Flight equipment outer escape layer locking method, electronic equipment and storage medium

Abstract

The invention discloses a flight equipment outer escape layer locking method, electronic equipment and a storage medium, and the method comprises the steps: generating an adjustment signal in response to a predetermined orbit, deviating from an atmospheric outer escape layer, of flight equipment; generating a first power output strategy of the flight equipment based on the adjustment signal and first environment data of the flight equipment; and based on the first power output strategy, controlling a propulsion system of the flight equipment to carry out power output until the flight equipment is in a locked state of the atmospheric escape layer. According to the scheme, the stability of the flight equipment in an atmospheric escape layer can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of flight equipment, and in particular to an exosphere locking method for flight equipment, electronic equipment, and storage medium. Background Art

[0002] At present, locking a flying device in the exosphere is a difficult technical challenge that requires the comprehensive use of multiple technical means to achieve. In the existing technology, flying devices face many difficulties in the exosphere, such as harsh environment, cosmic rays, etc., which make the flying device unable to be stable in the exosphere, which will affect the control of the flying device. Summary of the invention

[0003] The present application at least provides a method for locking the flight equipment in the exosphere, an electronic device, and a storage medium, which can improve the stability of the flight equipment in the atmospheric exosphere.

[0004] A first aspect of the present application provides an exosphere locking method for a flying device, comprising: generating an adjustment signal in response to the flying device deviating from a predetermined orbit in the atmospheric exosphere; generating a first power output strategy for the flying device based on the adjustment signal and first environmental data in which the flying device is located; and based on the first power output strategy, controlling a propulsion system of the flying device to output power until the flying device is in a locked state in the atmospheric exosphere.

[0005] Among them, in response to the flight equipment deviating from the predetermined orbit of the atmospheric exosphere, generating an adjustment signal includes: obtaining a first current posture of the flight equipment; in response to the first current posture being within a preset range of the boundary of the atmospheric exosphere, generating an adjustment signal.

[0006] Among them, based on the adjustment signal and the first environmental data of the flight equipment, a first power output strategy of the flight equipment is generated, including: analyzing the adjustment signal and the first environmental data to determine the flight angle, flight speed and flight altitude that need to be adjusted for the flight equipment; based on the flight angle, flight speed and flight altitude, obtaining the first power output strategy.

[0007] Among them, the adjustment signal and the first environmental data are analyzed to determine the flight angle, flight speed and flight altitude that need to be adjusted for the flight equipment, including: predicting the first environmental data to obtain a prediction result; in response to the prediction result satisfying the path adjustment condition and receiving the adjustment signal, replanning the flight path of the flight equipment to obtain a changed flight path; based on the changed flight path, obtaining the flight angle, flight speed and flight altitude that need to be adjusted.

[0008] Among them, based on the first power output strategy, the propulsion system of the flight equipment is controlled to output power, including: adjusting the flight posture of the flight equipment based on the first power output strategy; in the process of adjusting the flight posture, obtaining the second current posture of the flight equipment and the second environmental data of the flight equipment; based on the second current posture and the second environmental data, adjusting the power output data of the propulsion system.

[0009] The method further includes: generating a heat dissipation strategy based on the second environmental data so that the temperature of the propulsion system is within a preset range.

[0010] The method further includes: generating a communication adjustment strategy based on the second environment data; adjusting the communication mode of the communication system of the flight equipment based on the communication adjustment strategy, wherein the flight equipment can use the adjusted communication mode to notify the target of the location information of the flight equipment.

[0011] Among them, based on the communication adjustment strategy, the communication mode of the communication system of the flight equipment is adjusted, including at least one of the following steps: detecting unoccupied spectrum segments in the communication system, and using the unoccupied spectrum segments for communication transmission; adjusting the direction of the adaptive antenna array to optimize the communication quality of the communication system; using a multi-beam LED array for communication; based on the channel conditions of the flight equipment, adjusting the physical parameters of the communication system, wherein the physical parameters include at least one of the power level, modulation scheme, and coding rate.

[0012] A second aspect of the present application provides an electronic device, comprising a memory and a processor coupled to each other, the processor being used to execute program instructions stored in the memory to implement the flight equipment exosphere locking method in the above-mentioned first aspect.

[0013] A third aspect of the present application provides a computer-readable storage medium having program instructions stored thereon, which, when executed by a processor, implements the flight equipment exosphere locking method of the first aspect.

[0014] The above scheme generates an adjustment signal when it is detected that the flight device deviates from the predetermined orbit of the atmospheric exosphere, and generates a first power output strategy for the flight device based on the adjustment signal and the first environmental data of the flight device. According to the first power output strategy, the propulsion system of the flight device is controlled to perform corresponding power output, so that the flight device is in a locked state in the atmospheric exosphere, thereby improving the stability of the flight device in the atmospheric exosphere.

