, Transportation equipment;

[0032] 2000, Aircraft; 2001, Connecting Mechanism; 2011, Oscillating Body; 2012, Mounting Body; 2013, Elastic Return Component;

[0033] 2002, Motion guide component; 2021, Guide body; 2022, Load-bearing body;

[0034] 1000. Land vehicles; 1340. Vehicle body;

[0035] 1900, Separation and connection mechanism; 1001, Locking mechanism; 1010, Support assembly; 1011, Support body; 1014, Receiving body; 1273, Opening; 1274, Inlet;

[0036] 1310. Guide structure component; 1312. Slide section; 1313. Guide groove section.

[0037] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0038] The technical solutions of 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.

[0039] It should be noted that if the embodiments of this application involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0040] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are 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, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0041] Reference Figure 1 and Figure 2 In one embodiment of this application, the vehicle includes a land vehicle 1000 and an aircraft 2000. The land vehicle 1000 is used for driving on the ground, and the aircraft 2000 is used for flying in the air after detaching from the land vehicle 1000. The aircraft 2000 and the land vehicle 1000 can be combined and separated. Figure 1As shown, when the aircraft 2000 is combined with the land vehicle 1000, the land vehicle 1000 can carry the aircraft 2000; when the aircraft 2000 is separated from the land vehicle, the aircraft 2000 can detach from the land vehicle 1000 and fly independently, and the land vehicle 1000 can detach from the aircraft 2000 and drive independently.

[0042] In some implementations, the aircraft 2000 may be an aircraft 2000 powered by conventional energy sources such as fuel, or it may be an aircraft 2000 such as a hybrid electric aircraft 2000, a pure electric aircraft 2000, or a fuel cell electric aircraft 2000.

[0043] In some embodiments, the land vehicle 1000 can be a vehicle powered by conventional energy sources such as gasoline or diesel, or it can be a hybrid electric vehicle, a pure electric vehicle, or a fuel cell electric vehicle. The land vehicle 1000 may have a camouflage compartment suitable for accommodating the aircraft 2000.

[0044] In some embodiments, the land vehicle 1000 is provided with a separation and connection mechanism 1900 for connecting or separating from the aircraft 2000, thereby enabling the land vehicle 1000 to connect or separate from the aircraft 2000.

[0045] Among them, reference Figure 2 The separation and connection mechanism 1900 is equipped with a locking mechanism 1001, and the aircraft 2000 is equipped with a connecting mechanism 2001. The locking mechanism 1001 is used to detachably lock with the connecting mechanism 2001. For example, when the aircraft 2000 needs to be connected with the land vehicle 1000, the locking mechanism 1001 can lock the aircraft 2000 and the land vehicle 1000 together through the connecting mechanism 2001. The locking mechanism 1001 is connected to the land vehicle 1000, and the connecting mechanism 2001 is located on the aircraft 2000, which reduces the added load on the aircraft 2000 due to the weight of the locking mechanism 1001.

[0046] In some implementations, refer to Figures 4 to 7The separation and connection mechanism 1900 includes a support assembly 1010, which is disposed on the body 1340 of the land vehicle 1000. The support assembly 1010 has an opening 1273, which gradually widens outward to guide the connection mechanism 2001 to move towards the center of the opening 1273. The support assembly 1010 has an opening 1273 on one side, which gradually widens outward. When the aircraft 2000 moves towards the land vehicle 1000, the connection mechanism 2001 of the aircraft 2000 enters the opening 1273. Then, the connection mechanism 2001 contacts the inner wall of the opening 1273 and moves towards the center of the opening 1273. The aircraft 2000 can sway horizontally towards the support assembly 1010 as the connection mechanism 2001 moves, thereby correcting the direction of movement of the aircraft 2000. Next, the aircraft 2000 can be pulled by a traction mechanism installed inside the body 1340 of the land vehicle 1000, thereby moving the aircraft 2000 towards the interior of the body 1340. Alternatively, the connecting mechanism 2001 can be locked at the opening 1273 by the locking mechanism 1001, and then the locking mechanism 1001 can be driven to move towards the interior of the body 1340. The movement of the locking mechanism 1001 drives the connecting mechanism 2001 to move, thereby moving the aircraft 2000 towards the interior of the body 1340.

