CN108859640B - Air-ground dual-purpose aircraft - Google Patents
Air-ground dual-purpose aircraft Download PDFInfo
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- CN108859640B CN108859640B CN201810990200.4A CN201810990200A CN108859640B CN 108859640 B CN108859640 B CN 108859640B CN 201810990200 A CN201810990200 A CN 201810990200A CN 108859640 B CN108859640 B CN 108859640B
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- lifting
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 30
- 210000001503 joint Anatomy 0.000 claims abstract description 12
- 238000004804 winding Methods 0.000 claims description 20
- 238000013016 damping Methods 0.000 claims description 11
- 230000007246 mechanism Effects 0.000 claims description 10
- 230000009977 dual effect Effects 0.000 claims description 9
- 230000035939 shock Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 5
- 230000003028 elevating effect Effects 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000004308 accommodation Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- VVQNEPGJFQJSBK-UHFFFAOYSA-N Methyl methacrylate Chemical compound COC(=O)C(C)=C VVQNEPGJFQJSBK-UHFFFAOYSA-N 0.000 description 1
- 229920005372 Plexiglas® Polymers 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000005341 toughened glass Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
- Motorcycle And Bicycle Frame (AREA)
Abstract
The invention discloses a land-air dual-purpose aircraft, which comprises a flight execution body, a car body capable of being in butt joint with the flight execution body and a lifting device for lifting or lowering the car body relative to the flight execution body, wherein the lifting device is used for lifting or lowering the car body relative to the flight execution body; the flight execution body comprises a spiral device and a cover body which is butted with the vehicle body and shields the vehicle body; the vehicle body comprises a riding cabin body and wheels arranged on the riding cabin body; and the riding cabin body is provided with a flight control system, a vehicle body running control system and a lifting device control system. When the land-air dual-purpose aircraft disclosed by the invention lifts the vehicle body relative to the flight execution body through the lifting device and is in butt joint with the flight execution body, a user controls the flight control system to enable the vehicle body to fly in the air in combination with the flight execution body; when the vehicle body descends relative to the flight execution body through the lifting device and is separated from the flight execution body, a user can independently drive the vehicle body on a road surface by controlling the vehicle body operation control system. The air-ground dual-purpose aircraft can effectively relieve the problem of traffic jam.
Description
Technical Field
The invention relates to a vehicle, in particular to a land-air dual-purpose aircraft which can run on a road surface and fly off the ground.
Background
With the continuous development of social economy, the method has great development improvement in both urban and rural traffic road construction and mountain area or plain road network construction. More towns and rural residents purchase automobiles due to the improvement of living standard, so that the traveling is facilitated. The phenomenon of road congestion caused by the increase of the number of automobiles becomes a problem that more and more cities are difficult to avoid. Even if the automobile is owned, travel is not necessarily as convenient as imagination. Traffic jam is a normal traffic state in some places, especially in large cities, and brings a lot of inconveniences to people's daily life. The problem of alleviating traffic congestion is one of the important problems faced at present.
Therefore, it is desirable to provide a vehicle that can travel both on the road and in the air.
Disclosure of Invention
The invention aims to provide a land-air dual-purpose vehicle.
In order to solve the technical problems, the invention provides the following technical scheme: a land-air dual-purpose aircraft comprises a flight execution body, a car body capable of being in butt joint with the flight execution body and a lifting device for lifting or lowering the car body relative to the flight execution body; the flight execution body comprises a spiral device and a cover body which is butted with the vehicle body and shields the vehicle body; the vehicle body comprises a riding cabin body and wheels arranged on the riding cabin body; and the riding cabin body is provided with a flight control system, a vehicle body running control system and a lifting device control system.
Compared with the prior art, the invention has the following beneficial effects: when the land-air dual-purpose aircraft disclosed by the invention is used for lifting the vehicle body relative to the flight execution body through the lifting device and is in butt joint with the flight execution body, a user controls the flight control system to enable the vehicle body to fly in the air in combination with the flight execution body; the air-ground aircraft descends the vehicle body relative to the flight execution body through the lifting device, and when the air-ground aircraft is separated from the flight execution body, a user can independently drive the vehicle body on a road surface by controlling the vehicle body operation control system. The air-ground dual-purpose aircraft can effectively relieve the problem of traffic jam.
Preferably, the flight executing body further comprises a main body part, the plurality of screw devices are distributed on the periphery of the main body part, and the cover body is fixedly connected to the main body part and is positioned on the upper side of the main body part.
Preferably, the screw device comprises a cantilever fixedly connected with the main body part, a screw motor arranged on the cantilever, and a screw propeller connected with the screw motor; the spiral motor is controlled by a flight control system.
Preferably, the edge of the main body part extends to the periphery to form a protection wing plate surrounding a plurality of screw devices, and the protection wing plate is provided with a plurality of air guide channels respectively corresponding to a plurality of screw propellers; the screw stretches into in the air guide channel, the diameter of air guide channel is greater than the length of screw.