[0015] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings herein are incorporated into the specification and constitute a part of the specification. These drawings illustrate embodiments consistent with the present application and are used together with the specification to illustrate the technical solution of the present application.

[0017] Figure 1 It is a schematic diagram of the framework of an embodiment of the flight equipment of the present application;

[0018] Figure 2 This is a flow chart of an embodiment of an exosphere locking method for a flight device of the present application;

[0019] Figure 3 It is a flowchart of an embodiment of a method for adjusting communication of flight equipment of the present application;

[0020] Figure 4 It is a flow chart of another embodiment of the exosphere locking method for flight equipment of the present application;

[0021] Figure 5 It is a schematic diagram of the framework of an embodiment of the electronic device of the present application;

[0022] Figure 6 It is a schematic diagram of a framework of an embodiment of a computer-readable storage medium of the present application. DETAILED DESCRIPTION

[0023] The scheme of the embodiment of the present application is described in detail below in conjunction with the drawings of the specification.

[0024] In the following description, for the purpose of explanation rather than limitation, specific details such as specific system structures, interfaces, and technologies are provided to facilitate a thorough understanding of the present application.

[0025] The term "and / or" in this article is only a description of the association relationship of associated objects, indicating that there may be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the objects associated before and after are in an "or" relationship. In addition, "many" in this article means two or more than two. In addition, the term "at least one" in this article means any combination of at least two of any one or more of a plurality of, for example, including at least one of A, B, and C, can mean including any one or more elements selected from the set consisting of A, B, and C.

[0026] The exosphere is the outermost layer of the Earth's atmosphere, located in an altitude area about 500 to 1000 kilometers from the Earth's surface, with a relatively rarefied gas composition and a strong radiation environment. Due to its special physical and chemical properties, the exosphere has many unique application values, one of which is as an important application scenario in the aerospace field. The locked state of flight equipment in the exosphere refers to controlling the flight equipment to operate in the exosphere, and using its stable high-altitude environment to carry out various tasks and experiments. Compared with conventional low-altitude flight, the exosphere has lower air resistance and wind resistance, which can reduce energy consumption and improve the endurance of flight equipment; at the same time, because fewer gas molecules in the exosphere will reduce the heat loss of the body, it makes it easier to control the temperature of the body. The application range of flight equipment locked in the exosphere is very wide, including scientific exploration, communication and positioning, monitoring and observation. For example, NASA's (National Aeronautics and Space Administration) International Space Station and Earth Observation Satellites use the atmospheric exosphere to operate; in addition, some new wireless communication technologies and global positioning systems are also using the atmospheric exosphere for exploration and application. Among them, the flying equipment can be unmanned aerial vehicles, motorboats, helium balloons, helium floats, satellites, aircraft and other equipment, which are not specifically limited here.

[0027] See also Figure 1 , Figure 1 It is a schematic diagram of the framework of an embodiment of the flight device 100 of the present application. The flight device 100 mainly includes a flight body 110, a communication system 120, a navigation system 130, a propulsion system 140 and a cooling system 150. In addition, the flight device 100 may also include an energy storage system (not shown) to convert solar energy into electrical energy to provide sufficient energy for the flight device 100, thereby achieving stable operation of the flight device 100 in the atmospheric exosphere. It is understandable that the flight device 100 can also add or delete systems according to the actual tasks to be performed, and no specific limitation is made here.

[0028] In some embodiments, in order to ensure that the flying device 100 can fly for a long time in the atmospheric exosphere, it is necessary to consider what type of equipment to use as the flying body 110 of the flying device 100 at the beginning of the design. For example, a light-weight gas aircraft such as a balloon and an airship can be used as the flying body 110, and for light-weight gas aircraft such as a balloon and an airship, it is generally chosen to fly at an altitude of about 20-30 kilometers from the ground; a satellite can be used as the flying body 110, and for a satellite, a higher orbital altitude needs to be selected, generally more than 1,000 kilometers from the ground; a drone can be used as the flying body 110, and the drone can design its flight altitude according to the actual mission.

[0029] In the exosphere, the atmospheric density is low and the wind resistance is small. Airships and satellites can usually achieve higher flight speeds, but the cost is high. Balloons are affected by factors such as atmospheric flow and wind speed, and their speeds are relatively low. Therefore, in this embodiment, a drone is selected as the flight subject 110. The drone can choose a higher flight speed in the exosphere. The drone needs to have higher stability in the exosphere to ensure that it can fly for a long time in harsh environments. This requires consideration of factors such as the design, structure, and control of the drone. Factors such as the center of gravity and aerodynamic characteristics need to be considered in the design; lightweight and high-strength materials need to be selected in the structure; and a high-precision, high-reliability control system needs to be selected in terms of control.

