Electric rail flight system

Abstract

The invention provides an electric flight rail flight system, which relates to the field of traffic transportation and is characterized by comprising a rail contact net system, a flight accompanying device power receiving and transmitting system, a main aircraft system and an electric flight operation command and control system. The rail contact network system comprises a supporting structure, an overhead guide rail and a rigid contact network, wherein the rigid contact network is used for external electric energy transmission; the accompanying device system comprises an accompanying device and a power receiving and transmitting device, and a roller power receiving barrel structure is arranged at the lower end of the power receiving and transmitting device and used for electric transmission connection; the main aircraft system comprises a main aircraft body and a power receiving docking device or an integrated power receiving device and is used for continuous power receiving during flight. The system has the advantages that accompanying or integrated wired power supply can be realized in the flying process of the electric aircraft, long-time wire direct connection power supply and energy charging of the aircraft are met, continuous and stable wired power supply is provided for the aircraft, and the flying time, the efficiency and the load are effectively improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of transportation, in particular to an electric flying rail system. BACKGROUND

[0002] The existing various types of transportation tools have respective shortcomings in different aspects. The current general aircraft needs a large amount of fuel for long-distance transportation, causing environmental pollution of exhaust emission. The ground transportation tools such as automobiles generally have the problems of low driving speed and frequent road congestion. The public transportation system has the defects of long waiting time, many stops, crowded passenger room and poor riding comfort. The general electric aircraft has limited electric energy provided by the battery power supply, generally has short endurance mileage and insufficient payload capacity, resulting in that it cannot become a widely used transportation tool. SUMMARY

[0003] The present application aims to provide an electric flying rail system, which solves the technical problems of insufficient endurance, long-time parking for electric energy supplement and low payload of the existing electric aircraft, realizes the synchronous implementation of transportation operation and electric energy supplement, and improves the overall load performance of the aircraft.

[0004] In order to achieve the above-mentioned application purposes, the technical scheme adopted by the present application is as follows:

[0005] The electric flying rail system comprises a rail contact system, a companion aircraft power transmission system, a main aircraft system and an electric flying operation command and control system; the rail contact system comprises a support device, an overhead rail and a rigid contact net, the support device fixes the overhead rail and the rigid contact net on the corresponding working plane through a high-rigidity support structure made of steel beams (or alloys, carbon fibers, composite materials) and the like; the rigid contact net is embedded with a power transmission line for external power transmission; the companion aircraft power transmission system comprises a companion aircraft, a suspension magnet, a variable voltage stabilizing automatic control power supply device and a power transmission wire frame, the companion aircraft is provided with a rotor power structure and a battery and has an autonomous flight function; the suspension magnet is located at the lower end of the companion aircraft and is used for cooperating with the overhead rail to realize track limiting and directional movement in the magnetic suspension mode; the lower end of the power transmission wire frame is provided with a roller power receiving cylinder structure (or a power receiving bow structure) and a variable voltage stabilizing automatic control device (which can dynamically adjust output voltage and current parameters according to the real-time flight requirements of the main aircraft to ensure power supply adaptation and stability), and is used for cooperating with the rigid contact net to realize power transmission connection; the main aircraft system comprises a main aircraft, the lower end of the main aircraft is provided with a power receiving docking device with an automatic control function, and can quickly and automatically dock and separate with the companion aircraft power transmission device, including automatic docking and separation in the air flight state; the main aircraft can also be directly integrated with a power receiving device such as a roller power receiving cylinder or a power receiving bow for continuous power receiving during flight.

[0006] As an improvement, electromagnets or permanent magnets are fixed on the upper end and both sides of the overhead rail for cooperating with the suspension magnet of the companion aircraft to realize magnetic suspension limiting and moving; a gap sensor is fixed in the middle of the suspension magnet for monitoring the relative distance between the suspension magnet and the overhead rail in real time to assist in completing the magnetic suspension gap moving control automatic regulation.

