Flight device escape layer locking method, electronic device and storage medium

Abstract

The application discloses a flight equipment escape layer locking method, an electronic device and a storage medium. The method comprises the following steps: in response to the flight equipment deviating from a predetermined orbit of the atmospheric escape layer, an adjustment signal is generated; based on the adjustment signal and first environment data of the flight equipment, a first power output strategy of the flight equipment is generated; and based on the first power output strategy, the propulsion system of the flight equipment is controlled to perform power output until the flight equipment is in a locking state of the atmospheric escape layer. The above scheme can improve the stability of the flight equipment in the atmospheric escape layer.

Description

TECHNICAL FIELD

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

[0002] At present, the exosphere locking of flight equipment is a high-difficulty technical challenge, which needs to comprehensively use multiple technical means to realize. In the prior art, the flight equipment in the exosphere needs to face various difficulties, such as harsh environment, cosmic rays, etc., so that the flight equipment cannot be stably in the exosphere, which will affect the control of the flight equipment. SUMMARY

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

[0004] The first aspect of the present application provides a flight equipment exosphere locking method, comprising: generating an adjustment signal in response to the flight equipment deviating from a predetermined orbit of the exosphere; generating a first power output strategy of the flight equipment based on the adjustment signal and first environment data of the flight equipment; and controlling the propulsion system of the flight equipment to perform power output based on the first power output strategy until the flight equipment is in a locked state of the exosphere.

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

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

[0007] Among them, the adjustment signal and the first environment data are analyzed to determine the flight angle, flight speed and flight height of the flight equipment that need to be adjusted, comprising: predicting the first environment data to obtain a prediction result; re-planning the flight path of the flight equipment to obtain a changed flight path in response to the prediction result meeting a path adjustment condition and receiving the adjustment signal; and obtaining the flight angle, flight speed and flight height that need to be adjusted based on the changed flight path.

[0008] The method further comprises: generating a heat dissipation strategy based on the second environment data, so that the temperature of the propulsion system is within a preset range.

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

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

[0011] The method further comprises: generating a communication adjustment strategy based on the second environment data; and adjusting a communication mode of a communication system of the flight device based on the communication adjustment strategy, wherein the flight device can use the adjusted communication mode to notify a target of the position information of the flight device.

[0012] The second aspect of the application provides an electronic device, comprising a memory and a processor coupled to each other, the processor being configured to execute program instructions stored in the memory to implement the flight device escape layer locking method in the first aspect.

[0013] The third aspect of the application provides a computer readable storage medium having program instructions stored thereon, the program instructions being executed by a processor to implement the flight device escape layer locking method in the first aspect.

[0014] The above scheme, when detecting that the flight device deviates from the predetermined orbit of the atmospheric escape layer, generates an adjustment signal, and generates a first power output strategy of the flight device according to the adjustment signal and first environment data in which the flight device is located, and controls the propulsion system of the flight device to perform corresponding power output according to the first power output strategy, so that the flight device is in a locked state of the atmospheric escape layer, thereby improving the stability of the flight device in the atmospheric escape layer.

[0015] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, but not limiting the application. BRIEF DESCRIPTION OF DRAWINGS

[0016] The drawings herein are incorporated into and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification serve to explain the technical solutions of the present application.

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

[0018] Figure 2 is a schematic diagram of a flow of an embodiment of the outboard layer locking method of the flight equipment of the present application;

[0019] Figure 3 is a schematic diagram of a flow of an embodiment of the communication adjustment method of the flight equipment of the present application;

[0020] Figure 4 is a schematic diagram of a flow of another embodiment of the outboard layer locking method of the flight equipment of the present application;

[0021] Figure 5 is a schematic diagram of a frame of an embodiment of the electronic equipment of the present application;

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

[0023] The technical solutions of the embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0024] In the following description, specific details are set forth in order to provide a thorough understanding of the present application, but the present application can be practiced without these details. In other instances, well-known methods, structures and techniques have not been described in detail in order to avoid obscuring the present application.