[0047] In some implementations, refer to Figure 3 The separation and connection mechanism 1900 also includes a guide structure 1310, which guides the motion guide 2002 to move along the length of the guide structure 1310. The aircraft 2000 moves horizontally along the length of the guide structure 1310 as the motion guide 2002 moves.

[0048] In some embodiments, there are two guide structures 1310, which are arranged on both sides of the locking mechanism 1001. The aircraft 2000 is provided with two sets of motion guides 2002 corresponding to the two guide structures 1310. During the process of the aircraft 2000 being pulled into the body 1340 of the land vehicle 1000, the two sets of motion guides 2002 move onto the two guide structures 1310 one by one, and each set of motion guides 2002 moves along the length of the guide structure 1310, thereby correcting the overall movement direction of the aircraft 2000 and restricting it to move along the length of the guide structure 1310.

[0049] The aircraft 2000 is towed towards the land vehicle 1000. The connecting mechanism 2001 of the aircraft 2000 contacts the opening 1273 of the support assembly 1010. Then, the connecting mechanism 2001 can enter the center of the opening 1273 against the wall of the opening 1273. Further, a detection device can be installed on the land vehicle 1000 to detect the presence of the connecting mechanism 2001 at the center of the opening 1273 and transmit the detection signal to the drive device of the locking mechanism 1001, causing the drive device to operate. The locking element on the locking mechanism 1001 locks the connecting mechanism 2001, thereby locking the connecting mechanism 2001 at the opening 1273. Afterwards, the connecting mechanism 2001 can be pulled to move the aircraft 2000 towards the interior of the vehicle body 1340 of the land vehicle 1000. The locking element can be configured as a ring structure to lock the connecting mechanism 2001 at the opening 1273.

[0050] Because the positional deviation of the aircraft 2000 is relatively large, there is a gap between the connecting mechanism 2001 and the inner wall surface of the opening 1273. To facilitate the connecting mechanism 2001 contacting the support assembly 1010 and entering the opening 1273, in some embodiments, refer to... Figures 4 to 7 The bracket assembly 1010 also includes an inlet 1274, which communicates with the opening 1273 and is located outside the opening 1273. The outward expansion angle of the inlet 1274 is greater than that of the opening 1273. The inner wall surface of the inlet 1274 is inclined outward relative to the inner wall surface of the opening 1273, allowing the connecting mechanism 2001 to contact and be guided into the opening 1273. The bracket assembly 1010 has a guide portion protruding outward, and the guide portion has the inlet 1274, so that the connecting mechanism 2001 can contact the inner wall surface of the inlet 1274 and enter the opening 1273 along the inner wall surface of the inlet 1274. Optionally, the outward expansion angle of the inlet 1274 can be set between 100 degrees and 120 degrees, and the outward expansion angle of the opening 1273 can be set between 60 degrees and 90 degrees. The inlet 1274 is shaped like the number "8". The connecting mechanism 2001 of the aircraft 2000 can abut against the inner wall of the inlet 1274 and then slide along the inner wall of the inlet 1274 into the inner wall of the opening 1273 until it enters the center of the opening 1273.

[0051] Because the connecting mechanism 2001 of the aircraft 2000 frequently rubs against the guide portion of the support assembly 1010, especially the inlet 1274 and outlet of the guide portion, and even frequently impacts the inlet 1274 and outlet of the guide portion, the guide portion of the support assembly 1010 may break. Therefore, referring to... Figure 4The support assembly 1010 includes a support body 1011 and a receiving body 1014, with the support body 1011 supporting the receiving body 1014. In this application, a guide portion is provided on the receiving body 1014, and the guide portion of the receiving body 1014 has an inlet 1274 and an outlet. If the connecting mechanism 2001 breaks the guide portion of the receiving body 1014, the receiving body 1014 can be removed from the support body 1011 to replace it with a new one, thus completing the replacement of the guide portion. The support body 1011 can support the receiving body 1014, indirectly increasing the strength of the receiving body 1014 and reducing the likelihood of the receiving body 1014 being broken by the connecting mechanism 2001. In some embodiments, refer to... Figure 8 To prevent the support body 1011 from interfering with the connection mechanism 2001 entering the opening 1273 of the housing 1014, the support body 1011 is provided with a flared opening corresponding to the opening 1273 of the housing 1014. The outward flaring angle of the flared opening is the same as or greater than the outward flaring angle of the opening 1273, so as to prevent the support body 1011 from interfering with the connection mechanism 2001 entering the opening 1273 of the housing 1014.