[0007] As an improvement, limit rollers are arranged at the positions adjacent to the overhead rail on both sides of the companion aircraft, the limit rollers are located at the side and upper positions of the overhead rail, and the axes of the limit rollers are vertically arranged with the overhead rail, for limiting the displacement deviation of the companion aircraft during flight to ensure that the deviation is controlled within a preset range.

[0008] As an improvement, the rigid contact net comprises an insulation device and a contact wire, the insulation device is arranged on both sides of the overhead rail for insulation protection to prevent short circuit failure of the circuit where the contact wire is located; current collecting wires and return wires are respectively arranged on both sides of the insulation device through busbars, and the contact wire is fixed on the surface of the insulation device through the busbar, the contact wire is a rigid metal wire (including an alloy wire) for continuously supplying power in cooperation with the roller power receiving cylinder or the power receiving bow structure at the lower end of the power receiving and power transmission device.

[0009] As an improvement, the accompanying aircraft is configured with multiple groups of rotor structures, and the outer side is fixed with a protective structure such as a duct or protective net cover; the accompanying aircraft also includes a cable reel, which is located on one side of the power transmission cable reel and at a preset installation position of the accompanying aircraft body, and the inner side of the cable reel is movably wound with a cable, which is controllably powered to the main aircraft through the power transmission cable reel, and is used to adapt to the working condition requirements of different flight altitudes.

[0010] As an improvement, the accompanying aircraft and the main aircraft are both integrated with an automatic driving control module, which can realize data interaction of multiple sensors and electric control adjustment modules, thereby realizing autonomous control adjustment of flight attitude.

[0011] As an improvement, the main aircraft can also adopt an integrated power receiving and transmission architecture, and the roller power receiving cylinder or power receiving bow structure is directly integrated with the main aircraft body, which adopts an integrated or one-piece design and does not need to carry an accompanying aircraft; the power receiving and transmission device, i.e., the structure of the cable reel and the power transmission cable reel, can be selected as a rigid chain drag chain with an automatic control device, and the built-in cable is embedded in the chain body cavity of the rigid chain drag chain, which can meet the layout requirements of heavy weight cables and can also guarantee the structural strength under flight working conditions, avoiding structural interference or performance impact on the cable and the aircraft body.

[0012] As an improvement, it also includes an electric flight operation command and control system; the electric flight operation command and control system is bidirectionally communicated and interconnected with the accompanying aircraft and the main aircraft, and is used to implement remote air command and control on the accompanying aircraft and the main aircraft, and the control instructions cover all process actions such as take-off and landing, cruise flight, docking and separation, etc., and the electric flight operation command and control system, the accompanying aircraft and the main aircraft constitute an integrated control system for cooperative work.

[0013] As an improvement, the roller power receiving cylinder is provided with two or more groups, which are symmetrically arranged on both sides of the lower end of the accompanying aircraft or integrated on both sides of the lower end of the main aircraft; the outer contact surface of the roller power receiving cylinder is a cylindrical surface structure, and the outer rotating body is made of conductive material, and a stable conductive path is formed by elastic contact or rolling lapping.

[0014] The beneficial effects of the present application are: adopting the ground overhead guideway wired power supply mode, the power supply network can continuously transport stable power to the aircraft along the low-altitude fixed guideway; analogizing the high-speed railway power supply framework, relying on the fixed guideway route to realize long-time and long-distance power direct feeding. The power supply mode not only enables the aircraft to achieve super-long endurance capability, but also can significantly improve its power performance and effective load level. The present application supports adaptive electric flying cars, flying cars, unmanned aerial vehicles and various manned / cargo aircrafts and other equipment, and the foregoing many devices can not only carry the low-altitude guideway for wired power supply flight, but also can realize offline autonomous flight by relying on the onboard battery of the device itself, and at the same time have the flexibility of vertical take-off and landing. The technical scheme can greatly reduce the operating cost of the aircraft, improve the flight efficiency, and provide technical support for the large-scale and industrialized application of electric aircrafts. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is the device front view of the electric flying rail flying system of the present application.

[0016] Figure 2 It is the structure block diagram of the electric flying rail flying system of the present application.