[0025] The term "and / or" herein is merely a description of the association relationship of the associated objects, and represents that there can be three relationships, for example, A and / or B can represent the three cases of A alone, A and B together, and B alone. In addition, the character " / " herein generally represents that the front and rear associated objects are in an "or" relationship. In addition, "multiple" herein represents two or more than two. In addition, the term "at least one" herein represents any one of multiple or any combination of at least two of multiple, for example, including at least one of A, B and C can represent 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 the high-altitude region about 500 kilometers to 1000 kilometers from the Earth's surface, with a relatively thin gas composition and a strong radiation environment. Due to its special physical and chemical properties, the exosphere has a variety of unique application values, one of which is as an important application scenario in the field of aerospace. The locked state of the flight device in the exosphere refers to the control of the flight device in the exosphere to run, and use 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 the flight device; at the same time, due to the fewer gas molecules in the exosphere, the heat loss of the machine body is reduced, making the temperature control of the machine body easier. The application range of the flight device in the exosphere is very wide, including scientific exploration, communication and positioning, monitoring and observation, etc. For example, the International Space Station and Earth observation satellites of NASA (National Aeronautics and Space Administration, USA) adopt the exospheric operation mode; in addition, some new wireless communication technologies and global positioning systems are also exploring and applying in the exosphere. Among them, the flight device can be a drone, a hydrofoil, a helium balloon, a helium float ball, a satellite, an aircraft, etc., without specific limitation here.

[0027] Please refer to Figure 1 , Figure 1 is a frame diagram of an embodiment of the flight device 100 of the present application. The flight device 100 mainly includes a flight main body 110, a communication system 120, a navigation system 130, a propulsion system 140 and a heat dissipation system 150. In addition, the flight device 100 can also include an energy storage system (not shown), which converts solar energy into electrical energy to provide sufficient energy for the flight device 100, thereby realizing the stable operation of the flight device 100 in the exosphere. It can be understood that the flight device 100 can also increase or delete systems according to the actual tasks to be performed, without specific limitation here.

[0028] In some embodiments, in order to ensure that the flight device 100 can fly in the exosphere for a long time, it should be considered at the beginning of the design which type of device to use as the flight main body 110 of the flight device 100. For example, a gas light aircraft such as a balloon and an airship can be used as the flight main body 110, and for the gas light aircraft such as a balloon and an airship, the flight height is generally selected to be about 20-30 kilometers from the ground; a satellite can be used as the flight main body 110, and for the satellite, a higher orbital height is needed, generally above 1000 kilometers from the ground; a drone can be used as the flight main body 110, and the flight height of the drone can be designed according to the actual task.

[0029] In the exosphere, the atmospheric density is low, and the wind resistance is small, so the airship, satellite and other flying objects can usually achieve a high flight speed, but the cost is high, while the balloon will be affected by atmospheric flow and wind speed and other factors, and the speed is relatively low. Therefore, in this embodiment, the unmanned aerial vehicle is selected as the flight main body 110, which can choose a higher flight speed in the exosphere. The unmanned aerial vehicle needs to have high stability in the exosphere to ensure long-term flight in harsh environments. This requires consideration of the design, structure and control of the unmanned aerial vehicle. In the design, the center of gravity, aerodynamic characteristics and other factors need to be considered; in terms of structure, lightweight and high-strength materials need to be selected; in terms of control, a high-precision and high-reliability control system needs to be selected.

[0030] In some embodiments, since the flight device 100 is flying in the exosphere, in order to avoid the flight device 100 from leaving the predetermined orbit uncontrollably in the exosphere, the design of the communication system 120 is crucial. Before designing the communication system 120, it is necessary to determine which communication system to use, so that 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 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 radio communication systems and laser communication systems can provide some help, they are greatly affected by weather and environment, and cannot guarantee the communication quality when used in the exosphere. Therefore, in this embodiment, an LED communication system is used to ensure high communication stability and data transmission speed.

