CN110877507A

CN110877507A - Split type aerocar and consignment method aerocar scheduling system

Info

Publication number: CN110877507A
Application number: CN201911315751.1A
Authority: CN
Inventors: 徐彬; 黄彬; 马罡; 邢志强
Original assignee: Cool Black Technology (beijing) Co Ltd
Current assignee: Cool Black Technology (beijing) Co Ltd
Priority date: 2019-12-19
Filing date: 2019-12-19
Publication date: 2020-03-13

Abstract

The invention discloses a split type hovercar which comprises an aircraft and a carrying bin, wherein the aircraft is at least provided with a first butt joint mechanism and a second butt joint mechanism; the carrying bin is provided with at least one first butt joint mechanism and one second butt joint mechanism, and the first butt joint mechanism and the second butt joint mechanism can be mutually matched to realize engagement and disengagement. This split type hovercar can realize the aircraft replacement, carries out goods or personnel's transportation through the form of aircraft replacement, has broken through the restriction of aircraft energy deposit, does not rely on under the prerequisite of building a large amount of ground stop stations and charging facility, has effectively increased hovercar's transportation radius, greatly expands hovercar's delivery range. The invention also discloses a consignment method based on the split type hovercar and a hovercar dispatching system.

Description

Split type aerocar and consignment method aerocar scheduling system

Technical Field

The invention relates to the technical field of hovercar transportation, in particular to a split type hovercar, a consignment method and a hovercar dispatching system.

Background

The existing flying automobile is mainly an integrated flying automobile, the integrated flying automobile has an integrated structure of an air module and a ground module no matter flying in the air or driving on the ground, the whole load burden is large, the flexibility is poor, particularly, when the air encounters an emergency (such as flight fault or energy shortage), the adjusting capacity is poor, only emergency forced landing can be selected, and the nearby transfer station is selected for charging or replacing, so that the transportation operation efficiency is influenced.

Disclosure of Invention

In view of the above, the present invention discloses a split type flying automobile, so that when the energy of an aircraft is insufficient, the transportation of a carrier cabin itself can be completed by the engagement of other aircraft with the carrier cabin, thereby effectively improving the carrying efficiency.

The invention further discloses a consignment method based on the aerocar.

The invention further discloses a flight vehicle dispatching system.

In order to achieve the above purpose, the split flying automobile disclosed by the invention comprises an aircraft and a carrying cabin, wherein,

the aircraft is at least provided with a first docking mechanism and a second docking mechanism;

the carrying bin is at least provided with one first butt joint mechanism and one second butt joint mechanism;

the first docking mechanism and the second docking mechanism can be mutually matched to realize engagement and disengagement.

Preferably, in the flying automobile, the flying automobile further comprises a traveling chassis, and the first docking mechanism is arranged on the top surface of the traveling chassis.

Preferably, in the hovercar, the first docking mechanism is arranged on the top surface of the aircraft, and the second docking mechanism is arranged on the bottom surface of the aircraft; in the carrier magazine, the first docking mechanism is provided on a top surface of the carrier magazine, and the second docking mechanism is provided on a bottom surface of the carrier magazine.

Preferably, in the flying automobile, one of the first docking mechanism and the second docking mechanism is a boss, and the other of the first docking mechanism and the second docking mechanism is a sink into which the boss can be fitted.

Preferably, in the hovercar, a clamping device is further arranged between the boss and the sinking groove, the clamping device includes a clamping groove and a clamping part capable of extending into the clamping groove, the clamping groove is arranged on one of the boss and the sinking groove, and the clamping part is arranged on the other of the boss and the sinking groove; or the first butt joint mechanism and the second butt joint mechanism are mutually matched electromagnetic butt joint mechanisms.

Preferably, in the flying automobile, a visual mark is provided on one of the first docking mechanism and the second docking mechanism, and a visual sensor capable of recognizing the visual mark and a docking controller in communication connection with the visual sensor are provided on the other of the first docking mechanism and the second docking mechanism;

or the first docking mechanism and the second docking mechanism are respectively provided with a visual mark and a visual sensor capable of identifying the visual mark, and each visual sensor is in communication connection with the docking controller.

Preferably, in the flying automobile, the first docking mechanism is provided with a visual marker, the second docking mechanism is provided with the visual sensor, and the docking controller is disposed in the aircraft.

The invention also discloses a consignment method adopting the split automobile, when the aircraft is jointed with the carrying bin and is in a flight state, the aircraft is called a target aircraft, if a request for assisting carrying of the target aircraft is received, a replacement aircraft is selected, if the replacement aircraft can be selected, the replacement aircraft is controlled to converge with the target aircraft, an idle docking mechanism on the replacement aircraft is jointed with an idle and adaptive docking mechanism on the carrying bin, and the replacement aircraft replaces the target aircraft to carry the carrying bin to a set position.

Preferably, in the shipping method,

when the assist bearer request is: upon request to carry the combination of the target aircraft and the carrier bay, the target aircraft remaining engaged with the carrier bay after the replacement aircraft is engaged with the carrier bay;

when the assist bearer request is: upon request to separately carry the carrier pod, the target aircraft disengages from the carrier pod after the replacement aircraft engages with the carrier pod;

when the assist bearer request is: when the target aircraft itself is requested to be carried individually, and the carrier bins are carried individually, then:

selecting two replacement aircrafts, and controlling an idle docking mechanism of one replacement aircraft to be jointed with an idle and adaptive docking mechanism of the carrier bin, so that the replacement aircraft replaces the target aircraft to carry the carrier bin to a set position;

and controlling the target aircraft to be disengaged from the carrying bin, and carrying the target aircraft to a charging station after enabling the other docking mechanism with the replacement aircraft idle to be engaged with the docking mechanism with the target aircraft idle and adaptive.

Preferably, in the consignment method, the selecting step of the replacement aircraft is:

1) taking the current position of the target aircraft as a center, judging whether an empty aircraft in a flight state exists in a preset radius range, if so, selecting the empty aircraft closest to the target aircraft as the replacement aircraft, and if not, entering the step 2);

2) taking the current position of the target aircraft as a center, judging whether an idle aircraft exists in the ground station within a preset radius range, if so, selecting the idle aircraft closest to the target aircraft as the replacement aircraft, and if not, entering step 3);

3) judging whether an idle aircraft exists in the central control station, if so, selecting the idle aircraft with enough energy as the replacement aircraft, and if not, entering the step 4);

4) and taking the current position of the target aircraft as a center, judging whether a loaded aircraft which is in a flight state and has a load exists in a preset radius range, if so, selecting the loaded aircraft closest to the target aircraft as the replacement aircraft, and if not, selecting the replacement aircraft to fail.