[0017] In the figure: 1, rigid contact network; 2, overhead guideway; 3, accompanying device; 4, suspension magnet; 5, limit roller; 6, take-up frame; 7, power transmission wire frame; 8, main aircraft; 9, roller power receiving cylinder. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0019] It should be noted that the terms "first", "second" in the present application are only used for description purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically limited. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device including a series of steps or units is not limited to the listed steps or units, but can optionally include steps or units not listed, or can optionally include other steps or units inherent to the process, method, product or device.

[0020] The application adopts a low-altitude guide rail wired power supply mode, and the electric flying power supply network can continuously provide power to the aircraft, so that the aircraft has super-long endurance capability and its power and load are significantly improved. The technical scheme supports electric flying vehicles, flying cars, unmanned aerial vehicles and various manned / cargo aircrafts and many other devices, and supports a dual-mode operation mechanism: one is the guide rail wired power supply mode, and the aircraft is carried on the low-altitude guide rail and obtains continuous power through a wired mode; the other is the off-line autonomous operation mode, that is, after being separated from the guide rail, the aircraft relies on the on-board battery pack to provide power to complete the vertical take-off and landing and free flight task. The application can greatly reduce the operation cost of the electric aircraft, improve the flight efficiency, and lay a foundation for the large-scale and popular application of the electric aircraft.

[0021] As shown in Figure 1 and Figure 2 , the electric flying rail flying system comprises a rail contact net system, a companion flying vehicle power receiving and transmission system, a main flying vehicle system and an electric flying operation command and control system; the rail contact net system comprises a support device, an overhead guide rail 2 and a rigid contact net 1; the support device fixes the overhead guide rail 2 and the rigid contact net 1 on the corresponding working plane through a high-rigidity support structure such as a steel beam; the rigid contact net 1 is embedded with a power transmission line for external power transmission; the companion flying vehicle power receiving and transmission system comprises a companion flying vehicle 3, a suspension magnet 4 and a power transmission wire frame 7; the companion flying vehicle 3 is provided with a rotor power structure and a battery and has an autonomous flight function; the suspension magnet 4 is located at the lower end of the companion flying vehicle 3 and is used to cooperate with the overhead guide rail 2 to realize track limiting and directional movement in the magnetic suspension mode; the lower end of the power transmission wire frame 7 is provided with a roller power receiving cylinder 9 structure (or a power receiving bow structure) and is equipped with a variable voltage stabilizing automatic control module, and through the adaptive connection with the rigid contact net, stable power transmission is realized; the main flying vehicle system comprises a main flying vehicle 8, and the lower end of the main flying vehicle 8 is provided with a power receiving docking device with an automatic control function, which can quickly and automatically dock and separate with the companion flying vehicle power receiving and transmission device, including automatic docking and separation in the air flight state; the main flying vehicle 8 can also be directly integrated with a roller power receiving cylinder 9 or a power receiving bow and the like, which is used for continuous power receiving during flight.

[0022] The rigid contact net 1, the companion flying vehicle 3 and the main flying vehicle 8 can access the electric flying operation command system through wired and wireless signal transmission; the electric flying operation command system comprises a signal base station and a ground control system, and can monitor the status of each flying vehicle in real time, including position, speed, trajectory, distance between front and rear flying vehicles and the like.

[0023] The upper end and both sides of the overhead guide rail 2 are fixed with electromagnets or permanent magnets, which are used for magnetic suspension and position limiting movement with the suspension magnets 4 of the accompanying aircraft 3; the middle part of the suspension magnets 4 is fixed with a gap sensor, which is used for real-time monitoring of the relative distance between the suspension magnets 4 and the overhead guide rail 2, and assists in completing the automatic regulation of the magnetic suspension gap movement control.

[0024] The position adjacent to the overhead guide rail 2 of the two sides of the accompanying aircraft 3 is provided with a limiting roller 5, which is located at the side and upper position of the overhead guide rail 2, and the axis of the limiting roller 5 is vertically arranged with the overhead guide rail 2, which is used to limit the displacement deviation of the accompanying aircraft 3 during flight, so as to ensure that the deviation is controlled within the preset range.