[0031] Before installing the related equipment of the LED communication system to the flight device 100, the power, wavelength, light-emitting angle and other parameters of the LED communication system related equipment need to be determined. According to the task requirements and technical conditions, appropriate LED devices and driving circuits and other elements are selected, and system design and assembly are carried out. At the same time, the cooling measures of the equipment also need to be considered 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 the 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 limited by factors such as signal-to-noise ratio and interference. While the transmission rate of the LED communication system can be calculated by the Shannon formula, which is as follows:

[0034]

[0035] Where C is the transmission rate in bits per second (bps), B is the channel bandwidth in hertz (Hz), and 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 typically in the visible light range, approximately 400-700 nanometers. In the atmospheric exosphere, the wavelength is subject to some limitations, such as limitations due to atmospheric absorption and scattering. Therefore, it is necessary to select a wavelength range that can be transmitted in the atmospheric 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] Where 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 atmospheric exosphere, the signal will be subject to some attenuation, so it is necessary to use sufficient transmission power to ensure that the signal can be received. The calculation of the power of the LED communication system can be referred to the following formula:

[0040] P = I × V

[0041] Where 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 method of data, as well as the transmission method and format, etc. In the atmospheric exosphere, it is necessary to select a protocol that can adapt to the channel environment and has sufficient error correction ability. 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 improve the transmission rate.

[0043] 5. Emission angle: The emission angle can be controlled by the structure and manufacturing process of the LED device. When selecting the LED device, it is necessary to consider the emission angle and beam shape of the device to ensure that the task requirements can be met.

[0044] Based on the above parameters, the general steps to design 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 the appropriate communication protocol, and perform simulation and optimization to improve communication efficiency and error correction capability. After determining the system parameters, perform experimental verification and performance testing to evaluate the reliability and actual transmission rate of the system. Optimize the system parameters to further improve system performance. It should be noted that LED communication in the atmospheric exosphere needs to consider some special environmental factors, such as radiation interference, high-energy particles, etc. These factors may affect system performance and need special treatment.

[0045] To protect LED communication equipment from the harmful effects 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, preventing damage to sensitive electronic components. The shielding ensures the robustness and integrity of the LED communication system in the harsh radiation environment of the atmospheric exosphere.

[0046] In addition, to expand the communication coverage of the LED communication system and improve system capacity, multi-beam LED arrays can be used in the LED communication system. These arrays can generate multiple simultaneous beams, enabling flight equipment 100 to communicate with multiple ground stations or other flight equipment 100 simultaneously. This multi-beam array architecture enhances the flexibility and redundancy of the LED communication system, allowing seamless switching between communication links and enabling efficient data propagation in a network of flight equipment 100 in the atmospheric exosphere.

[0047] In some embodiments, when installing communication system 120 equipment, the robustness and reliability of the equipment also need to be considered. By selecting high-strength, lightweight materials and designing appropriate mechanical structures, the equipment can be ensured to withstand high-speed flight and harsh environmental conditions. At the same time, sufficient testing and verification are also needed to ensure the reliability and performance of the equipment. For example, when communication system 120 is an LED communication system, the installation of LED communication system equipment needs to fully consider the power, wavelength, light-emitting angle, etc. 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, the robustness and reliability of the equipment need to be ensured to meet mission requirements.

[0048] To further improve the reliability of the equipment, self-repairing materials are used in the design of communication system 120 equipment, which can automatically repair after exospheric radiation damage, improving equipment life.

[0049] In addition, to enable the flight device 100 to efficiently transmit data after it locks onto the exosphere, cognitive radio technology can be incorporated into the communication system 120 before the flight device 100 is officially commissioned to effectively utilize the limited frequency spectrum resources in the exosphere. The cognitive radio technology can dynamically detect and utilize unoccupied frequency spectrum segments, enabling the flight device 100 to have the opportunity to share the frequency spectrum with other objects or avoid interference with existing transmissions. This adaptive approach can maximize the utilization of the frequency spectrum and ensure efficient data transmission in the crowded environment of the exosphere.

[0050] In some embodiments, to optimize communication performance and mitigate the effects of ionospheric refraction in the exosphere, an adaptive control mechanism can be added to the communication system 120. This mechanism can 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 can minimize signal distortion and ensure reliable communication links with ground stations or other flight devices 100.

[0051] In addition, to protect the communication system 120 equipment from the dangers of exospheric electromagnetic radiation, a radiation shielding layer design is also added to the communication system 120.

[0052] In other embodiments, to cope with the unpredictable and dynamic nature of the 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 approach can effectively mitigate the effects of ionospheric interference, atmospheric turbulence, and signal fading, ensuring consistent and high-quality data transmission for the communication system 120.