Preferably, the protection wing plate is provided with a plurality of landing devices which are used for being matched with the land-air dual-purpose aircraft to land and can be supported on the ground; the landing device comprises a damping support frame and a driving mechanism, wherein the damping support frame is rotatably connected with the protection wing plate, and the driving mechanism is used for pushing the damping support frame to unfold or fold relative to the protection wing plate; the driving mechanism is controlled by a flight control system.
Preferably, wheels are arranged at one end of the shock-absorbing support frame, which is supported on the ground.
Preferably, the lifting device comprises a lifting motor arranged on the vehicle body, a winding roller connected with an output shaft of the motor, a pull rope wound on the winding roller and a lifting hook bound on the pull rope; the flying execution body is provided with a hanging ring for connecting the hanging hook;
or the lifting device comprises a lifting motor arranged on the flight executing body, a winding roller connected with an output shaft of the motor, a pull rope wound on the winding roller and a lifting hook bound on the pull rope; the automobile body is equipped with rings that are used for linking the lifting hook.
Preferably, the land-air dual purpose aircraft further comprises a fixing device for fixing the vehicle body to the flight performing body.
Preferably, the fixing device comprises a pin shaft arranged on the vehicle body and a pin hole formed on the flight executing body for accommodating the expansion of the pin shaft.
Preferably, the seating cabin comprises a bearing seat for installing a seat, the bearing seat is in an open structure, and the seat body part of the seat protrudes out of the bearing seat; when the vehicle body is in butt joint with the flight execution body, the seat body part of the seat stretches into the cover body.
Drawings
FIG. 1 is a schematic perspective view of a land-air dual-purpose aircraft of the present invention;
FIG. 2 is a left side schematic view of the air-ground dual purpose aircraft of FIG. 1;
FIG. 3 is a schematic front view of a vehicle body of the air-ground dual-purpose aircraft of the present invention detached from a flight execution body and a shock-absorbing support frame deployed opposite to a protection wing plate;
FIG. 4 is a schematic bottom view of the air-ground aircraft of FIG. 1;
FIG. 5 is a perspective view of the body of the air-ground dual-purpose aircraft of the present invention detached from the flight actuator and the shock-absorbing support frame deployed against the protective wing plate;
FIG. 6 is a schematic view of the landing gear and shield wing connection of the land and air craft of the present invention;
FIG. 7 is a schematic perspective view of a body of the air-ground aircraft of the present invention;
FIG. 8 is a cross-sectional view taken along line A-A of FIG. 7;
FIG. 9 is a schematic illustration of the connection of the power supply of the air-ground aircraft of the present invention;
FIG. 10 is a schematic view of a lifting hook of a lifting device of the land-air dual-purpose aircraft of the present invention being hooked to a lifting ring;
fig. 11 is a schematic front view of a land-air dual-purpose aircraft according to another embodiment of the present invention.
Detailed Description
The following detailed description of the invention is, therefore, not to be taken in a limiting sense, and is set forth in the appended drawings. The terms "front," "rear," "left," "right," "upper," "lower," and the like refer to an orientation or positional relationship based on that shown in the drawings, for convenience of description and simplicity of description, and do not necessarily indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention. The terms "first" and "second" are used merely to simplify the description and distinguish between similar objects, and are not to be construed as precedence relationships between a particular order.
The term "separation" in the description of the present invention and the claims thereof, in which the vehicle body 2 is separated from the flight performing body 1 and independently runs on the road surface ", means that the vehicle body 2 is completely independent of the flight performing body 1, and there is no case where the vehicle bodies are connected to each other by the elevating device 3.
Example 1
Referring to fig. 1, 2 and 3, the present embodiment provides a land-air dual-purpose aircraft, which includes a flight performing body 1, a vehicle body 2 assembled or disassembled to the flight performing body 1, and a lifting device 3 for lifting or lowering the vehicle body 2 relative to the flight performing body 1. The flight actuator 1 has a screw device 4, and the screw device 4 can fly in the air by an air flow. The body 2 can be understood as a car in the prior art, but the body 2 can also be other land vehicles with power, such as: an electric wheelchair or an electric scooter, etc. The air-ground aircraft is provided with a flight control system, a car body running control system and a lifting device control system. The air-ground aircraft is controlled by a flight control system when flying in the air, and the vehicle body 2 is controlled by a vehicle body running control system when being separated from the flight execution body 1. The lifting device 3 is controlled by a lifting device control system, and the vehicle body 2 is lifted or put down relative to the flight execution body 1 by controlling the lifting device control system, so that the vehicle body 2 is conveniently assembled or detached from the flight execution body 1. When the land-air dual-purpose aircraft disclosed by the invention lifts the vehicle body 2 relative to the flight execution body 1 through the lifting device 3 and is in butt joint with the flight execution body 1, a user controls the flight control system to enable the vehicle body 2 to fly in the air in combination with the flight execution body 1; when the air-ground aircraft descends the vehicle body 2 relative to the flight execution body 1 through the lifting device 3 and is separated from the flight execution body 1, a user can independently drive the vehicle body 2 on a road surface by controlling the vehicle body operation control system. The land-air dual-purpose aircraft can effectively relieve the problem of traffic jam, and can be used for conveniently exploring mountainous areas, carrying out emergency rescue and other tasks.