Preferably, in the consignment method, the split type hovercar further comprises a running chassis, the top surface of the running chassis is provided with the first docking mechanism, the consignment method further comprises a chassis transfer mode, and the chassis transfer mode comprises: controlling the target aircraft to converge with the travel chassis, and:

controlling the first docking mechanism on the running chassis to be combined with a second docking mechanism which is idle on the carrying cabin, wherein the running chassis replaces the target aircraft to carry the carrying cabin to a set position, or,

and controlling the first docking mechanism on the running chassis to be combined with the second docking mechanism which is idle on the target aircraft, wherein the running chassis replaces the target aircraft to carry the combination of the carrying bin and the target aircraft to a set position.

Preferably, in the chassis transfer mode of the consignment method,

when the first docking mechanism on the running chassis is combined with the second docking mechanism which is idle on the carrying bin:

if the assisted carrying request is: when the combination of the target aircraft and the carrying bin is requested to be carried, after the running chassis is jointed with the carrying bin, the target aircraft and the carrying bin are kept jointed;

if the assisted carrying request is: when the separate carrying of the carrier bay is requested, the target aircraft is disengaged from the carrier bay after the running chassis is engaged with the carrier bay.

If the assisted carrying request is: when the target aircraft itself is requested to be carried individually, and the carrier bins are carried individually, then:

dispatching two running chassis, and controlling a first docking mechanism of one running chassis to be jointed with the second docking mechanism of the carrying bin which is idle, so that the running chassis carries the carrying bin to a set position instead of the target aircraft;

and controlling the target aircraft to be disengaged from the carrying bin, enabling the first docking mechanism of the other running chassis to be engaged with the second docking mechanism of the target aircraft, and controlling the running chassis to carry the target aircraft to a charging station.

The invention discloses a flying automobile dispatching system, which comprises a plurality of split flying automobiles, a control center, a first information acquisition device, a first signal transceiver and a first docking control device, wherein the first information acquisition device, the first signal transceiver and the first docking control device are arranged in the flying automobiles,

the control center is used for receiving a first assisted carrying request of a target aircraft, selecting a replacement aircraft according to the first assisted carrying request, sending a first assisted carrying instruction to the replacement aircraft, and establishing communication connection between the replacement aircraft and a first docking control device in the target aircraft;

the first state information acquisition device is used for acquiring state information of an aircraft where the first state information acquisition device is located, and generating the first assisted carrying request when a first preset condition is met;

the first signal transceiver is used for sending the first assisted carrying request to the control center and receiving a first assisted carrying instruction of the control center;

the first docking control means is for controlling the docking mechanism on board the replacement aircraft to engage with the docking mechanism on board the carrier bay that is idle and adapted.

Preferably, the vehicle further comprises a second signal transceiver and a second butt-joint control device which are arranged in the running chassis, wherein,

when the selection of the replacement aircraft fails, the control center is further used for selecting a running chassis according to the first assisted carrying request, sending the first assisted carrying instruction to the running chassis, and establishing communication connection between the second docking control device in the running chassis and the first docking control device in the target aircraft;

the second signal transceiver is used for receiving the first assistance carrying instruction;

the first docking control device and the second docking control device are in communication connection and are used for controlling the docking mechanism of the traveling chassis to be jointed with the idle and adaptive docking mechanism on the carrying cabin or controlling the docking mechanism of the traveling chassis to be jointed with the idle and adaptive docking mechanism on the target aircraft.

Preferably, the split type hovercar further comprises a running chassis with the first docking mechanism arranged on the top surface, the hovercar dispatching system further comprises a second state information acquisition device arranged in the running chassis, the second state information acquisition device is used for acquiring state information of the running chassis where the hovercar dispatching system is located, and generating a second carrying assisting request when a second preset condition is met, and the second signal transceiver is further used for sending the second carrying assisting request to the control center;

the control center is further used for receiving the second assisted carrying request, selecting a replacement aircraft according to the second assisted carrying request, sending a second assisted carrying instruction to the replacement aircraft, and establishing communication connection between a first docking control device in the replacement aircraft and a second docking control device in the running chassis;

the first signal transceiver is further configured to receive the second assistance carrying instruction;

the first docking control device and the second docking control device are communicatively connected and are used to control the docking mechanism on board the carrier bay to engage with the docking mechanism on board the replacement aircraft that is idle and adaptive.

Preferably, the system also comprises a plurality of ground stations, the ground stations supply the aircraft and the running chassis to park, charge and maintain, the ground stations are provided with station master control devices, the station master control devices are in communication connection with the control center, and the station master control devices are also in communication connection with first state acquisition devices in the aircraft in the ground stations and second state acquisition devices in the running chassis of the ground stations.

Preferably, the control center selects the replacement aircraft according to a preset selection rule, where the preset selection rule is:

4) and taking the current position of the target aircraft as a center, judging whether a loaded aircraft which is in a flight state and has a load exists in a preset radius range, and if so, selecting the loaded aircraft which is closest to the target aircraft as the replacement aircraft.

Preferably, the first preset condition and the second preset condition are both: energy shortage, failure or the need to perform new tasks.

According to the technical scheme, in the flying automobile disclosed by the invention, the aircraft and the carrying cabin are respectively provided with at least one first butt joint mechanism and one second butt joint mechanism, when the first butt joint mechanism of the aircraft is jointed with the second butt joint mechanism of the carrying cabin and the energy of the aircraft is insufficient, the second butt joint mechanism of the aircraft with sufficient energy and the idle first butt joint mechanism on the carrying cabin can be used for automatically butt joint in the air, so that the carrying cabin can be carried to a set position in an aircraft replacement mode; when the second docking mechanism of the aircraft is jointed with the first docking mechanism of the carrying bin and the energy of the aircraft is insufficient, the first docking mechanism of the aircraft with sufficient energy and the idle second docking mechanism on the carrying bin can realize automatic docking in the air, so that the carrying bin can be carried to the set position in an aircraft replacement mode.

Goods or personnel are transported in an aircraft replacement mode, the limitation of energy storage of the aircraft is broken through, the transportation radius of the flying automobile is effectively increased on the premise of not depending on the construction of a large number of ground parking stations and charging facilities, and the carrying range of the flying automobile is greatly expanded; the aircraft can also realize automatic butt joint and separation in the air in the replacement process, so that the problem of low transportation efficiency caused by midway landing or stopping is solved, and the transportation efficiency of the hovercar is effectively improved.