[0053] In other embodiments, an artificial intelligence (AI) based real-time environment perception system can also be introduced into the communication system 120. This system uses machine learning algorithms to continuously monitor and predict changes in the exosphere environment, including temperature, radiation intensity, particle flow, and other factors. By analyzing these changes in real time using the AI system, the AI system can actively optimize communication strategies, not only dynamically adjusting physical parameters such as power and modulation scheme, but also automatically switching communication modes or selecting the best channel when the environment changes dramatically, to maximize the stability and efficiency of communication. By deeply integrating AI algorithms into the communication system 120, the communication system 120 has the ability to learn and adapt, no longer relying solely on traditional physical parameter adjustments, thus realizing a more intelligent communication system 120 suitable for the exosphere.

[0054] In some embodiments, to achieve precise control of the flight device 100 and to keep the flight device 100 in a stable position in the exoatmosphere, the navigation system 130 can use high-precision attitude navigation systems, such as inertial navigation systems, star trackers, and GPS receivers, etc. Specifically, a quantum navigation system can be used, which integrates multiple sensors to provide accurate information about the attitude, position, and velocity of the flight device 100 relative to the Earth, etc. The navigation system 130 can also incorporate advanced control algorithms that can effectively compensate for disturbances and keep the attitude and trajectory of the flight device 100 within strict tolerances.

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

[0056]

[0057] where θ i is the incident angle, i.e., the flight angle of the flight device 100; n1 is the refractive index of air, which is about 1; 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 flight device 100, the flight device 100 can maintain a stable refraction angle in the ionosphere height range, thereby achieving the purpose of locking the exoatmosphere. In this way, the special properties of the ionosphere can be used for long-distance communication, navigation, and atmospheric layer detection applications.

[0058] In some embodiments, to achieve the required maneuverability and efficiency of the flight device 100 in the exoatmosphere, a hybrid propulsion system can be integrated into the propulsion system 140. The hybrid propulsion system can combine electric propulsion with traditional chemical propulsion, thereby taking advantage of both. Electric propulsion has the characteristics of high efficiency and low noise, while chemical propulsion can provide high thrust for rapid maneuvering and initial ascent. The hybrid propulsion system can dynamically switch between propulsion modes according to task requirements, maximizing the performance of the propulsion system 140 and minimizing fuel consumption.

[0059] And to ensure stable and autonomous operation of the flight device 100 in the exoatmosphere, an advanced autonomous control system can also be added to the flight device 100. The autonomous control system should incorporate an adaptive flight path planning algorithm that can take into account the dynamic and unpredictable environment of the exoatmosphere. The algorithm can adjust the trajectory of the flight device 100 in real time to avoid obstacles, maintain a stable position relative to the Earth, and optimize energy consumption.

[0060] In some embodiments, to address 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 can be designed in the flight device 100. Specifically, an active thermal management system can be integrated into the flight device 100, which can employ various 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 maintain the operating temperature within a safe range. This active method ensures the long-term reliability and performance of the flight device 100 in the atmospheric exosphere.

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

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

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

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

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

[0066] The quantum navigation system is incorporated into the design of the flight device 100, which utilizes the characteristics of quantum entanglement to achieve higher precision navigation and attitude control. Compared with traditional navigation technology, quantum navigation provides more accurate positioning and trajectory control capabilities, especially suitable for complex and unpredictable environments such as the exosphere.

[0067] The communication system 120 device uses self-repairing materials that can automatically repair after radiation damage in the exosphere, improving the device's lifespan and reliability. This technological innovation significantly enhances the device's durability in extreme environments and reduces maintenance requirements.

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

[0069] Please refer to Figure 2 , Figure 2 is a flowchart of an embodiment of the flight device exosphere locking method of the present application. Specifically, it can include the following steps:

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

[0071] In some embodiments, the first current pose of the flight device 100 can be obtained by real-time detection or timing detection, and in response to the first current pose being within a preset range of the boundary of the exosphere, an adjustment signal is generated. The preset range can be 1 km, 2 km, 5 km, etc. away from the boundary of the exosphere.

[0072] Specifically, the first current pose of the flight device 100 can be detected in real time by the navigation system 130 in the flight device 100, and when it is detected that the first current pose of the flight device 100 is within a range of 5 km from the boundary of the exosphere, the navigation system 130 will issue an alarm signal and generate an adjustment signal.