Referring to fig. 1 and 4, in the present embodiment, the flight actuator 1 includes a main body 11, a screw 4 mounted on the main body 11, and a cover 12 fixedly connected to the main body 11 and located above the main body 11. The main body 11 is annular and is located in the central region of the flight actuator 1. When the vehicle body 2 is abutted against the flight vehicle 1 by the elevating device 3, it is assembled to the lower side of the main body 11. The vehicle body 2 and the cover 12 are located on the upper and lower sides of the main body 11, respectively, and are disposed opposite to each other. The cover 12 covers over the vehicle body 2 to shield the vehicle body 2 so that a closed space is formed between the cover 12 and the vehicle body 2. When the vehicle body 2 is combined with the flight execution body 1 to fly at high altitude, the cover body 12 can further improve the performance of the vehicle body 2 against atmospheric pressure. Of course, the flight actuator 1 may not be provided with a cover body, and the atmospheric pressure resistance may be realized by using a closed casing of the vehicle body itself; alternatively, the vehicle body need not be provided with a closed housing, i.e., the vehicle body 2 has an open structure (convertible), in which case the open structure of the vehicle body 2 can utilize the cover 12 as a housing against atmospheric pressure.
Referring to fig. 4, fig. 4 is a bottom view of the air-ground dual purpose aircraft. In this embodiment, the number of the screw devices 4 is eight, and the eight screw devices 4 are uniformly distributed on the periphery of the main body 11. The bottom end surface of the main body 11 is provided with eight fixing seats 13 to which eight screw devices 4 are respectively mounted. Each screw 4 comprises a cantilever 41 fixedly connected to the fixed seat 13, a screw motor 42 mounted on the cantilever 41, and a propeller 43 connected to the screw motor 42. Each cantilever 41 extends toward the periphery of the main body 11. Eight cantilevers 41 are on the same plane, and the included angle between two adjacent cantilevers 41 is 45 degrees. The propeller 43 is disposed in a spatially up-down orientation with the screw motor 42, i.e. the propeller 43 is mounted above the screw motor 42. The beneficial effect of this setting is that the screw motor 42 generates heat when the circular telegram rotates, and the air flow downwards is promoted to screw 43 when rotatory, and the air of constantly flowing is favorable to the heat dissipation of screw motor 42. The screw motor 42 is controlled by a flight control system to propel the air-ground dual purpose aircraft in the air. Of course, in other embodiments, the number of the screw devices 4 may be two, three, four, etc., and the specific number may be set as required. Wherein, when the number of the screw devices is one, the screw devices are arranged above the main body part.
Referring to fig. 1 and 4, in the present embodiment, the edge of the main body 11 extends to the periphery to form a protection wing 14 surrounding the eight screw devices 4. The protection wing plate 14 is disc-shaped and surrounds the periphery of the main body 11, and the protection wing plate 14 and the main body 11 are integrally formed. The disc-shaped protection wing plate 14 is beneficial to the flight executive body 1 to reduce air resistance, save energy consumption and improve the flight speed; and has better rotation inertia, which is beneficial to steering in the air. The protection wing plate 14 is provided with eight air guide channels 15 corresponding to eight propellers 43 respectively. If the number of the screw devices 4 is six, six air guide channels are correspondingly formed on the protection wing plate 14. The air guide channel 15 is circular, and is convenient to manufacture. The propeller 43 protrudes into the air guide channel 15, and the diameter of the air guide channel 15 is larger than the length of the propeller 43, so that the propeller 43 can rotate in the air guide channel 15. At this time, the screw motor 42 is correspondingly located below the protection wing plate 14 (as shown in fig. 2). The protection wing plate 14 provided with the plurality of air guide channels 15 can prevent the screw 43 from colliding with other objects, prolong the service life of the screw device 4 and prevent the screw 43 from damaging the other objects.
