Air-space cooperative unmanned aerial vehicle emergency communication system and communication method

Abstract

The invention discloses an air-space cooperative unmanned aerial vehicle emergency communication system and a communication method. The system comprises an unmanned aerial vehicle, and the unmanned aerial vehicle is provided with a solar photovoltaic panel, an energy storage device and an air-space integrated base station. The solar photovoltaic panel is used for adjusting the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to charge the energy storage device according to the maximum output power all the time; the energy storage device is used for supplying power to the unmanned aerial vehicle and the air-space integrated base station; and the air-space integrated base station is used for receiving the communication data of the user terminal, sending the communication data to the core network deployed in the communication satellite, and receiving return data of the core network in response to the communication data. The technical problem that the flexibility of the communication coverage range is limited due to the fact that a mooring type unmanned aerial vehicle is adopted for emergency communication in the prior art is solved.

Description

Technical Field

[0001] The present application relates to the field of communication technology, and more specifically, to an air-space collaborative UAV emergency communication system and communication method. Background Art

[0002] In the case of natural disasters, the communication network is often severely damaged, resulting in large-scale paralysis, which seriously affects post-disaster rescue. In order to quickly restore communications, eliminate "communication islands", and ensure the smooth communication network after the disaster, the traditional method is to use emergency communication vehicles to provide emergency rescue guarantees when sudden communications are interrupted. However, due to the unpredictability of sudden natural disaster areas, it is difficult to guarantee the time for emergency vehicles to arrive at the scene and be put into use. Disasters often cause road damage, which will greatly delay the efficiency of emergency vehicle communication guarantees. With the maturity and popularization of drone technology, tethered drone emergency communications have gradually been applied in emergency guarantees for various emergencies. The existing drone emergency communication technology uses drones to carry miniaturized base station equipment and provide reliable data transmission services through tethered optical cables, thereby building a temporary communication network. However, considering that traditional drones are small in size, have short battery life, and have limited load capacity, the miniaturized base stations they carry can usually only be equipped with a directional antenna that radiates a 120° fan-shaped area, which greatly limits the network coverage of the base station and cannot fully guarantee the use of large-scale disaster victims, which in turn causes rescue personnel to be unable to grasp disaster information in a timely and accurate manner. Moreover, the miniaturized base station on the drone needs to be connected to the airborne base station through an optical cable from the ground to complete data transmission. The limited length of the optical cable also limits the flight radius of the drone and the coverage distance of the base station. Therefore, the tethered drone emergency communication system requires the deployment of tethered cables and other ground supporting facilities, which significantly increases the deployment difficulty and time cost. Its flexibility is limited, its mobility is insufficient, and its equipment cost and maintenance complexity are high. Summary of the invention

[0003] The embodiments of the present application provide an air-space collaborative UAV emergency communication system and a communication method to at least solve the technical problem in the related art that the flexibility of communication coverage is limited due to the use of tethered UAVs for emergency communications.

[0004] According to one aspect of an embodiment of the present application, there is provided an air-space collaborative UAV emergency communication system, comprising: a UAV, on which is provided a solar photovoltaic panel, an energy storage device and an air-space integrated base station; the solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy to always charge the energy storage device according to the maximum output power; the energy storage device is used to supply power to the UAV and the air-space integrated base station; the air-space integrated base station is used to receive communication data of a user terminal, and send the communication data to a core network deployed in a communication satellite, and receive return data of the core network in response to the communication data.

[0005] Optionally, the integrated air-space base station includes: an omnidirectional radio frequency antenna, used to receive the communication data sent by the user terminal and send the communication data to a radio frequency processing unit, the omnidirectional radio frequency antenna includes: a smart surface, the smart surface includes multiple sub-smart surfaces, the multiple sub-smart surfaces include: multiple reconfigurable smart surfaces RIS and multiple Huygens metasurfaces HMS, wherein the multiple reconfigurable smart surfaces RIS and the multiple Huygens metasurfaces HMS; the radio frequency processing unit is used to process the communication data and send the processed communication data to the communication satellite via the omnidirectional radio frequency antenna.

[0006] Optionally, the smart surface is used to receive the radio frequency signal corresponding to the communication data, and divide the radio frequency signal into three parts to obtain a first part of the radio frequency signal, a second part of the radio frequency signal and a third part of the radio frequency signal. The first part of the radio frequency signal is emitted through the gaps between the multiple sub-smart surfaces and propagates in the original direction of the radio frequency signal. The second part of the radio frequency signal is reflected by the RIS, and the third part of the radio frequency signal is transmitted by the HMS.

[0007] Optionally, the RIS includes: a reflection unit, a metal plate and a controller; the reflection unit is used to receive the second part of the radio frequency signal and reflect the adjusted second part of the radio frequency signal; the metal plate is used to isolate signal penetration; the controller is used to adjust the reflection direction, phase and amplitude of the second part of the radio frequency signal.

[0008] Optionally, the reflection signal of each reflection unit on the RIS includes:

[0009]

[0010] In the formula, Q k represents the incident signal of the kth reflection unit, P k represents the reflection signal of the kth reflection unit; δ k∈[0, 1], represents the amplitude factor of the electromagnetic wave after being reflected by the kth reflection unit, θ k ∈[0, 2π), represents the phase factor of the electromagnetic wave after being reflected by the kth reflection unit, k∈[1, N], k and N represent positive integers, and j represents an imaginary number.

[0011] Optionally, the HMS comprises: an outer layer, a middle layer and an inner layer; the outer layer periodically arranges a plurality of metal patches to form a first metal ring band, wherein a first notch is left at the head and tail parts of the first metal ring band; the middle layer is a base dielectric layer; the inner layer periodically arranges a plurality of metal patches to form a second metal ring band, wherein a second notch is left at the head and tail parts of the second metal ring band; the first notch and the second notch are used to adjust the transmission direction, phase and amplitude of the second part of the radio frequency signal.

[0012] Optionally, it also includes: a Starlink antenna; the Starlink antenna is used to forward the communication data received by the integrated air-space base station from the user terminal to the communication satellite.

[0013] According to another aspect of an embodiment of the present application, a communication method for an air-space collaborative UAV emergency communication system is also provided, including: receiving communication data of a user terminal through an air-space integrated base station; transmitting the communication data to a communication satellite, and receiving return data from the communication satellite in response to the communication data, wherein the air-space integrated base station is powered by an energy storage device, and the energy storage device is composed of a solar photovoltaic panel arranged on the UAV, which adjusts the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge according to the maximum output power.