According to the consignment method disclosed by the invention, when the energy of the aircraft butted with the carrying bin is insufficient, the aircraft with sufficient energy is butted with the idle butting mechanism on the carrying bin through other aircrafts, so that the carrying bin is carried to a set position in an aircraft replacement mode, the characteristic of flexible butting of the split type flying automobile is fully utilized, the flying automobile is directly replaced point to point in the air, the operation is convenient, the separation combination form of the split type flying automobile is improved, the flexible combination of multiple directions and multiple postures is realized, the transportation efficiency is improved, and the energy consumption is reduced.

The flying automobile dispatching system disclosed by the invention can dispatch the split flying automobile to execute the consignment method.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic structural representation of the topside of an aircraft as disclosed in a first embodiment of the present invention;

FIG. 2 is a schematic view of the underside structure of the aircraft disclosed in the first embodiment of the invention;

FIG. 3 is a schematic top view of a first embodiment of a disclosed carrier magazine;

fig. 4 is a schematic bottom structure of a carrier magazine according to the first embodiment of the present invention;

FIG. 5 is a schematic top view of the traveling chassis disclosed in the first embodiment of the present invention;

FIG. 6 is a schematic view of the hanging transportation mode of the carrying cabin;

FIG. 7 is a schematic view of the transfer chamber from the lower hanging type to the upper supporting type;

FIG. 8 is a schematic view of the carrier on-board mode of transport;

FIG. 9 is a schematic view of a loaded aircraft in a temporary consignment;

FIG. 10 is a schematic structural diagram of the topside of the aircraft disclosed in a second embodiment of the present invention;

FIG. 11 is a schematic view of the underside structure of the aircraft disclosed in a second embodiment of the invention;

FIG. 12 is a schematic flow chart illustrating the flow of information in the exemplary disclosed hovercar dispatch system;

FIG. 13 is a schematic flow chart diagram illustrating a shipping method according to one embodiment of the present disclosure;

FIG. 14 is a schematic illustration of the communication relationship between the replacement aircraft and the target aircraft and the control center, as disclosed in an embodiment of the present invention;

FIG. 15 is a schematic illustration of the communication between the target vehicle and the chassis and control center, in accordance with an embodiment of the present invention;

FIG. 16 is a schematic illustration of the communication between an alternative vehicle and the chassis and control center disclosed in an embodiment of the present invention;

fig. 17 is a schematic flow chart of a first assistance request disclosed in the embodiment of the present invention;

fig. 18 is a schematic flow chart of a second assistance request disclosed in the embodiment of the present invention.

Wherein, 1 is the aircraft, 2 is the delivery storehouse, 3 is the chassis of traveling, and A is first docking mechanism, and B is the second docking mechanism.

Detailed Description

One of the cores of the invention is to provide a split type flying automobile, so that when the energy of the aircraft is insufficient, the transportation of the carrier cabin can be completed by connecting other aircraft with the carrier cabin, and the carrying efficiency is effectively improved.

The other core of the invention is to provide a consignment method based on the split type hovercar.

In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention are described below clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Compared with an integrated flying automobile, the split flying automobile has higher flexibility, generally comprises an aircraft, a carrying cabin and a running chassis, wherein the carrying cabin can be automatically butted and combined with the aircraft and/or the running chassis through a butting mechanism, the carrying cabin is only jointed with the aircraft during air flight, and when the flying cabin is converted into ground running, the carrying cabin is only jointed with the running chassis and can run on the road surface like an ordinary automobile, so that the split flying automobile has the advantages of small flying load, strong stability, long endurance time and the like.

Example one

In the present embodiment, the basic technical solution and more than one optimized technical solution capable of achieving the object of the present invention are included.

The basic technical scheme disclosed in the embodiment is as follows: the split type flying automobile comprises an aircraft 1 and a carrying cabin 2, wherein at least one first docking mechanism A and one second docking mechanism B are arranged on the aircraft 1, at least one first docking mechanism A and one second docking mechanism B are also arranged on the carrying cabin 2, the first docking mechanism A and the second docking mechanism B which are matched with each other can be mutually engaged, and certainly, the first docking mechanism A and the second docking mechanism B can also be mutually disengaged.

According to the flying automobile disclosed in the scheme, when the energy of the aircraft 1 is insufficient, the aircraft 1 with sufficient energy can be dispatched to meet the aircraft 1 with insufficient energy in the air, if the first docking mechanism A of the aircraft 1 with insufficient energy is in a docking state with the second docking mechanism B of the carrying bin 2, the second docking mechanism B of the aircraft 1 with sufficient energy and the idle first docking mechanism A of the carrying bin 2 can be in automatic docking in the air, and therefore the carrying bin 2 can be carried to a set position in a replacement mode of the aircraft 1; if the second docking mechanism B of the aircraft 1 with insufficient energy is in a docking state with the first docking mechanism a of the carrying bin 2, the first docking mechanism a of the aircraft 1 with sufficient energy and the idle second docking mechanism B of the carrying bin 2 can be automatically docked in the air, so that the carrying bin 2 can be carried to a predetermined position in a replacement mode of the aircraft 1.

In the present application, the first docking mechanism a and the second docking mechanism B may be implemented by using a conventional aerial docking technology in the field during aerial docking, and an automatic docking technology of the aircraft 1 with other components in the air has been disclosed in the fields of unmanned aerial vehicle technology and flying automobiles, for example, the automatic docking technology in the air is disclosed in chinese patent with publication number CN109334968A, and the above docking technologies are not described in detail in the present application.

In the technical scheme, goods or personnel are transported in a replacement mode of the aircraft 1, the limitation of energy storage of the aircraft 1 is broken through, the transportation radius of the flying automobile is effectively increased on the premise of not depending on the construction of a large number of ground parking stations and charging facilities, and the carrying range of the flying automobile is greatly expanded; because the aircraft 1 is automatically butted and separated in the air in the replacement process, the scheme also solves the problem of low transportation efficiency caused by midway landing or stopping of the flying automobile, and effectively improves the transportation efficiency of the flying automobile.

It will be appreciated that the first docking mechanism a and the second docking mechanism B should be provided at different positions, whether on the aircraft 1 or on the carrier pod 2, to prevent the second docking mechanism B from being obscured when the first docking mechanism a is in use, or the first docking mechanism a from being obscured when the second docking mechanism B is in use.

On the aircraft 1 and the carrying cabin 2, a plurality of first docking mechanisms a and a plurality of second docking mechanisms B may be provided as required, for example, when the aircraft 1 is a flat cuboid, four side surfaces, and a top surface and a bottom surface of the aircraft 1 may be provided with the first docking mechanism a and the second docking mechanism B, for example, two opposite side surfaces are provided with the first docking mechanism a and the second docking mechanism B respectively, the other two opposite side surfaces are also provided with the first docking mechanism a and the second docking mechanism B respectively, and the top surface and the bottom surface are also provided with the first docking mechanism a and the second docking mechanism B respectively; the arrangement form of the first docking mechanism a and the second docking mechanism B of the carrier chamber 2 may be changed in many ways according to the shape of the carrier chamber, for example, when the carrier chamber 2 is a rectangular parallelepiped, three pairs of the first docking mechanism a and the second docking mechanism B may be arranged with reference to the aircraft 1, and when the carrier chamber 2 is a regular octahedron or a regular dodecahedron, the number of the first docking mechanism a and the second docking mechanism B may be further increased.

In one solution, a first docking mechanism a is disposed on the top side of the aircraft 1, a second docking mechanism B is disposed on the bottom side of the aircraft 1, the first docking mechanism a is disposed on the top side of the carrier bay 2, and the second docking mechanism B is disposed on the bottom side of the carrier bay 2, as shown in fig. 1 to 4.

In order to avoid the first docking mechanism a and the second docking mechanism B from being hidden, the top surface of the aircraft 1 and the top surface of the carrier bay 2 are each provided with one first docking mechanism a, and the bottom surface of the aircraft 1 and the bottom surface of the carrier bay 2 are each provided with one second docking mechanism B, as shown in fig. 1 to 4.

In another technical scheme, the split type flying automobile further comprises a running chassis 3 capable of running on land, as shown in fig. 5, a first docking mechanism a is arranged on the top surface of the running chassis 3, when no suitable aircraft 1 replaces the aircraft 1 with insufficient energy, the aircraft 1 with insufficient energy can also be made to descend with the carrying cabin 2, and the first docking mechanism a on the running chassis 3 is made to be joined with a second docking mechanism B on the carrying cabin 2 or with a second docking mechanism B on the aircraft 1 with the carrying cabin 2, at this time, the carrying cabin 2 is switched from air transportation to land transportation, and the transportation efficiency is effectively guaranteed.

It should be understood that, one of the first docking mechanism a and the second docking mechanism B may be a boss, and the other may be a sink groove into which the boss can be inserted, so that the first docking mechanism a and the second docking mechanism B can be matched with each other, please refer to fig. 1 to 4. In order to further ensure the stability of the butt joint of the first butt joint mechanism A and the second butt joint mechanism B, a clamping device can be arranged between the lug boss and the sinking groove.

The clamping device generally comprises a clamping groove and a clamping part which can extend into the clamping groove, the clamping groove is arranged on any one of the boss and the sinking groove, the clamping part is arranged on the other one of the boss and the sinking groove, and the clamping part can be a clamping convex strip or a clamping claw according to the difference of the shapes of the clamping grooves.

In another technical scheme, the first docking mechanism a and the second docking mechanism B are electromagnetic docking mechanisms which are matched with each other, one of the first docking mechanism a and the second docking mechanism B is a boss, the other is a sink groove in which the boss can be embedded, when the first docking mechanism a and the second docking mechanism B are aligned, the electromagnet is powered on to realize stable connection of the first docking mechanism a and the second docking mechanism B.

In one technical scheme, a visual mark is arranged on any one of a first docking mechanism A and a second docking mechanism B, a visual sensor capable of identifying the visual mark and a docking controller in communication connection with the visual sensor are arranged on the other one of the first docking mechanism A and the second docking mechanism B, and the docking controller is mainly used for controlling a docking piece provided with the visual sensor to move towards a component provided with the visual mark so as to finish accurate docking or assist in finishing accurate docking;

in another technical scheme, the first docking mechanism a and the second docking mechanism B are respectively provided with a visual mark and a sensor capable of recognizing the visual mark, each visual sensor is in communication connection with the docking controller, and optionally, the docking controllers are respectively arranged on the parts (the aircraft 1, the carrying cabin 2 and the traveling chassis 3) provided with the visual sensors, and when the two parts are docked, the docking controllers in the two parts realize communication data connection so as to cooperatively control the two docked parts to realize accurate docking, or assist in realizing accurate docking of the two docked parts.

In the technical scheme, a visual mark is arranged on a first docking mechanism A, a visual sensor is arranged on a second docking mechanism B, and a docking controller is arranged in an aircraft 1; if the aircraft 1 is replaced in the air, the docking controller in the aircraft 1 with sufficient energy and the docking controller in the aircraft 1 with insufficient energy are in communication connection with each other, and cooperatively control the docking of the aircraft 1 with sufficient energy and an idle docking mechanism (a first docking mechanism A or a second docking mechanism B) on the carrying bin 2, or assist in realizing the docking of the aircraft 1 and the idle docking mechanism on the carrying bin 2; if the transportation needs to be changed from air to land transportation, the aircraft 1 with insufficient energy carries the carrying bin 2 to land, the visual mark arranged on the running chassis 3 is identified through the visual sensor, then the combination of the aircraft 1 with insufficient energy and the carrying bin 2 is controlled by the docking controller to be in accurate docking with the running chassis 3, or the combination of the aircraft 1 with insufficient energy and the carrying bin 2 is assisted to be in accurate docking with the running chassis 3.

Second embodiment

Referring to fig. 10 and 11, the second embodiment differs from the first embodiment in the arrangement positions of the first docking mechanism a and the second docking mechanism B on the aircraft 1, and the rest of the features can be obtained by referring to the first embodiment.

In one technical solution of the first embodiment, a first docking mechanism a is disposed on a top surface of the aircraft 1, and a second docking mechanism B is disposed on a bottom surface of the aircraft 1.

Based on the split type flying automobile disclosed in the embodiment, the invention also discloses a consignment method, the consignment method is applied to the flying car disclosed in the above embodiment, and when the aircraft 1 is engaged with the carrier bay 2 and in flight, the aircraft 1 may be referred to as a target aircraft, in the consignment method, a control center is provided, if the control center receives a request for assisted delivery from a target aircraft, the control center selects the replacement aircraft, if the selection of the replacement aircraft is successful, the control center controls the replacement aircraft to converge with the target aircraft, and to engage the docking mechanism on the replacement aircraft that is idle with the docking mechanism on the carrier bay 2 that is idle and adapted, the carrier box 2 is then carried by the replacement aircraft to the intended position (i.e., the target position of the carrier box 2 that has been set) in place of the target aircraft.

It should be noted that the docking mechanisms mentioned in the above consignment method are generic names of a first docking mechanism a and a second docking mechanism B, and if the first docking mechanism a on the carrier bay 2 is idle, the second docking mechanism B on the replacement aircraft is docked with the first docking mechanism a on the carrier bay 2, and if the second docking mechanism B on the carrier bay 2 is idle, the first docking mechanism a on the replacement aircraft is docked with the second docking mechanism B on the carrier bay 2; if there are both first docking mechanisms a and second docking mechanisms B on the carrier magazine 2, which are idle, the replacement aircraft can dock with the first docking mechanism a or the second docking mechanism B on the carrier magazine 2 according to a set replacement principle (e.g., the orientation is most easily adjusted).

In general, the request for assistance carrier may include the following situations: requesting to carry a combination of a target aircraft and a carrier bay 2, requesting to transport the carrier bay 2 individually, requesting to carry the target aircraft itself individually, and transporting the carrier bay 2 individually.

When the assisted bearer request is: when a request is made to carry the combination of the target aircraft and the carrier bay 2, the target aircraft and the carrier bay 2 may be kept in the engaged state after the replacement aircraft is engaged with the carrier bay 2, and such a request generally occurs when the target aircraft also needs to go to a predetermined location for charging or to perform a new mission.

When the assisted bearer request is: when the separate transport of the carrier magazine 2 is requested, the target aircraft is disengaged from the carrier magazine 2 after the replacement aircraft is engaged with the carrier magazine 2, and the disengaged target aircraft can automatically land to a charging station for charging or perform a new mission.

When the assisted bearer request is: when the target aircraft itself is requested to be carried individually, and the carrier box 2 is transported individually, then:

selecting two replacement aircrafts, and controlling an idle docking mechanism of one replacement aircraft to be jointed with an idle and adaptive docking mechanism of the carrying bin 2, so that the replacement aircraft replaces the target aircraft to carry the carrying bin 2 to a set position;

and controlling the target aircraft to be separated from the carrying bin 2, and carrying the target aircraft to a charging station after enabling another docking mechanism with the replacement aircraft idle to be engaged with the docking mechanism with the target aircraft idle and adaptive.

This is typically the case when the target aircraft does not need to follow the carrier bin 2 to a predetermined location and the energy stored on the target aircraft is not sufficient to return it to the nearest charging station.

In the method of consignment, the steps selected to replace the aircraft are:

1) taking the current position of the target aircraft as a center (usually realized by a positioning device), judging whether an unloaded aircraft in a flight state exists in a preset radius range (which can be set according to actual needs, such as 10km or 5km) by the control center, if so, selecting the unloaded aircraft which is closest to the target aircraft and has enough energy as a replacement aircraft by the control center, and if not, entering the step 2);

2) taking the current position of the target aircraft as a center (usually realized by a positioning device), judging whether an idle aircraft exists in a ground station within a preset radius range (which can be set according to actual needs, such as 10km or 5km) or not by the control center, if so, selecting the idle aircraft which is closest to the target aircraft and has enough energy as a replacement aircraft by the control center, and if not, entering the step 3);

3) judging whether an idle aircraft exists in a central control station (namely a station where the control center is located), if so, selecting the idle aircraft with enough energy as a replacement aircraft by the control center, and if not, entering a step 4);

4) centering on the current position of the target aircraft (usually by a positioning device), determining whether a loaded aircraft with a load in a flight state exists within a predetermined radius range (which can be set according to actual needs, such as 10km or 5km), if so, selecting the loaded aircraft with sufficient energy closest to the target aircraft as a replacement aircraft, and if not, failing to select the replacement aircraft.

After the replacement aircraft is selected, two results can be generated, one result is that the replacement aircraft is successfully selected, the other result is that the replacement aircraft is unsuccessfully selected, and if the replacement aircraft is successfully selected, the control center controls the replacement aircraft to converge with the target aircraft (usually through a positioning device), and carries the carrying bin 2 to a set position instead of the target aircraft; if the selection of the replacement aircraft fails, the mode can be changed from the air transportation mode to the land transportation mode (namely, the chassis transfer mode):

the control center controls the target aircraft to converge with the traveling chassis 3 (usually realized by a positioning device), then controls a first docking mechanism A on the traveling chassis 3 to be jointed with a second docking mechanism B which is idle on the carrying cabin 2, and the traveling chassis 3 replaces the target aircraft to carry the carrying cabin 2 to a set position; alternatively, the first and second electrodes may be,

the control center controls the first docking mechanism A on the running chassis 3 to be combined with the second docking mechanism B which is idle on the target aircraft, and the running chassis 3 replaces the target aircraft to carry the combination of the carrying bin 2 and the target aircraft to the set position.

Of course, the chassis transfer mode is not only used in the case of failure of the aircraft replacement selection, but also can be directly converted from the air transportation mode to the chassis transfer mode according to the actual carrying requirements.

Further, in the chassis transfer mode, if the request for assisting the carrying is: requesting to carry the combination of the target aircraft and the carrying bin 2, and keeping the target aircraft in a joint state with the carrying bin 2 after the running chassis 3 is jointed with the carrying bin 2;

if the assisted carrying request is: when the separate transportation of the carrier bunker 2 is requested, the target aircraft is disengaged from the carrier bunker 2 after the running chassis 3 is engaged with the carrier bunker 2;

if the assisted carrying request is: when the target aircraft itself is requested to be carried individually, and the carrier box 2 is transported individually, then:

dispatching two running chassis 3, and controlling a first docking mechanism A of one running chassis 3 to be jointed with a second docking mechanism B of the carrying bin 2 which is idle, so that the running chassis 3 replaces a target aircraft to carry the carrying bin 2 to a set position;

the target aircraft is controlled to be disengaged from the carrying bin 2, the first docking mechanism A of the other travelling chassis 3 is engaged with the second docking mechanism B of the target aircraft, and the travelling chassis 3 is controlled to carry the target aircraft to the charging station.

The following technical scheme that a first docking mechanism A is arranged at the top of an aircraft 1, a second docking mechanism B is arranged at the bottom of the aircraft, a first docking mechanism A is arranged at the top of a carrying bin 2, a second docking mechanism B is arranged at the bottom of the carrying bin, and a first docking mechanism A is arranged at the top of a traveling chassis 3 is introduced for actual delivery flight:

normally, when the ground transportation mode is changed into air flight, the second docking mechanism B at the bottom of the aircraft 1 is engaged with the first docking mechanism a at the top of the carrying cabin 2, the second docking mechanism B at the bottom of the carrying cabin 2 is disengaged from the first docking mechanism a at the top of the traveling chassis 3, the carrying cabin 2 is changed from ground transportation to air transportation, and at this time, the carrying cabin 2 is hung at the bottom of the aircraft 1, so that the mode is in downward hanging type flight.