[0073] Step S220: Based on the adjustment signal and the first environmental data of the flight device, a first power output strategy of the flight device is generated.

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

[0075] In some embodiments, when the flight device 100 is about to leave the exoatmosphere layer, a set of adjustment strategies should be generated as soon as possible to make the flight device 100 return to the predetermined orbit or the locked state of the exoatmosphere layer. During the adjustment of the flight device 100, to avoid the adjustment being too fast or too violent, causing the devices in the flight device 100 to be damaged due to the change of the surrounding environment, the adjustment of the flight device 100 should be as smooth as possible. Therefore, the first environmental data of the environment where the flight device 100 is currently located needs to be obtained. The adjustment signal and the first environmental data are analyzed to determine the flight angle, flight speed and flight height of the flight device 100 that needs to be adjusted; and based on the flight angle, flight speed and flight height, the first power output strategy is obtained.

[0076] For example, the sensor system (not shown in the figure) equipped in the flight device 100 can be used to monitor the environmental conditions of the exoatmosphere layer where the flight device 100 is located in real time 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 the environmental changes of the exoatmosphere layer to obtain the first environmental data.

[0078] After obtaining the first environmental data of the environment where 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 meeting the path adjustment condition and receiving the adjustment signal, the navigation system 130 re-plans the flight path of the flight device 100 to obtain a changed flight path. According to the changed flight path, the flight angle, flight speed and flight height that need to be adjusted are obtained. The navigation system 130 sends the flight angle, flight speed and flight height that need to be adjusted to the propulsion system 140, and the propulsion system 140 generates the first power output strategy according to the flight angle, flight speed and flight height that need to be adjusted, to ensure that the flight device 100 can quickly and smoothly re-enter the exoatmosphere layer.

[0079] The path adjustment condition is that the environment is relatively harsh, for example, when the cosmic radiation frequency is lower than 300 MHZ, it can be considered that the exoatmosphere layer condition is harsh. In addition, temperature or particle number can also be used as a basis for judging that the environment is harsh, which is not limited here.

[0080] Step S230: based on the first power output strategy, the propulsion system of the flight device is controlled to perform power output until the flight device is in the locked state of the exoatmosphere layer.

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

[0082] In addition, the propulsion system 140 will generate very high temperature during the flight pose adjustment of the flight device 100. If the excess heat is not removed in time, it will affect the power output efficiency of the propulsion system 140 and also damage the related equipment of the propulsion system 140. Therefore, when the propulsion system 140 is performing power output, the communication system 120 will also send the second environment data obtained by it 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 flight pose adjustment of the flight device 100, the change of the position and environment in which the flight device 100 is located will seriously affect the communication quality. Therefore, during the flight pose adjustment of the flight device 100, the communication quality of the communication system 120 also needs to be optimized. Please refer to Figure 3 , Figure 3 is a flowchart of an embodiment of the flight device communication adjustment method of the present application. Specifically, it can include the following steps:

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

[0085] In some embodiments, the sensor system in the flight device 100 can be used to monitor the environmental conditions of the atmosphere escape layer in which the flight device 100 is located in real time to obtain the second environment data. The communication system 120 analyzes and predicts the second environment data to generate the communication adjustment strategy.

[0086] Step S320: adjusting the communication mode of the communication system of the flight device based on the communication adjustment strategy, wherein the flight device can use the adjusted communication mode to notify the target of the position information of the flight device.

[0087] In some embodiments, to enable the flight device 100 to maintain good communication effect in the complex environment of the exoatmosphere, the communication system 120 needs to be adjusted in time. For example, after receiving the communication adjustment strategy, the cognitive radio technology in the communication system 120 can be used to detect the unoccupied frequency spectrum segment in the communication system 120, and the unoccupied frequency spectrum segment 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 can be adjusted to optimize the communication quality of the communication system.

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

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

[0091] Please refer to Figure 4 , Figure 4 is a flowchart of another embodiment of the exoatmosphere locking method of the flight device. Specifically, it can include the following steps:

[0092] Step S410: detecting the pose of the flight device to obtain the current pose.

[0093] In some embodiments, the navigation system 130 in the flight device 100 is used to monitor the pose of the flight device in the exoatmosphere in real time to obtain the current pose.

