CN112193409B

CN112193409B - Aircraft based on 5G and cluster control method based on aircraft

Info

Publication number: CN112193409B
Application number: CN202011156779.8A
Authority: CN
Inventors: 不公告发明人
Original assignee: Guangdong Xunxia Technology Co ltd
Current assignee: Guangdong Xunxia Technology Co ltd
Priority date: 2020-10-26
Filing date: 2020-10-26
Publication date: 2022-07-29
Anticipated expiration: 2040-10-26
Also published as: CN112193409A

Abstract

The invention discloses a 5G-based aircraft, which comprises an aircraft body and a rotor wing arranged on the aircraft body, wherein a base is arranged at the bottom of the aircraft body, supporting legs are arranged at two sides of the base at the bottom of the aircraft body, one ends of the supporting legs are hinged to the bottom of the aircraft body, the other ends of the supporting legs are buckled with the base, a fixed seat is arranged at the top of the aircraft body, a landing buffer device for the aircraft is installed through the fixed seat, an aircraft charging device is arranged on the landing buffer device, a guiding charging head for starting the aircraft charging device is arranged on the bottom surface of the base, and a signal transmission module, an information receiving module, a power supply module and a main control module are further assembled in the base. The base is arranged at the bottom of the aircraft charging device, and the guide charging head for starting the aircraft charging device is arranged on the base, so that the other aircraft can be charged by the aircraft charging device arranged at the upper end of the aircraft body in the flying process, and the flying distance of the aircraft is increased.

Description

Aircraft based on 5G and cluster control method based on aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft based on 5G and a cluster control method based on the aircraft.

Background

Along with the development of science and technology and the progress of technique, unmanned aerial vehicle has been applied to each trade of society more and more, unmanned aerial vehicle carries the battery and supplies power for the operation flight, it is great at operation flight in-process power consumption, conventional unmanned aerial vehicle charging mode is for charging unmanned aerial vehicle's battery through pegging graft the plug on unmanned aerial vehicle's battery charging socket, but battery endurance is not strong, and unmanned aerial vehicle in the flight process can not charge, so unmanned aerial vehicle's maximum flight distance is restricted, so unmanned aerial vehicle's range of application has been restricted.

Disclosure of Invention

The invention aims to solve the technical problems to a certain extent, and provides a 5G-based aircraft which can charge the flying aircraft and improve the flying distance of the aircraft.

The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides an aircraft based on 5G, includes the fuselage and sets up the rotor on the fuselage, the fuselage bottom is equipped with the base, the fuselage bottom is located the base both sides and is equipped with the supporting legs, and the one end of supporting legs articulates in the fuselage bottom, and the base is withheld to its other end, the fuselage top is equipped with the fixing base to install the descending buffer that the aircraft was used through the fixing base, be equipped with aircraft charging device on the descending buffer, and the pedestal bottom surface is equipped with the guide head that charges that is used for opening aircraft charging device, inside signal transmission module, information receiving module, power module and the host system of still being equipped with of base.

In some preferred embodiments, the fixing seat is assembled in a mounting groove formed in the top of the machine body, a clamping block penetrates through the side surface of the upper end of the mounting groove, the clamping block is connected with a transmission shaft inside the machine body, a sliding groove penetrates through the side surface of the bottom of the mounting groove, a push rod is arranged in the sliding groove in a sliding mode, the push rod is extruded when the fixing seat is assembled in the mounting groove, the push rod pushes the transmission shaft, the transmission shaft drives the clamping block to move, and the clamping block is buckled in a locking groove formed in the side surface of the fixing seat. So, can form the auto-lock through driven mode and fix, the dismouting of the base of being convenient for guarantees simultaneously that the base can be stable fixes in the fuselage bottom.

In some preferred embodiments, descending buffer includes fixed plate, buffer board and mounting panel, the up end at the fixing base is installed to the fixed plate bolt, the fixed plate up end is equipped with first buffer spring to being connected with the buffer board through first buffer spring, the buffer board border is equipped with all around and adjusts the elastic component, adjust the regulating plate swing joint that elastic component and mounting panel bottom surface set up, the buffer board is equipped with the intermediate position of first buffer spring homonymy terminal surface and is equipped with the alignment jig, and the inside upwards extension of alignment jig is equipped with the regulation pole, and should adjust the upper end and the mounting panel fixed connection of pole, adjust the pole and fix on the alignment jig through the pivot that runs through the alignment jig side setting. So, can eliminate the vibration that produces when the aircraft lands another aircraft upper end, guarantee the steadiness that the aircraft charges.