[0025] The rigid contact network 1 includes an insulation device and a contact wire, the insulation device is arranged on both sides of the overhead guide rail 2, which is used for insulation protection to prevent short circuit failure of the circuit where the contact wire is located; the two sides of the insulation device are respectively provided with current-carrying conductors and return conductors through busbars, and the surface of the insulation device is fixed with a contact wire through the busbar, the contact wire is a rigid metal conductor (including alloy conductor), which is used to cooperate with the roller current collection cylinder or the current collection bow structure at the lower end of the power transmission device to provide continuous power supply.

[0026] The accompanying aircraft 3 is provided with a plurality of groups of rotor structures, and the outer side is fixed with a duct or a protective net cover and other protective structures; the accompanying aircraft 3 further includes a take-up reel 6, which is located on one side of the power transmission conductor rack 7 and at a preset mounting position of the accompanying aircraft 3 body, the inner side of the take-up reel 6 is movably wound with a cable, the cable is controllably powered to the main aircraft 8 through the power transmission conductor rack 7, which is used to adapt to the working condition requirement of different flight altitudes.

[0027] The structure of the take-up reel 6 and the power transmission conductor rack 7 can be replaced with a rigid chain drag chain with automatic control device, and the built-in cable is embedded in the chain body cavity of the rigid chain drag chain, which can not only meet the layout requirement of heavy weight cable, but also can guarantee the structural strength under flight working condition, avoid the structure interference or performance influence on the cable and aircraft body.

[0028] The accompanying aircraft 3 and the main aircraft 8 are both provided with an automatic driving control module, which can realize data interaction of multiple sensors and electric control adjustment module, so as to realize autonomous control adjustment of flight attitude.

[0029] The electric flight operation command and control system is bidirectionally communicated and interconnected with the accompanying aircraft 3 and the main aircraft 8, which is used for remote air command and control of the accompanying aircraft 3 and the main aircraft 8, and the control instruction covers the whole process actions such as take-off and landing, cruise flight, docking and separation, etc., and the electric flight operation command and control system, the accompanying aircraft 3 and the main aircraft 8 constitute an integrated control system for cooperative work.

[0030] The two or more groups of symmetrical roller power receiving cylinders are arranged on both sides of the lower end of the accompanying aircraft or integrated on both sides of the lower end of the main aircraft. The power receiving device adopts a cylindrical surface structure on the outer side surface (contact surface with the contact net). The outer rotating body of the roller power receiving cylinder is made of conductive material, and the conductive path is formed by elastic contact or rolling lapping.

[0031] In example one, magnetic suspension bearings or suspension rollers are used as support components to form a non-contact suspension state between the outer cylindrical rotating body and the support shaft. A continuous conductive layer is applied to the outer surface of the rotating body, and elastic conductive contacts with graphite (or carbon brush) as the core material are arranged at the middle positions of the outer side surfaces at both ends. The elastic conductive contacts maintain constant force elastic contact with the conductive layer on the surface of the rotating body, thereby realizing stable electrical conduction of the rotating body in the non-contact suspension working condition. Or a recessed shaft structure is arranged in the middle of the rotating body, and an elastic conductive contact is configured. The contact maintains elastic contact with the conductive layer on the wall of the recessed shaft with constant force, realizing stable electrical conduction in the rotating working condition.

[0032] In example two, a configuration similar to an electric slip ring is adopted. The outer ring surface can rotate flexibly at high speed, serving as a rotor, and the material is selected from conductive metals, conductive glue, or conductive graphite (similar to the carbon slide plate material of high-speed rail pantograph). The inner ring surface is a fixed structure, serving as a stator, and is made of conductive metal. The electric wire is directly connected to the conductive material of the inner ring, realizing stable electrical conduction in the rotating working condition.