[0014] Optionally, a solar photovoltaic panel arranged on the drone adjusts the operating point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge at the maximum output power, including: detecting the conductance of the solar photovoltaic panel at the current operating point and the conductance at the previous operating point according to a preset period; and upon detecting the rate of change of the conductance of the solar photovoltaic panel at the current operating point relative to the conductance at the previous operating point, adjusting the output voltage of the solar photovoltaic panel so as to adjust the operating point of the solar photovoltaic panel to the maximum power point.

[0015] According to another aspect of the embodiment of the present application, a drone is also provided, comprising: a solar photovoltaic panel, an energy storage device, an aircraft battery, a Starlink antenna and an air-space integrated base station arranged on the wings; the solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy to always charge the energy storage device and the aircraft battery according to the maximum output power; the aircraft battery is used to power the drone; the energy storage device is used to power the air-space integrated base station and the Starlink antenna; the air-space integrated base station is used to receive communication data from a user terminal, and send the communication data to a core network deployed in a communication satellite, and receive return data from the core network in response to the communication data; the Starlink antenna is used to connect the air-space integrated base station and the communication satellite for communication.

[0016] According to another aspect of the embodiment of the present application, there is also provided an uplink data transmission method, including: receiving a request signal sent by a user terminal through an integrated air-space base station set on a drone; sending the request signal to a core network deployed on a communication satellite through a Starlink antenna, wherein the integrated air-space base station and the Starlink antenna are powered by an energy storage device deployed on the drone, and the energy storage device is powered by a solar photovoltaic panel set on the wing of the drone based on a predetermined adjustment strategy to adjust the working point of the solar photovoltaic panel so as to always charge at the maximum output power.

[0017] According to another aspect of the embodiment of the present application, a downlink data transmission method is also provided, including: receiving, through a space-air integrated base station disposed on a drone, backhaul data sent by a core network deployed on a communication satellite through a Starlink antenna: converting the backhaul data into a radio frequency signal and sending it to a user terminal, wherein the space-air integrated base station and the Starlink antenna are powered by an energy storage device deployed on the drone, and the energy storage device is powered by a solar photovoltaic panel disposed on the wing of the drone, and the working point of the solar photovoltaic panel is adjusted based on a predetermined adjustment strategy by the solar photovoltaic panel so as to always charge according to the maximum output power.

[0018] According to another aspect of an embodiment of the present application, a computer device is also provided, including: a memory and a processor, wherein the memory is used to store program instructions; and the processor is connected to the memory and is used to execute the communication method of the above-mentioned air-space collaborative drone emergency communication system.

[0019] According to another aspect of an embodiment of the present application, a non-volatile storage medium is also provided, which includes a stored computer program, wherein the device where the non-volatile storage medium is located executes the communication method of the above-mentioned air-space collaborative drone emergency communication system by running the computer program.

[0020] According to another aspect of the embodiments of the present application, a computer program product is also provided, including computer instructions, which, when executed by a processor, implement the communication method of the above-mentioned air-space collaborative drone emergency communication system.

[0021] In an embodiment of the present application, a drone is adopted, and the drone is provided with a solar photovoltaic panel, an energy storage device and an integrated air-space base station; the solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy to always charge the energy storage device according to the maximum output power; the energy storage device is used to supply power to the drone and the integrated air-space base station; the integrated air-space base station is used to receive communication data of the user terminal, and send the communication data to the core network deployed in the communication satellite, and receive the return data of the core network in response to the communication data, thereby achieving the purpose of eliminating the cables used to tether the drone, thereby achieving the technical effect of improving the flexibility of emergency communications of the drone, and further solving the technical problem in the related technology that the flexibility of communication coverage is limited due to the use of tethered drones for emergency communications. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0023] Figure 1 is a structural schematic diagram of an air-space collaborative UAV emergency communication system according to an embodiment of the present application;

[0024] Figure 2 is a structural schematic diagram of another air-space collaborative UAV emergency communication system according to an embodiment of the present application;

[0025] Figure 3 is a schematic diagram of an omnidirectional radio frequency antenna structure according to an embodiment of the present application;

[0026] Figure 4 This is a schematic diagram of a space-air integrated base station connection according to an embodiment of the present application;

[0027] Figure 5 It is a schematic diagram of a low-cost network rapid coverage method for emergency communication according to an embodiment of the present application;

[0028] Figure 6 It is a hardware structure block diagram of a computer terminal for implementing a communication method of an air-space collaborative UAV emergency communication system according to an embodiment of the present application;

[0029] Figure 7is a flow chart of a communication method of an air-space collaborative UAV emergency communication system according to an embodiment of the present application;

[0030] Figure 8 is a schematic diagram of the structure of a drone according to an embodiment of the present application;

[0031] Fig. 9 It is a schematic diagram of an air-space collaborative drone emergency communication network system according to an embodiment of the present application. DETAILED DESCRIPTION

[0032] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0033] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0034] The information collected in the embodiments of the present application is information and data authorized by the user or fully authorized by all parties, and the collection, storage, use, processing, transmission, provision, disclosure and application of the relevant data comply with the relevant laws, regulations and standards of the relevant regions, take necessary confidentiality measures, do not violate public order and good morals, and provide corresponding operation entrances for users to choose to authorize or reject automated decision-making results; if the user chooses to reject, the expert decision-making process will be entered.

[0035] In order to better understand the embodiments of the present application, the technical terms involved in the embodiments of the present application are explained as follows:

[0036] Reconfigurable Intelligent Surface (RIS);

[0037] Huygens' Metasurface (HMS);

[0038] Unmanned Aerial Vehicle (UAV);

[0039] Maximum Power Point Tracking (MPPT);

[0040] Space-Air Integrated Base Station (Space-Air IntegratedBS);

[0041] Super Capacitors (SC).

[0042] In order to solve the problems existing in the related art, the embodiment of the present application provides an air-space collaborative drone emergency communication system, such as Figure 1 As shown, including:

[0043] A drone 10, wherein the drone is provided with a solar photovoltaic panel 101, an energy storage device 102 and an air-space integrated base station 103;

[0044] The solar photovoltaic panel 101 is used to adjust the working point of the solar photovoltaic panel 101 based on a predetermined adjustment strategy so as to always charge the energy storage device 102 according to the maximum output power;

[0045] The energy storage device 102 is used to supply power to the drone 10 and the air-space integrated base station 103;

[0046] The integrated air-space base station 103 is used to receive communication data from user terminals, send the communication data to a core network deployed in a communication satellite, and receive return data from the core network in response to the communication data.