In some preferred embodiments, the adjusting frame is provided with two inclined rods at two sides of the adjusting rod, and two ends of each inclined rod are respectively connected with the adjusting frame and the adjusting rod. So, the down tube can offset and shake about producing when adjusting the pole atress, makes the stability of adjusting the pole assurance position, improves the effect that the aircraft charges.

In some preferred embodiments, a second buffer spring is sleeved outside the inclined rod, one end of the second buffer spring abuts against an auxiliary annular protrusion arranged on the outer surface of the inclined rod, and the other end of the second buffer spring abuts against the adjusting rod. Thus, the reaction force of the diagonal rod is increased by the recoil force of the second buffer spring.

In certain preferred embodiments, the pedestal top surface extends upwards to be equipped with the pillar, and the pillar top is provided with the solid fixed ring of taking the internal thread, gu fixed ring can be rotatory around self axis, fuselage bottom downwardly extending is equipped with the card post of outband screw thread, gu fixed ring just, the counter-rotation assembles the base screw thread on the card post of fuselage bottom. Therefore, the installation of the base at the bottom of the machine body is facilitated, and the stability of the installation of the base is improved.

In some preferred embodiments, the aircraft charging device comprises a rectangular base and an aircraft charging platform, wherein a clamping groove matched with the appearance of the mounting plate is formed in the bottom surface of the rectangular base, and the aircraft charging platform is arranged in the center of the top surface of the rectangular base and electrically connected with an internal power module.

In some preferred embodiments, be equipped with three shape and the same bounding walls of structure on the rectangle base and wrap up aircraft charging platform setting, the one end swing joint of bounding wall is at rectangle base lateral wall top, and its other end closes to disturb upwards and forms the circular cone shape, and the top is equipped with and guides the first assorted start-up hole that charges. So, bounding wall parcel lives aircraft charging platform when not charging, avoids it to receive external damage under the state of not using.

In some preferred embodiments, the inner surface of the enclosing plate extends upwards to form a positioning protrusion matched with the shape of the base. So, the location is protruding to play the effect of assistance-localization real-time, helps the aircraft landing stability in position.

A cluster control method of an aircraft comprises a plurality of aircraft, each aircraft is a node, and the plurality of aircraft are divided into a plurality of logic groups, wherein one aircraft serves as a cluster guide aircraft; the method specifically comprises the following steps:

s1, when the cluster-guided aircraft is insufficient in power supply, a signal transmission module of the aircraft sends out a signal, and the condition of the aircraft closest to the node in the logic group is analyzed;

s2, the signal receiving module receives the conditions of the aircrafts in the logic group, the cluster guides the aircrafts to fly to the aircrafts close to the node and with sufficient power supply through the main control module, and meanwhile, the selected aircrafts wait in situ;

S3, the cluster guides the aircraft to reach the position right above the selected aircraft, the aircraft descends through the main control module, when the cluster guides the aircraft to descend, the charging head of the cluster guides the enclosing plate at the upper end of the selected aircraft to be opened, the enclosing plate is opened, the internal aircraft charging platform is exposed, meanwhile, the aircraft descends to the aircraft charging platform for charging, the landing buffer device can buffer the shake generated when the cluster guides the aircraft to land, and the cluster guides the aircraft to land stably on the aircraft charging platform of the selected aircraft for charging;

and S4, the cluster guides the aircraft to fly away from the selected aircraft after charging is finished, the selected aircraft continues flying, and the selected aircraft lands in place or returns.