[0030] In some embodiments, since the flight device 100 is flying in the atmospheric exosphere, the design of the communication system 120 is crucial to prevent the flight device 100 from being out of control and deviating from the predetermined orbit in the atmospheric exosphere. Before designing the communication system 120, it is necessary to determine which communication system to use before the communication system 120 can be installed on the flight device 100. Existing communication systems include radio communication systems, laser communication systems, LED (Light-emitting Diode) communication systems, etc. In addition, in this embodiment, the communication system 120 is also integrated with a control unit to analyze or predict the data obtained by the communication system 120. At present, although technologies such as radio communication systems and laser communication systems can provide certain help, they are greatly affected by factors such as weather and environment, and the communication quality cannot be guaranteed when used in the atmospheric exosphere. Therefore, the LED communication system is used in this embodiment to ensure higher communication stability and data transmission speed.

[0031] Before installing the related equipment of the LED communication system to the flight equipment 100, it is necessary to determine the parameters of the related equipment of the LED communication system, such as power, wavelength, and light-emitting angle. According to the mission requirements and technical conditions, select appropriate LED devices and drive circuits and other components, and perform system design and assembly. At the same time, it is also necessary to consider the cooling measures of the equipment to ensure that the equipment can work normally in a high temperature environment.

[0032] Specifically, the following parameters can be considered in the design of LED communication system:

[0033] 1. Transmission rate: The transmission rate of the LED communication system depends on the switching speed of the LED and the communication protocol. The faster the switching speed of the LED communication system, the higher the transmission rate. In the exosphere, the transmission rate may be subject to some restrictions, such as signal-to-noise ratio and interference. The transmission rate of the LED communication system can be calculated using the Shannon formula, which is as follows:

[0034]

[0035] Among them, C is the transmission rate, measured in bits per second (bps); B is the channel bandwidth, measured in Hertz (Hz); S / N is the signal-to-noise ratio, which is the ratio of signal power to noise power.

[0036] 2. Wavelength: The wavelength used by LED communication systems is usually within the visible light range, about 400 to 700 nanometers. In the exosphere, the wavelength is subject to some restrictions, such as atmospheric absorption and scattering. Therefore, it is necessary to select a wavelength range for transmission in the exosphere to minimize signal loss. The calculation of the wavelength of the LED communication system can be referred to the following formula:

[0037] λ=hc / E

[0038] Among them, h is Planck's constant, c is the speed of light, and E is the photon energy.

[0039] 3. Power: The transmission power of the LED communication system depends on the communication distance and the sensitivity of the receiver. In the exosphere, since the signal will be attenuated, sufficient transmission power is required to ensure that the signal can be received. The calculation of the power of the LED communication system can refer to the following formula:

[0040] P=I×V

[0041] Wherein, I is the current of the LED device, and V is the voltage of the LED device.

[0042] 4. Protocol: The protocol of the LED communication system determines the encoding and decoding methods of the data, as well as the transmission method and format. In the atmospheric exosphere, it is necessary to select a protocol that can adapt to the channel environment and has sufficient error correction capabilities. At the same time, the communication protocol will also affect the transmission rate. For example, using more efficient protocols such as OFDM (Orthogonal Frequency Division Multiplexing) and QAM (Quadrature Amplitude Modulation) can increase the transmission rate.

[0043] 5. Lighting angle: The light-emitting angle can be controlled by the structure and manufacturing process of the LED device. When selecting LED devices, it is necessary to consider the device's light-emitting angle and beam shape to ensure that it can meet the task requirements.

[0044] Based on the above parameters, the general steps for designing an LED communication system are as follows: Determine the communication distance and transmission rate requirements. Select the wavelength range for transmission in the atmospheric exosphere and determine the transmission power. Then select an appropriate communication protocol and perform simulation and optimization to improve communication efficiency and error correction capabilities. After determining the system parameters, conduct experimental verification and performance testing to evaluate the reliability of the system and the actual transmission rate. Optimize the system parameters to further improve system performance. It should be noted that LED communication in the atmospheric exosphere requires consideration of some special environmental factors, such as radiation interference, high-energy particles, etc. These factors may affect system performance and require special treatment.

[0045] To protect LED communication equipment from the hazards of electromagnetic radiation in the atmospheric exosphere, a radiation shielding layer can be incorporated into the equipment design. This shielding layer can be made of materials that effectively absorb or deflect high-energy particles and electromagnetic waves to prevent damage to sensitive electronic components. Shielding ensures the robustness and integrity of LED communication systems in the harsh radiation environment of the atmospheric exosphere.

[0046] In addition, in order to extend the communication coverage of the LED communication system and improve the system capacity, multi-beam LED arrays can be used in the LED communication system. These arrays can generate multiple simultaneous beams, enabling the flying device 100 to communicate with multiple ground stations or other flying devices 100 at the same time. This multi-beam array architecture enhances the flexibility and redundancy of the LED communication system, allows seamless switching between communication links, and enables efficient data dissemination in a network of a group of flying devices 100 in the exosphere of the atmosphere.