Referring to fig. 2 to 6, in the present embodiment, eight landing devices 5 for landing and supporting the land-air craft are mounted on the protection wing plate 14. Eight landing gear 5 are uniformly distributed on the disc-shaped protection wing plate 14 (as shown in fig. 4), and are connected to the lower end surface of the protection wing plate 14. Referring to fig. 6, each landing gear 5 includes a shock absorbing support frame 51 rotatably connected to the protection wing plate 14, and a driving mechanism 52 for pushing the shock absorbing support frame 51 to be unfolded or folded relative to the protection wing plate 14. The shock absorbing support frame 51 includes a first rod 511, a second rod 512 telescopically coupled to the first rod 511, and a telescopic spring 513 coupled between the first rod 511 and the second rod 512. The lower end face of the protection wing plate 14 is welded with a fixed ear seat 141, and the top end of a first rod body 511 of the shock-absorbing support frame 51 is hinged to the fixed ear seat 141 through a pin shaft. The second rod 512 is used for supporting on the ground. The end of the second rod 512 supported on the ground is bent to disperse the reaction force of the ground to the shock-absorbing support frame 51. Preferably, a wheel (not shown) is installed at one end of the second rod body 512 supported on the ground, and when the flight performing body 1 falls on the uneven ground, a balance point of the flight performing body 1 is found by the homeotropic rolling of the wheel, so that the stability of the flight performing body 1 can be improved when falling.
The driving mechanism 52 of the landing gear 5 includes a motor 521, a gear 522 connected to an output shaft of the motor, a rack 523 engaged with the gear 522, a slide groove 524 in which the rack 523 is mounted, and a push lever 525 rotatably connected to the rack 523. The motor 521 and the sliding groove 524 are fixedly connected to the lower end surface of the protection wing plate 14. When the flight control system drives the motor 521 to rotate, the rack 523 slides relative to the slide groove 524. One end of the push rod 525 is hinged to the rack 523, and the other end is hinged to the middle of the first rod 511. The shock supporting frame 51 can be unfolded or folded with respect to the protection wing plate 14 by the forward and reverse rotation of the motor 521. The shock-absorbing support frames 51 and the racks 523 are staggered in space, that is, the shock-absorbing support frames 51 and the racks 523 are respectively located at two sides of the pushing rod 525, so that the racks 523 and the motor 521 can be avoided when the shock-absorbing support frames 51 are folded relative to the protection wing plates 14. In other embodiments, the number of landing devices 5 may be three, four, five, etc., and the specific number may be set as needed; the driving mechanism 52 may also be a cylinder or an electric push rod.
The drive mechanism 52 of the landing gear 5 is controlled by the flight control system. When the land-air dual-purpose aircraft flies in the air, the damping support frame 51 of the landing device 5 is in a folding state relative to the protection wing plate 14 (as shown in fig. 2) so as to reduce wind resistance; when the vehicle body 2 needs to be separated from the flight execution body 1 and independently runs on the road surface, the flight execution body 1 starts to fall, and the shock absorbing support frame 51 is unfolded relative to the protection wing plate 14 (as shown in fig. 3 and 5). The flying execution body 1 is supported on the ground through the landing device 5, the vehicle body 2 is lowered relative to the ground through the lifting device 3 and separated from the flying execution body 1, and after the vehicle body 2 is separated from the flying execution body 1, the vehicle body 2 can be driven to move on the ground through the vehicle body operation control system.
Referring to fig. 7, in the present embodiment, the vehicle body 2 has an open structure. The vehicle body 2 includes a cabin 21 for a user to ride and drive, and wheels 22 mounted on the cabin 21. The cabin 21 is in the shape of a circular bowl, and the diameter of the upper end surface is larger than that of the lower end surface. The round riding cabin 21 is beneficial to the reduction of air resistance of the vehicle body 2 and the energy consumption is saved. Of course, the cabin 21 may be square or spherical. The cabin 21 is provided with a seat 23 for a user. The vehicle body operation control system, the flight control system, and the lifter control system are all provided on the cabin 21. The vehicle body operation control system is applied to a land piloting mode, and the flight control system is applied to a flight piloting mode. The vehicle body operation control system and the flight control system are driving control operation systems in the prior art. The user may switch between the body operation control system and the flight control system according to the desired ride mode.
Referring to fig. 8, the cabin 21 includes a fixed base 212 on which the wheels 22 are mounted, a load-bearing seat 211 fixedly connected to the fixed base 212 for mounting the seat 23, and a power supply 213 for supplying operating power to the air-ground aircraft. The number of wheels 22 mounted on the fixed base 212 is three, and three wheels 22 are mounted on the bottom of the fixed base 212 in a triangle shape (as shown in fig. 4). One wheel 22 is mounted to the front of the vehicle body 2, and the other two wheels 22 are mounted to the rear of the vehicle body 2. The rear two wheels 22 are fitted with drive motors connected to a power source 213 and controlled by the vehicle body running control system, the front wheels 22 being driven by the rear wheels 22. Alternatively, the front one wheel 22 is fitted with a drive motor, the rear two wheels 22 being driven from the front one wheel 22; still alternatively, the front and rear three wheels 22 are each fitted with a drive motor. In the present embodiment, the wheel 22 on which the drive motor is mounted is employed as a hub motor wheel, and the mounting volume can be reduced.