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

[0095] In some embodiments, after the navigation system 130 obtains the current pose of the flight device 100, the current pose is compared with the predetermined flight path stored in the navigation system 130 to obtain a comparison result. If the comparison result is that the current pose of the flight device 100 is within the allowable deviation range of the predetermined flight path, it indicates that the flight device 100 is in the locking state of the exoatmosphere; if the comparison result is that the current pose of the flight device 100 has exceeded the allowable deviation range of 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 losing control.

[0096] Step S430: generating an adjustment signal in response to the comparison result that the flight device deviates.

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

[0098] Step S440: obtaining first environment data of the environment where the flight device is located.

[0099] In some embodiments, the real-time environment sensing system in the communication system 120 in the flight device 100 can be utilized to dynamically monitor the environment change of the exoatmospheric layer where the flight device is located, so as to obtain the first environment data.

[0100] In one implementation scenario, the above-mentioned steps S430 and S440 can be executed in a sequential order, for example, the step S430 is executed first and then the step S440 is executed, or the step S440 is executed first and then the step S430 is executed. In another implementation scenario, the above-mentioned steps S430 and S440 can also be executed simultaneously, which can be set according to actual application and is not limited herein.

[0101] Step S450: generating a first power output strategy of the flight device based on the adjustment signal and the first environment data.

[0102] This step is the same as the above-mentioned step S220, which will not be repeated here.

[0103] Step S460: controlling the propulsion system of the flight device to perform power output based on the first power output strategy, and adjusting the communication mode of the communication system of the flight device.

[0104] This step is the same as the above-mentioned step S230, which will not be repeated here.

[0105] When the flight device deviates from the predetermined orbit of the exoatmospheric layer is detected, the application generates an adjustment signal, and generates a first power output strategy of the flight device according to the adjustment signal and the first environment data where the flight device is located. 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 of the exoatmospheric layer, thereby improving the stability of the flight device in the exoatmospheric layer.

[0106] Those skilled in the art can understand that in the above-mentioned method of the specific implementation, the writing order of each step does not mean a strict execution order and does not constitute any limitation on the implementation process. The specific execution order of each step should be determined by its function and possible internal logic.

[0107] Please refer to Figure 5 , Figure 5is a schematic diagram of a framework of an embodiment of the electronic device 50 of the present application. The electronic device 50 comprises a memory 51 and a processor 52 coupled with each other. The processor 52 is configured to execute program instructions stored in the memory 51 to implement the steps of any of the above-described embodiments of the method for locking the out-of-control layer of the flight device, or implement the steps of any of the above-described embodiments of the method for adjusting the communication of the flight device. In a specific implementation scenario, the electronic device 50 can include, but is not limited to, a microcomputer, a server, and in addition, the electronic device 50 can also include a notebook computer, a tablet computer, and the like, without being limited thereto.

[0108] Specifically, the processor 52 is configured to control itself and the memory 51 to implement the steps of any of the above-described embodiments of the method for locking the out-of-control layer of the flight device, or implement the steps of any of the above-described embodiments of the method for adjusting the communication of the flight device. The processor 52 can also be referred to as a CPU (Central Processing Unit). The processor 52 can be an integrated circuit chip with a processing capability of signals. The processor 52 can also be a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field-Programmable Gate Array), 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 or the like. In addition, the processor 52 can be implemented by an integrated circuit chip together.

[0109] Please refer to Figure 6 , Figure 6 is a schematic diagram of a framework of an embodiment of the computer-readable storage medium 60 of the present application. The computer-readable storage medium 60 stores program instructions 601 capable of being executed by a processor, and the program instructions 601 are configured to implement the steps of any of the above-described embodiments of the method for locking the out-of-control layer of the flight device, or implement the steps of any of the above-described embodiments of the method for adjusting the communication of the flight device.

[0110] In some embodiments, the apparatus provided by the embodiments of the present application has functions or includes modules that can be used to execute the methods described in the above method embodiments, and the specific implementation can refer to the description of the above method embodiments. For the sake of brevity, the details are not described here.

[0111] The above description of each embodiment tends to emphasize the differences between each embodiment, and the same or similar parts can be mutually referred to. For the sake of brevity, the details are not described here.