[0047] In some embodiments, when installing the communication system 120 equipment, the stability and reliability of the equipment also need to be considered. High-strength, lightweight materials can be selected and suitable mechanical structures can be designed to ensure that the equipment can withstand high-speed flight and harsh environmental conditions. At the same time, sufficient testing and verification are required to ensure the reliability and performance of the equipment. For example, when the communication system 120 is an LED communication system, the installation of the LED communication system equipment needs to fully consider the power, wavelength, light-emitting angle and other parameters of the equipment, and take appropriate cooling measures to ensure that the equipment can work normally in the high temperature environment of the atmospheric exosphere. At the same time, it is also necessary to ensure the stability and reliability of the equipment to meet the mission requirements.

[0048] In order to further improve the reliability of the equipment, self-healing materials are used in the design of the communication system 120 equipment, which can automatically repair itself after exosphere radiation damage and increase the life of the equipment.

[0049] In addition, in order to enable the flight device 100 to efficiently transmit data after being locked in the atmospheric exosphere, the cognitive radio technology can be incorporated into the communication system 120 before the flight device 100 is officially activated to effectively utilize the limited spectrum resources in the atmospheric exosphere. Among them, cognitive radio technology can dynamically detect and utilize unoccupied spectrum segments, so that the flight device 100 can have the opportunity to share the spectrum with other objects or avoid interference with existing transmissions. This adaptive method can maximize the spectrum utilization and ensure efficient data transmission in the crowded environment of the atmospheric exosphere.

[0050] In some embodiments, in order to optimize communication performance and mitigate the effects of ionospheric refraction in the atmospheric exosphere, an adaptive control mechanism may be added to the communication system 120. The mechanism may continuously monitor ionospheric conditions and adjust the flight path and communication parameters of the flight device 100 accordingly. By dynamically adapting to the changing ionospheric environment, the communication system 120 may minimize signal distortion and ensure a reliable communication link with a ground station or other flight devices 100.

[0051] In addition, in order to protect the communication system 120 equipment from the harm of exosphere electromagnetic radiation, a radiation shielding layer design is added to the communication system 120.

[0052] In other embodiments, in order to cope with the unpredictable and dynamic nature of the atmospheric exosphere, a dynamic link adaptation mechanism can be incorporated into the communication system 120. The dynamic link adaptation mechanism dynamically adjusts transmission parameters, such as modulation scheme, coding rate, and power level, based on real-time channel conditions to ensure robust and reliable communication. This adaptive method can effectively mitigate the effects of ionospheric interference, atmospheric turbulence, and signal fading, ensuring consistent and high-quality data transmission in the communication system 120.

[0053] In other embodiments, a real-time environmental perception system based on artificial intelligence (AI) may also be introduced into the communication system 120. The system uses machine learning algorithms to continuously monitor and predict environmental changes in the exosphere, including factors such as temperature, radiation intensity, and particle flow. The AI ​​system is used to analyze these changes in real time, so that the AI ​​system can actively optimize the communication strategy, not only dynamically adjust physical parameters (such as power and modulation schemes), but also automatically switch communication modes or select the best channel when the environment changes drastically, so as to maximize the stability and efficiency of communication. Since the AI ​​algorithm is deeply integrated into the communication system 120, the communication system 120 has the ability of self-learning and self-adaptation, and no longer relies solely on traditional physical parameter adjustments, thereby realizing a more intelligent communication system 120 suitable for the atmospheric exosphere.

[0054] In some embodiments, in order to achieve precise control of the flying device 100 and keep the flying device 100 in a stable position in the atmospheric exosphere, the navigation system 130 can use a high-precision attitude navigation system, such as an inertial navigation system, a star tracker, and a GPS receiver. Specifically, a quantum navigation system can be used, which integrates multiple sensors to provide accurate information about the attitude, position, and speed of the flying device 100 relative to the earth. The navigation system 130 can also be combined with an advanced control algorithm that can effectively compensate for interference and keep the attitude and trajectory of the flying device 100 within a strict tolerance range.

[0055] The navigation system 130 can also be used to locate and adjust the altitude and speed of the flying device 100 to ensure that it maintains a stable flight state within the ionosphere altitude range of the atmospheric exosphere. The following is a formula for calculating the refraction angle of the flying device 100 at the ionosphere altitude:

[0056]

[0057] Among them, θ i is the incident angle, i.e., the flight angle of the flying device 100; n1 is the refractive index of air, which is approximately 1; and n2 is the refractive index of the ionosphere, which generally varies between 1.3 and 1.5. By controlling the flight angle and flight speed of the flying device 100, the flying device 100 can maintain a stable refractive angle within the ionosphere altitude range, thereby achieving the purpose of locking the atmospheric exosphere. In this way, the special properties of the ionosphere can be used for applications such as long-distance communication, navigation, and atmospheric detection.

