53 results about "Near space" patented technology

The invention relates to a near space non-uniform atmospheric refraction angle calculation method, which comprises the following steps: acquiring a deflection angle of light in the atmosphere, and obtaining a refraction angle model; determining atmospheric density change, obtaining a Boltzmann statistical model, and further obtaining a Boltzmann energy distribution model; determining molecular kinetic energy and potential energy, substituting the molecular kinetic energy and potential energy into a Boltzmann energy distribution model to obtain the atmospheric molecular number density away from the geocenter, and determining the change rule of the atmospheric molecular number density along with the altitude and the atmospheric temperature according to the atmospheric molecular number density away from the geocenter; acquiring a transmission path from the observation height to the top of the atmospheric layer, and acquiring the atmospheric temperature and atmospheric pressure at the observation height by combining the change rule of the atmospheric molecular number density along with the altitude and the atmospheric temperature; and inputting the atmospheric temperature and the atmospheric pressure at the observation height into an Elden refractive index model to obtain a refractive index value under a corresponding radiation condition, and inputting the refractive index value into a refraction angle model to obtain a refraction angle.

The invention discloses a near space detection method, device and equipment based on cooperation of multiple unmanned aerial vehicles, and a storage medium, and the method comprises the steps: carrying out the region division of a near space according to a meteorological detection task, generating a plurality of detection regions, and determining the number of unmanned aerial vehicles needed by each detection region; distributing each unmanned aerial vehicle in the unmanned aerial vehicle network to a corresponding detection area according to the performance parameters of the unmanned aerial vehicles and the number of the unmanned aerial vehicles; the unmanned aerial vehicles carry out cooperative detection in the corresponding detection areas to obtain meteorological detection data; carrying out fusion processing on the meteorological detection data to generate meteorological data of a near space; predicting through a weather prediction model according to the weather data to obtain a weather change trend; according to the invention, meteorological early warning is carried out according to the meteorological change trend, efficient and accurate detection of near space meteorological data is realized through cooperative operation of the unmanned aerial vehicle, meteorological prediction is accurately carried out through the meteorological prediction model, meteorological early warning is timely carried out, and risks caused by meteorological disasters are effectively reduced.

The invention relates to an ionosphere TEC prediction method in a near space, and belongs to the technical field of ionospheres. The method comprises the following steps: acquiring ionosphere environment data at three consecutive moments; wherein the ionosphere environment data comprises ionosphere TEC data and earth magnetic field data; inputting the ionosphere environment data at the three moments into the trained ionosphere TEC prediction model to obtain ionosphere TEC data at the next moment; wherein the ionosphere TEC prediction model comprises an encoder, a condition generator and a decoder; the encoder is used for encoding the ionized layer TEC data at the current moment to obtain potential representation of the ionized layer TEC data; the condition generator is used for performing inversion coding on the ionosphere environment data at the three moments to obtain ionosphere electron density information; and the decoder is used for reconstructing the ionospheric TEC data at the next moment from the potential representation of the ionospheric TEC data at the current moment by using the ionospheric electron density information. The state of the ionosphere is predicted through inversion of the electron density information of the ionosphere.

The invention relates to a near space multi-target large-scale constellation collaborative observation method. All-weather tracking and detection are carried out on multiple targets flying at hypersonic velocity in near space based on a space-based observation system on-orbit satellite; comprising the following steps: S1, in the whole process of a near space multi-target large-scale constellation collaborative observation task, distributing and scheduling the near space multi-target large-scale constellation observation task by using a staged multi-source triggering collaborative observation task planning method; and S2, in a near space multi-target low-uncertainty stage, resource scheduling is carried out through a learning-based low-uncertainty multi-target collaborative observation task planning method. The method has the advantages that large-scale observation constellation resources are effectively distributed, the multi-target capacity is high, the target loss rate is low, and the resource utilization efficiency is high.

The invention discloses an unmanned aerial vehicle track correction method and device based on near space environment parameters, equipment and a storage medium. The method comprises the steps of generating a plurality of detection tasks based on a natural disaster monitoring task; dividing the near space into a plurality of detection areas according to the detection tasks, and allocating corresponding detection tasks and detection areas to the unmanned aerial vehicle; planning a flight path in the detection area based on the detection task; simulation is carried out according to the environment parameters and the flight trajectory of the detection area, and trajectory correction values under different environment conditions are obtained; and under the condition that the flight path needs to be corrected, performing flight path correction in the flight process of the unmanned aerial vehicle based on the path correction value, and executing a detection task to obtain detection data. According to the method, the flight path is corrected through the path correction value, the correction effect of the flight path is effectively improved, the detection task is executed, the execution efficiency of the detection task and the accuracy of the detection data are remarkably improved, and natural disaster early warning can be accurately carried out.