[0112] In several embodiments provided in the present application, it should be understood that the disclosed methods and apparatuses can be implemented in other manners. For example, the division of the apparatus embodiments described above is merely a logical function division, and there can be another division manner in actual implementation. For example, a plurality of units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed mutual couplings or direct couplings or communication connections can be indirect couplings or communication connections through some interfaces, devices or units, and can be in electrical, mechanical or other forms.

[0113] In addition, each function unit in the various embodiments of the present application can be integrated into one processing unit, or each unit can exist physically independently, or two or more units can be integrated into one unit. The integrated unit can be implemented in the form of hardware or in the form of a software function unit.

[0114] If the integrated unit is implemented in the form of a software function unit and sold or used as an independent product, it can be stored in a computer readable storage medium. Based on such an understanding, the technical solutions of the present application, essentially or in part, or all or part of the technical solutions can be embodied in the form of a software product. The computer software product is stored in a storage medium, and includes several instructions for causing a computer device (such as a personal computer, a server, or a network device) or a processor (or a plurality of processors) to perform all or part of the steps of the methods in the various embodiments of the present application. The foregoing storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and the like.

Claims

1. A method for locking the exosphere of a flight device, characterized in that, include: In response to the flight equipment deviating from its predetermined trajectory in the exosphere, an adjustment signal is generated; Based on the adjustment signal and the first environmental data of the flight equipment, a first power output strategy for the flight equipment is generated. This generation of the first power output strategy includes: analyzing the adjustment signal and the first environmental data to determine the flight angle, flight speed, and flight altitude that the flight equipment needs to adjust; and obtaining the first power output strategy based on the flight angle, flight speed, and flight altitude. Based on the first power output strategy, the propulsion system of the flight equipment is controlled to output power until the flight equipment is locked in the exosphere. The step of controlling the propulsion system of the flight equipment to output power based on the first power output strategy includes: adjusting the flight attitude of the flight equipment based on the first power output strategy; during the flight attitude adjustment process, acquiring a second current attitude of the flight equipment and second environmental data of the flight equipment; and adjusting the power output data of the propulsion system based on the second current attitude and the second environmental data.

2. The method according to claim 1, characterized in that, The generation of an adjustment signal in response to the flight equipment deviating from its predetermined trajectory in the exosphere includes: Obtain the first current pose of the flight equipment; An adjustment signal is generated in response to the first current pose being within a preset range of the boundary of the atmospheric exosphere.

3. The method according to claim 1, characterized in that, The step of analyzing the adjustment signal and the first environmental data to determine the flight angle, flight speed, and flight altitude that the flight equipment needs to adjust includes: The first environmental data is used to make a prediction, and the prediction result is obtained. In response to the prediction result satisfying the path adjustment conditions and receiving the adjustment signal, the flight path of the flight equipment is replanned to obtain the changed flight path; Based on the changed flight path, the flight angle, flight speed, and flight altitude that need to be adjusted are obtained.

4. The method according to claim 1, characterized in that, The method further includes: Based on the second environmental data, a heat dissipation strategy is generated to keep the temperature of the propulsion system within a preset range.

5. The method according to claim 1, characterized in that, The method further includes: Based on the second environmental data, a communication adjustment strategy is generated; Based on the communication adjustment strategy, the communication mode of the flight equipment's communication system is adjusted, wherein the flight equipment can use the adjusted communication mode to notify the target of the flight equipment's location information.

6. The method according to claim 5, characterized in that, The step of adjusting the communication mode of the flight equipment's communication system based on the communication adjustment strategy includes at least one of the following steps: Detect unused spectrum segments in the communication system and use the unused spectrum segments for communication transmission; Adjusting the orientation of the adaptive antenna array to optimize the communication quality of the communication system; Communication is achieved using a multi-beam LED array; Based on the channel conditions of the flight equipment, the physical parameters of the communication system are adjusted, wherein the physical parameters include at least one of power level, modulation scheme, and coding rate.

7. An electronic device, characterized in that, It includes 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 according to any one of claims 1 to 6.

8. A computer-readable storage medium having program instructions stored thereon, characterized in that, When the program instructions are executed by the processor, they implement the flight equipment exosphere locking method according to any one of claims 1 to 6.

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