[0058] In some embodiments, in order for the flying device 100 to achieve the desired maneuverability and efficiency in the atmospheric exosphere, a hybrid propulsion system can be integrated into the propulsion system 140. The hybrid propulsion system can combine electric propulsion with traditional chemical propulsion to take into account the advantages of both. Electric propulsion has the characteristics of high efficiency and low noise, while chemical propulsion can provide high thrust for rapid maneuvers and initial ascent. The hybrid propulsion system can dynamically switch propulsion modes according to mission requirements, maximizing the performance of the propulsion system 140 and minimizing fuel consumption.

[0059] In order to ensure stable and autonomous operation of the flying device 100 in the exosphere, an advanced autonomous control system may be added to the flying device 100. The autonomous control system should be combined with an adaptive flight path planning algorithm that can take into account the dynamic and unpredictable environment of the exosphere. The algorithm can adjust the trajectory of the flying device 100 in real time to avoid obstacles, maintain a stable position relative to the earth, and optimize energy consumption.

[0060] In some embodiments, in order to cope with the thermal challenges brought by the high temperature of the atmospheric exosphere and the heat generated by the flight device 100 itself, a heat dissipation system 150 may be designed in the flight device 100. Specifically, an active thermal management system may be integrated into the flight device 100, and the active thermal management system may use a variety of heat dissipation technologies, such as heat pipes, liquid cooling, and phase change materials, etc., to effectively remove heat from the communication system 120 and the propulsion system 140 and keep the operating temperature within a safe range. This active approach ensures the long-term reliability and performance of the flight device 100 in the atmospheric exosphere.

[0061] For example, in order to ensure that the flying device 100 can work normally in the high temperature environment of the atmospheric exosphere, the heat dissipation system 150 may adopt the following design:

[0062] A. By installing a heat sink, the heat of the communication system 120 and the propulsion system 140 and other devices is dissipated into the surrounding environment to reduce the temperature of the devices.

[0063] B. By installing a temperature-controlled fan, the fan speed is automatically controlled according to the device temperature to achieve effective cooling.

[0064] C. By installing heat pipes, the heat of equipment such as the communication system 120 and the propulsion system 140 is transferred to the heat pipes, and then the heat is dissipated into the surrounding environment through cooling devices to achieve efficient cooling.

[0065] The communication system 120 in this application can dynamically monitor environmental changes in the exosphere by introducing a real-time environmental perception system based on artificial intelligence, and use machine learning algorithms to adjust communication strategies in real time. Compared with the traditional physical parameter adjustment method, this method has self-learning and self-adaptive capabilities, making the communication system 120 more intelligent, able to automatically switch communication modes or select the best channel, and improve communication stability and efficiency.

[0066] Incorporating a quantum navigation system into the design of the flight device 100, and utilizing the characteristics of quantum entanglement, achieves higher precision navigation and attitude control. Compared to traditional navigation technology, quantum navigation provides more precise positioning and trajectory control capabilities, and is particularly suitable for complex and unpredictable environments such as the exosphere.

[0067] The communication system 120 equipment uses self-healing materials that can automatically repair themselves after radiation damage in the exosphere, increasing the life and reliability of the equipment. This technological innovation significantly enhances the durability of the equipment in extreme environments and reduces maintenance requirements.

[0068] An adaptive antenna array is also introduced in the flight device 100, which can dynamically optimize the transmission quality of the communication signal through intelligent antenna direction adjustment. Compared with the traditional fixed array, this technology has higher flexibility and adaptability, especially in the complex environment of the exosphere, and can maintain higher signal quality and coverage.

[0069] See also Figure 2 , Figure 2 This is a flow chart of an embodiment of the method for locking the exosphere of a flight device of the present application. Specifically, the following steps may be included:

[0070] Step S210: In response to the flight device deviating from a predetermined orbit in the atmospheric exosphere, an adjustment signal is generated.

[0071] In some embodiments, the first current position of the flight device 100 may be acquired by real-time detection or timed detection, and an adjustment signal may be generated in response to the first current position being within a preset range of the boundary of the atmospheric exosphere, wherein the preset range may be 1 km, 2 km, 5 km, etc., close to the boundary of the atmospheric exosphere.

[0072] Specifically, the navigation system 130 in the flight device 100 can be used to detect the first current posture of the flight device 100 in real time. When it is detected that the first current posture of the flight device 100 is close to the boundary of the atmospheric exosphere within 5 kilometers, the navigation system 130 will issue an alarm signal and generate an adjustment signal at the same time.

[0073] Step S220: Generate a first power output strategy for the flight equipment based on the adjustment signal and the first environment data of the flight equipment.