[0047] It should be noted that the air-space collaborative UAV emergency communication system is equipped with a foldable and expandable solar photovoltaic panel with MPPT technology, which is used to provide fast and efficient charging for the SC. The solar photovoltaic panel is tightly attached to the UAV wing and is in a folded state when the UAV is shut down. When the wing is extended through a mechanical linkage before takeoff, its photovoltaic panel is also unfolded. At the same time, the MPPT technology on the board dynamically adjusts the working critical point of the photovoltaic cell to ensure that it is always in the maximum power output state, thereby improving the charging efficiency. This design can capture and utilize solar energy more effectively, and then convert solar energy into electrical energy for subsequent components through the photoelectric effect. It can also significantly reduce the footprint of the drone when it is stored on the ground. This is especially important for transporting, storing, and deploying drones in limited spaces, improving space utilization.

[0048] A device with high energy density and fast charge and discharge: SC is a new energy storage device between traditional capacitors and batteries, which combines the high power characteristics of capacitors and the high energy storage capacity of batteries. Compared with traditional capacitors, SC has higher energy density, and compared with batteries, it has higher power density and longer cycle life, and can achieve fast charge and discharge.

[0049] It is understandable that SC is an optional energy storage device 102 .

[0050] Based on the above two devices, before the fixed-wing UAV takes off, the solar photovoltaic panel equipped with MPPT technology, which is close to the top of the wing, enters the working state as the wing extends. Based on the photoelectric effect and semiconductor technology, the semiconductor material on the solar panel absorbs sunlight and generates current, converts solar energy into electrical energy efficiently, and realizes fast and safe charging of the SC through the intelligent charging control system. In this application, the MPPT control algorithm based on the incremental conductivity method can make the photovoltaic module always work at the maximum power point. This process is a dynamic optimization process. By continuously measuring the conductivity change trend of the photovoltaic cell, predicting the direction of the maximum power point, and controlling the working point to approach the maximum power point, this method is more robust to changes in external conditions such as light and temperature. Generally, the solar power generation system using the MPPT controller will increase the power generation efficiency by 50% compared with the traditional system. Even if it is affected by the surrounding environment and various energy losses, the final efficiency can be increased by about 30%. At the same time, in order to further improve the conversion efficiency, the wing photovoltaic module is optimized, including the selection of single crystal silicon and perovskite materials, and the structure design is back stacked, etc., which can increase the photoelectric conversion efficiency of the entire system to 40%.

[0051] The charging power formula of the MPPT solar photovoltaic panel 101 based on the increasing conductance method is as follows:

[0052] P out =θmppt *(E initial *s area *cosθ);

[0053] Where P out is the charging power of solar photovoltaic panel 101, is the photoelectric conversion efficiency of the solar photovoltaic panel 101, E initial Represents the total amount of solar radiation energy, θ is the incident angle of solar light, s area Represents the area of ​​the solar photovoltaic panel 101.

[0054] The area of ​​the solar photovoltaic panel 101 attached to the wing of the drone is 10m 2 , solar radiation energy intensity E initial The radiation intensity under standard test conditions is 1100W / m 2 , the sunlight shines vertically on the photovoltaic surface, and the incident angle θ is 0°, then the charging power of the solar photovoltaic panel 101 is:

[0055] P out =40%*(1100W / m 2 *10m 2 *1)=4400W.

[0056] In some embodiments of the present application, the operating power of the integrated air-space base station 103 is 300W, the operating power of the Starlink antenna is 50W, and the energy generated by the solar photovoltaic panel 101 is sufficient to ensure normal operation of the base station and the antenna while continuously charging the SC to provide battery life for the drone.

[0057] In addition, the core function of the intelligent charging control system shown in this application is to monitor the charging and discharging process of the SC in real time, dynamically adjust the current and voltage levels during the charging and discharging process through algorithms, effectively prevent overcharging, and ensure the long-term healthy operation and service life of the SC.

[0058] After the SC stores energy through the solar photovoltaic panel 101, on the one hand, it can charge the battery of the fixed-wing UAV to ensure the endurance of the UAV. On the other hand, it can also provide energy for the integrated space-air base station 103 and the Starlink antenna 107 on board, thereby realizing the normal operation between the integrated space-air base station 103 and the communication satellite.

[0059] The integrated air-space base station 103 includes an omnidirectional radio frequency antenna 104, such as Figure 2As shown, the omnidirectional RF antenna 104 is used to receive the communication data sent by the user terminal and send the communication data to the RF processing unit 105, and the omnidirectional RF antenna 104 includes: a smart surface 106, and the smart surface 106 includes multiple sub-smart surfaces, and the multiple sub-smart surfaces include: multiple reconfigurable smart surfaces RIS and multiple Huygens metasurfaces HMS, wherein the multiple reconfigurable smart surfaces RIS and the multiple Huygens metasurfaces HMS; the RF processing unit 105 is used to process the communication data and send the processed communication data to the communication satellite via the omnidirectional RF antenna 104.

[0060] Among them, the smart surface 106 is used to receive the radio frequency signal corresponding to the communication data, and divide the radio frequency signal into three parts to obtain a first part of the radio frequency signal, a second part of the radio frequency signal and a third part of the radio frequency signal. The first part of the radio frequency signal is emitted through the gaps between the multiple sub-smart surfaces and propagates in the original direction of the radio frequency signal. The second part of the radio frequency signal is reflected by the RIS, and the third part of the radio frequency signal is transmitted by the HMS.

[0061] The RIS includes: a reflection unit, a metal plate and a controller; the reflection unit is used to receive the second part of the radio frequency signal and reflect the adjusted second part of the radio frequency signal; the metal plate is used to isolate the signal from penetrating; the controller is used to adjust the reflection direction, phase and amplitude of the second part of the radio frequency signal.

[0062] It should be noted that the reflection signal of each reflection unit on the RIS is determined by the following formula:

[0063]

[0064] In the formula, Q k represents the incident signal of the kth reflection unit, P k represents the reflection signal of the kth reflection unit; δ k ∈[0, 1], represents the amplitude factor of the electromagnetic wave after being reflected by the kth reflection unit, θ k ∈[0, 2π), represents the phase factor of the electromagnetic wave after being reflected by the kth reflection unit, k∈[1, N], k and N represent positive integers, and j represents an imaginary number.

[0065] It can be understood that HMS includes: an outer layer, a middle layer and an inner layer; the outer layer periodically arranges multiple metal patches to form a first metal ring band, wherein the first and tail parts of the first metal ring band have a first notch; the middle layer is a base dielectric layer; the inner layer periodically arranges multiple metal patches to form a second metal ring band, wherein the first and tail parts of the second metal ring band have a second notch; the first notch and the second notch are used to adjust the transmission direction, phase and amplitude of the second part of the RF signal.