The fixing base 212 has a concave shape and constitutes a first accommodation groove in which the power supply 213 is installed. The bearing seat 211 is covered above the fixed base 212. The bearing seat 211 is recessed toward the fixed base 212 with respect to the wall of the fixed base 212, and forms a second accommodation groove for the mounting seat 23. The bottom of the second accommodating groove extends into the first accommodating groove of the fixed base 212, and the bottom wall of the second accommodating groove and the fixed base 212 are enclosed to form a closed accommodating space for installing the power supply 213. The fixing base 212 and the bearing base 211 are provided with heat dissipation holes so as to facilitate heat dissipation of the power supply 213. The fixed base 212 is provided with a charging interface, and the charging interface is connected to a power supply 213 through a power line.
Referring to fig. 2 and 8, the bearing seat 211 has an open structure, and the seat body 231 of the seat 23 protrudes from the bearing seat 211. When the vehicle body 2 is abutted against the main body 11 of the flight performing body 1, the seat body 231 of the seat 23 extends into the cover 12. The seat body 231 of the seat 23 extends through the annular main body 11 and into the cover 12, so that the overall volume of the vehicle body 2 when the vehicle body 1 is abutted against the flight actuator 1 can be relatively reduced, and the air resistance can be reduced. The cover 12 has a hemispherical shape. The hemispherical cover 12 can further increase the accommodating space on the basis of meeting the air diversion, so that the vehicle body 2 can further extend into the cover 12 of the flight executing body 1. The main body 11 is provided with a fixing bracket 13 for fixing the cover 12 to enhance the mounting firmness of the cover 12. The cover 12 is a transparent substrate, for example: tempered glass or plexiglass. Facilitating the user to view the exterior through the housing 12. It should be noted that: when a user observes the external situation, the cover 12 may not adopt a transparent substrate, and only a plurality of cameras need to be installed on the periphery of the flight execution body 1, and the cameras are connected to an image display system installed in the cabin 21, and the image display system is provided with a display screen.
Referring to fig. 9, in the present embodiment, the power supply 213 mounted on the stationary base 212 of the vehicle body 2 is electrically connected to the above-described respective control systems, the driving motor mounted on the wheels 22, the lifting motor 31 of the lifting device 3, the eight screw devices 4, and the eight landing devices 5, respectively. Each control system refers to a flight control system, a vehicle body operation control system and a lifting device control system. Wherein, each control system, the driving motor arranged on the wheel 22 and the lifting motor 31 of the lifting device 3 are arranged on the vehicle body 2; eight screws 4 and eight landing gear 5 are mounted on the flight actuator 1. In order to conveniently and electrically connect the power supply 213 mounted on the vehicle body 2 to the eight screw devices 4 and the eight landing devices 5 mounted on the flight performing body 1, the carrying seat 211 of the vehicle body 2 is provided with a male connector for communicating with a power line, and the main body 11 of the flight performing body 1 is provided with a female connector matched with the male connector. The male connector is connected to the power supply 213 via a power line, and the female connector is electrically connected to the eight screw devices 4 and the eight landing devices 5, respectively, via a power line. When the bearing seat 211 of the vehicle body 2 is in butt joint with the main body 11 of the flight executing body 1, the male connector is correspondingly inserted into the female connector, so that the power supply 213 between the upper body and the lower body is communicated. Of course, in other embodiments, the power supply 213 may be mounted on the flight performing body 1 (i.e. the power supply is not mounted on the vehicle body, which is applicable to the case that the vehicle body does not need to be separately operated on the road), and the power supply mounted on the flight performing body 1 is electrically connected to the eight screw devices and the eight landing devices, and also electrically connected to the wheel driving motor mounted on the vehicle body, each control system, and the lifting motor 31 of the lifting device 3 through the male and female connectors; alternatively, another power source is separately installed on the flight performing body 1 (i.e., one power source 213 is installed on each of the vehicle body 2 and the flight performing body 1), and at this time, the other power source installed on the flight performing body 1 is electrically connected to the eight screw devices 4 and the eight landing devices 5; a power supply 213 mounted on the vehicle body 2 is electrically connected to the lifting motor 31 of the lifting device 3, the respective control systems, and the wheel drive motor; facilitating the routing of power supply 213. It should be noted that: the power source provided by the invention for the operation of the land-air dual-purpose aircraft is not limited to the power source 213, and can be energy generated by engine conversion by using fuel oil or energy converted by hybrid fuel and electricity.
The bearing seat 211 and the main body 11 are also provided with a male connector and a female connector which are communicated with signal wires, so that a user can control eight screw devices 4 and eight landing devices 5 in a wired manner through a flight control system when the land-air dual-purpose aircraft is in a flight driving mode. Of course, the flight control system can also control the eight screw devices 4 and the eight landing devices 5 by wireless control.