Compared with the prior art, the beneficial effects are that: the base is arranged at the bottom of the aircraft, the guide charging head used for opening the aircraft charging device is arranged on the base, so that the other aircraft can be charged through the aircraft charging device arranged at the upper end of the aircraft body in the flight process, the flight distance of the aircraft is increased, further, the base is fixed on the aircraft body through the supporting legs and the fixing rings, tools are not needed in assembly and disassembly, the aircraft charging device is convenient to assemble and disassemble, the aircraft charging device is arranged on a landing buffer device at the top of the aircraft body, when the aircraft falls onto the aircraft charging device of the other aircraft, vibration caused by the aircraft can be eliminated through the landing buffer device, inertia of the aircraft in landing can be effectively buffered, the stability of the aircraft in landing is improved, and the charging safety of the aircraft is ensured.

Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Drawings

The invention is further illustrated with reference to the following figures and examples.

FIG. 1 is an assembly view of a landing gear and an aircraft charging device for an aircraft according to the present invention.

Fig. 2 is an assembly view of the landing gear and the aircraft charging device of the aircraft of the present invention.

FIG. 3 is an assembly view of the landing gear and the aircraft charging device of the aircraft of the present invention.

Fig. 4 is a partially enlarged view of fig. 3.

Fig. 5 is an exploded view of the assembly of the main body and the fixing base according to the present invention.

Description of the drawings: 1. a body; 2. a base; 3. supporting legs; 4. a pillar; 5. a fixing ring; 6. clamping the column; 7. a fixed seat; 8. a landing buffer device; 801. a fixing plate; 802. a buffer plate; 803. mounting a plate; 804. a first buffer spring; 805. adjusting the elastic member; 806. an adjusting plate; 807. an adjusting bracket; 808. adjusting a rod; 809. a rotating shaft; 9. a clamping block; 10. a drive shaft; 11. a push rod; 12. a locking groove; 13. an aircraft charging device; 1301. a rectangular base; 1302. an aircraft charging platform; 1303. enclosing plates; 14. guiding a charging head; 15. a diagonal bar; 16. a second buffer spring.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic views illustrating only the basic structure of the present invention in a schematic manner, and thus show only the constitution related to the present invention.

In the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation and operation, and thus should not be construed as limiting the invention; the terms "first", "second", and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The invention is implemented as follows: as shown in figures 1-5, the 5G-based aircraft comprises a fuselage 1 and a rotor wing arranged on the fuselage 1, wherein the bottom of the fuselage 1 is provided with a base 2, the bottom of the fuselage 1 is provided with supporting legs 3 positioned at two sides of the base 2, one end of each supporting leg 3 is hinged at the bottom of the fuselage 1, the other end of the base is buckled with the base 2, further, a support column 4 extends upwards from the top surface of the base 2, a fixing ring 5 with internal threads is arranged at the top end of the support column 4, the fixing ring 5 can rotate around the axis of the fixing ring, a clamping column 6 with external threads extends downwards from the bottom of the machine body 1, the fixing ring 5 rotates forwards and backwards to assemble the base 2 on the clamping column 6 at the bottom of the machine body 1 in a threaded manner, the installation of the base 2 at the bottom of the aircraft body 1 is facilitated through the two sections of fixing structures, the installation stability of the base 2 is improved, the top of the aircraft body 1 is provided with a fixed seat 7, and a landing buffer device 8 for the aircraft is installed through the fixed seat; specifically, the fixing seat 7 is assembled in a mounting groove formed in the top of the machine body 1, a clamping block 9 penetrates through the side face of the upper end of the mounting groove, the clamping block 9 is connected with a transmission shaft 10 in the machine body 1, a sliding groove is formed in the side face of the bottom of the mounting groove, a push rod 11 is arranged in the sliding groove in a sliding mode, when the fixing seat 7 is assembled in the mounting groove, the push rod 11 is extruded, the transmission shaft 10 is pushed by the push rod 11, the transmission shaft 10 drives the clamping block 9 to move, the clamping block 9 is buckled in a locking groove 12 formed in the side face of the fixing seat 7, self-locking fixing is formed in a transmission mode, and the base 2 can be conveniently assembled and disassembled while the base 2 can be stably fixed to the bottom of the machine body 1; the landing buffer device 8 is provided with an aircraft charging device 13, the bottom surface of the base 2 is provided with a guide charging head 14 for starting the aircraft charging device 13, and the base 2 is also internally provided with a signal transmission module, an information receiving module, a power supply module and a main control module.