[0066] In an optional manner, for RIS: Signal reception: When the RF signal reaches the surface of the RIS, the signal is received by the reflection units on the RIS. These reflection units are composed of electronic components (such as PIN diodes, varactor diodes) that can change the phase of the signal. Signal processing: The controller in the RIS (usually a field programmable gate array FPGA or other type of processor) independently adjusts the bias voltage of the electronic components on each reflection unit according to a preset control algorithm, thereby changing the phase and amplitude of the reflected signal. This adjustment is based on network requirements and the signal propagation environment to achieve intelligent signal directionality. Signal re-radiation: The adjusted signal is reflected by the RIS in the desired direction, achieving directional transmission and full spatial coverage of the signal. By precisely controlling the phase and amplitude of the reflection unit, the RIS is able to form a beam so that the signal can be directed to cover a specific area or user while reducing energy loss and interference.

[0067] For HMS: Signal reception: HMS also receives RF signals, but it can not only reflect signals but also transmit signals. Each unit structure on HMS is designed to control the phase and amplitude of the transmitted signal while maintaining a certain transmittance. Signal processing and re-radiation (transmission): Each unit in HMS controls the transmission characteristics of the signal, including transmission direction, phase and amplitude, by changing its internal structure (such as the position and size of the notch of the metal ring belt). These characteristics can be dynamically adjusted according to network requirements to achieve precise transmission of signals in a specific direction or uniform distribution in the entire space. When the two components work together: Signal distribution: A part of the signal directly passes through the gap between the RIS and HMS units and continues to propagate in the original direction; another part of the signal is reflected by the RIS, changing its propagation direction; and another part of the signal is transmitted by the HMS and directed to a specific direction or evenly distributed in the entire space. Intelligent control: The controllers of RIS and HMS work together to dynamically adjust the parameters of the reflection unit and the transmission unit according to the radiation requirements of the base station, the user location and the signal propagation environment to achieve intelligent signal orientation and omnidirectional coverage. Feedback mechanism: The control system of RIS and HMS can receive feedback from the integrated air-space base station and adjust the reflection and transmission parameters according to the signal quality of the base station and the user connection status to optimize the network performance. Energy management: RIS and HMS require electricity to work. In your solution, supercapacitors (SC) serve as high energy density energy storage devices to provide the required power for RIS and HMS to ensure that they can continue to work.

[0068] Through the above workflow, RIS and HMS can collaboratively optimize signal coverage and quality, while reducing energy consumption and improving system efficiency, providing stable, efficient and flexible wireless communication support for emergency communications and post-disaster rescue. The application of RIS and HMS in the intelligent drone emergency communication system not only improves the network coverage and signal quality, but also reduces the cost and complexity of building large-scale communication networks.

[0069] In some embodiments of the present application, the air-space collaborative drone emergency communication system further includes:

[0070] Starlink antenna 107, Starlink antenna 107, is used to forward the communication data received by the integrated air-space base station from the user terminal to the communication satellite.

[0071] Figure 3 Another omnidirectional radio frequency antenna is shown, which is used to effectively transmit directional radio frequency signals (high frequency electromagnetic waves) to the entire space or receive radio frequency signals from the entire space to realize the transmission and reception of wireless communication electromagnetic waves. The omnidirectional radio frequency antenna includes:

[0072] A special type of metasurface: RIS, a metasurface containing electronically controllable and low-power analog processing elements, can adjust the absorption, reflection, refraction and phase of passive reflective elements in real time to guide the incident electromagnetic signal to the desired direction. RIS can realize intelligent regulation of wireless signals through programming and control, optimize signal transmission paths, and improve the performance of wireless communication systems.

[0073] A special type of metasurface: HMS, an artificial sub-wavelength unit structure, realizes flexible control of the propagation characteristics of light or electromagnetic waves on a two-dimensional plane. Unlike reflective metasurfaces, HMS can not only change the reflection direction, phase and amplitude of electromagnetic waves, but also maintain a certain transmittance while controlling the incident electromagnetic waves, allowing part or all of the light / electromagnetic waves to pass through.

[0074] Based on the above two devices, the present application shows an omnidirectional RF antenna that integrates reconfigurable smart surfaces (RIS and HMS). A large smart surface composed of multiple small smart surfaces (RIS and HMS) is constructed in front of the antenna array with an original 120° radiation range, and there is a certain gap in the middle of each small smart surface. When the electromagnetic waves in the original 120° sector radiate forward in a fan shape, a part of the beam directly radiates out in a straight line through the gaps between the small smart surfaces.

[0075] The other part of the beam can independently adjust the bias voltage of the electronic components (such as PIN diodes, varactor diodes, etc.) in the RIS through the control circuit board carried by the smart surface, change its working state, and then change the phase and amplitude of the reflected signal, so as to reflect the electromagnetic wave to a specific direction. Specifically: the typical architecture of each small smart surface based on RIS consists of three layers of material surface plus a controller. In the outermost layer, a large number of components (reflection units) are integrated on the dielectric substrate for direct interaction with the incident signal; the second layer is a whole copper plate or other metal plate to prevent the signal from penetrating the reflection surface to isolate and avoid signal energy leakage; the innermost layer is a control circuit board, which is triggered by the controller attached to the reflection unit. The controller usually uses a field programmable gate array (FPGA), in which a PIN diode is embedded in each reflection unit, and its bias voltage is controlled by a DC feed line, which is equivalent to realizing the "on" and "off" states in the circuit and switching flexibly, thereby generating a phase shift difference. Therefore, by setting the corresponding bias voltage through the intelligent controller, different phase shifts of each RIS reflection unit can be independently achieved. On the other hand, in order to individually control the reflection amplitude of the electromagnetic wave, a variable resistance load is used in the component design. By changing the value of the resistance in each component, different parts of the incident signal energy are dissipated, thereby achieving a controllable reflection amplitude in [0, 1], and thus achieving the individual adjustment of the reflection amplitude of each component. Based on the structure of the above RIS reflection surface, the reflection signal of each reflection unit on the RIS can be simulated by the following formula:

[0076]

[0077] In the formula, Q k represents the incident signal of the kth reflection unit, P k represents the reflection signal of the kth reflection unit; δ k ∈[0, 1], represents the amplitude factor of the electromagnetic wave after being reflected by the kth reflection unit, θ k ∈[0, 2π), represents the phase factor of the electromagnetic wave after being reflected by the kth reflection unit, k∈[1, N], k and N represent positive integers, and j represents an imaginary number.