[0052] After the connecting mechanism 2001 enters the center of the opening 1273, the aircraft 2000 can be pulled by the traction mechanism to move towards the interior of the vehicle body 1340 of the land vehicle 1000; the aircraft 2000 enters the vehicle body 1340 of the land vehicle 1000 and moves within the vehicle body 1340. However, it is easy for the aircraft 2000 to tilt and move inside the vehicle body 1340 and collide with the inner wall of the vehicle body 1340. To address this, the land vehicle 1000 of this application is equipped with a separation and connection mechanism 1900 inside the vehicle body 1340, and the separation and connection mechanism 1900 includes a guide structure 1310, as shown in the figure. Figures 10 to 12The guide structure 1310 includes an inlet groove 1313 and a slide section 1312. The inlet groove 1313 is located at the end of the guide structure 1310 facing the aircraft 2000. The inlet groove 1313 is gradually widened outward relative to the slide section 1312 to guide the motion guide 2002 of the aircraft 2000 into the slide section 1312. With this configuration, the aircraft 2000 is pulled towards the interior of the vehicle body 1340, and the motion guide 2002 of the aircraft 2000 enters the inlet groove 1313 of the guide structure 1310. The motion guide 2002 abuts against the inner wall of the guide groove section 1313 and enters the slide section 1312 along the inner wall of the guide groove section 1313. Then, the motion guide 2002 of the aircraft 2000 moves along the length of the guide structure 1310 in the slide section 1312, thereby causing the aircraft 2000 to move along the length of the guide structure 1310 within the vehicle body 1340. This allows the aircraft 2000 to be aligned, reducing the possibility of the aircraft 2000 colliding with the vehicle body 1340 and being damaged. (Refer to...) Figure 10 The guide section 1313 has a trumpet-shaped structure to allow the motion guide 2002 of the aircraft 2000 to slide into the guide section 1313 and enter the slide section 1312 along the inner wall of the guide section 1313. The guide section 1313 can also be inclined downwards relative to the slide section 1312 to form an inclined section. The aircraft 2000's entry from the inclined section into the slide section 1312 allows for fine-tuning of its height within the vehicle body, facilitating its entry into the interior of the vehicle body 1340 of the land vehicle 1000. Optionally, the outer wall of the guide structure 1310 extends outwards with multiple pressure plates, each with threaded holes, allowing the guide structure 1310 to be installed into the interior of the vehicle body 1340 using screws passing through the threaded holes.

[0053] Furthermore, after the connecting mechanism 2001 touches the inlet 1274 and is guided into the center of the opening 1273, the connecting mechanism 2001 moves towards the center of the opening 1273, and the aircraft 2000 as a whole is prone to shifting with the movement of the connecting mechanism 2001. However, if the overall shift of the aircraft 2000 is too large, the aircraft 2000 will enter the vehicle body 1340 at an angle, occupying a large space, and the tail of the aircraft 2000 may easily scrape against the vehicle body 1340. Therefore, referring to... Figures 4 to 7The connecting mechanism 2001 of the aircraft 2000 includes a deflector 2011 and a mounting body 2012. The deflector 2011 is movably connected to the mounting body 2012, and the deflector 2011 is rotatably deflected relative to the mounting body 2012 toward the center of the opening 1273. Specifically, when the aircraft 2000 is pulled toward the vehicle body 1340, the deflector 2011 touches the inner wall of the inlet 1274 and deflects toward the center of the opening 1273. The connecting mechanism 2001 of the aircraft 2000 enters the opening 1273 of the support assembly 1010. The deflector 2011 of the connecting mechanism 2001 can deflect towards the center of the opening 1273. The aircraft 2000 as a whole can remain unchanged or deflect slightly, rather than deflecting significantly. This reduces the space occupied inside the vehicle body 1340 and ensures that the aircraft 2000 moves smoothly inside the vehicle body 1340 without scraping against it.