Referring to fig. 5 and 10, in the present embodiment, the number of the lifting devices 3 is four, and four lifting devices 3 are respectively mounted on the front and rear portions of the vehicle body 2, and two lifting devices 3 are respectively disposed on the front and rear portions and are opposite to each other. Each lifting device 3 includes a lifting motor 31 mounted on a bearing seat 211 of the vehicle body 2, a winding roller 33 connected to an output shaft 32 of the motor, a pulling rope 34 wound around the winding roller 33, and a hook 35 bound to the pulling rope 34. The main body 11 of the flight executing body 1 is provided with a hanging ring 16 for connecting the hanging hook 35. The lift motor 31 mounted on the vehicle body 2 is electrically connected to a power supply 213 mounted on the vehicle body 2 and controlled by a lift control system. The lifting device control system is controlled so that the vehicle body 2 can be lifted or put down relative to the flight execution body 1, so that the vehicle body 2 can be connected and disconnected relative to the flight execution body 1. The lifting device 3 is provided with a locking piece for limiting the rotation of the motor output shaft, the locking piece can prevent the motor output shaft from rotating accidentally, when the vehicle body 2 is in butt joint with the flight execution body 1 and flies in the air, the vehicle body 2 can be prevented from being detached from the flight execution body 1, and the safety of the flight is ensured.
In this embodiment, the air-ground dual purpose vehicle includes a fixing device for fixing the vehicle body 2 to the flight performing body 1. The fixing device comprises a pin shaft and a pin hole matched with the pin shaft to limit. The pin is mounted on the bearing seat 211 of the vehicle body 2, and a pin hole is formed on the main body 11 of the flight actuator 1, and can accommodate the expansion and contraction of the pin. When the bearing seat 211 of the vehicle body 2 is abutted against the main body 11 of the flight performing body 1, the user manually positions the pin shaft in the pin hole, so that the vehicle body 2 is firmly abutted against the flight performing body 1. The fixing device can prevent the vehicle body 2 from being detached from the flight executing body 1 under the conditions that the motor output shaft rotates accidentally and the locking piece loosens accidentally, so that the safety of flight is further ensured. When the vehicle body 2 is detached from the flight vehicle 1, the pin needs to be separated from the pin hole by the user.
Of course, in other embodiments, the fixing device may also be a locking device. The latch includes a lock lever mounted to the main body 11, a fixing portion mounted to the bearing 211, a locking ring rotatably coupled to the fixing portion, and a handle coupled to the locking ring. When the bearing seat 211 of the vehicle body 2 is abutted to the main body 11 of the flight executing body 1, a user pulls the handle to enable the lock ring to be buckled to the lock rod, so that the vehicle body 2 is firmly abutted to the flight executing body 1. In addition, when the vehicle body 2 is detached from the flight performing body 1, the user is required to pull the handle in the opposite direction to disengage the lock ring from the lock rod.
When the state that the vehicle body 2 independently runs on the road surface is converted into the state that the vehicle body 2 is combined with the flight execution body 1 to fly in the air, the vehicle body 2 needs to be lifted relative to the flight execution body 1 and is butted with the flight execution body 1, wherein the power line male and female connector and the signal line male and female connector can be correspondingly butted. The specific butt joint process comprises the following steps: at this time, the flight vehicle 1 is supported on the ground by the landing gear 5, and the screw 4 of the flight vehicle 1 is stopped. The vehicle body 2 moves to the lower part of the main body part 11 of the flight execution body 1 through the control of the vehicle body running control system, and a user closes the vehicle body running control system to stop the movement of the vehicle body 2; the user controls the lifting device control system to start the lifting motor 31, the lifting motor 31 rotates positively and releases the pull rope 34 wound on the winding roller 33; the length of the stay cord 34 to be released is such that the lifting hook 35 can contact the lifting ring 16, and the lifting motor 31 stops rotating positively; the user manually hangs and buckles the hanging hooks 35 of the four lifting devices 3 on the four hanging rings 16 of the flying actuating body 1 respectively, after the hanging and buckling are finished, the user controls the lifting device control system to enable the lifting motor 31 to reversely rotate, and the released pull rope 34 is wound on the winding roller 33; the lifting device 3 drives the vehicle body 2 to move relative to the flight execution body 1 while winding the pull rope 34, the vehicle body 2 is correspondingly butted with the flight execution body 1, and the power line male and female connector and the signal line male and female connector can also be correspondingly butted; the user starts the flight control system and controls the propellers 43 of the eight screws 4 to rotate and fly in the air; after the land-air dual-purpose aircraft leaves the ground, a user controls the eight landing devices 5 through the flight control system, and the damping support frames 51 are folded relative to the protection wing plates 14. The ground-air dual-purpose aircraft is converted from a state that the vehicle body 2 independently runs on the road surface to a state that the vehicle body 2 and the flight execution body 1 fly in the air.