[0078] In the embodiment of the present application, the amplitude factor δ k For example, to determine number 1, the phase factor θ k It can be designed as a 4-bit phase. Then the reflection unit of the entire RIS surface is divided into 0 to 15 units, and 360° can be divided into 16 equal parts. Unit 0 represents a 0° reflection phase, unit 1 represents a 22.5° reflection phase, unit 14 represents 315°, and unit 15 represents 337.5°. By increasing the number of bits, the quantization accuracy of the phase can be further improved. According to the generalized Snell reflection law, for the reflected signal, when the incident signal reaches the reflection unit of the RIS, its direction will also change accordingly through the change of the phase, thereby realizing the change of the phase adjustment factor on the reflection unit. Finally, the phase adjustment coefficients of all reflection units are jointly designed to complete the directional reflection of the incident signal. In the large smart surface, since there are multiple small RIS smart surfaces, the horizontal incident angle electromagnetic waves emitted by a single sector can be reflected as reflected signals in various directions such as 30°, 150°, and 280°, and the radiation gain is kept basically undamaged.

[0079] When the last part of the beam passes through the Huygens structural unit precisely designed by the Huygens transmission metasurface, each unit structure is specially designed to produce a specific phase delay for electromagnetic waves of a specific frequency. These phase delays are arranged in space according to a specific rule to form the required phase distribution. When the electromagnetic wave is incident on the Huygens transmission metasurface, its wavefront will be modulated, causing a difference in the phase distribution of the transmitted wave. When there is a gradient in the phase distribution on the metasurface, the propagation direction of the transmitted wave will no longer follow the traditional Snell's law, but will be determined according to the generalized Snell's transmission law. Further, by changing the size, shape, arrangement or rotation angle design of the structural unit, the propagation direction of the transmitted beam can be precisely controlled. This phase regulation can make the electromagnetic wave after transmission form a specific wavefront distribution in space, thereby changing its propagation direction. Specifically: The typical architecture of each HMS-based small smart surface consists of three layers of panels, with periodically arranged metal patches inlaid on the outermost and innermost panels, and the middle layer is a base dielectric layer. The metal sheets on the top and bottom layers are designed as metal rings with notches at the beginning and end of the rings to achieve specific electromagnetic responses, such as forming equivalent inductance or capacitance. When electromagnetic waves are incident vertically on the metasurface, the scatterers on the metasurface will excite orthogonal currents and magnetic currents, which will interact and generate new electromagnetic wave fields, that is, it can be regarded as a surface with equivalent electrical impedance and equivalent magnetic impedance. These equivalent impedances reflect the ability of the metasurface to respond to the electric and magnetic fields of electromagnetic waves. By adjusting the position layout of the notches on the two layers of metal sheets, the synchronous excitation of electric and magnetic dipoles is achieved. Due to the double-layer architecture of this metal transmission unit, the top and bottom layers can significantly induce strong surface currents in the polarization direction under the action of electromagnetic waves. These currents cancel each other out in the horizontal direction due to their opposite directions, but strengthen the dipole resonance in the vertical direction. In particular, when the upper and lower metal sheets adjust their geometric shape, size, and arrangement to form electric dipoles and magnetic dipoles, the forward and reverse flows of their surface currents produce Huygens resonance. When the Huygens resonance generated between the metal sheets can balance the surface current distribution, the vertical magnetic current (usually generated by the incident electromagnetic wave) can be transferred through the Huygens resonance mechanism to simulate the horizontal magnetic dipole resonance effect, thereby achieving the control of the azimuth, shape, polarization and other characteristics of the transmitted beam.

[0080] Usually, the radiation range of a single-sector directional antenna is about 120°, and a three-sector combination is often used to cover the entire space. However, according to the above theory, the electromagnetic wave radiation signal in the original 120° direction can be reflected and transmitted through RIS and HMS, and can be propagated in any direction to form a 360° full-space directional radiation, achieving omnidirectional coverage while having a high gain of directional coverage. In conventional coverage, three sectors are required to cover the entire space, but after using the omnidirectional RF antenna 104 shown in this application, only one directional antenna is needed to achieve the same or similar effect, which will greatly reduce the weight of the communication base station carried by the fixed-wing UAV and reduce the pressure on the UAV's endurance.

[0081] Figure 4 Another air-space integrated base station is shown. Figure 4 As shown, when the mobile phone hardware does not have satellite communication function or the ground network cannot cover, a communication core network is deployed on the satellite and connected to a miniaturized base station carried by the UAV to achieve flexible, independent and reliable communication services. The device includes:

[0082] The space-to-air integrated base station integrates the RIS omnidirectional RF antenna and RF processing unit. In addition to the highly integrated omnidirectional RF antenna, the base station also has some physical layer functions of the baseband processing unit built in. Its integrated design reduces the interfaces and connection points between devices, reduces the probability of failure, improves the overall reliability of the system, and can process network signals more efficiently.

[0083] A satellite specially designed to carry core network functions is usually called a communication satellite. The satellite needs to be equipped with components such as processing units, storage units, and communication units, and is equipped with network function virtualization (NFV) technology to achieve virtualized deployment of core network functions. NFV can virtualize core network functions (such as EPC, MME, SGW, PGW, 5GC, AMF, UPF, etc.) and run them on general hardware. The communication satellite then routes the source data to the corresponding egress gateway via radio waves through virtualized gateway functions such as UPF, and finally accesses the Internet through the Internet service provider's network.

[0084] A specially designed Starlink antenna that can transmit data from an integrated space-air base station to a communication satellite. The Starlink antenna is a directional antenna that can automatically adjust the radiation direction and angle of the antenna through a controller. Its working principle is similar to that of a classic optical reflecting telescope, where the signal on the reflector is focused on the center point of the feed system to capture and transmit satellite signals.

[0085] Based on the above device, when the affected users need to access the network, a random access request signal is sent out through the terminal. After the omnidirectional RF antenna receives the return signal, the data is sent to the baseband processing unit in the integrated space-air base station. After data processing, the terminal's access request and related information will be forwarded to the communication satellite through the external Starlink antenna. The virtual core network element on the satellite will perform legitimacy authentication on the terminal. After the authentication is passed, the data will be processed and forwarded by components such as the service gateway and data network gateway, and finally reach the Internet for data interaction.

[0086] Figure 5 A low-cost network rapid coverage method for emergency communications is shown. Figure 5 This method integrates a fixed-wing UAV, an omnidirectional RF antenna integrated with a reconfigurable smart surface, an air-space integrated base station, and a high-energy-density energy storage and power supply device.

[0087] This application also proposes a communication method for an air-space collaborative UAV emergency communication system, which can be run on Figure 6 In the computer terminal shown, the computer terminal is explained below.