[0033] In example three, a full-conductive bearing type cylindrical roller power receiving device is adopted. The core transmission and conductive unit is a full-conductive rolling bearing. The outer ring, inner ring, rolling body, and retainer of the bearing are made of high-conductivity metal materials, realizing full-conductive performance of the bearing body. The lubrication system is configured with conductive grease. The conductive filler (such as copper powder and graphite) is used as the functional phase of the lubricating grease, which is compounded with the base oil system, considering the dual functions of lubrication and friction reduction and electrical conduction. The design of the conductive path of the device is: external power supply rail / contact net → cylindrical roller → conductive bearing outer ring → rolling body → retainer → inner ring → conductive main shaft → wire outlet end, forming a low-contact-resistance current transmission path.

[0034] The roller power receiving cylinder includes but is not limited to three examples.

[0035] The core component unit of the accompanying aircraft system includes an unmanned aerial vehicle system body integrated with an intelligent autopilot, a multi-rotor system, a limiting mechanism, a power receiving and transmission device and other key components. Among them, the multi-rotor system adopts a ducted configuration or is equipped with a closed protective net cover, covering horizontal rotors, vertical rotors or tiltable rotor types; the power receiving and transmission device is composed of power receiving components (including power receiving tubes or power receiving bows), rigid chain drag chains, cables, electrical connectors, insulation components and power supply charging modules. The accompanying aircraft can realize physical protection of the rotors through the hidden rotor layout of the ducted design or the closed net cover, effectively avoiding the risk of collision with external objects during flight.

[0036] During the movement of the accompanying aircraft 3 along the rigid contact net 1, stable limiting travel can be achieved through the suspension magnet 4 structure; in the case of deviation or turning direction change, the attitude stability can be maintained in cooperation with the limiting roller 5. The two groups of roller-type power receiving tubes (or power receiving bows) on both sides of the accompanying aircraft 3 can adjust the distance and contact pressure relying on the matching control system to meet the reasonable threshold interval requirements of power receiving contact and realize quick disconnection with the guide rail. The displacement control device is configured between the two groups of power receiving tubes (or power receiving bows), integrating pressure sensors, distance sensors, positioning locking mechanisms and other types of sensing components, which can automatically control the distance and contact pressure between the left and right groups of power receiving tubes and the contact wire, ensuring the stability and controllability of power receiving operation.

[0037] The accompanying aircraft and the main aircraft are both configured with on-board energy storage batteries, when they are carried on the electric flying rail flying system, they are switched to the rail wired power supply mode, in this mode, the aircraft can complete online charging of the on-board battery during flight; when the aircraft is separated from the electric flying rail system, it is switched to the offline autonomous running mode, relying on the on-board battery energy storage to realize free endurance flight and vertical take-off and other operations.

[0038] The above only describes the preferred embodiments of the present application patent, and does not limit the present application patent, any modification, equivalent replacement and improvement made within the spirit and principle of the present application patent shall be included in the protection scope of the present application patent.

Claims

1. An electric-powered rail-guided flight system, characterized in that, The system includes a track contact network system, a companion aircraft power receiving and transmission system, a main aircraft system, and an electric flight operation command and control system. The track contact network system includes a support device, an overhead guide rail (2), and a rigid contact network (1). The support device uses a high-rigidity support structure made of steel beams (or alloys, carbon fibers, composite materials, etc.) to fix the overhead guide rail (2) and the rigid contact network (1) on the corresponding working plane. The rigid contact network (1) has embedded power transmission lines for external power transmission. The companion aircraft power receiving and transmission system consists of the companion aircraft... The system includes a device (3), a levitation magnet (4), and a power transmission line frame (7). The companion aircraft (3) is equipped with a rotor power structure and a battery, and has autonomous flight capabilities. The levitation magnet (4) is located at the lower end of the companion aircraft (3) and is used to cooperate with the overhead guide rail (2) to achieve track limiting and directional movement in magnetic levitation mode. The lower end of the power transmission line frame (7) is equipped with a roller power receiver (9) structure (or pantograph structure) and a transformer and voltage stabilization automatic control module. Through the adaptation connection with the rigid contact network, it completes the stable transmission of electrical energy. The main aircraft system includes a main aircraft (8). The lower end of the main aircraft (8) is equipped with a power receiving docking device with automatic control function, which can quickly and automatically dock and separate from the power receiving and transmission device of the companion aircraft, including automatic docking and separation in the air flight state. The main aircraft (8) can also directly integrate a roller power receiver (9) or pantograph and other power receiving devices for continuous power receiving during flight.