In this embodiment, as shown in fig. 4, the drop buffering device 8 includes a fixing plate 801, a buffering plate 802 and a mounting plate 803, the fixing plate 801 is bolted to the upper end surface of the fixing base 7, the upper end surface of the fixing plate 801 is provided with a first buffering spring 804, the buffer plate 802 is connected with a first buffer spring 804, the edge of the buffer plate 802 is provided with an adjusting elastic member 805 around, the adjusting elastic member 805 is movably connected with an adjusting plate 806 arranged on the bottom surface of the mounting plate 803, the buffer plate 802 is provided with the first buffer spring 804, an adjusting frame 807 is arranged at the middle position of the end surface at the same side with the first buffer spring 804, an adjusting rod 808 extends upwards in the adjusting frame 807, the upper end of the adjusting rod 808 is fixedly connected with the mounting plate 803, the adjusting rod 808 is fixed on the adjusting bracket 807 through a rotating shaft 809 which penetrates through the side surface of the adjusting bracket 807, so can eliminate the vibration that produces when the aircraft lands another aircraft upper end, guarantee the steadiness that the aircraft charges.

In this embodiment, as shown in fig. 4, the adjusting frame 807 is provided with the diagonal rods 15 at two sides of the adjusting rod 808, and two ends of the diagonal rod 15 are respectively connected with the adjusting frame 807 and the adjusting rod 808, so that the diagonal rod 15 can counteract the left-right shaking generated when the adjusting rod 808 is stressed, so that the adjusting rod 808 ensures the stability of the position, and the charging effect of the aircraft is improved.

Specifically, a second buffer spring 16 is sleeved outside the inclined rod 15, one end of the second buffer spring 16 abuts against an auxiliary annular protrusion arranged on the outer surface of the inclined rod 15, the other end of the second buffer spring abuts against the adjusting rod 808, and the reaction force of the inclined rod 15 is increased by the recoil force of the second buffer spring 16.

In this embodiment, the aircraft charging device 13 includes a rectangular base 1301 and an aircraft charging platform 1302, a card slot matching with the mounting plate 803 in shape is disposed on the bottom surface of the rectangular base 1301, and the aircraft charging platform 1302 is disposed in the center of the top surface of the rectangular base 1301 and electrically connected to the internal power module.

Further, be equipped with three shape and the same bounding wall 1303 of structure on the rectangular base 1301 and wrap up aircraft charging platform 1302 setting, the one end swing joint of bounding wall 1303 is on rectangular base 1301 lateral wall top, its other end upwards closes to disturb and forms the circular cone shape, and the top is equipped with and guides the first 14 assorted start-up holes that charges, bounding wall 1303 wraps up aircraft charging platform 1302 when not charging, avoid it to receive external damage under the state of not using, and is further, bounding wall 1303 internal surface upwards extends and is equipped with and 2 appearance assorted location archs of base, the location arch plays the effect of auxiliary positioning, help the aircraft landing time position stable.

In the embodiment of the invention, the base 2 is arranged at the bottom of the aircraft, the base 2 is provided with the guide charging head 14 for starting the aircraft charging device 13, so that the aircraft charging device 13 arranged at the upper end of the aircraft body 1 can charge another aircraft in the flying process, the flying distance of the aircraft is increased, furthermore, the base 2 is fixed on the aircraft body 1 through the supporting legs 3 and the fixing ring 5, tools are not needed in the disassembly and assembly, the disassembly and assembly are convenient, the aircraft charging device 13 is arranged on the landing buffer device 8 at the top of the aircraft body 1, when the aircraft is landed on the aircraft charging device 13 of another aircraft, the vibration caused by the aircraft can be eliminated through the landing buffer device 8, the inertia when can descending to the aircraft advances effectual buffering, improves the stability of aircraft when descending, guarantees the safety that the aircraft charges.