[0088] The communication method embodiment of the air-space collaborative drone emergency communication system provided in the embodiment of the present application can be executed in a mobile terminal, a computer terminal or a similar computing device. Figure 6 The hardware structure block diagram of a computer terminal for implementing a communication method of an air-space collaborative UAV emergency communication system is shown. Figure 6 As shown, the computer terminal 60 may include one or more (602a, 602b, ..., 602n are used to illustrate) processors (the processor may include but is not limited to a processing device such as a microprocessor MCU or a programmable logic device FPGA), a memory 604 for storing data, and a transmission module 606 for communication functions connected via a wired and / or wireless network. In addition, it may also include: a display, a keyboard, a cursor control device, an input / output interface (I / O interface), a universal serial bus (USB) port (which may be included as one of the ports of the I / O interface), a network interface, and a BUS bus. A person of ordinary skill in the art can understand that Figure 6 The structure shown is only for illustration and does not limit the structure of the above electronic device. Figure 6 More or fewer components as shown, or with Figure 6 Different configurations shown.

[0089] It should be noted that the one or more processors and / or other data processing circuits described above may generally be referred to herein as "data processing circuits". The data processing circuits may be embodied in whole or in part as software, hardware, firmware, or any other combination thereof. In addition, the data processing circuit may be a single independent processing module, or may be incorporated in whole or in part into any of the other components in the computer terminal 60. As described in the embodiments of the present application, the data processing circuit acts as a processor control (e.g., selection of a variable resistor terminal path connected to an interface).

[0090] The memory 604 can be used to store software programs and modules of application software, such as the program instructions / data storage device corresponding to the communication method of the air-space collaborative UAV emergency communication system in the embodiment of the present application. The processor executes various functional applications and data processing by running the software programs and modules stored in the memory 604, that is, realizing the communication method of the air-space collaborative UAV emergency communication system mentioned above. The memory 604 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some instances, the memory 604 may further include a memory remotely arranged relative to the processor, and these remote memories may be connected to the computer terminal 60 via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0091] The transmission module 606 is used to receive or send data via a network. The specific example of the above network may include a wireless network provided by a communication provider of the computer terminal 60. In one example, the transmission module 606 includes a network adapter (Network Interface Controller, NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the transmission module 606 can be a radio frequency (Radio Frequency, RF) module, which is used to communicate with the Internet wirelessly.

[0092] The display may be, for example, a touch screen liquid crystal display (LCD) that enables a user to interact with a user interface of the computer terminal 60 .

[0093] It should be noted that, in some optional embodiments, the above Figure 6 The computer terminal shown may include hardware elements (including circuits), software elements (including computer code stored on a computer-readable medium), or a combination of hardware elements and software elements. It should be noted that Figure 6 This is merely one example of a particular embodiment and is intended to illustrate the types of components that may be present in the computer terminal described above.

[0094] Under the above-mentioned operating environment, an embodiment of the present application provides an embodiment of a communication method for an air-space collaborative drone emergency communication system. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0095] Figure 7 is a flow chart of a communication method of an air-space collaborative UAV emergency communication system according to an embodiment of the present application, such as Figure 7 As shown, the method comprises the following steps:

[0096] Step S701, receiving communication data of a user terminal through an air-space integrated base station;

[0097] Step S702, transmit the communication data to the communication satellite, and receive the return data of the communication satellite in response to the communication data, wherein the integrated air-space base station is powered by an energy storage device, and the energy storage device is composed of solar photovoltaic panels arranged on the drone. The solar photovoltaic panels adjust the working point based on a predetermined adjustment strategy to always charge according to the maximum output power.

[0098] Among them, the solar photovoltaic panel arranged on the drone adjusts the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge according to the maximum output power, including: detecting the conductance of the solar photovoltaic panel at the current working point and the conductance at the previous working point according to a preset period; and adjusting the output voltage of the solar photovoltaic panel upon detecting the rate of change of the conductance of the solar photovoltaic panel at the current working point relative to the conductance of the previous working point, so as to adjust the working point of the solar photovoltaic panel to the maximum power point.

[0099] Specifically, the initial state setting: First, set a starting operating point, the voltage and current corresponding to this operating point can be near the open circuit voltage (Voc) and short circuit current (Isc) of the photovoltaic cell. Usually, the MPPT controller will first set an operating point and then start monitoring the output of the photovoltaic cell.

[0100] Conductivity measurement and calculation: The MPPT controller continuously measures the output voltage (V) and output current (I) of the photovoltaic cell at the current operating point, and calculates the current conductivity (G = I / V). At the same time, it also measures and calculates the instantaneous change in conductivity of the photovoltaic cell at the current operating point (ΔG = ΔI / VI / ΔV), that is, the rate of change of current when the voltage changes slightly.

[0101] Maximum Power Point Prediction: Based on the incremental conductance method, the controller predicts the direction of the maximum power point by comparing the current conductance (G) and the instantaneous change in conductance (ΔG). Specifically, if ΔG > G, it indicates that the maximum power point is in the direction of decreasing voltage at the current operating point; if ΔG < G, it means the maximum power point is in the direction of increasing voltage; if ΔG ≈ G, then the current operating point is already very close to the maximum power point.

[0102] Operating Point Adjustment: Based on the above prediction, the MPPT controller adjusts the load impedance of the photovoltaic cell, thereby changing the operating point of the cell and moving it towards the maximum power point. If the maximum power point prediction is in the direction of increasing voltage, the controller increases the load impedance to raise the operating voltage; conversely, if the prediction is in the direction of decreasing voltage, the controller decreases the load impedance to lower the operating voltage.

[0103] Iterative Optimization: This process is iterative. The controller continuously monitors the output of the photovoltaic cell and adjusts the operating point according to the change trend of conductance until the photovoltaic cell stably operates near the maximum power point. This iterative optimization method ensures that even when external conditions (such as light intensity, temperature) change, the photovoltaic cell can quickly respond and re-find the maximum power point.

[0104] System Stability and Robustness: The MPPT algorithm based on the incremental conductance method has strong robustness to changes in external conditions such as light intensity and temperature. In actual operation, the controller executes the above steps at a certain period (such as dozens of milliseconds) to ensure that the photovoltaic module can quickly respond to changes in external conditions and maintain operation near the maximum power point.

[0105] Achieving Maximum Electrical Energy Output: Through continuous optimization and adjustment, the MPPT algorithm based on the incremental conductance method ensures that the photovoltaic module can operate at the maximum electrical power output state under different light and temperature conditions, thereby providing the most efficient electrical energy charging for the supercapacitor (SC) and providing stable and reliable energy for devices such as unmanned aerial vehicles, aerospace integrated base stations, and Starlink antennas.