When the air-ground aircraft is converted from a state that the vehicle body 2 is combined with the air-ground executing body 1 to a state that the vehicle body 2 independently operates on a road surface, the vehicle body 2 needs to descend relative to the air-ground executing body 1 and be separated from the air-ground executing body 1, wherein the power line male and female connector and the signal line male and female connector can be correspondingly separated. The specific separation process comprises the following steps: the user reduces the flying speed through the flying control system and flies to the position above the target landing point; a user controls eight landing devices 5 through a flight control system, and deploys the damping support frame 51 relative to the protection wing plate 14; when the flying height of the land-air dual-purpose aircraft is reduced and the shock absorption support frame 51 can be contacted with the ground and stably supported on the ground (when the vehicle body 2 is in butt joint with the flying executing body 1 and suspended in the air), a user closes the flying control system; the user controls the lifting device control system to start the lifting motor 31, the lifting motor 31 rotates positively and releases the pull rope 34 wound on the winding roller 33; the lifting device 3 drives the vehicle body 2 to be detached relative to the flight execution body 1 and approach to the ground when releasing the pull rope 34, the vehicle body 2 is correspondingly detached from the flight execution body 1, and the power line male and female connector and the signal line male and female connector can be correspondingly detached; the length of the stay cord 34 to be released is such that the lifting motor 31 stops rotating forward after the wheels 22 of the vehicle body 2 are supported on the ground; the user manually separates the lifting hooks 35 of the four lifting devices 3 from the four lifting rings 16 of the flying actuating body 1 respectively, and after the separation is finished, the user controls the lifting device control system to enable the lifting motor 31 to reversely rotate and winds the released pull rope 34 on the winding roller 33; the user turns on the vehicle body running control system so that the vehicle body 2 moves and independently runs on the road surface. The ground-air dual-purpose aircraft is converted from a state that the vehicle body 2 is combined with the flight execution body 1 to fly in the air to a state that the vehicle body 2 independently runs on a road surface.
When the vehicle body 2 of the air-ground dual-purpose aircraft is combined with the flight execution body 1 to fly in the air and passengers need to get on and get off, the method specifically comprises the following steps: the pilot reduces the flying speed through a flying control system and flies to the position of a target passenger or above a target landing point; the driver controls the eight landing devices 5 through the flight control system to unfold the damping support frame 51 relative to the protection wing plate 14; when the flying height of the land-air dual-purpose aircraft is reduced and the shock absorption support frame 51 can be contacted with the ground and stably supported on the ground (at the moment, the vehicle body 2 is in butt joint with the flying executing body 1 and is suspended in the air), a pilot closes the flying control system; the driver controls the lifting device control system to start the lifting motor 31, and the lifting motor 31 rotates forward and releases the pull rope 34 wound on the winding roller 33; the lifting device 3 drives the vehicle body 2 to be detached relative to the flight execution body 1 and approach to the ground when releasing the pull rope 34, the vehicle body 2 is correspondingly detached from the flight execution body 1, and the power line male and female connector and the signal line male and female connector can be correspondingly detached; the length of the stay cord 34 to be released is such that the lifting motor 31 stops rotating forward after the wheels 22 of the vehicle body 2 are supported on the ground; the target passengers enter the vehicle body 2, or the passengers in the vehicle body 2 leave the vehicle body 2, so that the procedure of getting on and off the passengers can be completed; the driver controls the lifting device control system to enable the lifting motor 31 to reversely rotate, and the released pull rope 34 is wound on the winding roller 33; the lifting device 3 drives the vehicle body 2 to move relative to the flight execution body 1 while winding the pull rope 34, the vehicle body 2 is correspondingly butted with the flight execution body 1, and the power line male and female connector and the signal line male and female connector can also be correspondingly butted; the pilot starts the flight control system and controls the propellers 43 of the eight screws 4 to rotate and fly in the air; after the land and air dual-purpose aircraft leaves the ground, a pilot controls the eight landing devices 5 through the flight control system, and the damping support frame 51 is folded relative to the protection wing plate 14.
It should be noted that: the above three embodiments are all based on the technical scheme that the power supply 213 and the lifting device 3 are mounted on the vehicle body 2 and each control system is controlled by a wired control mode. In other embodiments, the lifting device 3 may be mounted on the flight performing body 1, and another power source is mounted on the flight performing body 1, and the other power source is electrically connected to the lifting device 3, the screw device 4 and the landing device 5, respectively. Each control system installed on the vehicle body 2 controls the lifting device 3, the screw device 4 and the landing device 5 by means of wired control when the vehicle body 2 is coupled to the flight execution body 1; the respective control systems mounted on the vehicle body 2 control the elevating device 3, the screw device 4, and the landing device 5 by means of wireless control when the vehicle body 2 is detached from the flight execution body 1. Reference is made to the above-mentioned procedure for specific procedures.
When the lifting device 3 is mounted on the flight performing body 1, the lifting device 3 includes a lifting motor 31 mounted on the flight performing body 1, a winding roller 33 connected to an output shaft 32 of the motor, a pull rope 34 wound around the winding roller 33, and a hook 35 bound to the pull rope 34. The carrying seat 211 of the car body 2 is provided with a hanging ring 16 for engaging the hanging hook 35.