[0074] In some embodiments, after receiving the adjustment signal, the flight path of the flying device 100 is replanned to obtain a changed flight path. Then, based on the changed flight path, the flight angle, flight speed, and flight altitude to be adjusted are obtained. Then, based on the flight angle, flight speed, and flight altitude, a first power output strategy is obtained.

[0075] In other embodiments, when it is known that the flight device 100 is about to fly out of the atmospheric exosphere, a set of adjustment strategies should be generated as soon as possible to enable the flight device 100 to return to the predetermined orbit or the locked state in the atmospheric exosphere. During the adjustment process of the flight device 100, in order to avoid too fast or drastic adjustment, which may cause damage to the components in the flight device 100 due to excessive changes in the surrounding environment, the adjustment of the flight device 100 should be as smooth as possible. Therefore, it is also necessary to obtain the first environmental data of the environment in which the flight device 100 is located at this time. The adjustment signal and the first environmental data are analyzed to determine the flight angle, flight speed and flight altitude that the flight device 100 needs to adjust; based on the flight angle, flight speed and flight altitude, the first power output strategy is obtained.

[0076] For example, a sensor system (not shown) equipped with the flying device 100 may be used to monitor in real time the environmental conditions of the atmospheric exosphere where the flying device 100 is located, so as to obtain the first environmental data.

[0077] For another example, the real-time environment perception system based on artificial intelligence in the flight device 100 can be used to continuously monitor and predict environmental changes in the exosphere to obtain first environmental data.

[0078] After obtaining the first environmental data of the environment in which the flight device 100 is located, the communication system 120 in the flight device can be used to predict the first environmental data to obtain a prediction result. In response to the prediction result satisfying the path adjustment condition and receiving the adjustment signal, the navigation system 130 replans the flight path of the flight device 100 to obtain a changed flight path. And according to the changed flight path, the flight angle, flight speed and flight altitude to be adjusted are obtained. The navigation system 130 then sends the flight angle, flight speed and flight altitude to be adjusted to the propulsion system 140, and the propulsion system 140 generates a first power output strategy according to the flight angle, flight speed and flight altitude to be adjusted to ensure that the flight device 100 can quickly and smoothly re-enter the exosphere.

[0079] The path adjustment condition is that the environment is relatively bad, for example, when the frequency of cosmic radiation is lower than 300 MHZ, it can be regarded as bad conditions in the atmospheric exosphere. In addition, the temperature or the number of particles can also be used as the basis for judging whether the environmental conditions are bad, which is not specifically limited here.

[0080] Step S230: Based on the first power output strategy, control the propulsion system of the flight device to output power until the flight device is in a locked state in the atmospheric exosphere.

[0081] In some embodiments, the propulsion system 140 of the flying device 100 will adjust the flight posture of the flying device 100 according to the first power output strategy. During the flight posture adjustment process, the navigation system 130 is used to obtain the latest second current posture of the flying device 100 and the communication system 120 is used to obtain the second environment data of the flying device. Based on the second current posture and the second environment data, the power output data of the propulsion system 140 is dynamically adjusted to keep the flying device 100 in a stable flight posture and avoid unnecessary vibration or yaw.

[0082] In addition, the propulsion system 140 will generate very high temperature during the process of adjusting the flight posture of the flight device 100. If the excess heat is not dissipated in time, it will affect the power output efficiency of the propulsion system 140 and damage the related equipment of the propulsion system 140. Therefore, when the propulsion system 140 outputs power, the communication system 120 will also send the acquired second environment data to the heat dissipation system 150. The heat dissipation system 150 generates a heat dissipation strategy based on the second environment data, so that the temperature of the propulsion system 140 is within a preset range, and the power adjustment of the propulsion system 140 can also be coordinated.

[0083] In some embodiments, during the process of adjusting the flight posture of the flying device 100, the change of the position and environment of the flying device 100 will seriously affect the communication quality. Therefore, during the process of adjusting the flight posture of the flying device 100, the communication quality of the communication system 120 needs to be optimized. Figure 3 , Figure 3 This is a flowchart of an embodiment of the flight equipment communication adjustment method of the present application. Specifically, it may include the following steps:

[0084] Step S310: Generate a communication adjustment strategy based on the second environment data.

[0085] In some embodiments, the sensor system in the flying device 100 can be used to monitor the environmental conditions of the atmospheric exosphere where the flying device 100 is located in real time to obtain the second environmental data. The communication system 120 analyzes and predicts the second environmental data to generate a communication adjustment strategy.

[0086] Step S320: Based on the communication adjustment strategy, the communication mode of the communication system of the flight equipment is adjusted, wherein the flight equipment can use the adjusted communication mode to notify the target of the location information of the flight equipment.