[0106] Through the above steps, the MPPT control algorithm based on the incremental conductance method can dynamically adjust the operating point of the photovoltaic module, ensuring that the system always maintains the best energy conversion efficiency in a changing environment and providing continuous and efficient energy support for the emergency communication network.

[0107] Figure 8A drone is shown, comprising: a solar photovoltaic panel arranged on a wing, an energy storage device (supercapacitor), an aircraft battery, a Starlink antenna and an air-space integrated base station; the solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy to always charge the energy storage device and the aircraft battery according to the maximum output power; the aircraft battery is used to power the drone; the energy storage device is used to power the air-space integrated base station and the Starlink antenna; the air-space integrated base station is used to receive communication data of a user terminal, and send the communication data to a core network deployed in a communication satellite, and receive return data of the core network in response to the communication data; the Starlink antenna is used to connect the air-space integrated base station and the communication satellite for communication.

[0108] based on Figure 8 The drone shown, Fig. 9 A space-air coordinated UAV emergency communication network system is shown. Fig. 9 As shown, it includes: a mother machine and a sub-machine. The sub-machine is the same as the mother machine, but the sub-machine does not communicate with the satellite. The air-space integrated base station carried by it communicates with the satellite through X 2 or X n The link transmits data with the mother machine, and finally interacts with the satellite through the Starlink antenna on the mother machine. This system can greatly expand the coverage of the communication network, allowing more disaster-stricken users to access the network. It is designed for emergency rescue support when the communication network is interrupted on a large scale in the area of ​​sudden natural disasters. It can quickly restore communications and provide stable, reliable and real-time information transmission capabilities.

[0109] It should be noted that the mother machine can be Figure 8 Drone shown.

[0110] According to some embodiments of the present application, there is also provided an uplink data transmission method, including:

[0111] Step S801, receiving a request signal sent by a user terminal through an air-space integrated base station set on the drone;

[0112] Step S802: Send the request signal to the core network deployed on the communication satellite through the Starlink antenna, wherein the integrated air-space base station and the Starlink antenna are powered by an energy storage device deployed on the drone, and the energy storage device is composed of solar photovoltaic panels arranged on the wings of the drone. The solar photovoltaic panels adjust the working point of the solar photovoltaic panels based on a predetermined adjustment strategy to always charge at the maximum output power.

[0113] According to some embodiments of the present application, a downlink data transmission method is also provided, including:

[0114] Step S901, through the space-air integrated base station set on the drone, the return data sent by the core network deployed on the communication satellite is received through the Starlink antenna:

[0115] Step S902: convert the return data into a radio frequency signal and send it to the user terminal, wherein the integrated air-space base station and the Starlink antenna are powered by an energy storage device deployed on the drone, and the energy storage device is composed of solar photovoltaic panels arranged on the wings of the drone. The solar photovoltaic panels adjust the working point based on a predetermined adjustment strategy to always charge at the maximum output power.

[0116] In order to better explain the transmission method of uplink data and downlink data, the present application also provides some embodiments for further explanation:

[0117] When a natural disaster occurs in a certain area, the roads are severely damaged, the communication network is severely damaged, and a large area is paralyzed. It is difficult for emergency communication vehicles to arrive in time. Traditional tethered drones are not qualified. In order not to affect the post-disaster rescue command work, a fixed-wing drone equipped with a fully directional RF antenna that integrates a reconfigurable intelligent surface, an integrated air-space base station, and a high-energy-density energy storage and power supply equipment takes off quickly. After takeoff, the foldable solar photovoltaic panel equipped on the wing with MPPT technology slowly unfolds, absorbing light energy and efficiently converting it into electrical energy and storing it in the supercapacitor SC. The SC can charge the drone battery to increase its endurance, and can also power the RIS controller in the fully directional RF antenna, the integrated air-space base station, and the Starlink antenna for satellite communications to ensure the normal operation of each active component.

[0118] Uplink data request:

[0119] When the affected users want to restore communication access to the network, they send out random access request signals through the terminal. After receiving the request, the omnidirectional RF antenna transmits the data to the baseband processing unit in the base station for data processing. Then the terminal's access request and related information will be forwarded to the communication satellite through the external Starlink antenna via the radio electromagnetic waves of the Ka band. The virtualized core network on the satellite will process the legitimacy of the terminal and related requests. These functions include mobility management (MME / AMF), session management (SGW / SMF), etc. After authentication, the data is processed and routed by gateway components such as packet forwarding (PGW / UPF) and finally reaches the Internet for data interaction.

[0120] Downlink data arrival:

[0121] When downlink data arrives, its transmission process between the integrated air-space base station and the communication satellite is consistent with the uplink data request process, but in the opposite direction, so it will not be repeated. After the data arrives at the airborne base station, it is sent to the RF transceiver, which converts the digital signal into an analog signal, and converts it into an RF signal through a series of frequency conversion, filtering and modulation processes. The amplified RF signal is sent to the antenna, and the antenna vibrator converts the RF signal into an electromagnetic wave and propagates in a fan shape in the 120° direction forward. Some of the beams are reflected and refracted by multiple small smart surfaces (RIS and HMS) with pre-designed reflection and transmission angles, changing their propagation direction or forming beams in a specific direction. Finally, the equivalent coverage of a single sector of 120° forms a 360° full-space radiation in three sectors, reducing the load of the fixed-wing UAV (from carrying 3 antennas to only carrying a single antenna), improving its endurance, and allowing more affected users to interact with the outside world through network connections.

[0122] An embodiment of the present application also provides a computer device, including: a memory and a processor, wherein the memory is used to store program instructions; the processor is connected to the memory and is used to execute the communication method of the above-mentioned air-space collaborative drone emergency communication system.

[0123] An embodiment of the present application also provides a non-volatile storage medium, which includes a stored computer program, wherein the device where the non-volatile storage medium is located executes the communication method of the above-mentioned air-space collaborative drone emergency communication system by running the computer program.

[0124] An embodiment of the present application also provides a computer program product, including a non-volatile computer-readable storage medium, wherein the non-volatile computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the communication method of the air-space collaborative drone emergency communication system in the present application are implemented.

[0125] An embodiment of the present application also provides a computer program product, including computer instructions, which, when executed by a processor, implement the steps of the communication method of the air-space collaborative drone emergency communication system in the present application.

[0126] An embodiment of the present application also provides a computer program, which, when executed by a processor, implements the steps of the communication method of the air-space collaborative drone emergency communication system in the present application.