The other power supply is electrically connected to the elevating device 3, the screw device 4 and the landing device 5 when the other power supply is installed on the flight performing body 1. When the air-ground aircraft needs to get on or off passengers, the pilot can control the flight execution body 1 in a wireless control mode without closing the flight control system. The flight execution body 1 can hover the flight execution body 1 in mid-air through the flight control system without unfolding the shock absorption support frame 51, the vehicle body 2 is lowered relative to the ground through the lifting device 3, passengers can leave the vehicle body 2 when the vehicle body 2 is supported on the ground, the vehicle body 2 rises relative to the ground through the lifting device 3 and is butted with the flight execution body 1, and at the moment, the flight execution body 1 flies in the air again.
Example two
Referring to fig. 11, the second embodiment differs from the first embodiment in that no wheel is mounted on the vehicle body 20. At this time, the vehicle body 20 may be understood as a cabin. The vehicle body 20 also does not need to be independently operated on the road surface.
Finally, it should be noted that: the above embodiments are only for illustrating the present invention and not for limiting the technical solution described in the present invention; thus, although the present invention has been described in detail with reference to the above embodiments, it will be understood by those skilled in the art that the present invention may be modified or equivalent; all technical solutions and modifications thereof that do not depart from the spirit and scope of the present invention are intended to be included in the scope of the appended claims.
Claims (5)
1. A land-air dual-purpose aircraft, characterized in that: the lifting device is used for lifting or lowering the vehicle body relative to the flight execution body; the flight execution body comprises a spiral device and a cover body which is butted with the vehicle body and shields the vehicle body; the vehicle body comprises a riding cabin body and wheels arranged on the riding cabin body; the riding cabin body is provided with a flight control system, a vehicle body operation control system and a lifting device control system;
the flight execution body further comprises a main body part;
the screw device comprises a cantilever fixedly connected with the main body part, a screw motor arranged on the cantilever and a screw propeller connected with the screw motor; the spiral motor is controlled by a flight control system;
the edge of the main body part extends to the periphery to form a protection wing plate surrounding a plurality of screw devices, and the protection wing plate is provided with a plurality of air guide channels respectively corresponding to a plurality of screw propellers; the propeller extends into the air guide channel, and the diameter of the air guide channel is larger than the length of the propeller;
the protection wing plates are provided with a plurality of landing devices which are used for being matched with the land-air dual-purpose aircraft to land and can be supported on the ground; the landing device comprises a damping support frame and a driving mechanism, wherein the damping support frame is rotatably connected with the protection wing plate, and the driving mechanism is used for pushing the damping support frame to unfold or fold relative to the protection wing plate; the driving mechanism is controlled by a flight control system;
the lifting device comprises a lifting motor arranged on the vehicle body, a winding roller connected with an output shaft of the motor, a pull rope wound on the winding roller and a lifting hook bound on the pull rope; the flying execution body is provided with a hanging ring for connecting the hanging hook;
or the lifting device comprises a lifting motor arranged on the flight executing body, a winding roller connected with an output shaft of the motor, a pull rope wound on the winding roller and a lifting hook bound on the pull rope; the automobile body is equipped with rings that are used for linking the lifting hook.
2. The land-air dual purpose aircraft of claim 1, wherein: the shock-absorbing support frame supports one end on the ground and is provided with wheels.
3. The land-air dual purpose aircraft of claim 1, wherein: the air-ground aircraft further comprises a fixing device for fixing the vehicle body to the flight execution body.
4. A land-air dual purpose aircraft according to claim 3, characterized in that: the fixing device comprises a pin shaft arranged on the vehicle body and a pin hole formed in the flight executing body for accommodating the expansion of the pin shaft.
5. The land-air dual purpose aircraft of claim 1, wherein: the riding cabin body comprises a bearing seat for installing a seat, the bearing seat is of an open structure, and the seat body part of the seat protrudes out of the bearing seat; when the vehicle body is in butt joint with the flight execution body, the seat body part of the seat stretches into the cover body.
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| CN201810990200.4A CN108859640B (en) | 2018-08-28 | 2018-08-28 | Air-ground dual-purpose aircraft |
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| CN201810990200.4A CN108859640B (en) | 2018-08-28 | 2018-08-28 | Air-ground dual-purpose aircraft |
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| CN110254150A (en) * | 2019-06-28 | 2019-09-20 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
| CN110303843A (en) * | 2019-06-28 | 2019-10-08 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
| CN110303838A (en) * | 2019-06-28 | 2019-10-08 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
| CN110303842A (en) * | 2019-06-28 | 2019-10-08 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
| CN110303841A (en) * | 2019-06-28 | 2019-10-08 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
| CN110303839A (en) * | 2019-06-28 | 2019-10-08 | 长城汽车股份有限公司 | Operation method and device for flight vehicle |
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