[0054] In some embodiments, in order to reset the yaw body 2011 and reduce the occurrence of the yaw body 2011 scraping against the vehicle body 1340 or components of the separation engagement mechanism 1900 after separating from the locking mechanism 1001, the connecting mechanism 2001 is further provided with an elastic return member 2013. The elastic return member 2013 is provided on the mounting body 2012 and connected to the yaw body 2011 to return the yaw body 2011 to its original position away from the center of the opening 1273. Specifically, refer to... Figure 9 The number of elastic return members 2013 can be two, and the two elastic return members 2013 are arranged opposite to each other on the mounting body 2012. One end of each elastic return member 2013 is connected to the mounting body 2012, and the other end is connected to the oscillating body 2011. After the oscillating body 2011 is separated from the locking mechanism 1001, the two elastic return members 2013 can return the oscillating body 2011 to the middle position of the two elastic return members 2013, so as to straighten the oscillating body 2011. In some embodiments, the elastic return member 2013 is a spring. The mounting body 2012 can be provided with a latch, and the oscillating body can be designed as a ring, so that one end of the spring can be hooked at the latch and the other end can be hooked in the ring of the oscillating body 2011. The oscillating body 2011 can be rotatably connected to 2012 by rotating a hinge, so that the oscillating body 2011 can rotate relative to the mounting body 2012. Optionally, the end of the oscillating body 2011 near the mounting body 2012 can be configured as a spherical structure, so that the oscillating body 2011 can oscillate and return relative to the mounting body 2012. Alternatively, a spherical bushing can be installed at the end of the oscillating body 2011 near the mounting body 2012, so that the oscillating body 2011 can oscillate and return relative to the mounting body 2012.

[0055] In some embodiments, the motion guide 2002 has at least one guide body 2021 that contacts the inner wall of the guide groove section 1313 and enters the slide section 1312 along the inner wall of the guide groove section 1313. Optionally, the guide body 2021 can be a guide wheel, which can be bolted to the bottom of the aircraft 2000.

[0056] Reference Figure 3 Two sets of motion guides 2002 can be installed on the bottom of the aircraft 2000. These two sets of motion guides 2002 correspond to two guide structures 1310 within the vehicle body 1340. During the process of the aircraft 2000 being pulled into the vehicle body 1340 of the land vehicle 1000, the two sets of motion guides 2002 move one-to-one onto the two guide structures 1310, and each set of motion guides 2002 moves along the length of the guide structure 1310, thereby correcting the overall direction of movement of the aircraft 2000 and restricting its movement to the length of the guide structure 1310. (Refer to...) Figures 10 to 14 Each set of motion guides 2002 is equipped with at least one guide body 2021 so that during the process of the aircraft 2000 being pulled into the body 1340 of the land vehicle 1000, the guide body 2021 can automatically correct its course by contacting the inner wall of the guide groove section 1313 to enter the slide section 1312. When the guide body 2021 enters the slide section 1312, it automatically aligns itself towards the length direction of the guide structure 1310, thereby allowing the guide body 2021 to slide within the slide section 1312. Optionally, the guide body 2021 can be configured as a cylinder, the outer surface of which can contact the inner wall of the guide groove section 1313 and enter the slide section 1312 along the inner wall of the guide groove section 1313. The width of the chute section 1312 can be set to be the same as or slightly larger than the diameter of the guide body 2021, so as to restrict the guide body 2021 from sliding within the chute section 1312.

[0057] Furthermore, due to the large size of the aircraft 2000, in order to move smoothly within the vehicle body 1340, the motion guide 2002 also includes a carrier 2022. The carrier 2022 is located at the bottom of the aircraft 2000 to support it. The carrier 2022 is spaced apart from the guide body 2021 and enters the chute section 1312 as the guide body 2021 moves. Optionally, the carrier 2022 can be a carrier wheel, with the carrier wheel guide body 2021 spaced apart. Multiple carrier wheels can be connected together by a mounting plate and installed together at the bottom of the aircraft 2000. The guide body 2021 enters the chute section 1312 from the guide groove section 1313, and the multiple carrier wheels, carrying the aircraft 2000, slide from the guide body 2021 into the chute section 1312.