S2, the signal receiving module receives the conditions of the aircrafts in the logic group, the cluster guides the aircrafts to fly to the aircrafts close to the node and with sufficient power supplies through the main control module, and meanwhile, the selected aircrafts wait in situ;

s3, the cluster guides the aircraft to reach the position right above the selected aircraft, the aircraft descends through the main control module, when the cluster guides the aircraft to descend, the charging head 14 of the cluster guides the aircraft to open the coaming 1303 at the upper end of the selected aircraft, the coaming 1303 is opened and the internal aircraft charging platform 1302 is exposed, meanwhile, the aircraft descends onto the aircraft charging platform 1302 for charging, the descending buffer device 8 can buffer the shake generated when the cluster guides the aircraft to descend, and the cluster guides the aircraft to stably descend onto the aircraft charging platform of the selected aircraft for charging;

and S4, the cluster guides the aircrafts to fly away from the selected aircraft after charging is finished, and the selected aircraft continues to fly, and simultaneously lands in situ or returns.

While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides an aircraft based on 5G, includes the fuselage and sets up the rotor on the fuselage, its characterized in that: the aircraft charging device comprises a fuselage, a base, a landing buffer device, an aircraft charging device, a guiding charging head, a signal transmission module, an information receiving module, a power module and a main control module, wherein the base is arranged at the bottom of the fuselage;

the fixing seat is assembled in a mounting groove formed in the top of the machine body, a clamping block penetrates through the side face of the upper end of the mounting groove, the clamping block is connected with a transmission shaft in the machine body, a sliding groove penetrates through the inside of the side face of the bottom of the mounting groove, a push rod is slidably arranged in the sliding groove, the push rod is extruded when the fixing seat is assembled in the mounting groove, the push rod pushes the transmission shaft, the transmission shaft drives the clamping block to move, and the clamping block is buckled in a locking groove formed in the side face of the fixing seat;

Descending buffer includes fixed plate, buffer board and mounting panel, the up end at the fixing base is installed to the fixed plate bolt, the fixed plate up end is equipped with first buffer spring to being connected with the buffer board through first buffer spring, the buffer board border is equipped with all around and adjusts the elastic component, adjust the regulating plate swing joint that elastic component and mounting panel bottom surface set up, the buffer board is equipped with the intermediate position of first buffer spring homonymy terminal surface and is equipped with the alignment jig, and the inside upwards extension of alignment jig is equipped with the regulation pole, and should adjust the upper end and the mounting panel fixed connection of pole, adjust the pole and fix on the alignment jig through the pivot that runs through the alignment jig side setting.

2. The 5G-based aircraft according to claim 1, wherein: the adjusting frame is located the regulation pole both sides and is equipped with the down tube, and the both ends of down tube are connected with adjusting frame and regulation pole respectively.

3. The 5G-based aircraft according to claim 2, wherein: the outside cover of down tube is equipped with second buffer spring, and the one end of second buffer spring offsets with the supplementary annular arch that the down tube surface set up, and the other end supports tightly with adjusting the pole.

4. The 5G-based aircraft according to claim 1, wherein: the base top surface upwards extends and is equipped with the pillar, and the pillar top is provided with the solid fixed ring of in-band screw thread, gu fixed ring can be rotatory around self axis, fuselage bottom downwardly extending is equipped with the card post of outband screw thread, gu fixed ring just, the anti-rotation assembles the base screw thread on the card post of fuselage bottom.

5. The 5G-based aircraft according to claim 1, wherein: aircraft charging device includes rectangular base and aircraft charging platform, the rectangular base bottom surface be equipped with mounting panel appearance assorted draw-in groove, aircraft charging platform set up at rectangular base top surface center and with inside power module electric connection.

6. A5G-based aircraft according to claim 5, wherein: be equipped with three shape and the same bounding walls of structure on the rectangular base and wrap up the aircraft charging platform setting, the one end swing joint of bounding wall is on rectangular base lateral wall top, and its other end upwards closes to disturb and forms conical shape, and the top be equipped with guide charge first assorted start-up hole.

7. The 5G-based aircraft according to claim 6, wherein: and the inner surface of the enclosing plate extends upwards to form a positioning bulge matched with the shape of the base.

8. A method for cluster control of aircraft according to claim 1, characterized in that: the system comprises a plurality of aircrafts, wherein each aircraft is a node, and the aircrafts are divided into a plurality of logic groups, wherein one aircraft serves as a cluster guide aircraft; the method specifically comprises the following steps: