19 results about "Near space" patented technology

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.

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 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 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 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 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 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.

The present application relates to the field of control, in particular to a kind of target information missing under the differential game guidance method for maneuvering target.The present application discloses a kind of differential game guidance method for near space high dynamic target scene under considering target incomplete information.The method comprises the following steps: the terminal interception problem is expressed, and the vertical plane is taken as the main research plane, and a two-dimensional missile-target relative motion engagement model is established;A linear extended observer is designed to estimate the target acceleration information;Then, the expression of zero-control miss distance is given, and the linear quadratic differential game (LQDG) guidance law under incomplete target information is obtained.The linear quadratic differential game (LQDG) guidance law under incomplete target information of the present application solves the problem of low control accuracy of interceptor under incomplete target information in the prior art.

The application discloses a motion control system for a near space antenna unmanned aerial vehicle, comprising a duct attitude adjustment system, a laser anemometer system and a Beidou satellite navigation system. The laser anemometer system monitors the wind speed and direction in the wind field and transmits the interference signals in real time; the Beidou satellite navigation system positions the antenna unmanned aerial vehicle in real time and transmits the position information; the duct attitude adjustment system comprises a sensor module, a controller module and a propulsion device, and adjusts the attitude of the propulsion device according to the interference signals and the position information. The propulsion device comprises eight duct propellers based on 3-RPS parallel structures and arranged in a cross shape, the design of the duct makes the airflow more stable and efficient, which helps to improve the propulsion efficiency and reduce the noise. The controller module adopts a strategy combining feedback linearization and terminal sliding mode control to generate control signals. The application realizes high-precision fixed-point hovering control of the antenna unmanned aerial vehicle in the complex wind field environment of the near space.

The application provides a near-space full-altitude environment multi-element laser radar detection platform, constructs a trinity structure of "common basic support + atmospheric composition detection + meteorological multi-element detection", solves a multi-device data fusion problem through a unified optical reference and a time synchronization mechanism, improves the spatiotemporal consistency of detection data, realizes high-precision collaborative detection of "full altitude and multi-element", breaks through the capability limitation of a single platform and a dispersed networking scheme, constructs an efficient multi-source heterogeneous data processing architecture, meets the real-time storage, analysis and visualization needs of massive data, improves the reliability and expandability of the equipment, realizes all-weather unattended operation, and supports flexible expansion of subsequent functional modules.

The invention discloses a near space environment climate data fusion analysis and visualization system and method, and belongs to the field of aerospace environment safeguard, and the system comprises a near space environment data storage management subsystem which is used for the unified management of multi-source heterogeneous data; the near space environment climate statistical modeling subsystem is used for establishing a static climate statistical model based on historical measured data and generating global fusion data; the near space environment data query and display subsystem is used for performing query and graphical display on single-station, one-dimensional section and two-dimensional plane data; and the flight path environment visualization subsystem is used for realizing real-time synchronous visualization of the flight path and the environment elements. Unified integration and efficient management of near space multi-source environment data are achieved, a statistical and fusion data set reflecting climate laws is generated, the omnibearing and visual visualization ability from a macroscopic field to a specific task trajectory is provided, and the expandability and long-term applicability of the system are guaranteed through modular design.

The application discloses a near-space sounding instrument with a rope cutter and a data processing splicing method, and relates to the technical field of sounding instruments. The near-space sounding instrument comprises a parachute, a parachute rope, a sounding instrument and a rope cutter. The parachute is connected with the sounding instrument through the parachute rope. The sounding instrument comprises a shell, a lithium battery, a digital transmitter, an air pressure sensor, a data acquisition circuit, a high dynamic satellite navigation positioning module, a wireless remote control module, a mechanical switch and a temperature sensor which are arranged in the shell. The rope cutter is arranged in a cavity in the shell. The data processing splicing method comprises data analysis, quality control, correction and splicing processes. The near-space sounding data from the ground to a height of 60km can be generated. The sounding instrument can be quickly landed on the ground, the data acquisition rate is improved, and the data accuracy, consistency and integrity are ensured.

The application provides a microgravity-normal air environment flying robot navigation method and system, and belongs to the technical field of robot autonomous navigation. In order to solve the problem of collision between the robot and the experimental personnel and the floating object in the environment in the near space. The application comprises the following steps: acquiring navigation positioning information based on the point cloud data of the depth vision camera carried by the robot and the attitude angle sensing data collected by the IMU module; determining the point cloud distribution and the voxelized space size; and constructing an environment map based on the acquired accurate positioning information. The application can realize stable control of position and attitude, autonomous navigation target identification and tracking in a complex environment in the cabin, motion planning and collision avoidance, and further realize high-level and more complex tasks such as efficient interaction with the experimental personnel and collaborative work, realize higher-level autonomous operation capability, and has the technical advantages of high safety and high reliability.

The invention discloses a near space lightweight communication resource configuration system. The near space lightweight communication resource configuration system comprises a satellite-borne base station and a plurality of satellite-borne terminals, the satellite-borne base station comprises a base station data management unit, a base station signaling / service control unit and a base station side physical layer unpacking and splicing unit corresponding to each terminal. The satellite-borne terminal comprises a terminal data management and signaling control unit and a physical layer unpacking and splicing unit. According to the invention, the uplink service channel / uplink control channel and the downlink service channel / downlink control channel of the access network communication system are fused in deep space exploration activities such as the lunar surface, and full-load transmission of each time slot is ensured through distributed flexible distribution of the time slots according to the TBS bearing capacity of the corresponding waveform, so that the transmission efficiency is improved. The problem of low protocol resource configuration efficiency of a traditional communication system is solved, and success of tasks is supported to the maximum extent.

The utility model discloses a detacher for a near space aerostat, and belongs to the technical field of near space detection. The device comprises a shell and a clamping plate, the shell is of a round box-shaped structure with a cover on one side and a hollow middle part, the shell is buckled above the clamping plate and is connected with the clamping plate, an energy storage device is arranged on the clamping plate, the energy storage device extends upwards from the middle part of the shell, and the energy storage device is connected with the clamping plate. A timing device and a releasing device are connected to the position, above the clamping plate, in the shell, the timing device and the releasing device are both engaged with the energy storage device, the energy storage device rotates to drive the timing device and the energy storage device to store energy, the timing device starts timing after the energy storage device stores energy, and the releasing device is engaged with the energy storage device. After timing of the timing device is finished, the releasing device releases energy through rotation. According to the utility model, unstable factors of the electronic device caused by environmental changes are effectively overcome.

This disclosure provides a method for controlling a hoisting mechanism used to lift an aircraft in near space, comprising: setting the ultimate load that the aircraft must meet under target operating conditions based on risk factors that may cause abnormalities in the aircraft; establishing a finite element model to characterize the aircraft to be lifted and the hoisting mechanism used to lift the aircraft, and using the ultimate load as the excitation input of the finite element model to calculate the mechanical simulation under the target operating conditions to obtain displacement simulation data of the aircraft under the target operating conditions; manufacturing a solid scale-down model including the aircraft and the hoisting mechanism; adjusting the hoisting rope structure with the structural strength of the solid scale-down model of the aircraft as the limit, so that the solid scale-down model of the aircraft can switch between multiple target operating conditions, and constructing the allowable force envelope of each hoisting rope of the hoisting rope structure; controlling the hoisting mechanism carrying the aircraft based on the allowable force envelope of each hoisting rope, so that the aircraft can switch between multiple target operating conditions, from the lifting stage to the release stage.