The invention relates to a near space low earth orbit satellite and satellite constellation luminosity spectral measurement method, which comprises the following steps: acquiring a low earth orbit satellite and satellite constellation model, and carrying out two-dimensional surface element grid division on the low earth orbit satellite and satellite constellation model; reconstructing a low earth orbit satellite and a satellite constellation model by using the divided surface element data, establishing different satellite and satellite constellation model scenes, and obtaining vector data of the satellite and the satellite constellation changing along with the solar altitude angle and the solar azimuth angle; and calculating the luminosity spectrums of satellites and satellite constellations in different observation scenes according to the vector data in combination with a bidirectional reflection distribution function model and an atmospheric radiation transmission model. The invention aims to improve the precision and stability of observation data, and compared with a space-based observation platform, the deployment and recovery cost of the near space observation platform is lower, and the observation position and angle are easier to adjust. The limitation of foundation observation and space-based observation is overcome, the observation precision and flexibility are improved, and an important means of diversified research is supported.

The invention relates to a method for detecting a near space wind field, temperature and density based on iron atom resonance fluorescence. The method comprises the following steps: emitting 372 nm laser to a near space, and receiving an iron atom resonance fluorescence echo signal generated by a UMLT region and a Rayleigh back scattering echo signal generated by a region below the UMLT; according to the iron atom resonance fluorescence echo signal, an atmospheric temperature response function and a wind speed response function are defined, and the atmospheric temperature and the wind speed of a UMLT area are calculated according to the atmospheric temperature response function and the wind speed response function; and according to the Rayleigh backscattering echo signal of the predetermined wavelength laser, using a normalization algorithm to invert the atmospheric molecular density of the area below the UMLT, and then according to the atmospheric molecular density, inverting the atmospheric temperature of the area below the UMLT. According to the invention, the atmospheric temperature and wind speed of the UMLT region and the atmospheric molecular density and atmospheric temperature of the region below the UMLT region can be detected, and the wind field, temperature and density profile information can be obtained all day long and all day long with high precision.

The invention relates to an energy storage battery pack heat dissipation structure on an unmanned aerial vehicle, and belongs to the field of aerospace vehicle heat management systems. Comprising an energy storage battery pack air duct, an incoming flow inlet and an incoming flow outlet, a plurality of holes are formed in each partition plate in the energy storage battery pack to form an energy storage battery pack air duct; a hole is formed in the machine head fairing and serves as an incoming flow inlet; a hole is formed in the fuselage cabin section and serves as an incoming flow outlet; incoming flow enters the machine body from the hole of the machine head fairing, flows through the energy storage battery pack air channel and then flows out from the hole of the machine body cabin section, and a complete air flow channel is formed. The high-heat-flux energy storage battery pack heat dissipation device can effectively dissipate heat of the high-heat-flux energy storage battery pack, and is suitable for aviation aircrafts at different flight heights. The system is especially suitable for a low-pressure high-flight-speed flight environment at a near space height.

The present application belongs to the technical field of hypersonic wind tunnel test, and discloses a test checking method of hypersonic frictional resistance standard value. The test checking method of hypersonic frictional resistance standard value is carried out in a hypersonic quiet wind tunnel, and the model is stably kept in a laminar flow state by means of a quiet flow field provided by the hypersonic quiet wind tunnel, so that the interference of flow field noise on the hypersonic frictional resistance is eliminated, real near space flight test data is obtained, and the obtained hypersonic frictional resistance standard value can be used for related test calculation or theoretical analysis, thereby providing technical support for the research on the frictional resistance of a spacecraft.

A method for reentry near-space aerodynamic large off-plane orbit reconstruction, which solves the problems of high energy consumption of current orbit control engines for orbit change and difficulty in large-range orbit change by aerodynamic assist, belongs to the field of aerospace technology. The present invention includes: designing the braking reentry section orbit of the aircraft from the initial orbit into the near space, designing the aerodynamic orbit change section orbit of the aircraft in the near space, designing the ascending orbit insertion section orbit of the aircraft from the near space into the target orbit, taking the designed quantities as integral performance indicators, setting the index function J, and seeking the state and control (x(t), u(t)) that make the selected index function J optimal, that is: #imgabs0# represents the state variable of the aircraft in the aerodynamic orbit change section, u(t) represents the control variable, t is the time, X represents the process index, φ[x(t f ),t f represents the performance index at time t f ; #imgabs1# t0 ≤ t ≤ t f , f[x(t), u(t), t] represents the motion dynamics equation of the aircraft; and setting the constraint conditions and boundary conditions, and performing optimization solution to obtain the optimal control variable u(t).

The invention belongs to the technical field of space atmospheric optical remote sensing, and particularly relates to a method for inverting an ozone concentration profile through airglow radiation of an oxygen atmospheric zone and a near-infrared atmospheric zone. According to the method, airglow radiation signals of the O2 atmospheric zone and the near-infrared atmospheric zone are combined, the ozone profile within the near space of 30 km to 130 km is obtained through calculation according to the photochemical reaction principle and the atmospheric radiation transmission model, and compared with a traditional O3 concentration profile inversion method, the method has better accuracy and a larger vertical coverage range.

The present invention discloses a heat dissipation control device for a propulsion system of a low-speed unmanned aerial vehicle in near space, which relates to the technical field of heat dissipation of unmanned aerial vehicles, comprising: an air inlet and an air outlet, which are correspondingly arranged at both ends of a propulsion support rod; a heat dissipation cover plate, which is movably arranged on the inner wall of the propulsion support rod, and the heat dissipation cover plate is connected to a self-locking structure. When the heat dissipation cover plate is pressed, the self-locking structure drives the heat dissipation cover plate to close the air outlet hole, and when the heat dissipation cover plate is pressed again, the self-locking structure drives the heat dissipation cover plate to open the air outlet hole; a light sensing control unit, which is arranged on the inner wall of the propulsion support rod, and the light sensing control unit cooperates with the heat dissipation cover plate, and the light sensing control unit touches the heat dissipation cover plate according to the brightness of the surrounding environment; the control device can alleviate the problem of energy shortage during the night flight of the unmanned aerial vehicle, and realizes the on-off of the heat dissipation path of the propulsion support rod by opening and closing the heat dissipation cover plate, so that the ambient temperature of the motor controller can be actively controlled to meet the heat dissipation requirements under different conditions.

The invention provides a supersonic velocity gas film distributed cooling method for a near space waverider aircraft, and the method comprises the steps: arranging a first cooling device on the upper surface of a waverider close to the head of the waverider, and enabling the first cooling device to be used for generating a tangential supersonic velocity gas film; a second cooling device is arranged at the front edge of a sweepback wing of the waverider, and the second cooling device is used for generating a normal supersonic velocity gas film; the flowing direction of the tangential supersonic air film is consistent with the incoming air flow, and the flowing direction of the normal supersonic air film is perpendicular to the incoming air flow. The surface of the wave rider is covered with cooling gas through the supersonic cooling gas film, the coverage area is large, the cooling effect is stable, and the wave rider is suitable for optical windows and has no requirement for aircraft structural materials. And meanwhile, similar cooling devices can be arranged at different positions of the wave rider for combined cooling, and distributed large-area cooling is achieved.

The application discloses a high-reliability multi-node cooperative in-situ communication system and method. The system comprises multiple transceivers, one of which is a master node and the rest are slave nodes. The master node comprises a channel collision management and control demodulation and signal modulation unit, a digital AGC compensation control unit, a special working condition signal-to-noise ratio switching unit and a process autonomous ending unit. The slave nodes each comprise a signal transmitting unit, a signal receiving unit and a control unit. The application realizes effective screening and control of multiple access nodes in deep space exploration activities such as lunar exploration, solves the problem of advanced planning caused by a large number of nodes in the lunar near space, and maximally supports flexible communication between lunar nodes.

This invention discloses a near-space target localization method based on dual-satellite imaging, comprising: simultaneously acquiring original observation images of the same target using two low-Earth orbit (LEO) satellites; acquiring the centroid coordinates of the target region in the two original observation images respectively, and performing coarse localization based on the centroid coordinates to obtain the coarse localization point coordinates of the near-space target; performing forward path correction to generate a simulated image of the target observed by the two LEO satellites under the current localization; performing residual correction on the estimated spatial position of the target to obtain the residual-corrected spatial position of the target; and repeating the above steps based on the residual-corrected spatial position in the current iteration until the iteration conditions are met to obtain the precise localization of the target. By constructing a closed-loop technical scheme of "dual-satellite synchronous imaging - coarse localization - non-uniform atmospheric and imaging system effect coupling correction - image centroid comparison - iterative optimization", the accurate inversion of the three-dimensional position of near-space targets can be achieved.

A pod performance test system for a near space aerostat includes: a HCI test control device, a motion simulation control device, a suspension device, and a motion simulation anti-twisting mechanism. The HCI test control device is electronically connected to the motion simulation control device, the motion simulation anti-twisting mechanism and a pod of the near space aerostat separately. The motion simulation control device is electronically connected to the motion simulation anti-twisting mechanism. The motion simulation anti-twisting mechanism is connected to the pod by a connector. The motion simulation control device controls the motion simulation anti-twisting mechanism to simulate various complex motion states according to a motion control parameter from the HCI test control device, and thus the pod is in the various complex motion states. When the pod is in the various complex motion states, performance test results of the pod under the various complex motion states can be obtained.

The invention provides an error compensation method for near space air pressure in-situ detection, and belongs to the technical field of near space environment detection, and the method comprises the steps: determining a change curve of the speed along with the height in the falling process of a sounding assembly; modeling an external flow field of the sounding assembly, and analyzing an external airflow field and a heat flow field of the sounding assembly; constructing an air pressure sensor arrangement point position temperature conversion model; constructing an error calculation model of the barometric sensor based on the position of the barometric sensor in the internal flow field, the analysis result and the heat flow field model; acquiring air pressure measurement data and environment measurement data of the near space; and according to the environmental parameter in-situ measurement data, compensating the near space in-situ air pressure measurement data by using the error calculation model to obtain a near space air pressure measurement error. The problem that the high-speed falling type sounding assembly cannot measure the ambient air pressure accurately is solved.

The invention provides a near space array plane, a radar and a temperature control method. The near space array plane comprises a frame, a rear cover plate, heat preservation cotton, a heat dissipation assembly, a heating assembly and a temperature control module, receiving and transmitting assemblies and antenna units are evenly distributed on the first end face of the frame and are sealed through an antenna cover, and the rear cover plate is installed on the second end face. The peripheral wall of the frame and the inner wall of the antenna housing are provided with heat preservation cotton. A plurality of independent spaces are arranged in the frame, the heat dissipation assembly comprises a uniform temperature plate and fans arranged in the independent spaces, and the heating assembly comprises a plurality of groups of heating devices and first temperature measuring devices which are arranged in the independent spaces in a one-to-one correspondence manner, and standby heating devices and second temperature measuring devices; the temperature control module is used for obtaining temperature measurement results of the first temperature measurement device and the second temperature measurement device and used for controlling the draught fan, the heating device and the standby heating device. The heat dissipation design, the heating design, the heat preservation design and the array surface structure are efficiently integrated, and the device can be reliably applied to the near space.

The invention belongs to the technical field of low-temperature heat exchange, and particularly relates to a circulating system for a near space environment and an aerostat, and the circulating system comprises an air inlet circulating module, a phase-change heat exchange module, a refrigerating and heating circulating module and a flow control module. The full contact between the phase change working medium and the phase change heat exchange module is realized through the air inlet circulation module. The liquefaction and vaporization process of a phase change working medium is achieved through the phase change heat exchange module, flow distribution of refrigerants in the first heat exchanger and the second heat exchanger is achieved through the flow control module, it is guaranteed that the refrigerants with the large flow flow flow through the first heat exchanger in the refrigeration mode, and it is guaranteed that the refrigerants with the large flow flow flow through the second heat exchanger in the heating mode. Rapid switching between a refrigeration mode and a heating mode is achieved through the working medium circulation module, so that the rapid liquefaction and vaporization process of the phase change working medium is achieved, finally buoyancy and height are regulated and controlled through large-volume change of the phase change working medium, and long-term stable flight of the stratospheric aerostat is achieved.

The present invention relates to an atmospheric density tomography scanning detection method, a computer device and a storage medium. The method comprises: constructing a forward model of the energy spectrum of the astronomical X-ray source in the process of the earth's atmospheric occultation based on the detector response matrix of the X-ray satellite calibration database, the X-ray cross section of the earth's atmospheric components calculated by using the XCOM database, the energy spectrum of the celestial X-ray source obtained by Xspec fitting, and the atmospheric density basis function provided by the NRLMSIS 2.0 model; constructing a likelihood function between the hypothesis and the actual measurement under Poisson statistics based on the X-ray satellite measured energy spectrum data with a sufficiently high signal-to-noise ratio and vertical resolution obtained by satellite platform processing; and fitting the observed energy spectrum and the model energy spectrum using a Markov chain Monte Carlo algorithm (MCMC) based on the Bayesian theorem and Bayesian estimation, thereby realizing the inversion of the atmospheric density in the near-space of the earth. The method can overcome the defects of the poor spatial coverage of the existing detection means and the difficulty in realizing global measurement.

The invention provides a near-space visible near-infrared solar spectrum irradiance measurement system, which relates to the technical field of optical measurement and comprises a near-space flying platform, a solar tracker, a first measurement unit, a second measurement unit and a data processing module. Wherein the sun tracker is used for tracking the direction of the sun; the near space flying platform is used for bearing the solar tracker; the first measuring unit is used for collecting absolute radiation data of sunlight; the second measuring unit is used for collecting relative spectral power distribution of sunlight in a target wave band range; and the data processing module is used for determining solar spectral irradiance based on the absolute radiation data and the relative spectral power distribution. According to the near space visible near infrared solar spectrum irradiance measurement system provided by the invention, the solar spectrum irradiance is calculated through the absolute radiation data and the relative spectrum power distribution, and the accuracy of solar spectrum irradiance measurement is improved.

The present invention relates to a method for calculating the refraction angle of a near-space non-uniform atmosphere. The method comprises the following steps: obtaining the deflection angle of light in the atmosphere to obtain a refraction angle model; determining atmospheric density changes to obtain a Boltzmann statistical model, and further obtaining a Boltzmann energy distribution model; determining molecular kinetic energy and potential energy, substituting the molecular kinetic energy and potential energy into the Boltzmann energy distribution model to obtain the number density of atmospheric molecules at a distance from the center of the earth; determining a variation law of the number density of atmospheric molecules with altitude and atmospheric temperature based on the number density of atmospheric molecules at the distance from the center of the earth; obtaining a transmission path from an observation altitude to the top of the atmosphere, and obtaining the atmospheric temperature and atmospheric pressure at the observation altitude in combination with the variation law of the number density of atmospheric molecules with altitude and atmospheric temperature; inputting the atmospheric temperature and atmospheric pressure at the observation altitude into an Elden refractive index model to obtain a refractive index value under corresponding radiation conditions, and inputting the refractive index value into a refraction angle model to obtain the refraction angle.

The invention discloses a near space large dynamic strong multipath communication access switching system, which comprises a communication master node and communication slave nodes, the communication main node comprises a physical layer processing module, a trigger detection module, a rapid scheduling processing module, a smooth optimization processing module and an exit monitoring module. The communication slave node comprises a physical layer processing module and a control management module. According to the method, in deep space exploration activities such as the lunar surface, a large dynamic strong multipath scene is quickly and accurately identified through a trigger detection algorithm, and blind switching to a strong multipath resistant lowest rate gear is realized by adopting quick scheduling processing on the premise of confirming that an effective signal still meets the capability of a receiver; the problem of large communication waste caused by switching failure-return-switching re-failure in a traditional communication system protocol switching mechanism is solved.

The invention relates to the technical field of atmospheric science and remote sensing, in particular to a space-based distributed near space atmosphere detection method, system, device and product, and the method comprises the steps: designing a plurality of satellites for detecting near space atmosphere based on the number of orbital planes and the number of satellites included in each orbital plane; detecting the near space atmosphere at a target moment based on each satellite, and obtaining state parameters of the near space atmosphere from different angles; obtaining a tomographic equation based on the global three-dimensional grid diagram and the obtained state parameters; and solving the tomographic equation to obtain the three-dimensional distribution characteristics of the near space atmosphere at the target moment. A plurality of satellites are designed through an orbital plane, various observation modes can be effectively compatible, and multi-dimensional data of near space atmosphere can be obtained; the state parameters are processed by using the global three-dimensional grid diagram so as to extract key three-dimensional parameter information, and the state and the change process of the near space atmosphere can be accurately monitored and predicted.