[0087] In some embodiments, in order to enable the flying device 100 to maintain good communication effects in the complex environment of the atmospheric exosphere, it is necessary to timely adjust the communication mode of the communication system 120. For example, after receiving the communication adjustment strategy, the cognitive radio technology in the communication system 120 can be used to detect unoccupied spectrum segments in the communication system 120, and the unoccupied spectrum segments can be used for communication transmission.

[0088] For another example, after receiving the communication adjustment strategy, the direction of the adaptive antenna array in the communication system 120 may be adjusted to optimize the communication quality of the communication system.

[0089] As another example, a multi-beam LED array may be used for communication.

[0090] In addition, the physical parameters of the communication system 120 may be adjusted based on the channel conditions of the flying device 100 , wherein the physical parameters include at least one of a power level, a modulation scheme, and a coding rate.

[0091] See also Figure 4 , Figure 4 This is a flow chart of another embodiment of the method for locking the exosphere of a flight device of the present application. Specifically, the following steps may be included:

[0092] Step S410: Detect the position and posture of the flying device to obtain the current position and posture.

[0093] In some embodiments, the navigation system 130 in the flying device 100 is used to monitor the position and posture of the flying device in the atmospheric exosphere in real time to obtain the current position and posture.

[0094] Step S420: Compare the current posture with the predetermined flight path of the flying device to obtain a comparison result.

[0095] In some embodiments, after obtaining the current position and posture of the flight device 100, the navigation system 130 compares the current position and posture with the predetermined flight path stored in the navigation system 130 to obtain a comparison result. If the comparison result shows that the current position and posture of the flight device 100 is within the deviation range allowed by the predetermined flight path, it indicates that the flight device 100 is in a locked state in the atmospheric exosphere; if the comparison result shows that the current position and posture of the flight device 100 has exceeded the deviation range allowed by the predetermined flight path, it indicates that the flight device 100 has deviated from the predetermined flight path, and therefore, the flight path of the flight device 100 needs to be adjusted in time to prevent the flight device 100 from falling or getting out of control.

[0096] Step S430: In response to the comparison result indicating that the flight equipment sends a deviation, an adjustment signal is generated.

[0097] This step is the same as the above step S210 and will not be described again here.

[0098] Step S440: Acquire first environmental data of the environment in which the flying device is located.

[0099] In some embodiments, the real-time environment perception system in the communication system 120 in the flying device 100 may be used to dynamically monitor the environmental changes in the atmospheric exosphere where the flying device is located to obtain first environmental data.

[0100] In one implementation scenario, the above step S430 and step S440 may be performed in a sequential order, for example, step S430 is performed first and then step S440; or, step S440 is performed first and then step S430. In another implementation scenario, the above step S430 and step S440 may also be performed simultaneously, which may be set according to actual application and is not limited here.

[0101] Step S450: Generate a first power output strategy for the flight equipment based on the adjustment signal and the first environmental data.

[0102] This step is the same as the above step S220 and will not be described again here.

[0103] Step S460: Based on the first power output strategy, control the propulsion system of the flight equipment to output power, and adjust the communication mode of the communication system of the flight equipment.

[0104] This step is the same as the above step S230 and will not be described again here.

[0105] When the present application detects that the flight equipment deviates from the predetermined orbit of the atmospheric exosphere, an adjustment signal is generated, and a first power output strategy of the flight equipment is generated according to the adjustment signal and the first environmental data of the flight equipment. According to the first power output strategy, the propulsion system of the flight equipment is controlled to perform corresponding power output, so that the flight equipment is in a locked state in the atmospheric exosphere, thereby improving the stability of the flight equipment in the atmospheric exosphere.

[0106] Those skilled in the art will appreciate that, in the above method of specific implementation, the order in which the steps are written does not imply a strict execution order and does not constitute any limitation on the implementation process. The specific execution order of the steps should be determined by their functions and possible internal logic.

[0107] See also Figure 5 , Figure 5: is a schematic diagram of a framework of an embodiment of an electronic device 50 of the present application. The electronic device 50 includes a memory 51 and a processor 52 coupled to each other, and the processor 52 is used to execute program instructions stored in the memory 51 to implement the steps of any of the above-mentioned flight equipment exosphere locking method embodiments, or to implement the steps of any of the above-mentioned flight equipment communication adjustment method embodiments. In a specific implementation scenario, the electronic device 50 may include but is not limited to: a microcomputer, a server, and in addition, the electronic device 50 may also include mobile devices such as a laptop computer and a tablet computer, which are not limited here.

[0108] Specifically, the processor 52 is used to control itself and the memory 51 to implement the steps of any of the above-mentioned flight equipment exosphere locking method embodiments, or to implement the steps of any of the above-mentioned flight equipment communication adjustment method embodiments. The processor 52 can also be called a CPU (Central Processing Unit). The processor 52 may be an integrated circuit chip with signal processing capabilities. The processor 52 can also be a general-purpose processor, a digital signal processor (Digital Signal Processor, DSP), an application-specific integrated circuit (Application Specific Integrated Circuit, ASIC), a field-programmable gate array (Field-Programmable Gate Array, FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor, etc. In addition, the processor 52 can be implemented by an integrated circuit chip.