[0058] In some implementations, refer to Figures 15 to 17 The guide body 2021 extends along the length of the aircraft 2000 to support it; the end of the guide body 2021 facing the inlet groove section 1313 has a rounded corner structure. Both the guide body 2021 and the support body 2022 can be made of polytetrafluoroethylene (PTFE). The guide body 2021 extends along the length of the aircraft 2000 to support it; the end of the guide body 2021 facing the inlet groove section 1313 has a rounded corner structure. After touching the inner wall of the inlet groove section 1313, the guide body 2021 automatically corrects its direction to face the slide section 1312, and then slides into the slide section 1312 when the connecting mechanism 2001 is pulled into the vehicle body 1340. Optionally, the guide body 2021 can be elliptical in shape, and it can be bolted to the bottom of the aircraft 2000. The end of the guide body 2021 facing the inlet groove 1313 can touch the inner wall of the inlet groove 1313 and enter the slide section 1312 along the inner wall of the inlet groove 1313. The guide body 2021 automatically corrects its direction to be oriented toward the length direction of the guide structure 1310, and can then slide within the slide section 1312.

[0059] The above description is merely an exemplary embodiment of this application and does not limit the patent scope of this application. Any equivalent structural transformations made based on the technical concept of this application and the contents of the specification and drawings of this application, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this application.

Claims

1. A separation and connection mechanism, characterized in that, A vehicle body mounted on a land vehicle, used for connecting or separating from an aircraft, wherein the aircraft is equipped with a connecting mechanism and a motion guide; the separating and connecting mechanism includes: A bracket assembly, disposed on the body of the land vehicle, the bracket assembly having an opening that gradually widens outward to guide the connecting mechanism to move toward the center of the opening; and A guide structure is provided to guide the motion guide to move along the length of the guide structure, and the aircraft moves horizontally along the length of the guide structure as the motion guide moves.

2. The separation and connection mechanism as described in claim 1, characterized in that, The bracket assembly also has an inlet that communicates with the opening and is located outside the opening. The inlet has a greater outward expansion angle than the opening. The inner wall of the inlet is inclined outward relative to the inner wall of the opening, so that the connecting mechanism can touch and guide the connecting mechanism into the opening.

3. The separation and connection mechanism as described in claim 1, characterized in that, The support assembly includes a support body and a receiving body. The support body supports the receiving body. The receiving body has the opening and the inlet. The support body has an flare corresponding to the opening.

4. The separation and connection mechanism as described in claim 1, characterized in that, The guide structure includes an inlet groove section and a slide section. The inlet groove section is located at the end of the guide structure facing the aircraft. The inlet groove section is gradually expanded outward relative to the slide section to guide the motion guide into the slide section.

5. A land-based vehicle, characterized in that, Includes the separation and connection mechanism as described in any one of claims 1 to 4.

6. A transportation device, characterized in that, This includes aircraft and land vehicles as described in claim 5.

7. The transportation equipment as described in claim 6, characterized in that, The connecting mechanism includes a deflector and a mounting body, the deflector being movably connected to the mounting body, and the deflector being rotatably deflected toward the center of the opening relative to the mounting body.

8. The transportation equipment as described in claim 7, characterized in that, The connecting mechanism is further provided with an elastic return member, which is located on the mounting body and connected to the swing body, so as to swing the swing body back in a direction away from the center of the opening.

9. A transportation device, characterized in that, Includes the aircraft and the separation and reassembly mechanism as described in claim 4.

10. The transportation equipment as described in claim 9, characterized in that, The motion guide has at least one guide body that touches the inner wall of the inlet groove section and enters the slide section along the inner wall of the inlet groove section.

11. The transportation equipment as claimed in claim 10, characterized in that, The motion guide also includes a carrier, which is located at the bottom of the aircraft to support the aircraft; the carrier is spaced apart from the guide and enters the chute section as the guide moves.

12. The transportation equipment as described in claim 10, characterized in that, The guide extends along the length of the aircraft to support it; the end of the guide facing the inlet groove is rounded.

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