The invention discloses a low-noise spatial heterodyne hyper-spectral detection simulation and evaluation method. The method comprises the following steps: simulating a satellite platform to obtain a satellite platform model; simulating a camera to obtain a camera model; setting a camera model on the satellite platform model; incident light passes through the camera model and then an interference image is output; performing spectrum restoration processing on the interference image to obtain a restored spectrum signal, and obtaining a signal-to-noise ratio of the image according to the restored spectrum signal, electronic system noise in the camera model and the number N of pixels merged by different limb heights in the satellite platform model; and obtaining a root-mean-square error RMSE and an average spectral similarity MSS according to the incident light and the recovered spectral signal. According to the method, the problem of near space detection data set missing can be solved, a high-reliability simulation data set is formed, technical support is provided for comprehensive system analysis and optimization of a near space atmospheric parameter hyper-spectrum detection scheme, and quantitative guarantee is provided for comprehensive verification and improvement of application capability.

The invention discloses a time sequence control load for small near space microorganism exposure, and relates to the technical field of load control equipment, the time sequence control load comprises a time sequence control load hardware end, and the time sequence control load hardware end comprises a microorganism exposure cabin. The fixed side plate and the microorganism exposure cabin body are positioned and mounted through a plurality of second positioning bolts, so that the time sequence controller and the vacuum tank are positioned and mounted, and the operation stability of the time sequence control loading mechanism is improved; the sequential control load software end is arranged, exposure conditions of microorganisms in an extreme environment can be accurately controlled through the sequential control load for exposure of the microorganisms in the small near space, the reliability of experimental results is ensured, meanwhile, the overall high integration level and miniaturization design are achieved, and the application range is wide. The device is suitable for being carried on platforms such as small spacecrafts and balloons, and has high practical application value.

The invention provides a space-based adaptive filtering method for a near space flying target, and the method comprises the steps: carrying out the state detection and tracking of a near space target through a satellite networking system composed of a plurality of space-based satellites, carrying out the filtering of measurement data through Kalman filtering, and obtaining the estimation of the state of the target; in the Kalman filtering process, the maneuvering frequency of a process noise covariance matrix in the one-step prediction link is corrected according to maneuvering frequency estimation; determining a first error factor of the satellite networking system for target positioning according to the networking geometric configuration of the satellite networking system, and determining a second error factor of a satellite networking system measurement model according to the information; and determining a correction factor according to the first error factor and the second error factor, and correcting the measurement noise covariance matrix in the Kalman filtering time updating link. According to the invention, the tracking precision of the space-based satellite on the target can be improved.

The application provides a near space temperature calculation method, and relates to the technical field of near space, and the method comprises the following steps: acquiring satellite observation data sets of TIMED / SABER, using an information entropy sampling method to perform hierarchical sampling on the observation data sets to obtain a sampling data set; the sampling data set comprises a turning point temperature data set, a temperature layer temperature data set and environmental parameters related to the turning point temperature data set; performing influence factor analysis on the environmental parameters related to the turning point temperature data set to obtain element information; fitting a turning point temperature function and a turning point height function based on the turning point temperature data set and the element information; establishing a near space temperature model of different temperature layers based on the temperature layer temperature data set, the element information, the turning point temperature function and the turning point height function; inputting the acquired current element information into the near space temperature model to obtain the current near space temperature. The application solves the problems of poor limitation, complex calculation and low accuracy in the existing near space temperature calculation method.

The invention provides a satellite Internet of Things system, a construction method, an application method and a storage medium, and a satellite constellation in the system comprises a perception application satellite used for collecting multi-source monitoring data and transmitting the multi-source monitoring data to a network transmission satellite; the network transmission satellite is used for transmitting the multi-source monitoring data to the calculation storage satellite; the calculation storage satellite is used for carrying out real-time preprocessing on the multi-source monitoring data and sending a data processing result to the ground station; the sensing application satellite is deployed at the top of a low earth orbit or a near space, the network transmission satellite is deployed at a middle earth orbit or a GEO adjacent orbit, the calculation storage satellite is deployed at a geosynchronous orbit, and laser links are respectively established between the network transmission satellite and the sensing application satellite and between the network transmission satellite and the calculation storage satellite. Through satellite function decoupling and reconstruction deployment, the reliability of the system is improved, wide-area coverage space complementing is realized, an emerging Internet of Things industry support is formed, and emergency communication guarantee requirements are met.