[0127] The serial numbers of the above-mentioned embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0128] In the above embodiments of the present application, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0129] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are only schematic. For example, the division of the units can be a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0130] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0131] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0132] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application is essentially or the part that contributes to the prior art or all or part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, server or network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, disk or optical disk and other media that can store program code.

[0133] The above is only a preferred embodiment of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. An air-space collaborative UAV emergency communication system, characterized in that: include: A drone, wherein the drone is provided with a solar photovoltaic panel, an energy storage device and an air-space integrated base station; The solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge the energy storage device according to the maximum output power; The energy storage device is used to supply power to the UAV and the air-space integrated base station; The integrated air-space base station is used to receive communication data from user terminals, send the communication data to a core network deployed in a communication satellite, and receive return data from the core network in response to the communication data.

2. The system according to claim 1, characterized in that The air-space integrated base station comprises: An omnidirectional radio frequency antenna, used for receiving communication data sent by the user terminal and sending the communication data to a radio frequency processing unit, wherein the omnidirectional radio frequency antenna comprises: a smart surface, wherein the smart surface comprises a plurality of sub-smart surfaces, wherein the plurality of sub-smart surfaces comprises: a plurality of reconfigurable smart surfaces RIS and a plurality of Huygens metasurfaces HMS, wherein the plurality of reconfigurable smart surfaces RIS and the plurality of Huygens metasurfaces HMS; The radio frequency processing unit is used to process the communication data and send the processed communication data to the communication satellite via the omnidirectional radio frequency antenna.

3. The system according to claim 2, characterized in that The smart surface is used to receive the radio frequency signal corresponding to the communication data, and divide the radio frequency signal into three parts to obtain a first part of the radio frequency signal, a second part of the radio frequency signal and a third part of the radio frequency signal. The first part of the radio frequency signal is emitted through the gaps between the multiple sub-smart surfaces and propagates in the original direction of the radio frequency signal. The second part of the radio frequency signal is reflected by the RIS, and the third part of the radio frequency signal is transmitted by the HMS.

4. The system according to claim 3, characterized in that The RIS includes: Reflection unit, metal plate and controller; The reflecting unit is used to receive the second part of the radio frequency signal and reflect the adjusted second part of the radio frequency signal; The metal plate is used to isolate signal penetration; The controller is used to adjust the reflection direction, phase and amplitude of the second part of the radio frequency signal.

5. The system according to claim 2, characterized in that The reflection signal of each reflection unit on the RIS includes: In the formula, Q k represents the incident signal of the kth reflection unit, P k represents the reflection signal of the kth reflection unit; δ k ∈[0, 1], represents the amplitude factor of the electromagnetic wave after being reflected by the kth reflection unit, θ k ∈[0, 2π), represents the phase factor of the electromagnetic wave after being reflected by the kth reflection unit, k∈[1, N], k and N represent positive integers, j represents an imaginary number.

6. The system according to claim 3, characterized in that The HMS comprises: Outer layer, middle layer and inner layer; The outer layer periodically arranges a plurality of metal patches to form a first metal ring belt, wherein the first and tail parts of the first metal ring belt have first notches; The intermediate layer is a base dielectric layer; The inner layer periodically arranges a plurality of metal patches to form a second metal ring belt, wherein the first and last parts of the second metal ring belt have second notches; The first notch and the second notch are used to adjust the transmission direction, phase and amplitude of the second part of the radio frequency signal.

7. The system according to claim 1, characterized in that Also includes: Starlink antennas; The Starlink antenna is used to forward the communication data received by the integrated air-space base station from the user terminal to the communication satellite.

8. A communication method for an air-space collaborative UAV emergency communication system, characterized in that: include: Receive communication data from user terminals through the space-air integrated base station; The communication data is transmitted to a communication satellite, and feedback data transmitted by the communication satellite in response to the communication data is received, wherein the integrated air-space base station is powered by an energy storage device, and the energy storage device is composed of solar photovoltaic panels arranged on the drone, which adjust the working point of the solar photovoltaic panels based on a predetermined adjustment strategy so as to always charge according to the maximum output power.

9. The method according to claim 8, characterized in that The solar photovoltaic panel disposed on the drone adjusts the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge at the maximum output power, including: Detecting the conductance of the solar photovoltaic panel at a current working point and the conductance at a previous working point according to a preset cycle; After detecting the rate of change of the conductance of the solar photovoltaic panel at the current working point relative to the conductance at the previous working point, the output voltage of the solar photovoltaic panel is adjusted to adjust the working point of the solar photovoltaic panel to the maximum power point.

10. A drone, characterized in that: include: Solar photovoltaic panels, energy storage devices, aircraft batteries, Starlink antennas and integrated air-space base stations installed on the wings; The solar photovoltaic panel is used to adjust the working point of the solar photovoltaic panel based on a predetermined adjustment strategy so as to always charge the energy storage device and the aircraft battery according to the maximum output power; The aircraft battery is used to power the drone; The energy storage device is used to power the integrated air-space base station and the Starlink antenna; The space-air integrated base station is used to receive communication data from user terminals, send the communication data to a core network deployed in a communication satellite, and receive return data from the core network in response to the communication data; The Starlink antenna is used to connect the integrated air-space base station and the communication satellite.

11. A method for uplink data transmission, characterized in that: include: The request signal sent by the user terminal is received through the air-space integrated base station set up on the UAV; The request signal is sent to the core network deployed on the communication satellite through the Starlink antenna, wherein the integrated air-space base station and the Starlink antenna are powered by an energy storage device deployed on the drone, and the energy storage device is composed of solar photovoltaic panels arranged on the wings of the drone. The solar photovoltaic panels adjust the working point of the solar photovoltaic panels based on a predetermined adjustment strategy to always charge at the maximum output power.

12. A downlink data transmission method, characterized in that: include: Through the integrated air-space base station set up on the drone, the Starlink antenna receives the return data sent by the core network deployed on the communication satellite: The backhaul data is converted into a radio frequency signal and sent to a user terminal, wherein the integrated air-space base station and the Starlink antenna are powered by an energy storage device deployed on a drone, and the energy storage device is composed of solar photovoltaic panels arranged on the wings of the drone. The solar photovoltaic panels adjust the working point of the solar photovoltaic panels based on a predetermined adjustment strategy to always charge at the maximum output power.

13. A computer device, characterized in that: include: A memory and a processor, wherein the memory is used to store program instructions; the processor, connected to the memory, is used to execute the communication method of the air-space collaborative drone emergency communication system as described in any one of claims 8-9.

14. A computer program product comprising computer instructions, characterized in that When the computer instructions are executed by the processor, the communication method of the air-space collaborative drone emergency communication system described in any one of claims 8-9 is implemented.

Images