2. The electric-rail-guided flight system according to claim 1, characterized in that, Electromagnets or permanent magnets are fixed on the upper end and both sides of the overhead guide rail (2) to cooperate with the levitation magnet (4) of the companion aircraft (3) for magnetic levitation limiting movement; a gap sensor is fixed in the middle of the levitation magnet (4) to monitor the relative distance between the levitation magnet (4) and the overhead guide rail (2) in real time, and assist in completing the automatic adjustment of magnetic levitation gap movement control.

3. The electric-rail-guided flight system according to claim 2, characterized in that, Limiting rollers (5) are provided on both sides of the companion aircraft (3) near the overhead guide rail (2). The limiting rollers (5) are located on the side and above the overhead guide rail (2), and the axis of the limiting rollers (5) is arranged perpendicular to the overhead guide rail (2). They are used to limit the displacement of the companion aircraft (3) during flight to ensure that its displacement is controlled within a preset range.

4. The electric-rail-guided flight system according to claim 1, characterized in that, The rigid contact network (1) includes an insulation device and a contact wire. The insulation device is installed on both sides of the overhead guide rail (2) for insulation protection to prevent short circuit faults in the circuit where the contact wire is located. The current receiving wire and the return wire are respectively installed on both sides of the insulation device through the busbar. The contact wire is fixed on the surface of the insulation device through the busbar. The contact wire is a rigid metal wire (including alloy wire) used to cooperate with the roller receiving tube or pantograph structure at the lower end of the power receiving and transmission device to provide continuous power supply.

5. The electric-rail-guided flight system according to claim 1, characterized in that, The companion aircraft (3) is equipped with multiple rotor structures, and protective structures such as ducts or protective nets are fixed on its outer side; the companion aircraft (3) also includes a cable retractor (6), which is located on one side of the power transmission cable frame (7) and at a preset installation position on the fuselage of the companion aircraft (3). The cable is movably wound on the inner side of the cable retractor (6), and the cable supplies power to the main aircraft (8) in a controllable manner through the power transmission cable frame (7) to adapt to the working conditions of different flight altitudes.

6. The electric-rail-guided flight system according to claim 5, characterized in that, Both the companion aircraft (3) and the main aircraft (8) are equipped with an autopilot control module. The autopilot control module can realize data interaction between multiple sensors and the electronic control adjustment module, thereby realizing autonomous control and adjustment of flight attitude.

7. The electric-rail-guided flight system according to claim 1, characterized in that, The main aircraft (8) adopts an integrated power receiving and transmission architecture. The roller power receiving tube (9) or pantograph structure is directly integrated into the main aircraft (8) body. It adopts an integrated or one-piece design and does not require a companion aircraft. The structure of the cable take-up frame (6) and the power transmission wire frame (7) can be a rigid chain drag chain equipped with an automatic control device. The built-in cable is embedded in the chain cavity of the rigid chain drag chain, which can meet the laying requirements of heavy cables and ensure the structural strength under flight conditions, avoiding structural interference or performance impact on the cable and the main aircraft body.

8. The electric-rail-guided flight system according to claim 1, characterized in that, It also includes an electric flight operation command and control system; the electric flight operation command and control system is bidirectionally interconnected with the escort aircraft (3) and the main aircraft (8) and is used to remotely command and control the escort aircraft (3) and the main aircraft (8). The control commands cover the entire process of take-off and landing, cruise flight, docking and separation. The electric flight operation command and control system, the escort aircraft (3) and the main aircraft (8) constitute an integrated control system that works in coordination.

9. The electric-rail-guided flight system according to claim 1, characterized in that, The roller power receiver (9) is configured in two or more sets, symmetrically arranged on both sides of the lower end of the companion aircraft (3), or integrated into both sides of the lower end of the main aircraft; the outer contact surface of the roller power receiver (9) is a cylindrical structure, and its outer rotating body is made of conductive material, forming a stable conductive path through elastic contact or rolling overlap.

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