[0109] See also Figure 6 , Figure 6 1 is a schematic diagram of a framework of an embodiment of a computer-readable storage medium 60 of the present application. The computer-readable storage medium 60 stores program instructions 601 that can be executed by a processor, and the program instructions 601 are used to implement the steps of any of the above-mentioned flight equipment exosphere locking method embodiments, or to implement the steps of any of the above-mentioned flight equipment communication adjustment method embodiments.

[0110] In some embodiments, the functions or modules included in the device provided by the embodiments of the present disclosure can be used to execute the method described in the above method embodiments. The specific implementation can refer to the description of the above method embodiments, and for the sake of brevity, it will not be repeated here.

[0111] The above description of various embodiments tends to emphasize the differences between the various embodiments. The same or similar aspects can be referenced to each other, and for the sake of brevity, they will not be repeated herein.

[0112] In the several embodiments provided in the present application, it should be understood that the disclosed methods and devices can be implemented in other ways. For example, the device implementation described above is only schematic. For example, the division of modules or units is only a logical function division. There may be other division methods in actual implementation, such as 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, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.

[0113] 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.

[0114] 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.) or a processor (processor) to perform all or part of the steps of each implementation method of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program code.

Claims

1. A method for locking the exosphere of a flying device, characterized in that: include: generating an adjustment signal in response to the flight device deviating from a predetermined trajectory in the atmospheric exosphere; generating a first power output strategy for the flight device based on the adjustment signal and first environmental data of the flight device; Based on the first power output strategy, the propulsion system of the flight device is controlled to output power until the flight device is in a locked state in the atmospheric exosphere.

2. The method according to claim 1, characterized in that The generating of the adjustment signal in response to the flight device deviating from the predetermined orbit of the atmospheric exosphere comprises: Acquire a first current position of the flying device; In response to the first current posture being within a preset range of a boundary of the atmospheric exosphere, an adjustment signal is generated.

3. The method according to claim 1, characterized in that The step of generating a first power output strategy for the flight device based on the adjustment signal and first environmental data of the flight device comprises: Analyze the adjustment signal and the first environmental data to determine the flight angle, flight speed, and flight altitude of the flying device that need to be adjusted; The first power output strategy is obtained based on the flight angle, flight speed and flight altitude.

4. The method according to claim 3, characterized in that The analyzing the adjustment signal and the first environmental data to determine the flight angle, flight speed, and flight altitude of the flying device to be adjusted includes: Predicting the first environmental data to obtain a prediction result; In response to the prediction result satisfying the path adjustment condition and receiving the adjustment signal, replanning the flight path of the flying device to obtain a changed flight path; Based on the changed flight path, the flight angle, flight speed and flight altitude that need to be adjusted are obtained.

5. The method according to claim 1, characterized in that The controlling the propulsion system of the flight device to output power based on the first power output strategy includes: Adjusting the flight posture of the flying device based on the first power output strategy; During the flight posture adjustment process, obtaining a second current posture of the flight device and second environment data of the flight device; Based on the second current position and the second environmental data, power output data of the propulsion system is adjusted.

6. The method according to claim 5, characterized in that The method further comprises: Based on the second environmental data, a heat dissipation strategy is generated to ensure that the temperature of the propulsion system is within a preset range.

7. The method according to claim 5, characterized in that The method further comprises: generating a communication adjustment strategy based on the second environment data; Based on the communication adjustment strategy, the communication mode of the communication system of the flight device is adjusted, wherein the flight device can use the adjusted communication mode to notify a target of the location information of the flight device.

8. The method according to claim 7, characterized in that The step of adjusting the communication mode of the communication system of the flight device based on the communication adjustment strategy includes at least one of the following steps: Detecting an unoccupied spectrum segment in the communication system, and utilizing the unoccupied spectrum segment for communication transmission; Adjust the direction of the adaptive antenna array to optimize the communication quality of the communication system; Use multi-beam LED array for communication; Based on the channel conditions of the flying device, the physical parameters of the communication system are adjusted, wherein the physical parameters include at least one of a power level, a modulation scheme, and a coding rate.

9. An electronic device, characterized in that: It comprises a memory and a processor coupled to each other, wherein the processor is used to execute program instructions stored in the memory to implement the flight equipment exosphere locking method as described in any one of claims 1 to 8.

10. A computer-readable storage medium having program instructions stored thereon, characterized in that: When the program instructions are executed by a processor, the flight equipment exosphere locking method described in any one of claims 1 to 8 is implemented.

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