The lower hanging type is converted into the upper supporting type:

when the target aircraft executes a flight task, the energy monitoring system on the target aircraft can detect the energy consumption, the surplus and the supportable surplus mileage on the target aircraft in real time, and when the monitoring device detects that the surplus of the energy is not enough to complete the flight task or the target aircraft receives a new task sent by the control center, the target aircraft can send an assisted carrying request to the control center;

after receiving the request for assisting in carrying, the control center selects a replacement aircraft according to the position of the target aircraft, wherein the replacement aircraft can be an idle aircraft of a ground station within a preset radius range of the position of the target aircraft, can also be an idle aircraft in a central control station, can also be an idle aircraft which performs mission return in the air, can also be an aircraft with load passing through the position of the target aircraft, and can also be an aircraft which is in charge of other missions within the preset radius range, such as a patrol machine and the like; after the replacement aircraft is selected, the control center respectively sends the positions of the target aircraft and the replacement aircraft to each other, and communication is established between the target aircraft and the replacement aircraft;

according to the position information and the positioning device, the replacement aircraft reaches the position of the target aircraft, the two parties carry out real-time communication, and acquiring the attitude information of the other party, realizing the butt joint between the replacement aircraft and the target aircraft through the butt joint controller based on the acquired attitude information, the docking controller can adjust the postures of the replacement aircraft and the target aircraft according to GPS positioning signals, difference GPS and the means of combining a visual positioning system and the like in the docking process, the first docking mechanism a at the top of the replacement aircraft is then gradually brought into abutment with and docked to the second docking mechanism B at the bottom of the carrier bin 2, when the replacement aircraft is engaged with the carrier magazine 2, the target aircraft is detached from the carrier magazine 2, returned to the charging station or performed a new mission, the replacement aircraft combined with the carrier magazine 2 carries the carrier magazine 2 to a given position, as shown in fig. 13. This mode becomes a pop-up mode of transportation, since the carrier magazine 2 is now being palletized by the top of the replacement aircraft.

The upper supporting type is converted into the lower hanging type:

the conversion is basically the same as the conversion from the lower hanging type to the upper supporting type, and is only adjusted to replace the butt joint of a second butt joint mechanism B at the bottom of the aircraft and a first butt joint mechanism A at the top of the carrying bin 2; after the docking is completed, the target aircraft is separated from the carrying bin 2.

Respectively consigning:

when the energy of the target aircraft is insufficient to complete the flight task and support the target aircraft to return to the nearest charging station, the control center dispatches two replacement aircraft at one time, the replacement aircraft and the target aircraft are in real-time communication, in the process that one replacement aircraft converts the carrying bin 2 from the down-hanging type to the up-hanging type, or in the process that one replacement aircraft converts the carrying bin 2 from the up-hanging type to the down-hanging type, the other replacement aircraft is in butt joint with the target aircraft, one replacement aircraft transports the carrying bin 2, and the other replacement aircraft carries the target aircraft to the charging station for supplementing energy, so that the respective consignment is realized.

Carrying out integral consignment:

when the energy of the target aircraft is insufficient to complete the flight mission and support the target aircraft to return to the nearest charging station, the assisted carrying request can be a combination of the target aircraft and the carrying bin 2 for carrying integrally, at the moment, the control center dispatches the replacing aircraft with strong carrying capacity and sufficient energy to execute the mission, the replacing aircraft communicates with the target aircraft in real time, the docking of the replacing aircraft and the target aircraft is completed through a differential GPS and a visual positioning means, and when the carrying bin 2 is in a down-hanging type, the replacing aircraft can be docked with the top of the target aircraft and also docked with the bottom of the carrying bin 2; when the carrier bay 2 is pop-up, the replacement aircraft may dock with either the top of the carrier bay 2 or the bottom of the target aircraft.

In this case, the replacement aircraft ships the combination of the target aircraft and the delivery bay 2 to the predetermined position, or after the replacement aircraft ships the combination for a certain distance, the target aircraft is disengaged from the cabin, the landing is automatically completed to charge the cabin, and the replacement aircraft continues to transport the delivery bay 2 to the predetermined position.

Temporary consignment:

if the central control station and the nearby ground station do not have idle aircrafts as replacement aircrafts after receiving the carrying assisting request, and no-load aircrafts return within the preset radius range, at the moment, if a loaded aircraft which is executing a task is within the preset radius range, the loaded aircraft can be controlled to carry out temporary consignment.

For example, if the target aircraft and the loaded aircraft are in a down-hanging state, the upper part of the loaded aircraft is butted with the lower part of a carrying bin 2 on the target aircraft, which means that one carrying bin 2 is loaded on both the upper and lower surfaces of the loaded aircraft, and the target aircraft is separated from the carrying bin 2 to execute a new task or return to a ground charging station for charging;

for example, if the target aircraft and the loaded aircraft are both in a pop-up state, the lower part of the loaded aircraft is in butt joint with the upper part of the carrying bin 2 on the target aircraft, which means that one carrying bin 2 is loaded on both the upper and lower surfaces of the loaded aircraft, and the target aircraft is separated from the carrying bin 2 to execute a new task or return to a ground charging station for charging;

for example, if the target aircraft is in a down-hanging type and the loaded aircraft is in an up-hanging type, the upper part of the carrying bin 2 on the loaded aircraft is butted with the lower part of the carrying bin 2 on the target aircraft, two carrying bins 2 are butted with each other, which means that two carrying bins 2 are arranged above the loaded aircraft, and the target aircraft is separated from the carrying bins 2 to execute a new task or return to a ground charging station for charging;

for example, if the target aircraft is in a pop-up type and the loaded aircraft is in a down-hanging type, the lower part of the carrying bin 2 on the loaded aircraft is in butt joint with the upper part of the carrying bin 2 on the target aircraft, two carrying bins 2 are in butt joint with each other, which means that two carrying bins 2 are arranged below the loaded aircraft, and the target aircraft is separated from the carrying bins 2 to execute a new task or return to a ground charging station for charging;

of course, the loaded aircraft may also ship the combination of the target aircraft and the carrier bay 2 as a whole.

For example, if the target aircraft is in a pop-up type and the loaded aircraft is in a down-hanging type, the lower part of the carrier bay 2 on the loaded aircraft is butted with the upper part of the carrier bay 2 on the target aircraft, two carrier bays 2 are butted with each other, which corresponds to the situation that the upper end of the combination of the two carrier bays 2 is the loaded aircraft and the lower end is the target aircraft,

of course, besides the docking mechanisms arranged on the top and bottom surfaces of the aircraft 1 and the carrier cabin 2, the docking mechanisms can also be arranged on other surfaces of the aircraft 1 and the carrier cabin 2 according to specific shapes, so that the mode of multi-azimuth docking and multi-attitude combination is changed.

Air consignment and ground combination:

when the air transportation is in a peak period, the weather is severe or the selection of replacing the aircraft fails, the carrying cabin 2 can be switched to the ground (land) transportation from the air transportation, and the running chassis 3 is provided with the standardized first docking mechanism A or the standardized second docking mechanism B, so that the running chassis 3 can be docked with the carrying cabin 2 and/or the aircraft 1, the switching from the air transportation to the ground transportation is realized, and the condition of air transportation tension is effectively relieved.

Referring to fig. 12, the present invention further discloses a hovercar dispatching system, which includes the split type hovercar disclosed in the above embodiment, and further includes a control center, and a first information collecting device, a first signal transceiver and a first docking control device built in the aircraft, wherein,

the control center is used for receiving a first assisted carrying request of a target aircraft (please refer to the definition in the consignment method), selecting a replacement aircraft according to the first assisted carrying request, sending a first assisted carrying instruction to the replacement aircraft, and establishing communication connection between the replacement aircraft and a first docking control device in the target aircraft;

the first state information acquisition device is used for acquiring state information of an aircraft where the first state information acquisition device is located, and generating a first assisted carrying request when a first preset condition is met;

the first signal transceiver is used for sending a first assisted carrying request to the control center and receiving a first assisted carrying instruction of the control center;

two first docking controls communicatively connected to each other are used to control the docking mechanism at rest on the replacement aircraft to engage with the docking mechanism at rest and adapted on the carrier bay, as shown in fig. 14.

The status information in this embodiment includes, but is not limited to, pose information of the aircraft, remaining energy information, mission destination information, remaining range information, whether there is a new delivery mission, etc.

In the hovercar dispatching system disclosed in this embodiment, when the target aircraft sends the first assistant carrying instruction, the replacement aircraft can be selected by the control center and the replacement aircraft replaces the target aircraft to transport the carrying bin, and the docking process between the replacement aircraft and the carrying bin can be automatically completed in the air by two first docking control devices which are in communication connection with each other (the automatic docking technology in the air is disclosed in the chinese patent with the publication number CN 109334968A), so that the flexible docking characteristics of the split type hovercar are fully utilized, the hovercar can be directly replaced point to point in the air, the operation is convenient, the split type hovercar is improved in a split combination form, the flexible combination of multiple directions and multiple postures is realized, the transportation efficiency is improved, the energy consumption is reduced, and the system has important significance for the popularization and application of future city automobiles, the practicability is very strong.

In order to further optimize the solution, the hovercar maneuver system disclosed in this embodiment further includes a second signal transceiver built in the driving chassis, and a second docking control device, wherein,

when the selection of the replacement aircraft fails, the control center is further used for selecting the running chassis according to the first assisted carrying request, sending a first assisted carrying instruction to the running chassis, and establishing communication connection between a second docking control device in the running chassis and a first docking control device in the target aircraft;

the first docking control device and the second docking control device are connected in communication and are used for controlling the docking mechanisms of the traveling chassis to be engaged with the docking mechanisms which are idle and adapted on the carrying cabin, or controlling the docking mechanism of one traveling chassis to be engaged with the docking mechanism which is idle and adapted on the target aircraft and controlling the docking mechanism of the other traveling chassis to be engaged with the docking mechanism which is idle and adapted on the carrying cabin when the aircraft and the carrying cabin need to be carried separately, as shown in fig. 15.

This makes the control center select the traveling chassis meeting the requirement to assist the transportation after the selection of the replacement aircraft fails, please refer to fig. 15 and 17, the air replacement in fig. 17 means that the replacement aircraft and the target aircraft complete the replacement process in the air, and the ground replacement means that the target aircraft and the traveling chassis complete the replacement process on the ground.

In another embodiment, a second state information acquisition device built in the running chassis is further arranged, the second state information acquisition device is used for acquiring state information of the running chassis where the second state information acquisition device is located, and generating a second carrying assisting request when a second preset condition is met, and the second signal transceiver is further used for sending the second carrying assisting request to the control center;

the first signal transceiver is also used for receiving a second assistance carrying instruction;

the first docking control device and the second docking control device are communicatively connected and are used to control the docking mechanism at rest on the carrier bay to engage with the docking mechanism at rest and adapted on the replacement aircraft, as shown in fig. 16.

Similarly, the status information in the driving chassis includes, but is not limited to, remaining energy information of the driving chassis, task destination information, remaining mileage information, whether there is a new delivery task, and the like.

According to the scheme, if problems or requirements occur in the transportation process of the running chassis, an auxiliary transportation request can be sent to the control center, the control center dispatches the replacement aircraft to replace the running chassis to transport the transportation bin, please refer to fig. 16 and 18, and the ground replacement in fig. 18 means that the replacement process of the replacement aircraft and the running chassis is completed on the ground.

In a preferred embodiment, the system further comprises a plurality of ground stations, the ground stations are used for parking, charging and maintaining the aircrafts and the running chassis, the ground stations are provided with a station master control device, the station master control device is in communication connection with a control center, the station master control device is also in communication connection with a first state acquisition device in the aircrafts in the ground stations and a second state acquisition device in the running chassis of the ground stations, and therefore state information of each aircraft and the running chassis can be mastered.

In the above embodiments, the control center selects the replacement aircraft according to a preset selection rule, where the preset selection rule is:

1) taking the current position of the target aircraft as a center, judging whether a no-load aircraft in a flight state exists in a preset radius range, if so, selecting the no-load aircraft closest to the target aircraft as a replacement aircraft, and if not, entering the step 2);

2) taking the current position of the target aircraft as a center, judging whether an idle aircraft exists in the ground station within a preset radius range, if so, selecting the idle aircraft closest to the target aircraft as a replacement aircraft, and if not, entering a step 3);

3) judging whether an idle aircraft exists in the central control station, if so, selecting the idle aircraft with enough energy as a replacement aircraft, and if not, entering the step 4);

4) and taking the current position of the target aircraft as a center, judging whether a loaded aircraft which is in a flight state and has a load exists in a preset radius range, if so, selecting the loaded aircraft closest to the target aircraft as a replacement aircraft, and if not, selecting the replacement aircraft to fail.

In the embodiment of the present invention, the first preset condition and the second preset condition are the same and both of them are: energy shortage, failure, or the need to perform a new mission (i.e., a new mission different from the current mission).

The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A split type flying automobile comprises an aircraft (1) and a carrying cabin (2), and is characterized in that,

the aircraft (1) is at least provided with a first docking mechanism (A) and a second docking mechanism (B);

the carrying bin (2) is at least provided with one first butt joint mechanism (A) and one second butt joint mechanism (B);

the first docking mechanism (A) and the second docking mechanism (B) can be mutually matched to realize engagement and disengagement.

2. Split aerocar according to claim 1, further comprising a running chassis (3), the top surface of said running chassis (3) being provided with said first docking mechanism (a).

3. Split flying automobile according to claim 2, characterized in that in the aircraft (1) the first docking mechanism (a) is arranged on the top side of the aircraft (1) and the second docking mechanism (B) is arranged on the bottom side of the aircraft (1); in the carrying bin (2), the first docking mechanism (A) is arranged on the top surface of the carrying bin (2), and the second docking mechanism (B) is arranged on the bottom surface of the carrying bin (2).

4. The split type hovercar of any one of claims 1 to 3, wherein one of the first docking mechanism (A) and the second docking mechanism (B) is a boss, and the other of the first docking mechanism (A) and the second docking mechanism (B) is a sink into which the boss can be inserted.

5. The split type hovercar of claim 4, wherein a snap fit device is further disposed between the boss and the sunken groove, the snap fit device comprises a snap groove and a snap fitting capable of extending into the snap groove, the snap groove is disposed on one of the boss and the sunken groove, and the snap fitting is disposed on the other of the boss and the sunken groove; or the first butt joint mechanism (A) and the second butt joint mechanism (B) are mutually matched electromagnetic butt joint mechanisms.

6. The split type hovercar as claimed in claim 1, wherein a visual mark is provided on one of the first docking mechanism (a) and the second docking mechanism (B), and a visual sensor capable of recognizing the visual mark and a docking controller communicatively connected to the visual sensor are provided on the other;

or the first docking mechanism (A) and the second docking mechanism (B) are respectively provided with a visual mark and a visual sensor capable of identifying the visual mark, and each visual sensor is in communication connection with the docking controller.

7. The split flying automobile of claim 6, wherein the first docking mechanism (A) is provided with a visual marker, the second docking mechanism (B) is provided with the visual sensor, and the docking controller is provided in the aircraft (1).

8. A consignment method using a split-type flying car as claimed in claim 1, wherein when the aircraft (1) is engaged with the carrying cabin (2) and in flight, the aircraft (1) is called a target aircraft, characterized in that if a request for assistance in carrying the target aircraft is received, a replacement aircraft is selected, if the replacement aircraft can be selected, the replacement aircraft is controlled to meet the target aircraft, and an idle docking mechanism on the replacement aircraft is engaged with an idle and adaptive docking mechanism on the carrying cabin (2), and the replacement aircraft carries the carrying cabin (2) to a predetermined position instead of the target aircraft.

9. The consignment method as claimed in claim 8,

when the assist bearer request is: -upon request to carry the combination of the target aircraft and the carrier bay (2), the target aircraft remains engaged with the carrier bay (2) after the replacement aircraft is engaged with the carrier bay (2);

when the assist bearer request is: -upon request for individual delivery of the pod (2), the target aircraft disengages from the pod (2) after the replacement aircraft engages with the pod (2);

when the assist bearer request is: when the target aircraft itself is requested to be carried individually and the carrier bins (2) are carried individually, then:

selecting two replacement aircrafts, and controlling an idle docking mechanism of one replacement aircraft to be engaged with an idle and adaptive docking mechanism of the carrying bin (2) so that the replacement aircraft carries the carrying bin (2) to a set position instead of the target aircraft;

and controlling the target aircraft to be disengaged from the carrying bin (2), and carrying the target aircraft to a charging station after enabling the other docking mechanism with the replacement aircraft idle to be engaged with the docking mechanism with the target aircraft idle and adaptive.

10. The consignment method as claimed in claim 8 wherein the step of replacing the aircraft is selected by:

11. The consignment method according to claim 10, wherein said split flying car further comprises a running chassis (3), said running chassis (3) being provided with said first docking means (a) on the top surface, said consignment method further comprising a chassis transfer mode comprising: controlling the target aircraft to converge with the running chassis (3) and:

controlling the first docking mechanism (A) on the traveling chassis (3) to be combined with the second docking mechanism (B) which is idle on the carrying cabin (2), and the traveling chassis (3) replaces the target aircraft to carry the carrying cabin (2) to a set position, or,

controlling the first docking mechanism (A) on the running chassis (3) to be jointed with the second docking mechanism (B) which is idle on the target aircraft, and carrying the combination of the carrying bin (2) and the target aircraft to a set position by the running chassis (3) instead of the target aircraft.

12. The method of claim 11, wherein in the chassis transfer mode:

if the assisted carrying request is: when the combination of the target aircraft and the carrying bin (2) is requested to be carried, the target aircraft and the carrying bin (2) are kept in an engaged state after the running chassis (3) is engaged with the carrying bin (2);

if the assisted carrying request is: upon request for individual transport of the pod (2), the target aircraft is disengaged from the pod (2) after engagement of the chassis (3) with the pod (2);

if the assisted carrying request is: when the target aircraft itself is requested to be carried individually and the carrier bins (2) are carried individually, then:

dispatching two running chassis (3), and controlling a first docking mechanism (A) of one running chassis (3) to be jointed with a second docking mechanism (B) of the carrying bin (2) which is idle, so that the running chassis (3) replaces the target aircraft to carry the carrying bin (2) to a set position;

controlling the target aircraft to disengage from the delivery cabin (2) and to engage the first docking means (A) of another one of the travelling chassis (3) with the second docking means (B) of the target aircraft, controlling the travelling chassis (3) to deliver the target aircraft itself to a charging station.

13. A flying car dispatching system, comprising a plurality of split flying cars of claim 1, further comprising a control center, and a first information collecting device, a first signal transceiver device and a first docking control device built in the flying car, wherein,

14. The hovercar dispatch system of claim 13, wherein the split type hovercar further comprises a traveling chassis (3) having the first docking mechanism (A) disposed on the top surface thereof, the hovercar dispatch system further comprises a second signal transceiving means built in the traveling chassis and a second docking control means, wherein,

15. An auto dispatch system according to claim 14,

the second state information acquisition device is used for acquiring state information of the running chassis where the second state information acquisition device is located, generating a second assisted carrying request when a second preset condition is met, and the second signal transceiver is also used for sending the second assisted carrying request to the control center;

16. The hovercar dispatch system of claim 15, further comprising a plurality of ground stations, wherein the ground stations are provided with a station master control device, the station master control device is in communication connection with the control center, and the station master control device is also in communication connection with a first state acquisition device located in an aircraft in the ground station and a second state acquisition device located in a running chassis of the ground station.

17. A flying vehicle dispatching system according to claim 16, wherein the control center effects the selection of the replacement aircraft according to preset selection rules:

18. A flying vehicle dispatching system according to any of claims 15 to 17, wherein the first and second predetermined conditions are both: energy shortage, failure or the need to perform new tasks.